subject:(film cooling)

University of Texas – Austin

1. -3677-5743. The effect of channel parameters on the adiabatic film cooling effectiveness of shaped holes in crossflow.

Degree: MSin Engineering, Mechanical engineering, 2015, University of Texas – Austin

URL: http://hdl.handle.net/2152/34143

► There is limited information in the literature on the behavior of shaped film cooling holes fed by crossflow and even less information on the effect… (more)

Subjects/Keywords: Film cooling; Turbomachinery

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APA (6^th Edition):

-3677-5743. (2015). The effect of channel parameters on the adiabatic film cooling effectiveness of shaped holes in crossflow. (Masters Thesis). University of Texas – Austin. Retrieved from http://hdl.handle.net/2152/34143

Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete

Chicago Manual of Style (16^th Edition):

-3677-5743. “The effect of channel parameters on the adiabatic film cooling effectiveness of shaped holes in crossflow.” 2015. Masters Thesis, University of Texas – Austin. Accessed January 23, 2021. http://hdl.handle.net/2152/34143.

Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete

MLA Handbook (7^th Edition):

-3677-5743. “The effect of channel parameters on the adiabatic film cooling effectiveness of shaped holes in crossflow.” 2015. Web. 23 Jan 2021.

Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete

Vancouver:

-3677-5743. The effect of channel parameters on the adiabatic film cooling effectiveness of shaped holes in crossflow. [Internet] [Masters thesis]. University of Texas – Austin; 2015. [cited 2021 Jan 23]. Available from: http://hdl.handle.net/2152/34143.

Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete

Council of Science Editors:

-3677-5743. The effect of channel parameters on the adiabatic film cooling effectiveness of shaped holes in crossflow. [Masters Thesis]. University of Texas – Austin; 2015. Available from: http://hdl.handle.net/2152/34143

Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete

Virginia Tech

2. Leblanc, Christopher N. Design, Analysis, and Development of a Tripod Film Cooling Hole Design for Reduced Coolant Usage.

Degree: PhD, Mechanical Engineering, 2012, Virginia Tech

URL: http://hdl.handle.net/10919/19206

► This research has a small portion focused on interior serpentine channels, with the primary focus on improving the effectiveness of the film cooling technique through… (more)

▼ This research has a small portion focused on interior serpentine channels, with the primary focus on improving the effectiveness of the film cooling technique through the use of a new approach to film cooling. This new approach uses a set of three holes sharing the same inlet and diverging from the central hole to form a three-legged, or tripod, design. The tripod design is examined in depth, in terms of geometric variations, through the use of flat plate and cascade rigs, with both transient and steady-state experiments. The flat plate tests provide a simplified setting in which to test the design in comparison to other geometries, and establish a baseline performance in a simple flow field that does not have the complications of surface curvature or mainstream pressure gradients. Cascade tests allow for testing of the design in a more realistic setting with curved surfaces and mainstream pressure gradients, providing important information about the performance of the design on suction and pressure surfaces of airfoils. Additionally, the cascade tests allow for an investigation into the aerodynamic penalties associated with the injection hole designs at various flow rates. Through this procedure the current state of film cooling technology may be improved, with more effective surface coverage achieved with reduced coolant usage, and with reduced performance penalties for the engine as a whole. This research has developed a new film hole design that is manufacturable and durable, and provides a detailed analysis of its performance under a variety of flow conditions. This cooling hole design provides 40% higher cooling effectiveness while using 50% less coolant mass flow. The interior serpentine channel research provides comparisons between correlations and experiments for internal passages with realistic cross sections. Advisors/Committee Members: Ekkad, Srinath V. (committeechair), Roy, Christopher John (committee member), Tafti, Danesh K. (committee member), Diller, Thomas E. (committee member), Ng, Wing Fai (committee member).

Subjects/Keywords: Heat Transfer; Gas Turbine Cooling; Film Cooling

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APA (6^th Edition):

Leblanc, C. N. (2012). Design, Analysis, and Development of a Tripod Film Cooling Hole Design for Reduced Coolant Usage. (Doctoral Dissertation). Virginia Tech. Retrieved from http://hdl.handle.net/10919/19206

Chicago Manual of Style (16^th Edition):

Leblanc, Christopher N. “Design, Analysis, and Development of a Tripod Film Cooling Hole Design for Reduced Coolant Usage.” 2012. Doctoral Dissertation, Virginia Tech. Accessed January 23, 2021. http://hdl.handle.net/10919/19206.

MLA Handbook (7^th Edition):

Leblanc, Christopher N. “Design, Analysis, and Development of a Tripod Film Cooling Hole Design for Reduced Coolant Usage.” 2012. Web. 23 Jan 2021.

Vancouver:

Leblanc CN. Design, Analysis, and Development of a Tripod Film Cooling Hole Design for Reduced Coolant Usage. [Internet] [Doctoral dissertation]. Virginia Tech; 2012. [cited 2021 Jan 23]. Available from: http://hdl.handle.net/10919/19206.

Council of Science Editors:

Leblanc CN. Design, Analysis, and Development of a Tripod Film Cooling Hole Design for Reduced Coolant Usage. [Doctoral Dissertation]. Virginia Tech; 2012. Available from: http://hdl.handle.net/10919/19206

Louisiana State University

3. Babaee, Hessam. Uncertainty quantification of film cooling effectiveness in gas turbines.

Degree: MS, Applied Mathematics, 2013, Louisiana State University

URL: etd-07082013-005157 ; https://digitalcommons.lsu.edu/gradschool_theses/1389

► In this study the effect of uncertainty of velocity ratio on jet in crossflow and particual- rly film cooling performance is studied. Direct numerical simulations… (more)

Subjects/Keywords: bifurcation; uncertainty quantification; Film cooling

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APA (6^th Edition):

Babaee, H. (2013). Uncertainty quantification of film cooling effectiveness in gas turbines. (Masters Thesis). Louisiana State University. Retrieved from etd-07082013-005157 ; https://digitalcommons.lsu.edu/gradschool_theses/1389

Chicago Manual of Style (16^th Edition):

Babaee, Hessam. “Uncertainty quantification of film cooling effectiveness in gas turbines.” 2013. Masters Thesis, Louisiana State University. Accessed January 23, 2021. etd-07082013-005157 ; https://digitalcommons.lsu.edu/gradschool_theses/1389.

MLA Handbook (7^th Edition):

Babaee, Hessam. “Uncertainty quantification of film cooling effectiveness in gas turbines.” 2013. Web. 23 Jan 2021.

Vancouver:

Babaee H. Uncertainty quantification of film cooling effectiveness in gas turbines. [Internet] [Masters thesis]. Louisiana State University; 2013. [cited 2021 Jan 23]. Available from: etd-07082013-005157 ; https://digitalcommons.lsu.edu/gradschool_theses/1389.

