subject:(high pressure turbine)

INP Toulouse

1. Segui Troth, Luis Miguel. Multiphysics coupled simulations of gas turbines : Simulations multiphysiques couplées de turbines à gaz.

Degree: Docteur es, Dynamique des fluides, 2017, INP Toulouse

URL: http://www.theses.fr/2017INPT0104

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La résolution d’équations différentielles de divers degrés de complexité est nécessaire afin de simuler tous les phénomènes présents dans les écoulements complexes de turbomachine et… (more)

Subjects/Keywords: Turbine haute pression; Méthodes Numériques; Injection de turbulence; High-pressure turbine; Numerical methods; Turbulence injection

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APA (6^th Edition):

Segui Troth, L. M. (2017). Multiphysics coupled simulations of gas turbines : Simulations multiphysiques couplées de turbines à gaz. (Doctoral Dissertation). INP Toulouse. Retrieved from http://www.theses.fr/2017INPT0104

Chicago Manual of Style (16^th Edition):

Segui Troth, Luis Miguel. “Multiphysics coupled simulations of gas turbines : Simulations multiphysiques couplées de turbines à gaz.” 2017. Doctoral Dissertation, INP Toulouse. Accessed January 22, 2021. http://www.theses.fr/2017INPT0104.

MLA Handbook (7^th Edition):

Segui Troth, Luis Miguel. “Multiphysics coupled simulations of gas turbines : Simulations multiphysiques couplées de turbines à gaz.” 2017. Web. 22 Jan 2021.

Vancouver:

Segui Troth LM. Multiphysics coupled simulations of gas turbines : Simulations multiphysiques couplées de turbines à gaz. [Internet] [Doctoral dissertation]. INP Toulouse; 2017. [cited 2021 Jan 22]. Available from: http://www.theses.fr/2017INPT0104.

Council of Science Editors:

Segui Troth LM. Multiphysics coupled simulations of gas turbines : Simulations multiphysiques couplées de turbines à gaz. [Doctoral Dissertation]. INP Toulouse; 2017. Available from: http://www.theses.fr/2017INPT0104

Linköping University

2. Farhanieh, Arman. Investigation on methods to improve heat loadprediction of the SGT-600 gas turbine.

Degree: Applied Thermodynamics and Fluid Mechanics, 2016, Linköping University

URL: http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-124552

► In modern gas turbines, with the increase of inlet gas temperature to raise thework output, the importance of accurate aero-thermal analysis has become of… (more)

▼ In modern gas turbines, with the increase of inlet gas temperature to raise thework output, the importance of accurate aero-thermal analysis has become of vitalimportance. These analysis are required for temperature prediction throughoutthe turbine and to predict the thermal stresses and to estimate the cooling requiredfor each component.In the past 20 years, computational fluid dynamics (CFD) methods have becomea powerfool tool aero-thermal analysis. Due to reasons including numericallimitation, flow complications caused by blade row interactions and the effect offilm cooling, using simple steady state CFD methods may result in inaccuratepredictions. Even though employing transient simulations can improve the accuracyof the simulations, it will also greatly increase the simulation time and cost.Therefore, new methods are constantly being developed to increase the accuracywhile keeping the computational costs relatively low. Investigating some of thesedeveloped methods is one of the main purposes of this study.A simplification that has long been applied in gas turbine simulations hasbeen the absence of cooling cavities. Another part of this thesis will focus onthe effect of cooling cavities and the importance of including them in the domain.Therefore, all transient and steady state simulations have been examined for twocases; a simplified case and a detailed case. The results are then compared tothe experimental measurements to evaluate the importance of their presence inthe model. The software used to perform all simulations is the commercial codeANSYS CFX 15.The findings suggest that even though including cooling cavities would improvethe results, the simulations should be run in transient. One important finding wasthat when performing transient simulations, especially the Time Transformationmethod, not only is the pitch ratio between every subsequent blade row important,but also the pitch ratio between the stators is highly influential on the accuracyof the results.

Subjects/Keywords: Gas Turbine; CFD; Turbomachinery; High Pressure Turbine; Heat Load; Time Transformation; Profile Transformation; Mixing Plane

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APA (6^th Edition):

Farhanieh, A. (2016). Investigation on methods to improve heat loadprediction of the SGT-600 gas turbine. (Thesis). Linköping University. Retrieved from http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-124552

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Farhanieh, Arman. “Investigation on methods to improve heat loadprediction of the SGT-600 gas turbine.” 2016. Thesis, Linköping University. Accessed January 22, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-124552.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Farhanieh, Arman. “Investigation on methods to improve heat loadprediction of the SGT-600 gas turbine.” 2016. Web. 22 Jan 2021.

Vancouver:

Farhanieh A. Investigation on methods to improve heat loadprediction of the SGT-600 gas turbine. [Internet] [Thesis]. Linköping University; 2016. [cited 2021 Jan 22]. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-124552.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Farhanieh A. Investigation on methods to improve heat loadprediction of the SGT-600 gas turbine. [Thesis]. Linköping University; 2016. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-124552

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

University of Toronto

3. Barua, Arup. Soot Formation in Diffusion Flames of Alternative Turbine Fuels at Elevated Pressures.

Degree: 2012, University of Toronto

URL: http://hdl.handle.net/1807/33333

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Laminar axisymmetric syngas-air, syngas-methane mixture-air and biogas-air diffusion fames were studied over the pressure range of 5 to 20 atm to investigate the effect of… (more)

Subjects/Keywords: Soot formation; Diffusion flames; Alternative turbine fuels; High pressure expeimentation; 0538

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APA (6^th Edition):

Barua, A. (2012). Soot Formation in Diffusion Flames of Alternative Turbine Fuels at Elevated Pressures. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/33333

Chicago Manual of Style (16^th Edition):

Barua, Arup. “Soot Formation in Diffusion Flames of Alternative Turbine Fuels at Elevated Pressures.” 2012. Masters Thesis, University of Toronto. Accessed January 22, 2021. http://hdl.handle.net/1807/33333.

MLA Handbook (7^th Edition):

Barua, Arup. “Soot Formation in Diffusion Flames of Alternative Turbine Fuels at Elevated Pressures.” 2012. Web. 22 Jan 2021.

Vancouver:

Barua A. Soot Formation in Diffusion Flames of Alternative Turbine Fuels at Elevated Pressures. [Internet] [Masters thesis]. University of Toronto; 2012. [cited 2021 Jan 22]. Available from: http://hdl.handle.net/1807/33333.

Council of Science Editors:

Barua A. Soot Formation in Diffusion Flames of Alternative Turbine Fuels at Elevated Pressures. [Masters Thesis]. University of Toronto; 2012. Available from: http://hdl.handle.net/1807/33333

University of Toronto

4. Cirtwill, Joseph Daniel Maxim. The Investigation and Semi-Empirical Modeling of Thermoacoustic Phase Relationships in a Lean Premixed Prevapourized Combustor at Elevated Pressure.

Degree: 2017, University of Toronto

URL: http://hdl.handle.net/1807/79056

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This document presents an investigation of the self-excited coupling mechanisms that occur to produce both low-amplitude intermittent, as well as high-amplitude limit-cycle pressure oscillations in… (more)

Subjects/Keywords: Aeronautical; Gas Turbine; High Pressure; Premixed Combustion; Thermoacoustics; Time Lag; 0538

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APA (6^th Edition):

Cirtwill, J. D. M. (2017). The Investigation and Semi-Empirical Modeling of Thermoacoustic Phase Relationships in a Lean Premixed Prevapourized Combustor at Elevated Pressure. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/79056

Chicago Manual of Style (16^th Edition):

Cirtwill, Joseph Daniel Maxim. “The Investigation and Semi-Empirical Modeling of Thermoacoustic Phase Relationships in a Lean Premixed Prevapourized Combustor at Elevated Pressure.” 2017. Masters Thesis, University of Toronto. Accessed January 22, 2021. http://hdl.handle.net/1807/79056.

MLA Handbook (7^th Edition):

Cirtwill, Joseph Daniel Maxim. “The Investigation and Semi-Empirical Modeling of Thermoacoustic Phase Relationships in a Lean Premixed Prevapourized Combustor at Elevated Pressure.” 2017. Web. 22 Jan 2021.

Vancouver:

Cirtwill JDM. The Investigation and Semi-Empirical Modeling of Thermoacoustic Phase Relationships in a Lean Premixed Prevapourized Combustor at Elevated Pressure. [Internet] [Masters thesis]. University of Toronto; 2017. [cited 2021 Jan 22]. Available from: http://hdl.handle.net/1807/79056.

Council of Science Editors:

Cirtwill JDM. The Investigation and Semi-Empirical Modeling of Thermoacoustic Phase Relationships in a Lean Premixed Prevapourized Combustor at Elevated Pressure. [Masters Thesis]. University of Toronto; 2017. Available from: http://hdl.handle.net/1807/79056

Northeastern University

5. Kopriva, James Earl. The role of free-stream turbulence on high pressure turbine aero-thermal stage interaction.

Degree: PhD, Department of Mechanical and Industrial Engineering, 2017, Northeastern University

URL: http://hdl.handle.net/2047/D20251494

► Turbulence plays an important role on the aero-thermal performance of modern aircraft engine High Pressure Turbines (HPT). The role of the vane wake and passage… (more)

▼ Turbulence plays an important role on the aero-thermal performance of modern aircraft engine High Pressure Turbines (HPT). The role of the vane wake and passage turbulence on the downstream blade flow field is an important consideration for both performance and durability. Obtaining measurements to fully characterize the flow field can be challenging and costly in an experimental facility. Advances in computational Fluid Dynamic (CFD) modeling and High Performance Computing (HPC) are providing opportunity to close these measurement gaps. In order for CFD to be adopted, methods need to be both accurate and efficient. Meshing approaches must also be able to resolve complex HPT geometry while maintaining quality adequate for scale-resolved simulations. Therefore, the accuracy of executing scale-resolved simulations with a second-order code on a mesh of prisms and tetrahedrals in Fluent is considered.; Before execution of the HPT computational study, a building block approach is taken to gain quantified predictive performance in the modeling approach as well as understanding limitations in lower computational cost modeling approaches. The predictive capability for Reynolds Averaged Navier Stokes (RANS), Hybrid Large Eddy Simulation (LES), and wall-resolved LES turbulence modeling approaches are first assessed for a cylinder in cross-flow at a Reynolds number of 2580. The flow condition and simple geometry facilitate a quick turn-around for modeling assessment before moving the HPT vane study at high Reynolds and Mach number conditions. Modeling approaches are then assessed relative to the experimental measurements of Arts and Rouvroit (1992) on a pitch-line HPT uncooled vane at high Mach and Reynolds numbers conditions with low (0-6%) free-stream turbulence. The current unstructured second-order LES approach agrees with experimental data and is found to be within the equivalent experimental uncertainty when compared to the structured high-ordered solver FDL3DI. The unstructured Hybrid LES aero-thermal predictions are found to be in close agreement with LES predictions and 4 times more computationally efficient.; A sliding mesh approach is then used to understand the complex HPT vane and blade stage aero-thermal interaction at 0 and 20% inlet turbulence. A HPT blade has been designed to pair with the uncooled vane of Arts and Rouvroit (1992) to evaluate the impact of passage turbulence and vane wake on the downstream blade boundary layer as well as wake formation and evolution. The learnings from the statistical 2D pitch-line stage simulations are applied to a 3D annular representation of the geometry including endwalls and blade tip clearance to demonstrate the impact of secondary flows on the overall aero-thermal performance. Compared to the 2D pitchline predictions, the vane and blade overall mass average relative total pressure loss for the 3D geometry increases by 73 and 107%, respectively. The blade loss is shown to be largely driven by the formation of the tip vortex. Hybrid LES predictions show that by increasing…

Subjects/Keywords: boundary layer; CFD; high pressure turbine; hybrid LES; turbulence; wake

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Kopriva, J. E. (2017). The role of free-stream turbulence on high pressure turbine aero-thermal stage interaction. (Doctoral Dissertation). Northeastern University. Retrieved from http://hdl.handle.net/2047/D20251494

Chicago Manual of Style (16^th Edition):

Kopriva, James Earl. “The role of free-stream turbulence on high pressure turbine aero-thermal stage interaction.” 2017. Doctoral Dissertation, Northeastern University. Accessed January 22, 2021. http://hdl.handle.net/2047/D20251494.

MLA Handbook (7^th Edition):

Kopriva, James Earl. “The role of free-stream turbulence on high pressure turbine aero-thermal stage interaction.” 2017. Web. 22 Jan 2021.