Council of Science Editors:

Babaee H. Uncertainty quantification of film cooling effectiveness in gas turbines. [Masters Thesis]. Louisiana State University; 2013. Available from: etd-07082013-005157 ; https://digitalcommons.lsu.edu/gradschool_theses/1389

Louisiana State University

4. Gonzalez Rodriguez, Carlos Rene. Experimental Study of a Cascade of Low Pressure Turbine Blades with Upstream Periodic Stator Wakes.

Degree: MSME, Mechanical Engineering, 2015, Louisiana State University

URL: etd-11122015-210639 ; https://digitalcommons.lsu.edu/gradschool_theses/1971

► The objective of this study is to experimentally study film cooling flows. A closed-loop wind tunnel with a four passage linear cascade of US Air… (more)

Subjects/Keywords: film cooling; periodic wakes; PIV

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APA (6^th Edition):

Gonzalez Rodriguez, C. R. (2015). Experimental Study of a Cascade of Low Pressure Turbine Blades with Upstream Periodic Stator Wakes. (Masters Thesis). Louisiana State University. Retrieved from etd-11122015-210639 ; https://digitalcommons.lsu.edu/gradschool_theses/1971

Chicago Manual of Style (16^th Edition):

Gonzalez Rodriguez, Carlos Rene. “Experimental Study of a Cascade of Low Pressure Turbine Blades with Upstream Periodic Stator Wakes.” 2015. Masters Thesis, Louisiana State University. Accessed January 23, 2021. etd-11122015-210639 ; https://digitalcommons.lsu.edu/gradschool_theses/1971.

MLA Handbook (7^th Edition):

Gonzalez Rodriguez, Carlos Rene. “Experimental Study of a Cascade of Low Pressure Turbine Blades with Upstream Periodic Stator Wakes.” 2015. Web. 23 Jan 2021.

Vancouver:

Gonzalez Rodriguez CR. Experimental Study of a Cascade of Low Pressure Turbine Blades with Upstream Periodic Stator Wakes. [Internet] [Masters thesis]. Louisiana State University; 2015. [cited 2021 Jan 23]. Available from: etd-11122015-210639 ; https://digitalcommons.lsu.edu/gradschool_theses/1971.

Council of Science Editors:

Gonzalez Rodriguez CR. Experimental Study of a Cascade of Low Pressure Turbine Blades with Upstream Periodic Stator Wakes. [Masters Thesis]. Louisiana State University; 2015. Available from: etd-11122015-210639 ; https://digitalcommons.lsu.edu/gradschool_theses/1971

Louisiana State University

5. Drewes, Christopher Michael. The Design, Fabrication, and Validation of a Film Cooled Rotating Turbine Cascade with an Actively Cooled Shroud in a Closed Loop Wind Tunnel.

Degree: MSME, Mechanical Engineering, 2016, Louisiana State University

URL: etd-04072016-074848 ; https://digitalcommons.lsu.edu/gradschool_theses/2030

► To test shroud and blade cooling effectiveness, a closed loop, heated wind tunnel housing a film cooled rotating turbine cascade with prescribed blade and vane… (more)

▼ To test shroud and blade cooling effectiveness, a closed loop, heated wind tunnel housing a film cooled rotating turbine cascade with prescribed blade and vane geometry surrounded by a fully cooled shroud with a leading edge gap were designed and assembled on Louisiana State University’s campus. Heat transfer coefficients and film cooling effectiveness results were computed using a 1-D semi-infinite solid conduction analysis of material temperatures obtained with liquid crystal thermography. Proper analysis required a step change in air temperature; so a bypass loop provided mainstream air heating while maintaining the shroud and blades at ambient temperature. Also, analysis required hollow tip film cooled turbine blades constructed of low thermal conductivity material, resulting in fabrication by 3-D plastic printing. An analytical stress model and finite element analysis validated plastic blade structural base design. Static-structural and dynamic fatigue loading analyses determined rotor shaft size. Heat transfer and pressure loss calculations verified the system’s required blade and shroud cooling characteristics. Finally, velocity vector measurements at the nozzle guide vane leading edge and recorded pressures in a nozzle guide vane passageway upstream of the turbine cascade location validated incoming freestream flow properties for the design condition at which heat transfer measurements were recorded. A total pressure loss analysis for varying rotor speed and blowing ratio was conducted with the development of total pressure contours downstream of the exit guide vanes to understand losses in the nozzle-rotor passage. Loss structures were found at the tip and root of the exit guide vane, attributed to the shed vortex and tip leakage vortex developed from the rotor blade. Total pressure loss decreased as blowing ratio increased due to energy added to the mainstream flow through the film cooling air. Rotor speed was varied from 55 to 655 RPM. Total pressure losses were lowest at 55 RPM, increased with increasing rotor speed past the 355 RPM design speed, and decreased as rotor speed approached 655 RPM. These results could be attributed to the introduction or extraction of shaft work in the rotating system along with aerodynamic losses associated with changes from the incidence angle design.

Subjects/Keywords: shroud cooling; tip cooling; heat transfer; gas turbine; film cooling

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APA (6^th Edition):

Drewes, C. M. (2016). The Design, Fabrication, and Validation of a Film Cooled Rotating Turbine Cascade with an Actively Cooled Shroud in a Closed Loop Wind Tunnel. (Masters Thesis). Louisiana State University. Retrieved from etd-04072016-074848 ; https://digitalcommons.lsu.edu/gradschool_theses/2030

Chicago Manual of Style (16^th Edition):

Drewes, Christopher Michael. “The Design, Fabrication, and Validation of a Film Cooled Rotating Turbine Cascade with an Actively Cooled Shroud in a Closed Loop Wind Tunnel.” 2016. Masters Thesis, Louisiana State University. Accessed January 23, 2021. etd-04072016-074848 ; https://digitalcommons.lsu.edu/gradschool_theses/2030.

MLA Handbook (7^th Edition):

Drewes, Christopher Michael. “The Design, Fabrication, and Validation of a Film Cooled Rotating Turbine Cascade with an Actively Cooled Shroud in a Closed Loop Wind Tunnel.” 2016. Web. 23 Jan 2021.

Vancouver:

Drewes CM. The Design, Fabrication, and Validation of a Film Cooled Rotating Turbine Cascade with an Actively Cooled Shroud in a Closed Loop Wind Tunnel. [Internet] [Masters thesis]. Louisiana State University; 2016. [cited 2021 Jan 23]. Available from: etd-04072016-074848 ; https://digitalcommons.lsu.edu/gradschool_theses/2030.