Vancouver:

Kopriva JE. The role of free-stream turbulence on high pressure turbine aero-thermal stage interaction. [Internet] [Doctoral dissertation]. Northeastern University; 2017. [cited 2021 Jan 22]. Available from: http://hdl.handle.net/2047/D20251494.

Council of Science Editors:

Kopriva JE. The role of free-stream turbulence on high pressure turbine aero-thermal stage interaction. [Doctoral Dissertation]. Northeastern University; 2017. Available from: http://hdl.handle.net/2047/D20251494

Queen Mary, University of London

6. Saleh, Zainab Jabbar. An investigation into turbine blade tip leakage flows at high speeds.

Degree: PhD, 2015, Queen Mary, University of London

URL: http://qmro.qmul.ac.uk/xmlui/handle/123456789/33937 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.667337

► This investigation studies the leakage flows over the high pressure turbine blade tip at high speed flow conditions. There is an unavoidable gap between the… (more)

▼ This investigation studies the leakage flows over the high pressure turbine blade tip at high speed flow conditions. There is an unavoidable gap between the un-shrouded blade tip and the engine casing in a turbine stage, where the pressure difference between the pressure and the suction surfaces of the blade gives rise to the development of leakage flows through this gap. These flows contribute to about one third of the aerodynamic losses in a turbine stage. In addition they expose the blade tip to a very high temperature and result in thermal damages which reduce the blade‟s operational life. Therefore any improvement on the tip design to reduce these flows has a significant impact on the engine‟s efficiency and turbine blade‟s operational life. At the engine operational condition, the leakage flows over the high pressure turbine blade tip are mostly transonic. On the other hand literature survey has shown that most of the studies on the tip leakage flows have been performed at low speed conditions and there are only a few experimental works on the transonic tip flows. This project aims to explore the tip leakage flows at high speed condition which is the real engine condition, both experimentally and computationally and establish a comprehensive understanding of these flows on different tip geometries. The effect of tip geometry was studied using the flat tip and the cavity tip models and the effect of in-service burnout on these two tip models was established using the radius-edge flat tip and the radius-edge cavity tip models. The experimental work was carried out in the transonic wind tunnel of Queen Mary University of London and the computational simulations were performed using RANS and URANS. As the flow approached each tip model it turned and accelerated around its leading edge in the same way as the flow turns around the leading edge of an aerofoil. In the case of the tip models with sharp edges the tip flow separated at the inlet to the tip gap. For the flat tip model the flow reattachment occurred further downstream whereas in the case of the cavity tip model the length of the pressure side rim was not sufficient for the reattachment to occur and the separated flow left the rim as a free shear layer. The cavity tip model was found to have a smaller effective tip gap and hence smaller discharge coefficient in comparison to the flat tip model. For the radius-edge tip models, no separation occurred at the inlet to the tip gap and the effective tip gap was found to be the same as the geometrical tip gap. Therefore it was concluded that the tip model with radius-edges had a larger effective tip gap and hence a greater discharge coefficient than the tip geometry with sharp edges. It was observed that in the case of the supersonic tip leakage flows, decreasing the pressure ratio PR (i.e. the ratio of the static pressure at the tip gap exit to the stagnation pressure at the inlet to the tip gap) increased the discharge coefficient Cd for the tip models with sharp edges but it decreased the Cd value in the case of…

Subjects/Keywords: 621.406; high pressure turbine blade tip; transonic tip flows

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APA (6^th Edition):

Saleh, Z. J. (2015). An investigation into turbine blade tip leakage flows at high speeds. (Doctoral Dissertation). Queen Mary, University of London. Retrieved from http://qmro.qmul.ac.uk/xmlui/handle/123456789/33937 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.667337

Chicago Manual of Style (16^th Edition):

Saleh, Zainab Jabbar. “An investigation into turbine blade tip leakage flows at high speeds.” 2015. Doctoral Dissertation, Queen Mary, University of London. Accessed January 22, 2021. http://qmro.qmul.ac.uk/xmlui/handle/123456789/33937 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.667337.

MLA Handbook (7^th Edition):

Saleh, Zainab Jabbar. “An investigation into turbine blade tip leakage flows at high speeds.” 2015. Web. 22 Jan 2021.

Vancouver:

Saleh ZJ. An investigation into turbine blade tip leakage flows at high speeds. [Internet] [Doctoral dissertation]. Queen Mary, University of London; 2015. [cited 2021 Jan 22]. Available from: http://qmro.qmul.ac.uk/xmlui/handle/123456789/33937 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.667337.

Council of Science Editors:

Saleh ZJ. An investigation into turbine blade tip leakage flows at high speeds. [Doctoral Dissertation]. Queen Mary, University of London; 2015. Available from: http://qmro.qmul.ac.uk/xmlui/handle/123456789/33937 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.667337

Delft University of Technology

7. De Prieelle, L.S.B. (author). A Numerical Study into the Effect of Optimised Profiled End-Wall Design on High Pressure Turbine Performance.

Degree: 2014, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:4ef5f1a7-ebd9-4a05-96e1-cabc71d42d63

► In order to provide further improvements in thermal efficiency, engine designers are trying to optimise one of the components of the engine that has to… (more)

▼ In order to provide further improvements in thermal efficiency, engine designers are trying to optimise one of the components of the engine that has to endure the most severe conditions: the High Pressure Turbine. Furthermore, from a cost perspective, turbine designers are constantly trying to reduce the number of blades in the turbine which leads to stronger secondary flow features. Since secondary flow features are one of the main contributors to losses in the turbine, there is a potential for improvements when the development of secondary flow in the stage can be controlled and reduced. The non-axisymmetric profiling of end-walls has shown to be a powerful method to reduce loss and secondary flows. However, the development of consistent measures for the assessment of profiled end-wall designs is still in progress and the loss mechanisms of secondary flows are not yet fully understood. Therefore, the achievement of optimal end-wall design is still challenging. The main obstacle remains the complexity of the three-dimensional flows involved and the difficulty to visualise and accurately evaluate their flow structures. The aim of this thesis is to show that applying profiled end-walls and making use of optimisation algorithms can lead to a reduction of losses in the High Pressure Turbine. A parametric optimisation study has been performed to determine the regions of the hub profiled end-wall in the High Pressure rotor that are having the largest impact on performance. The objective has set to increase component efficiency while constraints have been set in terms of the reaction and inlet capacity of the High Pressure stage. A high efficiency improvement is obtained by the profiled end-wall created near the leading edge, while the profiled end-wall close to the trailing edge of the blade loses most of its efficiency improvement due to its strong violation of the constraints. Analysis of the flow field has revealed that the profiled end-wall near the leading edge is affecting the interaction of inlet boundary layer flow and purge flow emerging from the rim seal. By creating an effective flow passage, the profiled end-wall forces the purge flow to emerge from the rim seal closer to the suction surface of the blade. In this way, the profiled end-wall is influencing the development of the hub passage vortex. A new post-processing method has been developed based on the generation of entropy in order to gain a deeper understanding of the flow mechanisms taking place. The specific entropy generation has shown to be a powerful tool to identify loss sources and compare designs. It has been determined that the reduction in work losses due to shear stresses between adjacent cells in the numerical domain has the largest contribution to the reported efficiency improvements. Two loss reduction mechanisms have been identified. By forcing the purge flow to stay close to the suction surface, shear stress work losses that were first being generated by flow that was entrained between the hub passage vortex and suction side of the blade… Advisors/Committee Members: Langelaar, M. (mentor), Van Keulen, A. (mentor).

Subjects/Keywords: Numerical Study; Optimised Profiled End-Wall Design; High Pressure Turbine

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APA (6^th Edition):

De Prieelle, L. S. B. (. (2014). A Numerical Study into the Effect of Optimised Profiled End-Wall Design on High Pressure Turbine Performance. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:4ef5f1a7-ebd9-4a05-96e1-cabc71d42d63

Chicago Manual of Style (16^th Edition):

De Prieelle, L S B (author). “A Numerical Study into the Effect of Optimised Profiled End-Wall Design on High Pressure Turbine Performance.” 2014. Masters Thesis, Delft University of Technology. Accessed January 22, 2021. http://resolver.tudelft.nl/uuid:4ef5f1a7-ebd9-4a05-96e1-cabc71d42d63.

MLA Handbook (7^th Edition):

De Prieelle, L S B (author). “A Numerical Study into the Effect of Optimised Profiled End-Wall Design on High Pressure Turbine Performance.” 2014. Web. 22 Jan 2021.

Vancouver:

De Prieelle LSB(. A Numerical Study into the Effect of Optimised Profiled End-Wall Design on High Pressure Turbine Performance. [Internet] [Masters thesis]. Delft University of Technology; 2014. [cited 2021 Jan 22]. Available from: http://resolver.tudelft.nl/uuid:4ef5f1a7-ebd9-4a05-96e1-cabc71d42d63.

Council of Science Editors:

De Prieelle LSB(. A Numerical Study into the Effect of Optimised Profiled End-Wall Design on High Pressure Turbine Performance. [Masters Thesis]. Delft University of Technology; 2014. Available from: http://resolver.tudelft.nl/uuid:4ef5f1a7-ebd9-4a05-96e1-cabc71d42d63

University of New South Wales

8. Ubulom, Iroizan. Fluid-structure and thermal interactions modelling for an HP turbine blade fatigue life evaluation.

Degree: Engineering & Information Technology, 2019, University of New South Wales

URL: http://handle.unsw.edu.au/1959.4/61829 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:57730/SOURCE02?view=true

► A numerical study is presented on the influence of fluid-structure coupling on a turbine blade fatigue life estimation. Varying levels of fluid-solid coupling including; a… (more)

▼ A numerical study is presented on the influence of fluid-structure coupling on a turbine blade fatigue life estimation. Varying levels of fluid-solid coupling including; a fully-coupled, decoupled and uncoupled solution approaches are implemented. In the fully-coupled analysis, a time-dependent fluid solver is coupled to a transient structural solver with information transfer at the fluid-solid interface for every solution step. A minimum of 3-iterations is performed per solution step to ensure the fluid-solid compatibility and conservation requirements at the fluid-solid interface are met. In the uncoupled method, the unsteady aerodynamic pressure is first computed and transferred unilaterally to the solid solver in an independent analysis. Two uncoupled methods are implemented, the case with and without a separate consideration of the aerodynamic damping ratio. In the third method of a decoupled analysis, the fully-coupled is performed but with a reduced iteration per time-step, enabling a converged solution to be obtained with reduced computational resources.The above numerical approaches are implemented to investigate the problem of high-cycle and low-cycle fatigue failure modes. In the high-cycle problem case, the influence of the unsteady aerodynamics on the structural response is investigated, where the rotor blade is modelled with the upstream influence of the stator blades. The resulting stress magnitude for this condition leads to fatigue cycles in the domain of the ultra-high cycle frequency range. The low-cycle fatigue condition includes the influence of centrifugal forces from the high-rotational speed of the turbine rotor. The analysis shows that the centrifugal stiffening effect from the rotational loads, in addition to the independently estimated aerodynamic damping term, leads to a strongly damped response for the damped uncoupled method. This resulted in a fatigue life that is higher than that of the fully-coupled approach. An application of the fully-coupled method is also extended for a thermomechanical analysis with additional temperature effect in the coupled equations. The solid metal temperature distribution is predicted by coupling the fluid-code with a conjugate heat transfer capability to a transient structural code for the analysis of thermally-induced stress. The thermomechanical fatigue condition is investigated using the universal slope method and the creep strains are predicted based on a continuum damage mechanics approach. The fully-coupled method with temperature addition predicts a blade temperature profile similar to that from a stand-alone conjugate heat transfer solver.Lastly, given that fatigue loading is inherently stochastic, a probability sensitivity study is presented where the reliability coefficients of the input parameters are estimated as a first-hand indication of the influence of the three parameters: rainflow fatigue cycles, stress amplitude and the S-N curve fatigue cycles, on the overall fatigue life estimation process. Advisors/Committee Members: Shankar, Krishna, Engineering & Information Technology, UNSW Canberra, UNSW, Neely, Andrew, Engineering & Information Technology, UNSW Canberra, UNSW.

Subjects/Keywords: Aeroelasticity; Fluid-structure interaction; High pressure turbine blade; Fatigue life

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APA (6^th Edition):

Ubulom, I. (2019). Fluid-structure and thermal interactions modelling for an HP turbine blade fatigue life evaluation. (Doctoral Dissertation). University of New South Wales. Retrieved from http://handle.unsw.edu.au/1959.4/61829 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:57730/SOURCE02?view=true

Chicago Manual of Style (16^th Edition):

Ubulom, Iroizan. “Fluid-structure and thermal interactions modelling for an HP turbine blade fatigue life evaluation.” 2019. Doctoral Dissertation, University of New South Wales. Accessed January 22, 2021. http://handle.unsw.edu.au/1959.4/61829 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:57730/SOURCE02?view=true.

MLA Handbook (7^th Edition):

Ubulom, Iroizan. “Fluid-structure and thermal interactions modelling for an HP turbine blade fatigue life evaluation.” 2019. Web. 22 Jan 2021.

Vancouver:

Ubulom I. Fluid-structure and thermal interactions modelling for an HP turbine blade fatigue life evaluation. [Internet] [Doctoral dissertation]. University of New South Wales; 2019. [cited 2021 Jan 22]. Available from: http://handle.unsw.edu.au/1959.4/61829 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:57730/SOURCE02?view=true.

Council of Science Editors:

Ubulom I. Fluid-structure and thermal interactions modelling for an HP turbine blade fatigue life evaluation. [Doctoral Dissertation]. University of New South Wales; 2019. Available from: http://handle.unsw.edu.au/1959.4/61829 ; https://unsworks.unsw.edu.au/fapi/datastream/unsworks:57730/SOURCE02?view=true

University of Notre Dame

9. Lionel Obadiah Pittman Jr. Aerothermal Experiments in Turbine Rim Seals</h1>.

Degree: Aerospace and Mechanical Engineering, 2014, University of Notre Dame

URL: https://curate.nd.edu/show/qn59q239z3r

► Purge flows are necessary for ensuring that hot gasses do not penetrate the thermally sensitive rim seal and disk cavity regions of turbines. The… (more)

Subjects/Keywords: low pressure turbine; Rim; efficiency; hpt; lpt; Experiments; Turbine; high pressure turbine; pressures; highly loaded turbine; flow angles; cfd; temperatures; computational fluid dynamics; flows; Aerothermal; Seals; purge

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APA (6^th Edition):

Jr., L. O. P. (2014). Aerothermal Experiments in Turbine Rim Seals</h1>. (Thesis). University of Notre Dame. Retrieved from https://curate.nd.edu/show/qn59q239z3r

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Jr., Lionel Obadiah Pittman. “Aerothermal Experiments in Turbine Rim Seals</h1>.” 2014. Thesis, University of Notre Dame. Accessed January 22, 2021. https://curate.nd.edu/show/qn59q239z3r.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Jr., Lionel Obadiah Pittman. “Aerothermal Experiments in Turbine Rim Seals</h1>.” 2014. Web. 22 Jan 2021.

Vancouver:

Jr. LOP. Aerothermal Experiments in Turbine Rim Seals</h1>. [Internet] [Thesis]. University of Notre Dame; 2014. [cited 2021 Jan 22]. Available from: https://curate.nd.edu/show/qn59q239z3r.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Jr. LOP. Aerothermal Experiments in Turbine Rim Seals</h1>. [Thesis]. University of Notre Dame; 2014. Available from: https://curate.nd.edu/show/qn59q239z3r

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Université Catholique de Louvain

10. Mersinligil, Mehmet. Development of a high temperature cooled fast response probe for gas turbine applications.

Degree: 2014, Université Catholique de Louvain

URL: http://hdl.handle.net/2078.1/144020

►

The measurement of unsteady pressures within the hot components of gas turbine engines still remains a true challenge for test engineers. Several high temperature pressure… (more)

Subjects/Keywords: Instrumentation; Unsteady Pressure Measurement; High Temperature; Time-Resolved Measurements; Probe; Pressure; Turbine

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APA (6^th Edition):

Mersinligil, M. (2014). Development of a high temperature cooled fast response probe for gas turbine applications. (Thesis). Université Catholique de Louvain. Retrieved from http://hdl.handle.net/2078.1/144020

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Mersinligil, Mehmet. “Development of a high temperature cooled fast response probe for gas turbine applications.” 2014. Thesis, Université Catholique de Louvain. Accessed January 22, 2021. http://hdl.handle.net/2078.1/144020.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Mersinligil, Mehmet. “Development of a high temperature cooled fast response probe for gas turbine applications.” 2014. Web. 22 Jan 2021.

Vancouver:

Mersinligil M. Development of a high temperature cooled fast response probe for gas turbine applications. [Internet] [Thesis]. Université Catholique de Louvain; 2014. [cited 2021 Jan 22]. Available from: http://hdl.handle.net/2078.1/144020.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Mersinligil M. Development of a high temperature cooled fast response probe for gas turbine applications. [Thesis]. Université Catholique de Louvain; 2014. Available from: http://hdl.handle.net/2078.1/144020

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

11. Wlassow, Fabien. Analyse instationnaire aérothermique d'un étage de turbine avec transport de points chauds : application à la maîtrise des performances des aubages.

Degree: Docteur es, Mécanique, 2012, Ecully, Ecole centrale de Lyon

URL: http://www.theses.fr/2012ECDL0006

►

Afin d’augmenter le rendement et la puissance spécifique des turbines à gaz, la température en entrée de la turbine haute pression a été continuellement augmentée,… (more)

▼

Afin d’augmenter le rendement et la puissance spécifique des turbines à gaz, la température en entrée de la turbine haute pression a été continuellement augmentée, au point d’atteindre une valeur de l’ordre de la température de fusion des matériaux. La capacité à prédire l’écoulement (température en particulier) dans la turbine est donc un élément essentiel pour la conception des turbines à gaz, particulièrement pour celle qui ne sont pas refroidies. Toutefois, cette tâche est rendue difficile par l’extrême complexité de l’environnement dans lequel la turbine évolue (interaction avec la chambre de combustion, effets technologiques, couplage thermique fluide / solide, etc.).L’objectif de ce travail de thèse est de proposer, d’une part une stratégie de simulation numérique afin de prédire au mieux les champs aérothermiques dans une turbine haute-pression, d’autre part une méthode d’analyse permettant de quantifier l’impact des différents éléments de l’environnement sur les performances. Pour répondre à ces objectifs, des simulations instationnaires d’un étage de turbine ont été réalisées avec le code elsA, prenant en compte les effets technologiques (baignoire, refroidissement externe grâce aux évents du distributeur et aux cavités moyeu et carter du rotor qui sont alimentés par le système d’air secondaire, congés de raccordement) et les transferts thermiques conjugués. Une analyse de la production locale d’entropie a aussi été menée afin de comparer les performances aérodynamiques pour plusieurs niveaux d’approximations dans la définition de la turbine (prise en compte ou non de tel ou tel effet technologique) et de localiser l’origine de ces différences. L’analyse des résultats a montré que la hauteur de jeu et le système de refroidissement externe ont l’impact le plus significatif sur les performances aérodynamiques de la turbine. La température de paroi de la pale de rotor est de son côté fortement influencée par l’écoulement issu de la chambre de combustion, le refroidissement externe et le couplage thermique fluide / solide. Ce travail est un premier pas vers la réalisation de simulations totalement intégrées qui doivent permettre d’améliorer la précision des conceptions.

In order to increase the thermodynamic efficiency of gas turbine engines, the high-pressure turbine inlet temperature has been continually increased up to reach levels of the order of magnitude of the vanes and blades melting temperatures. The ability of predicting the flow through the turbine(especially the temperature) is a key point for the design of gas turbines, especially for the uncooled ones. However, this is challenging because of the complex environment that interacts with the turbine(hot-streak migration, technological details, fluid/solid thermal coupling . . .).The aim of this work is to develop a strategy based on CFD in order to predict aerothermal fields in a high-pressure turbine as well as an analysis allowing to quantify the impact of the environment on the turbine performances. To achieve these goals, the elsA code has…

Advisors/Committee Members: Ngo-Boum, Ghislaine (thesis director), Gourdain, Nicolas (thesis director), Leboeuf, Francis (thesis director).

Subjects/Keywords: Simulation numérique; Turbine haute-pression; Chimère; Couplage thermique fluide-solide; Entropie; CFD; High-pressure turbine; Chimera; Fluid-solid thermal coupling; Entropy

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APA (6^th Edition):

Wlassow, F. (2012). Analyse instationnaire aérothermique d'un étage de turbine avec transport de points chauds : application à la maîtrise des performances des aubages. (Doctoral Dissertation). Ecully, Ecole centrale de Lyon. Retrieved from http://www.theses.fr/2012ECDL0006

Chicago Manual of Style (16^th Edition):

Wlassow, Fabien. “Analyse instationnaire aérothermique d'un étage de turbine avec transport de points chauds : application à la maîtrise des performances des aubages.” 2012. Doctoral Dissertation, Ecully, Ecole centrale de Lyon. Accessed January 22, 2021. http://www.theses.fr/2012ECDL0006.

MLA Handbook (7^th Edition):

Wlassow, Fabien. “Analyse instationnaire aérothermique d'un étage de turbine avec transport de points chauds : application à la maîtrise des performances des aubages.” 2012. Web. 22 Jan 2021.

Vancouver:

Wlassow F. Analyse instationnaire aérothermique d'un étage de turbine avec transport de points chauds : application à la maîtrise des performances des aubages. [Internet] [Doctoral dissertation]. Ecully, Ecole centrale de Lyon; 2012. [cited 2021 Jan 22]. Available from: http://www.theses.fr/2012ECDL0006.

Council of Science Editors:

Wlassow F. Analyse instationnaire aérothermique d'un étage de turbine avec transport de points chauds : application à la maîtrise des performances des aubages. [Doctoral Dissertation]. Ecully, Ecole centrale de Lyon; 2012. Available from: http://www.theses.fr/2012ECDL0006

KTH

12. Leung, Pak Wing. Aerodynamic Loss Co-Relations and Flow- Field Investigations of a Transonic Film- Cooled Nozzle Guide Vane.

Degree: Heat and Power Technology, 2015, KTH

URL: http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-162130

► Over the last two decades, most developed countries have reached a consensus that greener energy production is necessary for the world, due to the… (more)

▼ Over the last two decades, most developed countries have reached a consensus that greener energy production is necessary for the world, due to the climate changes and limited fossil fuel resources. More efficient turbine is desirable and can be archived by higher turbine-inlet temperature (TIT). However, it is difficult for nozzle guide vane (NGV), which is the first stage after combustion chamber, to withstand a very high temperature. Thus, cooling methods such as film cooling have to be implemented. Film-cooled NGV of an annular sector cascade (ASC) is studied in this thesis, for getting comprehensive calculation of vorticity, and analyzing applicability of existing loss models, namely Hartsel model and Young & Wilcock model. The flow-field calculation methods from previously published studies are reviewed. Literatures focusing on Hartsel model and Young & Wilcock model are studied. Measurement data from previously published studies are analyzed and compared with the loss models. In order to get experience of how measurements take place, participation of a test run experiment is involved. Calculation of flow vector has been evaluated and modified. Actual flow angle is introduced when calculating velocity components. Thus, more exact results are obtained from the new method. Calculation of vorticity has been evaluated and made more comprehensive. Vorticity components as well as magnitude of total streamwise vorticity are calculated and visualized. Vorticity is higher and more extensive for fully cooled case than uncooled case. Highest vorticity is found at regions near the hub, tip and TE. Axial and circumferential vorticities show similar patterns, while the radial vorticity is relatively simpler. Compressibility is introduced as a new method when calculating circumferential and radial vorticities, resulting more extensive and higher vorticities than results from incompressible solutions. Hartsel model and Young & Wilcock model have been evaluated and compared to the ASC to see the applicability of the models. In general, Hartsel model cannot agree with the ASC to a satisfactory level and thus cannot be applied. Coolant velocity is found to be the dominant factor of Hartsel model. Young & Wilcock model may match SS1 and SS2 cases, or even PS and SH4 cases, but cannot match TE case. The applicability of Young & Wilcock model is much dependent on the location of cooling rows.

Subjects/Keywords: gas turbine; aerodynamics; secondary flow; external cooling; film cooling; aerodynamic loss; high pressure turbine; nozzle guide vane

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APA (6^th Edition):

Leung, P. W. (2015). Aerodynamic Loss Co-Relations and Flow- Field Investigations of a Transonic Film- Cooled Nozzle Guide Vane. (Thesis). KTH. Retrieved from http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-162130

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Leung, Pak Wing. “Aerodynamic Loss Co-Relations and Flow- Field Investigations of a Transonic Film- Cooled Nozzle Guide Vane.” 2015. Thesis, KTH. Accessed January 22, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-162130.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Leung, Pak Wing. “Aerodynamic Loss Co-Relations and Flow- Field Investigations of a Transonic Film- Cooled Nozzle Guide Vane.” 2015. Web. 22 Jan 2021.