Council of Science Editors:

Drewes CM. The Design, Fabrication, and Validation of a Film Cooled Rotating Turbine Cascade with an Actively Cooled Shroud in a Closed Loop Wind Tunnel. [Masters Thesis]. Louisiana State University; 2016. Available from: etd-04072016-074848 ; https://digitalcommons.lsu.edu/gradschool_theses/2030

The Ohio State University

6. Prenter, Robin Michael Patrick. Investigating the Physics and Performance of Reverse-Oriented Film Cooling.

Degree: PhD, Aero/Astro Engineering, 2017, The Ohio State University

URL: http://rave.ohiolink.edu/etdc/view?acc_num=osu1500505248644198

► Reverse-oriented film cooling, which consists of film cooling holes oriented to inject coolant in the opposite direction of the freestream, is experimentally and numerically investigated.… (more)

▼ Reverse-oriented film cooling, which consists of film cooling holes oriented to inject coolant in the opposite direction of the freestream, is experimentally and numerically investigated. Tests are conducted at various blowing ratios (M = 0.25, 0.5, and 1.0) under both low and high freestream turbulence (Tu = 0.4% and 13%), with a density ratio near unity. The interesting flow field that results from the reverse jet-in-crossflow interaction is characterized using flow visualization, particle imagevelocimetry, and thermal field measurements. Heat transfer performance is evaluated with adiabatic film effectiveness and heat transfer coefficient measurements obtained using infrared thermography. Adiabatic effectiveness results show that reverse film cooling produces very uniform and total coverage downstream of the holes, with some reduction due to increased freestream turbulence. The reverse film cooling holes are evaluated against cylindrical holes in the conventional configuration, and were found to perform better in terms of average effectiveness and comparably in terms of netheat flux reduction, despite augmented heat transfer coefficient. Compared to shaped hole data from the current study as well as previous literature, the reverse film cooling holes generally exhibited worse heat transfer performance. The aerodynamic losses associated with the film cooling are characterized using total pressure measurements downstream of the holes. Losses from the reverse configuration were found to be higher when compared to cylindrical holes in the conventional and compound angle configurations. To investigate the unsteady three-dimensional flow physics, large eddy simulations were conducted to replicate the experiment at all three blowing ratios, under low and high freestream turbulence. The models were first validated against the experimental measurements, before being used to provide insight into the complicated flowfield associated with the interaction between the reverse film cooling jet and main crossflow. The specific in-hole velocity profile that arises within the short L/D hole was found to be closely tied to the nature of the resulting interaction, with different in-hole fluid regions playing specific roles. Additionally, the model was ableto capture many of the coherent turbulent structures observed in the experimental flow visualization. A quasi-periodic shedding of the coolant fluid within the strong recirculation zone at the apex of the jet trajectory was identified. The cause of this phenomenon was found to be the migration of windward jet shear layer vortices to the leeward side, which disrupts the jet and subsequently the recirculation zone, allowing for the detachment of fluid in this region. Turbulent heat flux components from thelarge-eddy simulation were compared, with a discussion on the implications for use of isotropic turbulent diffusivity in RANS models. Insight gained from the experiments and numerical simulations was used to make notional suggestions of possible design improvements, to augment the… Advisors/Committee Members: Bons, Jeffrey (Advisor).

Subjects/Keywords: Aerospace Engineering; Engineering; Reverse film cooling; film cooling; backward injection

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APA (6^th Edition):

Prenter, R. M. P. (2017). Investigating the Physics and Performance of Reverse-Oriented Film Cooling. (Doctoral Dissertation). The Ohio State University. Retrieved from http://rave.ohiolink.edu/etdc/view?acc_num=osu1500505248644198

Chicago Manual of Style (16^th Edition):

Prenter, Robin Michael Patrick. “Investigating the Physics and Performance of Reverse-Oriented Film Cooling.” 2017. Doctoral Dissertation, The Ohio State University. Accessed January 23, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=osu1500505248644198.

MLA Handbook (7^th Edition):

Prenter, Robin Michael Patrick. “Investigating the Physics and Performance of Reverse-Oriented Film Cooling.” 2017. Web. 23 Jan 2021.

Vancouver:

Prenter RMP. Investigating the Physics and Performance of Reverse-Oriented Film Cooling. [Internet] [Doctoral dissertation]. The Ohio State University; 2017. [cited 2021 Jan 23]. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=osu1500505248644198.

Council of Science Editors:

Prenter RMP. Investigating the Physics and Performance of Reverse-Oriented Film Cooling. [Doctoral Dissertation]. The Ohio State University; 2017. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=osu1500505248644198

7. Underwood, Sean Christopher. Aerothermodynamics of Impingement and Film Cooling in a Gas Turbine Blade.

Degree: PhD, Aerospace Engineering, 2018, University of Kansas

URL: http://hdl.handle.net/1808/27605

► The service life of gas turbine engine turbine blades depends on the blade’s material, service temperature and total stress. In high-performance gas turbines, film cooling… (more)

Subjects/Keywords: Aerospace engineering; Mechanical engineering; Aerothermodynamics; Film Cooling; Gas Turbine; Impingement Cooling; Propulsion; Turbine Blade Cooling

10 more images…

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APA (6^th Edition):

Underwood, S. C. (2018). Aerothermodynamics of Impingement and Film Cooling in a Gas Turbine Blade. (Doctoral Dissertation). University of Kansas. Retrieved from http://hdl.handle.net/1808/27605

Chicago Manual of Style (16^th Edition):

Underwood, Sean Christopher. “Aerothermodynamics of Impingement and Film Cooling in a Gas Turbine Blade.” 2018. Doctoral Dissertation, University of Kansas. Accessed January 23, 2021. http://hdl.handle.net/1808/27605.

MLA Handbook (7^th Edition):

Underwood, Sean Christopher. “Aerothermodynamics of Impingement and Film Cooling in a Gas Turbine Blade.” 2018. Web. 23 Jan 2021.

Vancouver:

Underwood SC. Aerothermodynamics of Impingement and Film Cooling in a Gas Turbine Blade. [Internet] [Doctoral dissertation]. University of Kansas; 2018. [cited 2021 Jan 23]. Available from: http://hdl.handle.net/1808/27605.

Council of Science Editors:

Underwood SC. Aerothermodynamics of Impingement and Film Cooling in a Gas Turbine Blade. [Doctoral Dissertation]. University of Kansas; 2018. Available from: http://hdl.handle.net/1808/27605

Texas A&M University

8. Ullah, Izhar. Flat Plate Film Cooling with Linear and Curved Round-to-Diffusion Shaped Slots Using PSP Measurement Technique.

Degree: MS, Mechanical Engineering, 2018, Texas A&M University

URL: http://hdl.handle.net/1969.1/173881

► This thesis is an experimental study to examine the effect of different hole shapes and coolant hole trajectory on film cooling effectiveness and discharge coefficient.… (more)

Subjects/Keywords: Film cooling; Pressure sensitive paint (PSP)

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APA (6^th Edition):

Ullah, I. (2018). Flat Plate Film Cooling with Linear and Curved Round-to-Diffusion Shaped Slots Using PSP Measurement Technique. (Masters Thesis). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/173881

Chicago Manual of Style (16^th Edition):

Ullah, Izhar. “Flat Plate Film Cooling with Linear and Curved Round-to-Diffusion Shaped Slots Using PSP Measurement Technique.” 2018. Masters Thesis, Texas A&M University. Accessed January 23, 2021. http://hdl.handle.net/1969.1/173881.

MLA Handbook (7^th Edition):

Ullah, Izhar. “Flat Plate Film Cooling with Linear and Curved Round-to-Diffusion Shaped Slots Using PSP Measurement Technique.” 2018. Web. 23 Jan 2021.

Vancouver:

Ullah I. Flat Plate Film Cooling with Linear and Curved Round-to-Diffusion Shaped Slots Using PSP Measurement Technique. [Internet] [Masters thesis]. Texas A&M University; 2018. [cited 2021 Jan 23]. Available from: http://hdl.handle.net/1969.1/173881.

Council of Science Editors:

Ullah I. Flat Plate Film Cooling with Linear and Curved Round-to-Diffusion Shaped Slots Using PSP Measurement Technique. [Masters Thesis]. Texas A&M University; 2018. Available from: http://hdl.handle.net/1969.1/173881

Texas A&M University

9. Rice, Tyler Grant. Numerical Analysis of the Film Cooling Effectiveness on a Highly Loaded Low Pressure Turbine Blade in Conjunction with Endwall Effects.

Degree: MS, Mechanical Engineering, 2017, Texas A&M University

URL: http://hdl.handle.net/1969.1/161663

► This thesis is a numerical investigation of the flow development of film coolant injected from a turbine blade with considerations to the effects of the… (more)

▼ This thesis is a numerical investigation of the flow development of film coolant injected from a turbine blade with considerations to the effects of the passage vortex. By studying the film cooling effectiveness of a low pressure turbine blade subjected to film cooling parameters such as the compound angle injection, Density Ratio, and Blowing Ratio are varied to understand the impact that these parameters have on the passage vortex and film cooling effectiveness in the near endwall region where the passage vortex effects are most prominent. Film Cooling is important in this region as the passage vortex region of a blade is susceptible to high heat transfer and thermal stresses, which can greatly reduce the life cycle of a turbine blade. For this study, a special blade was designed that has a total of 605 holes distributed along 13 different rows on the blade surfaces. 6 rows cover the suction side, 6 other rows cover the pressure side and one last row feeds the leading edge. There are six coolant cavities inside the blade. Each cavity is connected to one row on either sides of the blade, except for the closest cavity to leading edge since it is connected to the leading edge row as well. By using ANSYS CFX, a RANS based solver as a computational platform, the study first compared to an experimental benchmark to understand the deficiencies of the numerical simulation, in that the velocity fluctuations were overpredicted in the boundary layer, thus effecting the prediction of mass, momentum, and energy transport. Secondly, in varying the different parameters the interaction of the film cooling vortices and passage vortex is studied. The development of the film cooling iii vortices with varying parameters and the effects due to the passage vortex in the near endwall region is identified for each parameter. Ultimately, the passage vortex, displaced coolant away from the endwall at the same rate as the vorticity magnitude and size of the passage vortex is much larger than that produced from film cooling. Advisors/Committee Members: Schobeiri, Meinhard T (advisor), Anand, Nagamangala K (committee member), Strouboulis, Theofanis (committee member).

Subjects/Keywords: Turbine Blade; Film Cooling; Numerical Analysis

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APA (6^th Edition):

Rice, T. G. (2017). Numerical Analysis of the Film Cooling Effectiveness on a Highly Loaded Low Pressure Turbine Blade in Conjunction with Endwall Effects. (Masters Thesis). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/161663

Chicago Manual of Style (16^th Edition):

Rice, Tyler Grant. “Numerical Analysis of the Film Cooling Effectiveness on a Highly Loaded Low Pressure Turbine Blade in Conjunction with Endwall Effects.” 2017. Masters Thesis, Texas A&M University. Accessed January 23, 2021. http://hdl.handle.net/1969.1/161663.

MLA Handbook (7^th Edition):

Rice, Tyler Grant. “Numerical Analysis of the Film Cooling Effectiveness on a Highly Loaded Low Pressure Turbine Blade in Conjunction with Endwall Effects.” 2017. Web. 23 Jan 2021.

Vancouver:

Rice TG. Numerical Analysis of the Film Cooling Effectiveness on a Highly Loaded Low Pressure Turbine Blade in Conjunction with Endwall Effects. [Internet] [Masters thesis]. Texas A&M University; 2017. [cited 2021 Jan 23]. Available from: http://hdl.handle.net/1969.1/161663.

Council of Science Editors:

Rice TG. Numerical Analysis of the Film Cooling Effectiveness on a Highly Loaded Low Pressure Turbine Blade in Conjunction with Endwall Effects. [Masters Thesis]. Texas A&M University; 2017. Available from: http://hdl.handle.net/1969.1/161663

Penn State University

10. Jennings, Timothy John. FILM-COOLED GAS TURBINE VANE TEMPERATURE CALCULATIONS WITH AN ITERATIVE CONJUGATE HEAT TRANSFER APPROACH USING EMPIRICAL FILM CORRELATIONS .

Degree: 2011, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/11935

► The design of gas turbine blades and vanes is a challenging task. The nature of the problem calls for high speed, high temperature, turbulent flows… (more)

Subjects/Keywords: conjugate; gas turbine; film-cooling; heat transfer

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APA (6^th Edition):

Jennings, T. J. (2011). FILM-COOLED GAS TURBINE VANE TEMPERATURE CALCULATIONS WITH AN ITERATIVE CONJUGATE HEAT TRANSFER APPROACH USING EMPIRICAL FILM CORRELATIONS . (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/11935

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):

Jennings, Timothy John. “FILM-COOLED GAS TURBINE VANE TEMPERATURE CALCULATIONS WITH AN ITERATIVE CONJUGATE HEAT TRANSFER APPROACH USING EMPIRICAL FILM CORRELATIONS .” 2011. Thesis, Penn State University. Accessed January 23, 2021. https://submit-etda.libraries.psu.edu/catalog/11935.

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

MLA Handbook (7^th Edition):

Jennings, Timothy John. “FILM-COOLED GAS TURBINE VANE TEMPERATURE CALCULATIONS WITH AN ITERATIVE CONJUGATE HEAT TRANSFER APPROACH USING EMPIRICAL FILM CORRELATIONS .” 2011. Web. 23 Jan 2021.

Vancouver:

Jennings TJ. FILM-COOLED GAS TURBINE VANE TEMPERATURE CALCULATIONS WITH AN ITERATIVE CONJUGATE HEAT TRANSFER APPROACH USING EMPIRICAL FILM CORRELATIONS . [Internet] [Thesis]. Penn State University; 2011. [cited 2021 Jan 23]. Available from: https://submit-etda.libraries.psu.edu/catalog/11935.