Vancouver:

Leung PW. Aerodynamic Loss Co-Relations and Flow- Field Investigations of a Transonic Film- Cooled Nozzle Guide Vane. [Internet] [Thesis]. KTH; 2015. [cited 2021 Jan 22]. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-162130.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Leung PW. Aerodynamic Loss Co-Relations and Flow- Field Investigations of a Transonic Film- Cooled Nozzle Guide Vane. [Thesis]. KTH; 2015. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-162130

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

The Ohio State University

13. Banks, William V, III. Analysis of Turbine Rotor Tip Clearance Losses and Parametric Optimization of Shroud.

Degree: MS, Mechanical Engineering, 2019, The Ohio State University

URL: http://rave.ohiolink.edu/etdc/view?acc_num=osu155718636896448

► Aerodynamic losses due to tip leakage in a High Pressure Turbine (HPT) rotor setting are analyzed using the commercial CFD software Star-CCM+. The compressible RANS… (more)

Subjects/Keywords: Aerospace Engineering; Mechanical Engineering; High Pressure Turbine, Turbofan, Tip Clearance, Tip Leakage, Turbine Rotor, Shroud, Tip Loss, Stage Efficiency

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Banks, William V, I. (2019). Analysis of Turbine Rotor Tip Clearance Losses and Parametric Optimization of Shroud. (Masters Thesis). The Ohio State University. Retrieved from http://rave.ohiolink.edu/etdc/view?acc_num=osu155718636896448

Chicago Manual of Style (16^th Edition):

Banks, William V, III. “Analysis of Turbine Rotor Tip Clearance Losses and Parametric Optimization of Shroud.” 2019. Masters Thesis, The Ohio State University. Accessed January 22, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=osu155718636896448.

MLA Handbook (7^th Edition):

Banks, William V, III. “Analysis of Turbine Rotor Tip Clearance Losses and Parametric Optimization of Shroud.” 2019. Web. 22 Jan 2021.

Vancouver:

Banks, William V I. Analysis of Turbine Rotor Tip Clearance Losses and Parametric Optimization of Shroud. [Internet] [Masters thesis]. The Ohio State University; 2019. [cited 2021 Jan 22]. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=osu155718636896448.

Council of Science Editors:

Banks, William V I. Analysis of Turbine Rotor Tip Clearance Losses and Parametric Optimization of Shroud. [Masters Thesis]. The Ohio State University; 2019. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=osu155718636896448

University of Notre Dame

14. John Thomas Schmitz. Experimental Measurements in a Highly Loaded Low Pressure Turbine</h1>.

Degree: Aerospace and Mechanical Engineering, 2010, University of Notre Dame

URL: https://curate.nd.edu/show/j098z89301d

► The performance and detailed flow physics of a transonic, low-pressure turbine (LPT) stage with design Zw=1.35, ∆hT /U2 = 2.8, ϕ = 0.78, and… (more)

Subjects/Keywords: low pressure turbine; turbine; high load; turbomachinery; gas turbine; high lift

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APA (6^th Edition):

Schmitz, J. T. (2010). Experimental Measurements in a Highly Loaded Low Pressure Turbine</h1>. (Thesis). University of Notre Dame. Retrieved from https://curate.nd.edu/show/j098z89301d

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Schmitz, John Thomas. “Experimental Measurements in a Highly Loaded Low Pressure Turbine</h1>.” 2010. Thesis, University of Notre Dame. Accessed January 22, 2021. https://curate.nd.edu/show/j098z89301d.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Schmitz, John Thomas. “Experimental Measurements in a Highly Loaded Low Pressure Turbine</h1>.” 2010. Web. 22 Jan 2021.

Vancouver:

Schmitz JT. Experimental Measurements in a Highly Loaded Low Pressure Turbine</h1>. [Internet] [Thesis]. University of Notre Dame; 2010. [cited 2021 Jan 22]. Available from: https://curate.nd.edu/show/j098z89301d.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Schmitz JT. Experimental Measurements in a Highly Loaded Low Pressure Turbine</h1>. [Thesis]. University of Notre Dame; 2010. Available from: https://curate.nd.edu/show/j098z89301d

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

University of Toronto

15. Luymes, Benjamin Thomas. The Investigation of Transient Wake Dynamics in Highly-Loaded High-Pressure Turbine Stages under Transonic Engine Conditions.

Degree: 2018, University of Toronto

URL: http://hdl.handle.net/1807/91606

►

The convection of unsteady wakes through a downstream blade row and the interaction of these wakes with subsequent blade wakes were investigated in characteristic highly-loaded… (more)

Subjects/Keywords: Blade Loading; High-Pressure Turbine; Phase-Conditioning; Transonic; Unsteady Fluid Mechanics; Wake Development; 0538

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APA (6^th Edition):

Luymes, B. T. (2018). The Investigation of Transient Wake Dynamics in Highly-Loaded High-Pressure Turbine Stages under Transonic Engine Conditions. (Masters Thesis). University of Toronto. Retrieved from http://hdl.handle.net/1807/91606

Chicago Manual of Style (16^th Edition):

Luymes, Benjamin Thomas. “The Investigation of Transient Wake Dynamics in Highly-Loaded High-Pressure Turbine Stages under Transonic Engine Conditions.” 2018. Masters Thesis, University of Toronto. Accessed January 22, 2021. http://hdl.handle.net/1807/91606.

MLA Handbook (7^th Edition):

Luymes, Benjamin Thomas. “The Investigation of Transient Wake Dynamics in Highly-Loaded High-Pressure Turbine Stages under Transonic Engine Conditions.” 2018. Web. 22 Jan 2021.

Vancouver:

Luymes BT. The Investigation of Transient Wake Dynamics in Highly-Loaded High-Pressure Turbine Stages under Transonic Engine Conditions. [Internet] [Masters thesis]. University of Toronto; 2018. [cited 2021 Jan 22]. Available from: http://hdl.handle.net/1807/91606.

Council of Science Editors:

Luymes BT. The Investigation of Transient Wake Dynamics in Highly-Loaded High-Pressure Turbine Stages under Transonic Engine Conditions. [Masters Thesis]. University of Toronto; 2018. Available from: http://hdl.handle.net/1807/91606

Delft University of Technology

16. Ravisankar, Sneha (author). Modeling and Prediction of Pollutant Emissions in an Axial Turbine.

Degree: 2020, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:e5aa7277-ab72-4106-810d-90e03409e24e

►

The aviation market has seen a drastic rise in past decades, and is projected to follow a similar trend in the coming years. Stricter regulations… (more)

▼

The aviation market has seen a drastic rise in past decades, and is projected to follow a similar trend in the coming years. Stricter regulations and ambitious targets have been framed to effectively curtail the rise in emissions due to this surge in aviation. A multi-fuel blended wing body aircraft is being developed in TUDelft, with the goal of drastically reducing aircraft emissions. To this end, a dual-combustor configuration, which operates with a main combustion chamber and an inter-turbine burner has been proposed. The exhaust gas from the main combustion chamber passes through the high pressure turbine and then proceeds to the inter-turbine burner. It is important to accurately model the evolution of exhaust gas species, from the main combustion chamber through the high-pressure turbine, since this constitutes the species concentration at the inlet of the inter-turbine burner. This, in turn, can have impacts on its performance too. Therefore, this thesis aims to do a detailed parametric analysis to study the individual impact of the operating conditions on the chemical kinetics after the main combustor. The operating temperature has been identified as the most significant parameter that would have drastic impacts on the way emissions evolve after the combustor. The predictions of Turbine Inlet Temperatures for future aircraft have shown only a steady increase. Although the assumption of frozen chemistry after the combustor may have been valid for older engines, the same does not hold as good for futuristic configurations. Newer and different engine architectures like the hybrid engine, which are designed to operate on high cycle temperatures and pressures, cannot ignore the consequence of change in emissions after the combustor in order to retain accuracy in estimations.

Aerospace Engineering

Advisors/Committee Members: Gangoli Rao, Arvind (mentor), Augusto Viviani Perpignan, André (graduation committee), Delft University of Technology (degree granting institution).

Subjects/Keywords: Chemical Reactor Network; High Pressure Turbine; NOx; CO Emissions; Emissions; Chemical Reaction Mechanism

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APA (6^th Edition):

Ravisankar, S. (. (2020). Modeling and Prediction of Pollutant Emissions in an Axial Turbine. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:e5aa7277-ab72-4106-810d-90e03409e24e

Chicago Manual of Style (16^th Edition):

Ravisankar, Sneha (author). “Modeling and Prediction of Pollutant Emissions in an Axial Turbine.” 2020. Masters Thesis, Delft University of Technology. Accessed January 22, 2021. http://resolver.tudelft.nl/uuid:e5aa7277-ab72-4106-810d-90e03409e24e.

MLA Handbook (7^th Edition):

Ravisankar, Sneha (author). “Modeling and Prediction of Pollutant Emissions in an Axial Turbine.” 2020. Web. 22 Jan 2021.

Vancouver:

Ravisankar S(. Modeling and Prediction of Pollutant Emissions in an Axial Turbine. [Internet] [Masters thesis]. Delft University of Technology; 2020. [cited 2021 Jan 22]. Available from: http://resolver.tudelft.nl/uuid:e5aa7277-ab72-4106-810d-90e03409e24e.

Council of Science Editors:

Ravisankar S(. Modeling and Prediction of Pollutant Emissions in an Axial Turbine. [Masters Thesis]. Delft University of Technology; 2020. Available from: http://resolver.tudelft.nl/uuid:e5aa7277-ab72-4106-810d-90e03409e24e

Universitat Politècnica de València

17. Lavagnoli, Sergio. On the Aerothermal Flow Field in a Transonic HP Turbine Stage with a Multi-Profile LP Stator Vane .

Degree: 2012, Universitat Politècnica de València

URL: http://hdl.handle.net/10251/17799

► The quest for higher performances and durability of modern aero-engines requires the understanding of the complex aero-thermal flow experienced in a multi-row environment. In particular,… (more)

▼ The quest for higher performances and durability of modern aero-engines requires the understanding of the complex aero-thermal flow experienced in a multi-row environment. In particular, the high and low pressure turbine components have a great impact into the engine overall performance, and improvements in the turbine efficiencies can only be achieved through detailed research on the three-dimensional unsteady aerodynamics and heat transfer. The present thesis presents an experimental study of the aerothermodynamics in one and a half turbine stage, focusing on: the aero-thermal flow in the overtip region of a transonic highly loaded high pressure (HP) rotor, and the aerodynamics and heat transfer of an innovative low pressure (LP) stator with a multi-profile configuration placed downstream of the high pressure turbine, within an s-shaped duct. Advanced instrumentation and measurement techniques were used and developed to perform the experimental investigation in a short-duration turbine test rig where both high spatial and time accuracy is indispensable. The flow field at the rotor shroud was investigated with simultaneous measurements of heat transfer, static pressure and blade tip clearance by using fast response pressure, wall temperature and capacitance probes. Through repeat experiments at the same turbine operating point, the time-averaged and time-resolved adiabatic wall temperature and convective heat transfer coefficient were evaluated. In the frame of new engine architectures, a novel stator for an LP turbine is proposed with a multi-splitter layout that represents a new design solution towards compact, lighter and performing aero-engine turbomachinery. It contains small aero-vanes and large structural aerodynamic airfoils which are used to support the engine shaft and house service devices. The research focuses on the experimental investigation of the global performance, aerodynamics and thermodynamics of this novel HP-LP vane layout. The turbine was Advisors/Committee Members: Desantes Fernández, José Mª (advisor), Paniagua Pérez, Guillermo (advisor).

Subjects/Keywords: Heat transfer; Turbine; Multi-profile; Unsteady; High-pressure; Stator; Tip clearance; Adiabatic wall temperature; Interaction

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Lavagnoli, S. (2012). On the Aerothermal Flow Field in a Transonic HP Turbine Stage with a Multi-Profile LP Stator Vane . (Doctoral Dissertation). Universitat Politècnica de València. Retrieved from http://hdl.handle.net/10251/17799

Chicago Manual of Style (16^th Edition):

Lavagnoli, Sergio. “On the Aerothermal Flow Field in a Transonic HP Turbine Stage with a Multi-Profile LP Stator Vane .” 2012. Doctoral Dissertation, Universitat Politècnica de València. Accessed January 22, 2021. http://hdl.handle.net/10251/17799.