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

Council of Science Editors:

Jennings TJ. FILM-COOLED GAS TURBINE VANE TEMPERATURE CALCULATIONS WITH AN ITERATIVE CONJUGATE HEAT TRANSFER APPROACH USING EMPIRICAL FILM CORRELATIONS . [Thesis]. Penn State University; 2011. Available from: https://submit-etda.libraries.psu.edu/catalog/11935

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

Texas A&M University

11. Ullah, Izhar. Flat Plate Film Cooling with Linear and Curved Round-to-Diffusion Shaped Slots Using PSP Measurement Technique.

Degree: MS, Mechanical Engineering, 2018, Texas A&M University

URL: http://hdl.handle.net/1969.1/173786

► This thesis is an experimental study to examine the effect of different hole shapes and coolant hole trajectory on film cooling effectiveness and discharge coefficient.… (more)

Subjects/Keywords: Film cooling; Pressure sensitive paint (PSP)

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APA (6^th Edition):

Ullah, I. (2018). Flat Plate Film Cooling with Linear and Curved Round-to-Diffusion Shaped Slots Using PSP Measurement Technique. (Masters Thesis). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/173786

Chicago Manual of Style (16^th Edition):

Ullah, Izhar. “Flat Plate Film Cooling with Linear and Curved Round-to-Diffusion Shaped Slots Using PSP Measurement Technique.” 2018. Masters Thesis, Texas A&M University. Accessed January 23, 2021. http://hdl.handle.net/1969.1/173786.

MLA Handbook (7^th Edition):

Ullah, Izhar. “Flat Plate Film Cooling with Linear and Curved Round-to-Diffusion Shaped Slots Using PSP Measurement Technique.” 2018. Web. 23 Jan 2021.

Vancouver:

Ullah I. Flat Plate Film Cooling with Linear and Curved Round-to-Diffusion Shaped Slots Using PSP Measurement Technique. [Internet] [Masters thesis]. Texas A&M University; 2018. [cited 2021 Jan 23]. Available from: http://hdl.handle.net/1969.1/173786.

Council of Science Editors:

Ullah I. Flat Plate Film Cooling with Linear and Curved Round-to-Diffusion Shaped Slots Using PSP Measurement Technique. [Masters Thesis]. Texas A&M University; 2018. Available from: http://hdl.handle.net/1969.1/173786

12. Kingery, Joseph. An Experimental Investigation Into The Effects Of High Free-Stream Turbulence On Full Coverage Shaped Hole Film Cooling In An Accelerating Boundary Layer.

Degree: MS, Mechanical Engineering, 2015, University of North Dakota

URL: https://commons.und.edu/theses/1789

► The purpose of this study is to experimentally investigate the effects of high free stream turbulence on shaped hole film cooling and heat transfer… (more)

▼ The purpose of this study is to experimentally investigate the effects of high free stream turbulence on shaped hole film cooling and heat transfer in an accelerating boundary layer. Film cooling is one of most widely used techniques in cooling high pressure turbine blades and endwalls, whether they are land based power turbines or those used for aircraft propulsion. In the section immediately after the combustor, there is very high turbulence and acceleration, and adequate cooling must be implemented to ensure that components do not prematurely fail. This study is able to apply high turbulence intensities to a test section whose acceleration profile yields a favorable pressure gradient and allows us to see the real world effects on shaped hole film cooling effectiveness and heat transfer from high turbulence intensities. The experimentation was conducted in the University of North Dakota large scale low velocity wind tunnel facility. A total of six well documented turbulence intensities ranging from 0.7% to 13.7% were implemented on a large cylindrical test surface at Reynolds numbers of 250,000 and 500,000 and four blowing ratios. The low Reynolds number setup used blowing ratios of M = 0.55, 0.97, 1.35, and 1.89, while only the lowest two blowing ratios were tested at the high Reynolds number. The six turbulence intensities were achieved using a low turbulence (LT) nozzle (Tu = 0.7%), the LT nozzle with a small grid at two locations (Tu = 3.5% and 7.8%), the LT nozzle with a large grid (Tu = 8.1%), and a mock aero combustor with and without a decay spool (Tu = 9.3% and 13.7%). The shaped holes leading edge insert was designed to provide full coverage with two staggered rows of holes with 8Âº lateral expansion. Both rows of holes are introduced to the surface at 30Âº. Data showed turbulence to be detrimental to shaped hole film cooling effectiveness in all cases, and to increase heat transfer as the early onset of transition was amplified. The low Reynolds number showed improved film cooling effectiveness over the high Reynolds number due to a longer transition region and slower boundary layer growth. Comparisons of shaped hole film cooling to previous slot film cooling data show the slot to have similar performance in the latter half of the test surface. However, heat transfer and adiabatic effectiveness were much higher in near region due to the slot’s superior coverage. IR camera measurements of shaped hole film cooling show the coolant coverage of the surface at the two low blowing ratios, giving a better perspective on the behavior of the coolant jets after ejection. These data should be useful for comparison in future studies. Advisors/Committee Members: Forrest Ames.

Subjects/Keywords: film cooling; gas turbine; shaped holes; turbulence

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APA (6^th Edition):

Kingery, J. (2015). An Experimental Investigation Into The Effects Of High Free-Stream Turbulence On Full Coverage Shaped Hole Film Cooling In An Accelerating Boundary Layer. (Masters Thesis). University of North Dakota. Retrieved from https://commons.und.edu/theses/1789

Chicago Manual of Style (16^th Edition):

Kingery, Joseph. “An Experimental Investigation Into The Effects Of High Free-Stream Turbulence On Full Coverage Shaped Hole Film Cooling In An Accelerating Boundary Layer.” 2015. Masters Thesis, University of North Dakota. Accessed January 23, 2021. https://commons.und.edu/theses/1789.

MLA Handbook (7^th Edition):

Kingery, Joseph. “An Experimental Investigation Into The Effects Of High Free-Stream Turbulence On Full Coverage Shaped Hole Film Cooling In An Accelerating Boundary Layer.” 2015. Web. 23 Jan 2021.

Vancouver:

Kingery J. An Experimental Investigation Into The Effects Of High Free-Stream Turbulence On Full Coverage Shaped Hole Film Cooling In An Accelerating Boundary Layer. [Internet] [Masters thesis]. University of North Dakota; 2015. [cited 2021 Jan 23]. Available from: https://commons.und.edu/theses/1789.

Council of Science Editors:

Kingery J. An Experimental Investigation Into The Effects Of High Free-Stream Turbulence On Full Coverage Shaped Hole Film Cooling In An Accelerating Boundary Layer. [Masters Thesis]. University of North Dakota; 2015. Available from: https://commons.und.edu/theses/1789

13. Busche, Mitch. Experimental Investigation Of The Effect Of Turbulence On Slot-Fed Film Cooling Adiabatic Effectiveness And Downstream Heat Transfer.