MLA Handbook (7^th Edition):

Lavagnoli, Sergio. “On the Aerothermal Flow Field in a Transonic HP Turbine Stage with a Multi-Profile LP Stator Vane .” 2012. Web. 22 Jan 2021.

Vancouver:

Lavagnoli S. On the Aerothermal Flow Field in a Transonic HP Turbine Stage with a Multi-Profile LP Stator Vane . [Internet] [Doctoral dissertation]. Universitat Politècnica de València; 2012. [cited 2021 Jan 22]. Available from: http://hdl.handle.net/10251/17799.

Council of Science Editors:

Lavagnoli S. On the Aerothermal Flow Field in a Transonic HP Turbine Stage with a Multi-Profile LP Stator Vane . [Doctoral Dissertation]. Universitat Politècnica de València; 2012. Available from: http://hdl.handle.net/10251/17799

The Ohio State University

18. Green, Brian Richard. Time-Averaged and Time-Accurate Aerodynamic Effects of Rotor Purge Flow for a Modern, Rotating, High-Pressure Turbine Stage and Low-Pressure Turbine Vane.

Degree: PhD, Mechanical Engineering, 2011, The Ohio State University

URL: http://rave.ohiolink.edu/etdc/view?acc_num=osu1322535026

► Rotor purge flow cavity seals are used in gas turbine engines to prevent ingestion of the mainstream gas flow into the purge cavity. Ingestion… (more)

▼ Rotor purge flow cavity seals are used in gas turbine engines to prevent ingestion of the mainstream gas flow into the purge cavity. Ingestion into this cavity leads to an increase in the cavity air temperature and subsequently to the rotor disk and stator metal temperatures leading to higher thermal stresses and reduced disk and stator fatigue life. An over designed cavity seal with an excess amount of purge flow has the downside of increasing engine fuel consumption through reduced turbine efficiency. The opposite approach of strengthening the hardware to withstand the higher stress and temperatures would increase the weight of the propulsion system. Understanding how the purge flow cavity and cavity seals interact with the mainstream gas is important to producing a balanced design between weight, fuel consumption, efficiency, and fatigue life of surrounding hardware. The main objective of this research was to perform an experimental and computational study of a one and one half stage high-pressure turbine installed at The Ohio State University Gas Turbine Laboratory Turbine Test Facility with emphasis on the rotor purge cavity. The rig housing the turbine stage incorporated many features found in a typical commercial high-pressure turbine such as a cooled high-pressure vane row with hub and shroud cooling, a downstream blade row followed by a downstream vane row, the ability to created elevated radial inlet temperature profiles using a combustor emulator, and a cooling supply line to the purge cavity. Multiple runs were performed to study the effects of cooling flows from both an aerodynamic and heat transfer perspective and incorporated instrumentation throughout the rig in order to capture time-accurate temperature, pressure, and heat flux measurements. The run matrix included cold rig configurations with no cooling flow, high-temperature uniform inlet profiles at the vane inlet for cases with and without cooling flows, and high-temperature radial inlet profiles with and without cooling flows. The computational study was performed using the Numeca FINE/Turbo code utilizing a multiple blade row model with both a steady and harmonic unsteady technique in order to simulate the physics of the experiments. Comparisons between the data and the computational results were performed for five different operational conditions: cold inlet and no cooling flow run, an elevated radial inlet temperature profile with purge and without purge cooling, and an elevated flat inlet temperature profile with purge and without purge cooling flow. The solutions were found to match very well to the exit rake measurements, the leading edge blade profile in the rotating frame of reference, the time-averaged and time-accurate static pressure on the vane hub, the stationary cavity wall, and the rotating cavity. Time-average comparisons were shown for the thermocouples located on the blade platform and in the stationary and rotating side of the cavity. For the two radial inlet cases and for the cold inlet case, these comparisons… Advisors/Committee Members: Dunn, Michael (Advisor).

Subjects/Keywords: Aerospace Engineering; Mechanical Engineering; Turbomachinery; High-pressure Turbine Rotor Purge Flow; Unsteady CFD

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APA (6^th Edition):

Green, B. R. (2011). Time-Averaged and Time-Accurate Aerodynamic Effects of Rotor Purge Flow for a Modern, Rotating, High-Pressure Turbine Stage and Low-Pressure Turbine Vane. (Doctoral Dissertation). The Ohio State University. Retrieved from http://rave.ohiolink.edu/etdc/view?acc_num=osu1322535026

Chicago Manual of Style (16^th Edition):

Green, Brian Richard. “Time-Averaged and Time-Accurate Aerodynamic Effects of Rotor Purge Flow for a Modern, Rotating, High-Pressure Turbine Stage and Low-Pressure Turbine Vane.” 2011. Doctoral Dissertation, The Ohio State University. Accessed January 22, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=osu1322535026.

MLA Handbook (7^th Edition):

Green, Brian Richard. “Time-Averaged and Time-Accurate Aerodynamic Effects of Rotor Purge Flow for a Modern, Rotating, High-Pressure Turbine Stage and Low-Pressure Turbine Vane.” 2011. Web. 22 Jan 2021.

Vancouver:

Green BR. Time-Averaged and Time-Accurate Aerodynamic Effects of Rotor Purge Flow for a Modern, Rotating, High-Pressure Turbine Stage and Low-Pressure Turbine Vane. [Internet] [Doctoral dissertation]. The Ohio State University; 2011. [cited 2021 Jan 22]. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=osu1322535026.

Council of Science Editors:

Green BR. Time-Averaged and Time-Accurate Aerodynamic Effects of Rotor Purge Flow for a Modern, Rotating, High-Pressure Turbine Stage and Low-Pressure Turbine Vane. [Doctoral Dissertation]. The Ohio State University; 2011. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=osu1322535026

Brno University of Technology

19. Kissler, Martin. Použití parních turbin: The use of Steam Turbines.

Degree: 2018, Brno University of Technology

URL: http://hdl.handle.net/11012/23905

► The aim of this bachelor’s thesis is to present the development of steam turbines from their construction to the detailed description of one of the… (more)

Subjects/Keywords: Parní turbína; jaderná elektrárna; turbosoustrojí; nízkotlaký díl; vysokotlaký díl; výkon.; Steam turbine; nuclear power plant; turbine; low pressure part; high pressure part; performance.

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APA (6^th Edition):

Kissler, M. (2018). Použití parních turbin: The use of Steam Turbines. (Thesis). Brno University of Technology. Retrieved from http://hdl.handle.net/11012/23905

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Kissler, Martin. “Použití parních turbin: The use of Steam Turbines.” 2018. Thesis, Brno University of Technology. Accessed January 22, 2021. http://hdl.handle.net/11012/23905.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Kissler, Martin. “Použití parních turbin: The use of Steam Turbines.” 2018. Web. 22 Jan 2021.

Vancouver:

Kissler M. Použití parních turbin: The use of Steam Turbines. [Internet] [Thesis]. Brno University of Technology; 2018. [cited 2021 Jan 22]. Available from: http://hdl.handle.net/11012/23905.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Kissler M. Použití parních turbin: The use of Steam Turbines. [Thesis]. Brno University of Technology; 2018. Available from: http://hdl.handle.net/11012/23905

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

University of Alabama

20. Williams, Larry Justin. Passive mitigation of combustion noise and thermo-acoustic instability using porous inert media at elevated pressure.

Degree: 2012, University of Alabama

URL: http://purl.lib.ua.edu/55100

► Combustion instabilities have presented major problems in high-pressure, turbulent combustion systems for nearly a century, beginning with rocket propulsion systems. To enhance combustion efficiencies, other… (more)

▼ Combustion instabilities have presented major problems in high-pressure, turbulent combustion systems for nearly a century, beginning with rocket propulsion systems. To enhance combustion efficiencies, other engines, such as gas turbines for power generation, operate at high pressures and reactant flow rates that are only small relative to those of rocket engine operation. The majority of power generation systems today extract energy from such efficient combustion processes. Recently, gas turbine engines, both power generation and propulsion platforms, are operated under very lean conditions to reduce flame temperatures and thus, emissions of the primary smog forming constituent, NOx. Extinction, flashback, blowoff , and autoignition pose challenges when operating at lean-premixed conditions. Flame stability at such lean conditions is problematic; thus, a swirled flow method is used to anchor and stabilize these flames. Intense turbulence, resulting from the pressure drop across flow swirlers, drives fluctuations in pressure and heat release rate. The feedback between pressure oscillations and heat release fluctuations in the reaction zone often drives resonant instabilities that propagate through the flow and surrounding structures. Such self-excited instabilities influence high rates of heat release in the reaction zone, which is located near the point of injection. Vibrations and high temperatures lead to the fatigue of injection components, instrumentation, and downstream turbine blades. A novel passive combustion noise control technique is experimentally investigated in the present study. The approach involves the mating of a porous inert material (PIM) with the inlet of a swirl-stabilized, lean-premixed combustor. The foam insert reduces turbulent intensities within the inner and outer recirculation zones of a common swirl-stabilized burner, thus reducing the amplitude of combustion driven instabilities. Experiments are conducted at high pressures, with high reactant flow rates and equivalence ratios. Results show that the ceramic foam insert is effective at mitigating combustion instabilities, suppressing combustion noise, and potentially, acoustic damping. The total sound pressure level for many of the cases investigated is reduced by 10 dB and greater. Furthermore, the approach can easily be retrofitted to commercial, industrial, and propulsion gas turbine combustion systems. (Published By University of Alabama Libraries) Advisors/Committee Members: Agrawal, Ajay K., Schreiber, Willard, Lang, Amy, Taylor, Bob, University of Alabama. Dept. of Mechanical Engineering.

Subjects/Keywords: Electronic Thesis or Dissertation; – thesis; Mechanical engineering; Aerospace engineering; Combustion instability; Combustion Noise; gas turbine engine; high pressure combustion; turbulent combustion

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Williams, L. J. (2012). Passive mitigation of combustion noise and thermo-acoustic instability using porous inert media at elevated pressure. (Thesis). University of Alabama. Retrieved from http://purl.lib.ua.edu/55100

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Williams, Larry Justin. “Passive mitigation of combustion noise and thermo-acoustic instability using porous inert media at elevated pressure.” 2012. Thesis, University of Alabama. Accessed January 22, 2021. http://purl.lib.ua.edu/55100.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Williams, Larry Justin. “Passive mitigation of combustion noise and thermo-acoustic instability using porous inert media at elevated pressure.” 2012. Web. 22 Jan 2021.

Vancouver:

Williams LJ. Passive mitigation of combustion noise and thermo-acoustic instability using porous inert media at elevated pressure. [Internet] [Thesis]. University of Alabama; 2012. [cited 2021 Jan 22]. Available from: http://purl.lib.ua.edu/55100.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Williams LJ. Passive mitigation of combustion noise and thermo-acoustic instability using porous inert media at elevated pressure. [Thesis]. University of Alabama; 2012. Available from: http://purl.lib.ua.edu/55100

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

KTH

21. Chandramouli, Sathyanarayanan. ON SIMULATING COMPRESSIBLE FLOWS WITH A DENSITY BASED SOLVER.

Degree: Mechanics, 2016, KTH

URL: http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-198926

► A coupled density based solver in the framework of foam-extend is used to perform simulations of transonic flows. The solver is based on an… (more)

Subjects/Keywords: Coupled density based solver; High Pressure Turbine Nozzle Guide Vane; Engineering and Technology; Teknik och teknologier

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APA (6^th Edition):

Chandramouli, S. (2016). ON SIMULATING COMPRESSIBLE FLOWS WITH A DENSITY BASED SOLVER. (Thesis). KTH. Retrieved from http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-198926

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Chandramouli, Sathyanarayanan. “ON SIMULATING COMPRESSIBLE FLOWS WITH A DENSITY BASED SOLVER.” 2016. Thesis, KTH. Accessed January 22, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-198926.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Chandramouli, Sathyanarayanan. “ON SIMULATING COMPRESSIBLE FLOWS WITH A DENSITY BASED SOLVER.” 2016. Web. 22 Jan 2021.

Vancouver:

Chandramouli S. ON SIMULATING COMPRESSIBLE FLOWS WITH A DENSITY BASED SOLVER. [Internet] [Thesis]. KTH; 2016. [cited 2021 Jan 22]. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-198926.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Chandramouli S. ON SIMULATING COMPRESSIBLE FLOWS WITH A DENSITY BASED SOLVER. [Thesis]. KTH; 2016. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-198926

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Brno University of Technology

22. Mašek, Martin. Kondenzační parní turbina 25 MW: Condesing Steam Turbine 25 MW.

Degree: 2019, Brno University of Technology

URL: http://hdl.handle.net/11012/23943

► Master’s thesis deals with design and calculation of one body condensing steam turbine of 25 MW with samples for paper-making industry. The thesis is focused… (more)

Subjects/Keywords: Kondenzační parní turbína; průtočná část; rovnotlaké lopatkování; regenerace; vysokootáčkový.; Condensing steam turbine; flow part; equal pressure blading; regeneration; high speed.

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APA (6^th Edition):

Mašek, M. (2019). Kondenzační parní turbina 25 MW: Condesing Steam Turbine 25 MW. (Thesis). Brno University of Technology. Retrieved from http://hdl.handle.net/11012/23943

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Mašek, Martin. “Kondenzační parní turbina 25 MW: Condesing Steam Turbine 25 MW.” 2019. Thesis, Brno University of Technology. Accessed January 22, 2021. http://hdl.handle.net/11012/23943.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Mašek, Martin. “Kondenzační parní turbina 25 MW: Condesing Steam Turbine 25 MW.” 2019. Web. 22 Jan 2021.

Vancouver:

Mašek M. Kondenzační parní turbina 25 MW: Condesing Steam Turbine 25 MW. [Internet] [Thesis]. Brno University of Technology; 2019. [cited 2021 Jan 22]. Available from: http://hdl.handle.net/11012/23943.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Mašek M. Kondenzační parní turbina 25 MW: Condesing Steam Turbine 25 MW. [Thesis]. Brno University of Technology; 2019. Available from: http://hdl.handle.net/11012/23943

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

23. Tang, Etienne. Modélisation et analyse de l'interaction turbine HP-Anneau de roue : Modeling and Analysis of the High Pressure Turbine-Rotor Shroud Interactions.

Degree: Docteur es, Mécanique, Energétique, Génie Civil et Acoustique, 2016, Lyon

URL: http://www.theses.fr/2016LYSEC053

►

L’influence de certains effets technologiques sur les performances d’une turbine n’est pas encore bien comprise. En particulier, des essais ont été réalisés par Safran Helicopter… (more)

▼

L’influence de certains effets technologiques sur les performances d’une turbine n’est pas encore bien comprise. En particulier, des essais ont été réalisés par Safran Helicopter Engines sur un étage de turbine haute pression dont l’anneau de roue forme une cavité reliée à la veine au niveau de l’espace inter-grilles, dans laquelle est injecté de l’air de refroidissement. Ils ont montré une sensibilité inattendue des performances à certains paramètres géométriques. Cette thèse a pour but d’expliquer ce comportement, et d’améliorer la compréhension et la prédiction par simulation numérique de l’effet d’une telle cavité sur l’aérodynamique et l’aérothermique de la turbine. Cette problématique a été traitée à l’aide de simulations numériques RANS instationnaires, réalisées avec le code elsA. Dans un premier temps, seule une partie de la cavité a été simulée, ce qui la ramène à une simple injection d’air de refroidissement dans la veine par une fente axisymétrique. Ces calculs ont montré que l’écoulement dans la veine est profondément modifié par l’air de refroidissement. Entre autres, le tourbillon de passage au carter et l’écoulement de jeu dans le rotor sont impactés, et deviennent fortement instationnaires. Les mécanismes d’interaction entrant en jeu sont détaillés, et l’effet sur les pertes est discuté. Des calculs prenant en compte la cavité entière ont ensuite été mis en place, d’abord avec un écoulement dans la veine simplifié, puis avec l’étage de turbine complet. Ils ont permis d’identifier une structure composée de poches de gaz de veine ingéré dans la cavité et de zones d’éjection d’air de refroidissement, tournant à une vitesse inférieure à celle du rotor, et manifestement générée par une instabilité. Des structures semblables avaient déjà été identifiées dans des turbines par de nombreuses études concernant des cavités inter-disques au moyeu, mais c’est ici la première fois qu’un tel comportement est obtenu dans une cavité composée de parois fixes et débouchant au carter. L’effet de cette structure sur l’écoulement dans la veine est qualitativement identique à celui obtenu par les simulations avec seulement une partie de la cavité, mais l’intensité et la fréquence des phénomènes d’interaction entre l’air de refroidissement injecté et l’écoulement principal sont modifiés par la rotation de la structure dans la cavité. Finalement, bien que les résultats d’essai n’ont pas pu être entièrement expliqués, ces travaux ont permis d’améliorer la compréhension des phénomènes se produisant dans une telle configuration, d’identifier les défis qu’ils posent aux simulations numériques, et d’ouvrir de nouvelles pistes de recherche.

The impact of some technological effects on the performances of a turbine are not yet well understood. More specifically, tests were performed by Safran Helicopter Engines on a high pressure turbine stage featuring a cavity over the rotor shroud, connected to the main gas path in the inter-rows space. Cooling air is injected in this cavity. This experimental campaign has shown an unexpected…

Advisors/Committee Members: Trebinjac, Isabelle (thesis director).

Subjects/Keywords: Turbine haute pression; Aérodynamique; Simulation numérique; Effets technologiques; Écoulements de cavités; Pertes; Instabilités; High pressure turbine; Aerodynamics; Numerical simulation; Technological effects; Cavity flows; Losses; Instabilities

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Tang, E. (2016). Modélisation et analyse de l'interaction turbine HP-Anneau de roue : Modeling and Analysis of the High Pressure Turbine-Rotor Shroud Interactions. (Doctoral Dissertation). Lyon. Retrieved from http://www.theses.fr/2016LYSEC053

Chicago Manual of Style (16^th Edition):

Tang, Etienne. “Modélisation et analyse de l'interaction turbine HP-Anneau de roue : Modeling and Analysis of the High Pressure Turbine-Rotor Shroud Interactions.” 2016. Doctoral Dissertation, Lyon. Accessed January 22, 2021. http://www.theses.fr/2016LYSEC053.

MLA Handbook (7^th Edition):

Tang, Etienne. “Modélisation et analyse de l'interaction turbine HP-Anneau de roue : Modeling and Analysis of the High Pressure Turbine-Rotor Shroud Interactions.” 2016. Web. 22 Jan 2021.

Vancouver:

Tang E. Modélisation et analyse de l'interaction turbine HP-Anneau de roue : Modeling and Analysis of the High Pressure Turbine-Rotor Shroud Interactions. [Internet] [Doctoral dissertation]. Lyon; 2016. [cited 2021 Jan 22]. Available from: http://www.theses.fr/2016LYSEC053.

Council of Science Editors:

Tang E. Modélisation et analyse de l'interaction turbine HP-Anneau de roue : Modeling and Analysis of the High Pressure Turbine-Rotor Shroud Interactions. [Doctoral Dissertation]. Lyon; 2016. Available from: http://www.theses.fr/2016LYSEC053

24. Wan, Aizon Bin W Ghopa. Studies on Aero-Thermal Performances of Leakage Flows lnjection from the Endwall Slot in Linear Cascade of High-Pressure Turbine : エンドウォールスロットからの漏れ流れを伴う高圧タービン直線翼列の熱流体的特性に関する研究.

Degree: 博士 (工学), 2016, Iwate University / 岩手大学

URL: http://hdl.handle.net/10140/5325

► Present studies focus on thermal and aerodynamics investigations of leakage flow injection through a slot which is located at upstream of blade leading edge. In… (more)

▼ Present studies focus on thermal and aerodynamics investigations of leakage flow injection through a slot which is located at upstream of blade leading edge. In the real gas turbine, this slot is actually the gap between the combustor and turbine endwall as for the maintenance works consideration. However, the slot induced to the leakage phenomenon caused by the bypassed air that coming from the compressor side for turbine cooling purposes. Gas turbine manufactures intended to minimize these kinds of leakages in maintaining the aerodynamics performance of the turbine cascade. However, previous researchers found that the leakages could be used to protect the endwall surfaces from the hot gas since it could not be completely prevented. Thus, present study investigated the potential of leakage flows as a function of film cooling. Chapter 1 gives some introduction on present works about the need of film cooling to protect the wall surfaces. Several related studies by previous researchers are also explained. Chapter 2 explained the details of methodologies used in present studies. A leakage flow with 90° of injection angle was considered as for the baseline configuration. Liquid crystal was used for the time-varying endwall temperature measurement. The transient method was applied to determine the film cooling effectiveness, η and the heat transfer coefficient, h for the thermal performance evaluations. The details of the aerodynamics performances was revealed by conducting 5-holes Pitot tube measurement at blade downstream plane (1.25Cax) and the total pressure loss coefficient, Cpt as well as the flow vorticity, ζ contours were plotted. Furthermore, the effects of the leakage flow with the mainstream consist of complex secondary flows structures also have been revealed by numerical investigation. In present study, the flow is analyzed by using the three-dimensional, steady Reynolds-averaged Navier-Stokes (RANS) equations by conducting Shear Stress Transport, SST turbulence model. The leakage was injected with a various amount (which is described by mass flow ratio, MFR) to observe theηperformance at different injection cases. Chapter 3 provided details discussions on the aero and thermal performances of the leakage injection. Both experimental and numerical presented the performance ofηincreased when the injection amount increases. SST turbulence model captured the presence of the separation flow that caused the lower h region which also captured by the experimental. As for the aerodynamics performance, Cpt was increased after the introduction of leakage injection and indicated the increase trend when the MFR was being increased. Leakage flows were prevented to be injected into high pressure region thus they tended to move towards lower pressure region which is between two stagnation regions. As a result, a newly generated vortex core was predicted. This accumulated vortex core (AFV) is considered to contribute to the additional losses at blade downstream. Chapter 4 presents the numerical investigation on the…

Subjects/Keywords: Turbomachinery; secondary flow; endwall film cooling; leakage flow; purge flow; heat transfer; high-pressure turbine; liquid crystal; transient method; pressure loss; slot orientation; slot position

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Wan, A. B. W. G. (2016). Studies on Aero-Thermal Performances of Leakage Flows lnjection from the Endwall Slot in Linear Cascade of High-Pressure Turbine : エンドウォールスロットからの漏れ流れを伴う高圧タービン直線翼列の熱流体的特性に関する研究. (Thesis). Iwate University / 岩手大学. Retrieved from http://hdl.handle.net/10140/5325

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Wan, Aizon Bin W Ghopa. “Studies on Aero-Thermal Performances of Leakage Flows lnjection from the Endwall Slot in Linear Cascade of High-Pressure Turbine : エンドウォールスロットからの漏れ流れを伴う高圧タービン直線翼列の熱流体的特性に関する研究.” 2016. Thesis, Iwate University / 岩手大学. Accessed January 22, 2021. http://hdl.handle.net/10140/5325.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Wan, Aizon Bin W Ghopa. “Studies on Aero-Thermal Performances of Leakage Flows lnjection from the Endwall Slot in Linear Cascade of High-Pressure Turbine : エンドウォールスロットからの漏れ流れを伴う高圧タービン直線翼列の熱流体的特性に関する研究.” 2016. Web. 22 Jan 2021.

Vancouver:

Wan ABWG. Studies on Aero-Thermal Performances of Leakage Flows lnjection from the Endwall Slot in Linear Cascade of High-Pressure Turbine : エンドウォールスロットからの漏れ流れを伴う高圧タービン直線翼列の熱流体的特性に関する研究. [Internet] [Thesis]. Iwate University / 岩手大学; 2016. [cited 2021 Jan 22]. Available from: http://hdl.handle.net/10140/5325.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Wan ABWG. Studies on Aero-Thermal Performances of Leakage Flows lnjection from the Endwall Slot in Linear Cascade of High-Pressure Turbine : エンドウォールスロットからの漏れ流れを伴う高圧タービン直線翼列の熱流体的特性に関する研究. [Thesis]. Iwate University / 岩手大学; 2016. Available from: http://hdl.handle.net/10140/5325

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

25. Wan, Aizon Bin W Ghopa. Studies on Aero-Thermal Performances of Leakage Flows lnjection from the Endwall Slot in Linear Cascade of High-Pressure Turbine : エンドウォールスロットからの漏れ流れを伴う高圧タービン直線翼列の熱流体的特性に関する研究.