Degree: MS, Mechanical Engineering, 2013, University of North Dakota

URL: https://commons.und.edu/theses/1405

► Modern turbine designers are greatly concerned with power out and the efficiency of their engines. One way to increase the power output and effectiveness… (more)

▼ Modern turbine designers are greatly concerned with power out and the efficiency of their engines. One way to increase the power output and effectiveness of the engine is to increase the hot gas temperature inside the combustion chamber. The hot gas can reach a temperature that exceeds the physical limitations of parts inside the engine, causing the parts to fail prematurely. One possible method to cool the parts is with the use film cooling. Film cooling takes cool air from the compressor, bypasses the combustor, and ducts the air to internal chambers of parts, and then ejects the cool air onto the surface of the part. This provides both cooling and protection from deposition. Due to the large number of turbine engines in service today, it is impossible to know what the perfect film cooling package is. Different turbines have different inlet conditions, burn at different temperatures, have different turbulence intensities in the flow, and require different amount of cooling. Research has been done in the past to determine some of the parameters that affect film cooling performance. The purpose of this research was to determine the effects of turbulence, Reynolds number, and blowing ratio on the adiabatic effectiveness of film cooling and the downstream heat transfer. This research utilized the large scale, low speed cascade wind tunnel facility at the University of North Dakota. The effectiveness of two different cylindrical leading edge test surfaces was investigated. For this project, a unique pin fin array was developed and integrated in the two cylindrical leading edge test sections. The test sections were designed, fabricated, and instrumented to be able to acquire temperature measurements and pressure measurements at different locations along the test surface. A way to produce and deliver coolant air was designed, fabricated, and instrumented. Data was acquired for each of the cylinders at the different test conditions. The turbulence intensities were acquired by another student. In the future, additional data will be taken with the cylindrical test sections. Temperature data while film cooling will be measured via infrared camera. Shaped coolant ejection holes are being designed and will be tested. A leading edge with deposition will also be tested. All of the future data will be compared to this baseline data. Hopefully, the data from this research will be used by turbine designers to better understand the effects on film cooling, and produce a better, more efficient engine. Advisors/Committee Members: Forrest E. Ames.

Subjects/Keywords: Effectiveness; Film Cooling; Heat Transfer; Slot; Turbulence

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APA (6^th Edition):

Busche, M. (2013). Experimental Investigation Of The Effect Of Turbulence On Slot-Fed Film Cooling Adiabatic Effectiveness And Downstream Heat Transfer. (Masters Thesis). University of North Dakota. Retrieved from https://commons.und.edu/theses/1405

Chicago Manual of Style (16^th Edition):

Busche, Mitch. “Experimental Investigation Of The Effect Of Turbulence On Slot-Fed Film Cooling Adiabatic Effectiveness And Downstream Heat Transfer.” 2013. Masters Thesis, University of North Dakota. Accessed January 23, 2021. https://commons.und.edu/theses/1405.

MLA Handbook (7^th Edition):

Busche, Mitch. “Experimental Investigation Of The Effect Of Turbulence On Slot-Fed Film Cooling Adiabatic Effectiveness And Downstream Heat Transfer.” 2013. Web. 23 Jan 2021.

Vancouver:

Busche M. Experimental Investigation Of The Effect Of Turbulence On Slot-Fed Film Cooling Adiabatic Effectiveness And Downstream Heat Transfer. [Internet] [Masters thesis]. University of North Dakota; 2013. [cited 2021 Jan 23]. Available from: https://commons.und.edu/theses/1405.

Council of Science Editors:

Busche M. Experimental Investigation Of The Effect Of Turbulence On Slot-Fed Film Cooling Adiabatic Effectiveness And Downstream Heat Transfer. [Masters Thesis]. University of North Dakota; 2013. Available from: https://commons.und.edu/theses/1405

Delft University of Technology

14. Moreno Castan, Clara (author). Film cooling aerodynamic performance: Flow structures and aerodynamic losses in an airfoil with pressure side injection.

Degree: 2018, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:1769608d-3c1d-413d-95b5-61b08a45ac8b

► As a response to a socio-economic framework which demands lower fuel consumption and CO₂ emissions, gas turbine manufacturers strive to attain higher thermal… (more)

▼ As a response to a socio-economic framework which demands lower fuel consumption and CO₂ emissions, gas turbine manufacturers strive to attain higher thermal efficiency and specific work output in their engines. The enhancement of these two performance parameters is linked to higher turbine inlet temperatures (TIT), which explains the increasing trend in TIT accompanying aero engines industrial development. Turbine cooling technology is one of the disciplines strongly contributing to this aim, enabling operational hot gas temperatures to be higher than the melting temperature of the material. This study deals with film cooling: an external type of turbine cooling. Coolant air, bled from the compressor, is injected into the turbine blades and vanes and discharged through small holes into the airfoil´s external boundary layer, creating a thin insulating layer that reduces convective heat transfer from the hot gas to the surface. However, this gain in thermal capability brings along an aerodynamic penalty. The purpose of this work is to understand the aerodynamic performance of a NACA 0012 airfoil with four rows of holes on the pressure side, as a follow-up experimental study of a previous one using the same model but with suction side injection (Lanzillotta, et al., 2017). A configuration with angle of attack α=0º, freestream velocity V∞=15m/s and air as secondary flow is tested as a baseline to understand the effect of blowing ratio BR∈(0,2) on flow field characteristics. Then, other configurations are tested to analyse the effect of angle of attack, freestream velocity, single row injection and density ratio by using CO₂as secondary flow, to simulate the temperature ratio existing in real gas turbine applications. Pointwise pressure measurements at a location downstream of the airfoil (x= 1.25c) and planar and stereo PIV are used as flow measurement techniques. Wake velocity profile characteristics and aerodynamic losses are retrieved from pressure measurements. Results for the baseline configuration show how the wake velocity profile displaces towards the pressure side when blowing is introduced. For low blowing ratios, the low momentum of the coolant induces high mixing losses whereas for high blowing ratios, the energizing effect of the high momentum coolant outweighs the mixing losses. Maximum losses are found for BR=0.5 and they decrease for higher blowing ratios. For BR=1.4, a shift from wake to jet local behaviour is observed in the wake velocity profile. The high and low velocity regions in the 2D average velocity fields computed from planar PIV… Advisors/Committee Members: Gangoli Rao, Arvind (mentor), Sciacchitano, Andrea (mentor), Delft University of Technology (degree granting institution).