Degree: 博士 (工学), 2016, Iwate University / 岩手大学

URL: http://id.nii.ac.jp/1399/00010395/

► Present studies focus on thermal and aerodynamics investigations of leakage flow injection through a slot which is located at upstream of blade leading edge. In… (more)

▼ Present studies focus on thermal and aerodynamics investigations of leakage flow injection through a slot which is located at upstream of blade leading edge. In the real gas turbine, this slot is actually the gap between the combustor and turbine endwall as for the maintenance works consideration. However, the slot induced to the leakage phenomenon caused by the bypassed air that coming from the compressor side for turbine cooling purposes. Gas turbine manufactures intended to minimize these kinds of leakages in maintaining the aerodynamics performance of the turbine cascade. However, previous researchers found that the leakages could be used to protect the endwall surfaces from the hot gas since it could not be completely prevented. Thus, present study investigated the potential of leakage flows as a function of film cooling. Chapter 1 gives some introduction on present works about the need of film cooling to protect the wall surfaces. Several related studies by previous researchers are also explained. Chapter 2 explained the details of methodologies used in present studies. A leakage flow with 90° of injection angle was considered as for the baseline configuration. Liquid crystal was used for the time-varying endwall temperature measurement. The transient method was applied to determine the film cooling effectiveness, η and the heat transfer coefficient, h for the thermal performance evaluations. The details of the aerodynamics performances was revealed by conducting 5-holes Pitot tube measurement at blade downstream plane (1.25Cax) and the total pressure loss coefficient, Cpt as well as the flow vorticity, ζ contours were plotted. Furthermore, the effects of the leakage flow with the mainstream consist of complex secondary flows structures also have been revealed by numerical investigation. In present study, the flow is analyzed by using the three-dimensional, steady Reynolds-averaged Navier-Stokes (RANS) equations by conducting Shear Stress Transport, SST turbulence model. The leakage was injected with a various amount (which is described by mass flow ratio, MFR) to observe theηperformance at different injection cases. Chapter 3 provided details discussions on the aero and thermal performances of the leakage injection. Both experimental and numerical presented the performance ofηincreased when the injection amount increases. SST turbulence model captured the presence of the separation flow that caused the lower h region which also captured by the experimental. As for the aerodynamics performance, Cpt was increased after the introduction of leakage injection and indicated the increase trend when the MFR was being increased. Leakage flows were prevented to be injected into high pressure region thus they tended to move towards lower pressure region which is between two stagnation regions. As a result, a newly generated vortex core was predicted. This accumulated vortex core (AFV) is considered to contribute to the additional losses at blade downstream. Chapter 4 presents the numerical investigation on the…

Subjects/Keywords: Turbomachinery; secondary flow; endwall film cooling; leakage flow; purge flow; heat transfer; high-pressure turbine; liquid crystal; transient method; pressure loss; slot orientation; slot position

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Wan, A. B. W. G. (2016). Studies on Aero-Thermal Performances of Leakage Flows lnjection from the Endwall Slot in Linear Cascade of High-Pressure Turbine : エンドウォールスロットからの漏れ流れを伴う高圧タービン直線翼列の熱流体的特性に関する研究. (Thesis). Iwate University / 岩手大学. Retrieved from http://id.nii.ac.jp/1399/00010395/

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Wan, Aizon Bin W Ghopa. “Studies on Aero-Thermal Performances of Leakage Flows lnjection from the Endwall Slot in Linear Cascade of High-Pressure Turbine : エンドウォールスロットからの漏れ流れを伴う高圧タービン直線翼列の熱流体的特性に関する研究.” 2016. Thesis, Iwate University / 岩手大学. Accessed January 22, 2021. http://id.nii.ac.jp/1399/00010395/.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Wan, Aizon Bin W Ghopa. “Studies on Aero-Thermal Performances of Leakage Flows lnjection from the Endwall Slot in Linear Cascade of High-Pressure Turbine : エンドウォールスロットからの漏れ流れを伴う高圧タービン直線翼列の熱流体的特性に関する研究.” 2016. Web. 22 Jan 2021.

Vancouver:

Wan ABWG. Studies on Aero-Thermal Performances of Leakage Flows lnjection from the Endwall Slot in Linear Cascade of High-Pressure Turbine : エンドウォールスロットからの漏れ流れを伴う高圧タービン直線翼列の熱流体的特性に関する研究. [Internet] [Thesis]. Iwate University / 岩手大学; 2016. [cited 2021 Jan 22]. Available from: http://id.nii.ac.jp/1399/00010395/.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Wan ABWG. Studies on Aero-Thermal Performances of Leakage Flows lnjection from the Endwall Slot in Linear Cascade of High-Pressure Turbine : エンドウォールスロットからの漏れ流れを伴う高圧タービン直線翼列の熱流体的特性に関する研究. [Thesis]. Iwate University / 岩手大学; 2016. Available from: http://id.nii.ac.jp/1399/00010395/

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Brno University of Technology

26. Fialová, Michaela. Modernizace sekundárního okruhu JE Dukovany: Upgrading the secondary circuit of the Dukovany NPP.

Degree: 2019, Brno University of Technology

URL: http://hdl.handle.net/11012/12190

► With the ever increasing usage of electric power and decreasing supply of natural resources, there is a growing effort to effectivelly maximise current dispositions of… (more)

Subjects/Keywords: Parogenerátor; parní turbína; nízkotlaký díl; vysokotlaký díl; kondenzátor; generátor; blokový transformátor; Steam generator; steam turbine; low pressure part; high pressure part; steam condenser; generator; block transformer

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APA (6^th Edition):

Fialová, M. (2019). Modernizace sekundárního okruhu JE Dukovany: Upgrading the secondary circuit of the Dukovany NPP. (Thesis). Brno University of Technology. Retrieved from http://hdl.handle.net/11012/12190

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Fialová, Michaela. “Modernizace sekundárního okruhu JE Dukovany: Upgrading the secondary circuit of the Dukovany NPP.” 2019. Thesis, Brno University of Technology. Accessed January 22, 2021. http://hdl.handle.net/11012/12190.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Fialová, Michaela. “Modernizace sekundárního okruhu JE Dukovany: Upgrading the secondary circuit of the Dukovany NPP.” 2019. Web. 22 Jan 2021.

Vancouver:

Fialová M. Modernizace sekundárního okruhu JE Dukovany: Upgrading the secondary circuit of the Dukovany NPP. [Internet] [Thesis]. Brno University of Technology; 2019. [cited 2021 Jan 22]. Available from: http://hdl.handle.net/11012/12190.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Fialová M. Modernizace sekundárního okruhu JE Dukovany: Upgrading the secondary circuit of the Dukovany NPP. [Thesis]. Brno University of Technology; 2019. Available from: http://hdl.handle.net/11012/12190

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

27. Sassy, Odin. Etude expérimentale du comportement sous chargement de fretting simple à haute température de superalliages à base nickel MC2 et CMSX-4. : Application aux aubes de turbine pour moteur d'hélicoptère : Experimental study of the damage response of MC2 and CMSX-4 superalloys subjected to fretting loading at high temperature : Application to turbine blades of helicopter englnes.

Degree: Docteur es, Matériaux, 2017, Lyon

URL: http://www.theses.fr/2017LYSEC017

►

Ce travail porte sur l'étude du comportement sous sollicitation de fretting sirnple à haute température de superalliages monocristallins à base de nickel MC2 et CMSX-4.… (more)

▼

Ce travail porte sur l'étude du comportement sous sollicitation de fretting sirnple à haute température de superalliages monocristallins à base de nickel MC2 et CMSX-4. Il trouve son application dans le domaine aéronautique, plus précisément au niveau de la turbine haute pression des moteurs d'hélicoptère. Celle-ci a pour fonction de convertir l'énergie cinétique des gaz brûlés en un couple qui entraîne en rotation le compresseur. Elle participe ainsi directement à l'entretien du cycle de combustion du moteur ce qui fait d'elle un organe clé. Située directement en aval de la chambre de combustion, la turbine haute pression (HP) est composée d'un disque central polycristallin et d'aubages monocristallins rapportés, liés au disque par une liaison dite pied de sapin. La rotation de la turbine et la température élevée des gaz de combustion va générer sur les aubes, le disque et l'attache qui les relie，des sollicitations thermomécaniques importantes. Du fait de la force centrifuge et du défilement des aubes devant les étages fixes des distributeurs, l'attache pied de sapin est la cible d 'oscillations dynamiques à l'origine de phénomènes d'endommagement par fretting. Ce fretting,, l'interface de contact entre l'aube et le disque fait l'objet d'une attention toute particulière，ce qui a motivé la conduite de ces travaux. Après une première phase et développement et de validation d'un banc d'essai innovant qui a nécessité la mise en place d'un dispositif de chauffage par induction, un soin tout particulier est apporté à la préparation des échantillons. La nature monocristalline du matériau constitutif des aubes nécessite en effet de respecter précisément l'orientation de la microstructure par rapport aux axes de sollicitation et la surface de contact. Pour cela une mesure systématique de la désorientation des axes primaires et secondaires des barreaux bruts est réalisée. La désorientation relevée est ensuite compensée au cas par cas lors du prélèvement par électroérosion des échantillons. Le lot d'échantillons obtenu peut dès lors être considéré comme homogène en terme d'orientation, malgré le fait que les barreaux bruts présentent des désorientations différentes. [...]

The aim of this work is to study the behavior of MC2 and CMSX-4 nickel based superalloys when subjected to fretting load at high temperature. Since it drives the compressor shaft, the high pressure turbine is a key part of the helicopter engine. 1n order to increase the global reliability and efficiency of the engine, single crystal nickel based superalloys are employed for turbine blades while disk parts are made of polycrystalline materials. Each turbine blade is attached to the central disk via a special link called fir tree root. Due to high temperature and dynamic oscillations, the contact zone between blades and disk is subjected to high thermomechanical stresses. 1t causes fretting phenomena that can lead to wear and cracking damage. This work focuses on both the partial slip and gross slip regime in order to study the damage process of single…

Advisors/Committee Members: Fouvry, Siegfried (thesis director), Berthel, Bruno (thesis director).

Subjects/Keywords: Superalliage à base nickel; Turbine haute pression; Fretting simple; Haute température; Fissuration; Usure; Glaze layer; Chauffage par induction; Nickel based superalloys; High pressure turbine; Fretting; High temperature; Crack; Wear; Glaze layer; Induction heating system

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Sassy, O. (2017). Etude expérimentale du comportement sous chargement de fretting simple à haute température de superalliages à base nickel MC2 et CMSX-4. : Application aux aubes de turbine pour moteur d'hélicoptère : Experimental study of the damage response of MC2 and CMSX-4 superalloys subjected to fretting loading at high temperature : Application to turbine blades of helicopter englnes. (Doctoral Dissertation). Lyon. Retrieved from http://www.theses.fr/2017LYSEC017

Chicago Manual of Style (16^th Edition):

Sassy, Odin. “Etude expérimentale du comportement sous chargement de fretting simple à haute température de superalliages à base nickel MC2 et CMSX-4. : Application aux aubes de turbine pour moteur d'hélicoptère : Experimental study of the damage response of MC2 and CMSX-4 superalloys subjected to fretting loading at high temperature : Application to turbine blades of helicopter englnes.” 2017. Doctoral Dissertation, Lyon. Accessed January 22, 2021. http://www.theses.fr/2017LYSEC017.

MLA Handbook (7^th Edition):

Sassy, Odin. “Etude expérimentale du comportement sous chargement de fretting simple à haute température de superalliages à base nickel MC2 et CMSX-4. : Application aux aubes de turbine pour moteur d'hélicoptère : Experimental study of the damage response of MC2 and CMSX-4 superalloys subjected to fretting loading at high temperature : Application to turbine blades of helicopter englnes.” 2017. Web. 22 Jan 2021.

Vancouver:

Sassy O. Etude expérimentale du comportement sous chargement de fretting simple à haute température de superalliages à base nickel MC2 et CMSX-4. : Application aux aubes de turbine pour moteur d'hélicoptère : Experimental study of the damage response of MC2 and CMSX-4 superalloys subjected to fretting loading at high temperature : Application to turbine blades of helicopter englnes. [Internet] [Doctoral dissertation]. Lyon; 2017. [cited 2021 Jan 22]. Available from: http://www.theses.fr/2017LYSEC017.

Council of Science Editors:

Sassy O. Etude expérimentale du comportement sous chargement de fretting simple à haute température de superalliages à base nickel MC2 et CMSX-4. : Application aux aubes de turbine pour moteur d'hélicoptère : Experimental study of the damage response of MC2 and CMSX-4 superalloys subjected to fretting loading at high temperature : Application to turbine blades of helicopter englnes. [Doctoral Dissertation]. Lyon; 2017. Available from: http://www.theses.fr/2017LYSEC017

University of Saskatchewan

28. Yang, Yongxu. The effect of submerged arc welding parameters on the properties of pressure vessel and wind turbine tower steels.