Subjects/Keywords: aerodynamic performance; film cooling; pressure measurements; PIV

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APA (6^th Edition):

Moreno Castan, C. (. (2018). Film cooling aerodynamic performance: Flow structures and aerodynamic losses in an airfoil with pressure side injection. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:1769608d-3c1d-413d-95b5-61b08a45ac8b

Chicago Manual of Style (16^th Edition):

Moreno Castan, Clara (author). “Film cooling aerodynamic performance: Flow structures and aerodynamic losses in an airfoil with pressure side injection.” 2018. Masters Thesis, Delft University of Technology. Accessed January 23, 2021. http://resolver.tudelft.nl/uuid:1769608d-3c1d-413d-95b5-61b08a45ac8b.

MLA Handbook (7^th Edition):

Moreno Castan, Clara (author). “Film cooling aerodynamic performance: Flow structures and aerodynamic losses in an airfoil with pressure side injection.” 2018. Web. 23 Jan 2021.

Vancouver:

Moreno Castan C(. Film cooling aerodynamic performance: Flow structures and aerodynamic losses in an airfoil with pressure side injection. [Internet] [Masters thesis]. Delft University of Technology; 2018. [cited 2021 Jan 23]. Available from: http://resolver.tudelft.nl/uuid:1769608d-3c1d-413d-95b5-61b08a45ac8b.

Council of Science Editors:

Moreno Castan C(. Film cooling aerodynamic performance: Flow structures and aerodynamic losses in an airfoil with pressure side injection. [Masters Thesis]. Delft University of Technology; 2018. Available from: http://resolver.tudelft.nl/uuid:1769608d-3c1d-413d-95b5-61b08a45ac8b

University of Limerick

15. Lundy, Ross. Surface, interface and thin film studies for nano & heat transfer applications.

Degree: 2017, University of Limerick

URL: http://hdl.handle.net/10344/6771

►

peer-reviewed

This thesis is focused on the study of surfaces, interfaces and thin films. The main goal of this project is to produce and examine… (more)

▼

peer-reviewed

This thesis is focused on the study of surfaces, interfaces and thin films. The main goal of this project is to produce and examine thin films and interfaces that can lead to the development of heat transfer and nano applications. High-performance dropwise condensers are an effective means of heat transfer but widespread use in industry relies on identifying a durable, cost effective dropwise condensation promoter with adequate thermal conductivity. The focus of the work here investigates using rare earth oxides as a possible candidate to address these requirements. A next generation intrachip cooling technology is necessary to overcome the stringent heat dissipation needs of high-heat flux GaN based electronics. A two phase (liquid-tovapor) intrachip cooling technology requires fabrication of a nanoporous membrane with sub 25 nm features for pumping a working fluid within the device. Patterning at these length scales is difficult due to the cost of ownership of state of the art photolithography. The work here aims to develop a high fidelity, low cost block copolymer lithography technique using PS-b-P4VP for large-scale feature definition suitable for patterning. The long anneal times and polymer dewetting issues associated with standard solvent vapour annealing have been addressed in this work by developing a custom-built block copolymer annealing chamber. Finally surface and interface studies were performed on porous low-κ dielectric thin films for use in back end of line microelectronic device fabrication. The continued shrinking of on chip devices has resulted in increased line resistance and parasitic capacitance within the multilevel interconnects leading to delays in signal propagation. Low-κ dielectrics combined with self-forming copper diffusion barrier layers are a promising candidate to alleviate resistance and capacitance within the interconnect structure. The thesis is presented in an article based format, with each chapter comprising a research topic that includes a review of the literature in the introduction of each chapter.

Advisors/Committee Members: Dalton, Eric D..

Subjects/Keywords: heat transfer; cooling technology; thin film studies

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APA (6^th Edition):

Lundy, R. (2017). Surface, interface and thin film studies for nano & heat transfer applications. (Thesis). University of Limerick. Retrieved from http://hdl.handle.net/10344/6771

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):

Lundy, Ross. “Surface, interface and thin film studies for nano & heat transfer applications.” 2017. Thesis, University of Limerick. Accessed January 23, 2021. http://hdl.handle.net/10344/6771.

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

MLA Handbook (7^th Edition):

Lundy, Ross. “Surface, interface and thin film studies for nano & heat transfer applications.” 2017. Web. 23 Jan 2021.

Vancouver:

Lundy R. Surface, interface and thin film studies for nano & heat transfer applications. [Internet] [Thesis]. University of Limerick; 2017. [cited 2021 Jan 23]. Available from: http://hdl.handle.net/10344/6771.

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

Council of Science Editors:

Lundy R. Surface, interface and thin film studies for nano & heat transfer applications. [Thesis]. University of Limerick; 2017. Available from: http://hdl.handle.net/10344/6771

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

Louisiana State University

16. Babaee, Hessam. Analysis and optimization of film cooling effectiveness.

Degree: PhD, Mechanical Engineering, 2013, Louisiana State University

URL: etd-07082013-001815 ; https://digitalcommons.lsu.edu/gradschool_dissertations/2178

► In the first part, an optimization strategy is described that combines high-fidelity simu- lations with response surface construction, and is applied to pulsed film… (more)

▼ In the first part, an optimization strategy is described that combines high-fidelity simu- lations with response surface construction, and is applied to pulsed film cooling for turbine blades. The response surface is constructed for the film cooling effectiveness as a function of duty cycle, in the range of DC between 0.05 and 1, and pulsation frequency St in the range of 0.2-2, using a pseudo-spectral projection method. The jet is fully modulated and the blowing ratio, when the jet is on, is 1.5 in all cases. Overall 73 direct numerical sim- ulations (DNS) using spectral element method were performed to sample the film cooling effectiveness on a Clenshaw-Curtis grid in the design space. It is observed that in the parameter space explored a global optimum exists, and in the present study, the best film cooling effectiveness is found at DC = 0.14 and St = 1.03. In the same range of DC and St, four other local optimums were found. The gradient-based optimization algorithms are argued to be unsuitable for the current problem due to the non-convexity of the objective function. In the second part, the effect of randomness of blowing ratio on film cooling performance is investigated by combining direct numerical simulations with a stochastic collocation ap- proach. The blowing ratio variations are assumed to have a truncated Gaussian distribution with mean of 0.3 and the standard variation of approximately 0.1. The parametric space is discretized using Multi-Element general Polynomial Chaos (ME-gPC) with five elements where general polynomial chaos of order 3 is used in each element. Direct numerical simula- tions were carried out using spectral/hp element method to sample the governing equations in space and time. The probability density function of the film cooling effectiveness was obtained and the standard deviation of the adiabatic film cooling effectiveness on the blade surface was calculated. A maximum standard deviation of 15% was observed in the region within a four-jet-diameter distance downstream of the exit hole. The spatially-averaged adiabatic film cooling effectiveness was 0.23 0.02. The calculation of all the statistical properties were carried out as off-line post-processing. Overall the computational strategy is shown to be very effective with the total computational cost being equivalent to solving twenty independent direct numerical simulations that are performed concurrently. In the third part, an accurate and efficient finite difference method for solving the incompressible Navier-Stokes equations on curvilinear grids is developed. This method combines the favorable features of the staggered grid and semi-staggered grid approaches. A novel symmetric finite difference discretization of the Poisson-Neumann problem on curvilinear grids is also presented. The validity of the method is demonstrated on four benchmark problems. The Taylor-Green vortex problem is solved on a curvilinear grid with highly skewed cells and a second-order convergence in .-norm is observed. The mixed convection in a lid-driven…

Subjects/Keywords: film cooling; spectral method; polynomial chaos

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APA (6^th Edition):

Babaee, H. (2013). Analysis and optimization of film cooling effectiveness. (Doctoral Dissertation). Louisiana State University. Retrieved from etd-07082013-001815 ; https://digitalcommons.lsu.edu/gradschool_dissertations/2178

Chicago Manual of Style (16^th Edition):

Babaee, Hessam. “Analysis and optimization of film cooling effectiveness.” 2013. Doctoral Dissertation, Louisiana State University. Accessed January 23, 2021. etd-07082013-001815 ; https://digitalcommons.lsu.edu/gradschool_dissertations/2178.