Degree: 2008, University of Saskatchewan

URL: http://hdl.handle.net/10388/etd-10072008-161112

► Submerged arc welding (SAW) is commonly used for fabricating large diameter linepipes, pressure vessels and wind turbine towers due to its high deposition rate, high… (more)

▼ Submerged arc welding (SAW) is commonly used for fabricating large diameter linepipes, pressure vessels and wind turbine towers due to its high deposition rate, high quality welds, ease of automation and low operator skill requirement. In order to achieve high melting efficiency required for high productivity, best weld quality and good mechanical properties in manufacturing industries, the welding process parameters need to be optimized. In this study, the effect of SAW current and speed on the physical and mechanical properties of ASME SA516 Gr. 70 (pressure vessel steel) and ASTM A709 Gr. 50 (wind turbine tower steel) were investigated. Three welding currents (700 A, 800 A and 850 A) and four travel speeds (5.9, 9.3, 12.3 and 15.3 mm/s) were used to weld sample plates measuring 915 mm x 122 mm x 17 mm. The weld quality and properties were evaluated using weld geometry measurements, visual inspection, ultrasonic inspection, hardness measurements, optical microscopy, tensile testing, Charpy impact testing and scanning electron microscopy. It was found that the physical and mechanical properties of the weldments were affected by SAW parameters. Severe undercuts were found at high travel speed and welding current. Low heat input caused lack of penetration defects to form in the weldments. The welding process melting efficiency (WPME) achieved was up to 80%. The hardness of the coarse grain heat affected zone (CGHAZ) and the weld metal increased with travel speed. The toughness of both materials increased with increasing travel speed and welding current. The yield and tensile strengths of the weldments of SA516 Gr.70 and A709 Gr.50 steels were within the same range as those of their respective parent metals because all test specimens broke in the parent metals. Also, the parent metals of both steels had the highest fracture strain and percent elongation. The percentage elongation increased with travel speed but decreased with welding current. Advisors/Committee Members: Oguocha, Ikechukwuka N., Yannacopoulos, Spiro, Yang, Qiaoqin, Fotouhi, Reza.

Subjects/Keywords: Pressure Vessel; Wind Turbine Tower; High Stength Low Alloy Steel; Submerged Arc Welding

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APA (6^th Edition):

Yang, Y. (2008). The effect of submerged arc welding parameters on the properties of pressure vessel and wind turbine tower steels. (Thesis). University of Saskatchewan. Retrieved from http://hdl.handle.net/10388/etd-10072008-161112

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Yang, Yongxu. “The effect of submerged arc welding parameters on the properties of pressure vessel and wind turbine tower steels.” 2008. Thesis, University of Saskatchewan. Accessed January 22, 2021. http://hdl.handle.net/10388/etd-10072008-161112.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Yang, Yongxu. “The effect of submerged arc welding parameters on the properties of pressure vessel and wind turbine tower steels.” 2008. Web. 22 Jan 2021.

Vancouver:

Yang Y. The effect of submerged arc welding parameters on the properties of pressure vessel and wind turbine tower steels. [Internet] [Thesis]. University of Saskatchewan; 2008. [cited 2021 Jan 22]. Available from: http://hdl.handle.net/10388/etd-10072008-161112.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Yang Y. The effect of submerged arc welding parameters on the properties of pressure vessel and wind turbine tower steels. [Thesis]. University of Saskatchewan; 2008. Available from: http://hdl.handle.net/10388/etd-10072008-161112

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

29. Malbois, Pierre. Analyse expérimentale par diagnostics lasers du mélange kérosène/air et de la combustion swirlée pauvre prémélangée, haute-pression issue d’un injecteur Low-NOx : Experimental investigation by laser diagnostics of the kerosene/air mixing and high-pressure swirl-stabilized lean premixed combustion from a low-NOx injection system.

Degree: Docteur es, Energie et propulsion, 2017, Normandie

URL: http://www.theses.fr/2017NORMIR25

►

Les motoristes aéronautiques misent sur le développement de systèmes d’injection de carburant innovants pour réduire la consommation de carburant et les émissions de polluants. L’objectif… (more)

▼

Les motoristes aéronautiques misent sur le développement de systèmes d’injection de carburant innovants pour réduire la consommation de carburant et les émissions de polluants. L’objectif de la thèse est de contribuer à l’étude expérimentale d’un injecteur « Lean Premixed » par le développement de diagnostics lasers couplant des approches basées sur la diffusion de Mie et l’émission fluorescente de traceurs. Les mesures ont été réalisées sur le banc de combustion haute pression HERON. Une approche novatrice avec l’imagerie de fluorescence du kérosène a permis d’obtenir une quantification du mélange kérosène/air. La structure de flamme a été mesurée simultanément par PLIF-OH et des mesures PIV de vitesse ont complété cette analyse. Un développement préliminaire de la PLIF-CO a également été mené. Les nombreuses mesures permettent de fournir une analyse détaillée des interactions flamme/spray/aérodynamique lors d’une combustion swirlée stabilisée kérosène/air à haute pression.

Aeronautical engine manufacturers are banking on the development of innovative fuel injection systems to reduce fuel consumption and pollutant emissions. The aim of the thesis is to contribute to the experimental investigation of a "Lean Premixed" injector by developing laser diagnostics coupling approaches based on Mie scattering and fluorescent emission of tracers. Measurements are performed at high pressure on the HERON combustion test bench. An innovative approach with fluorescence imaging of kerosene has resulted in the quantification of the kerosene/air mixture. The flame structure was analyzed simultaneously by OH-PLIF and velocity PIV measurements were performed to complete this analysis. A preliminary development of CO-PLIF was also conducted. The numerous measurements provided a detailed analysis of the mechanisms of flame/spray/aerodynamic interactions during a swirl-stabilized kerosene/air combustion at high pressure.

Advisors/Committee Members: Renou, Bruno (thesis director), Grisch, Frédéric (thesis director).

Subjects/Keywords: Mélange kérosène/air; Diagnostics optiques; High pressure spray combustion; Kerosene/air mixture; Aeronautical gas turbine; Optical diagnostics; Particule image velocimetry; Radical hydroxil-Planar laser induced fluorescence; Lean premixed injector

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Malbois, P. (2017). Analyse expérimentale par diagnostics lasers du mélange kérosène/air et de la combustion swirlée pauvre prémélangée, haute-pression issue d’un injecteur Low-NOx : Experimental investigation by laser diagnostics of the kerosene/air mixing and high-pressure swirl-stabilized lean premixed combustion from a low-NOx injection system. (Doctoral Dissertation). Normandie. Retrieved from http://www.theses.fr/2017NORMIR25

Chicago Manual of Style (16^th Edition):

Malbois, Pierre. “Analyse expérimentale par diagnostics lasers du mélange kérosène/air et de la combustion swirlée pauvre prémélangée, haute-pression issue d’un injecteur Low-NOx : Experimental investigation by laser diagnostics of the kerosene/air mixing and high-pressure swirl-stabilized lean premixed combustion from a low-NOx injection system.” 2017. Doctoral Dissertation, Normandie. Accessed January 22, 2021. http://www.theses.fr/2017NORMIR25.

MLA Handbook (7^th Edition):

Malbois, Pierre. “Analyse expérimentale par diagnostics lasers du mélange kérosène/air et de la combustion swirlée pauvre prémélangée, haute-pression issue d’un injecteur Low-NOx : Experimental investigation by laser diagnostics of the kerosene/air mixing and high-pressure swirl-stabilized lean premixed combustion from a low-NOx injection system.” 2017. Web. 22 Jan 2021.

Vancouver:

Malbois P. Analyse expérimentale par diagnostics lasers du mélange kérosène/air et de la combustion swirlée pauvre prémélangée, haute-pression issue d’un injecteur Low-NOx : Experimental investigation by laser diagnostics of the kerosene/air mixing and high-pressure swirl-stabilized lean premixed combustion from a low-NOx injection system. [Internet] [Doctoral dissertation]. Normandie; 2017. [cited 2021 Jan 22]. Available from: http://www.theses.fr/2017NORMIR25.

Council of Science Editors:

Malbois P. Analyse expérimentale par diagnostics lasers du mélange kérosène/air et de la combustion swirlée pauvre prémélangée, haute-pression issue d’un injecteur Low-NOx : Experimental investigation by laser diagnostics of the kerosene/air mixing and high-pressure swirl-stabilized lean premixed combustion from a low-NOx injection system. [Doctoral Dissertation]. Normandie; 2017. Available from: http://www.theses.fr/2017NORMIR25

Wright State University

30. McQuilling, Mark W. DESIGN AND VALIDATION OF A HIGH-LIFT LOW-PRESSURE TURBINE BLADE.

Degree: PhD, Engineering PhD, 2007, Wright State University

URL: http://rave.ohiolink.edu/etdc/view?acc_num=wright1189792837

► This dissertation is a design and validation study of the high-lift low-pressure turbine (LPT) blade designated L2F. High-lift LPTs offer the promise of reducing the… (more)

▼ This dissertation is a design and validation study of the high-lift low-pressure turbine (LPT) blade designated L2F. High-lift LPTs offer the promise of reducing the blade count in modern gas turbine engines. Decreasing the blade count can reduce development and maintenance costs and the weight of the engine, but care must be taken in order to maintain turbine section performance with fewer blades. For an equivalent amount of work extracted, lower blade counts increase blade loading in the LPT section. The high-lift LPT presented herein allows 38% fewer blades with a Zweifel loading coefficient of 1.59 and maintains the same inlet and outlet blade metal angles of conventional geometries in service today while providing an improved low-Reynolds number characteristic. The computational design method utilizes the Turbine Design and Analysis System (TDAAS) developed by John Clark of the Air Force Research Laboratory. TDAAS integrates several government-funded design utilities including airfoil and grid generation capability with a Reynolds-Averaged Navier-Stokes flow solver into a single, menu-driven, Matlab-based system. Transition modeling is achieved with the recently developed model of Praisner and Clark, and this study validates the use of the model for design purposes outside of the Pratt & Whitney (P&W) design system where they were created. Turbulence modeling is achieved with the Baldwin and Lomax zero-equation model. The experimental validation consists of testing the front-loaded L2F along with a previously designed, mid-loaded blade (L1M) in a linear turbine cascade in a low-speed wind tunnel over a range of Reynolds numbers at 3.3% freestream turbulence. Hot-wire anemometry and pressure measurements elucidate these comparisons, while a shear and stress sensitive film (S3F) also helps describe the flow in areas of interest. S3F can provide all 3 components of stress on a surface in a single measurement, and these tests extend the operational envelope of the technique to low speed air environments where small dynamic pressures and curved surfaces preclude the use of more traditional global measurement methods. Results are compared between the L1M and L2F geometries along with previous data taken in the same wind tunnel at identical flow conditions for the P&W Pack B geometry. Advisors/Committee Members: Wolff, Mitch (Advisor).

Subjects/Keywords: low-pressure turbine; high lift; L2F; L1M; transition; zweifel; surface stress; shear; S3F

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APA (6^th Edition):

McQuilling, M. W. (2007). DESIGN AND VALIDATION OF A HIGH-LIFT LOW-PRESSURE TURBINE BLADE. (Doctoral Dissertation). Wright State University. Retrieved from http://rave.ohiolink.edu/etdc/view?acc_num=wright1189792837

Chicago Manual of Style (16^th Edition):

McQuilling, Mark W. “DESIGN AND VALIDATION OF A HIGH-LIFT LOW-PRESSURE TURBINE BLADE.” 2007. Doctoral Dissertation, Wright State University. Accessed January 22, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=wright1189792837.

MLA Handbook (7^th Edition):

McQuilling, Mark W. “DESIGN AND VALIDATION OF A HIGH-LIFT LOW-PRESSURE TURBINE BLADE.” 2007. Web. 22 Jan 2021.

Vancouver:

McQuilling MW. DESIGN AND VALIDATION OF A HIGH-LIFT LOW-PRESSURE TURBINE BLADE. [Internet] [Doctoral dissertation]. Wright State University; 2007. [cited 2021 Jan 22]. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=wright1189792837.

Council of Science Editors:

McQuilling MW. DESIGN AND VALIDATION OF A HIGH-LIFT LOW-PRESSURE TURBINE BLADE. [Doctoral Dissertation]. Wright State University; 2007. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=wright1189792837

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Open Access Theses and Dissertations