MLA Handbook (7^th Edition):

Babaee, Hessam. “Analysis and optimization of film cooling effectiveness.” 2013. Web. 23 Jan 2021.

Vancouver:

Babaee H. Analysis and optimization of film cooling effectiveness. [Internet] [Doctoral dissertation]. Louisiana State University; 2013. [cited 2021 Jan 23]. Available from: etd-07082013-001815 ; https://digitalcommons.lsu.edu/gradschool_dissertations/2178.

Council of Science Editors:

Babaee H. Analysis and optimization of film cooling effectiveness. [Doctoral Dissertation]. Louisiana State University; 2013. Available from: etd-07082013-001815 ; https://digitalcommons.lsu.edu/gradschool_dissertations/2178

Texas A&M University

17. Chen, Andrew F. Turbine Platform Film Cooling Effectiveness and Rotational Effect on Internal Cooling Passages with a Converging Tip Turn.

Degree: PhD, Mechanical Engineering, 2018, Texas A&M University

URL: http://hdl.handle.net/1969.1/173507

► Through the advancement of gas turbine cooling technologies, gas turbine engines remain one of the most reliable technologies in the aviation and power generation industries.… (more)

▼ Through the advancement of gas turbine cooling technologies, gas turbine engines remain one of the most reliable technologies in the aviation and power generation industries. The combined cycle efficiency of a power generation gas turbine is expected to reach 65% by the year of 2020. The internal and external cooling designs of gas turbine components play an essential role in achieving this goal. In the first part, experimental investigations were conducted on a five-blade linear rotor cascade platform with upstream purge flow, slashface leakage flow, and discrete film cooling using both cylindrical and fan-shaped holes. Detailed film cooling effectiveness distributions were obtained using the pressure sensitive paint (PSP) technique. Parametric studies on the coolant to mainstream mass flow ratio (0.5% - 1%), blowing ratio (0.5 - 1.5), density ratio (1 – 2), or the purge flow swirl ratio (0.6 and 1) were performed. The area-averaged film cooling effectiveness values of the two film hole geometries are compared and discussed. In general, the design with the fan-shaped cooling holes provides better film effectiveness and coverage at higher blowing, density, and momentum flux ratios. In the second part, heat transfer and pressure measurements were performed in a two-pass rectangular channel with varying aspect ratios: AR = 4:1 in the first pass and AR = 2:1 in the second pass after a 180 deg converging tip turn. In addition to the smooth-wall case, surfaces roughened with 60 deg angled ribs and 45 deg angled ribs with three different rib coverages were investigated. Regionally averaged heat transfer measurement method was used to obtain the heat transfer coefficients on all surfaces within the flow passages. The Reynolds number ranges from 10,000 to 70,000 in the first passage, and the rotational speed ranges from 0 to 400 rpm. Under a pressurized condition, the highest rotation number achieved was Ro = 0.39 in the first passage and 0.16 in the second passage. The results showed that both heat transfer and pressure coefficients are sensitive to the geometrical and rib design of the channel. More importantly, significant heat transfer reduction was identified on the tip wall under rotation. Advisors/Committee Members: Han, Je-Chin (advisor), Schobeiri, Meinhard Taher (committee member), Kulatilaka, Waruna (committee member), Chang, Kuang-An (committee member).

Subjects/Keywords: Gas Turbine; Heat Transfer; Film Cooling; Internal Cooling; Converging Tip Turn

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APA (6^th Edition):

Chen, A. F. (2018). Turbine Platform Film Cooling Effectiveness and Rotational Effect on Internal Cooling Passages with a Converging Tip Turn. (Doctoral Dissertation). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/173507

Chicago Manual of Style (16^th Edition):

Chen, Andrew F. “Turbine Platform Film Cooling Effectiveness and Rotational Effect on Internal Cooling Passages with a Converging Tip Turn.” 2018. Doctoral Dissertation, Texas A&M University. Accessed January 23, 2021. http://hdl.handle.net/1969.1/173507.

MLA Handbook (7^th Edition):

Chen, Andrew F. “Turbine Platform Film Cooling Effectiveness and Rotational Effect on Internal Cooling Passages with a Converging Tip Turn.” 2018. Web. 23 Jan 2021.

Vancouver:

Chen AF. Turbine Platform Film Cooling Effectiveness and Rotational Effect on Internal Cooling Passages with a Converging Tip Turn. [Internet] [Doctoral dissertation]. Texas A&M University; 2018. [cited 2021 Jan 23]. Available from: http://hdl.handle.net/1969.1/173507.

Council of Science Editors:

Chen AF. Turbine Platform Film Cooling Effectiveness and Rotational Effect on Internal Cooling Passages with a Converging Tip Turn. [Doctoral Dissertation]. Texas A&M University; 2018. Available from: http://hdl.handle.net/1969.1/173507

Penn State University

18. Thrift, Alan Albright. Cooling of a Turbine Vane Endwall Through Contouring and Flow Injection .

Degree: 2011, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/12136

► High oil prices and environmental concerns serve to drive up the efficiencies of land based, power generation gas turbines. Increasing efficiencies requires raising the temperature… (more)

▼ High oil prices and environmental concerns serve to drive up the efficiencies of land based, power generation gas turbines. Increasing efficiencies requires raising the temperature of the air entering the turbine section of the engine. Turbine components must be protected from the increased air temperatures by advanced cooling designs that provide coolant to the hot flow surfaces. Secondary flows reduce the effectiveness of coolant injected along the vane endwalls as well as increase endwall heat transfer. Endwall contouring and strategic coolant injection can alter secondary flows to allow for improved endwall cooling, ultimately allowing for higher engine efficiencies. This research initially focused on understanding the flow physics and subsequent cooling characteristics of an axisymmetric contoured vane passage. Results indicated that coolant injected from discrete holes provided lower effectiveness values on the contoured endwall in comparison to the flat endwalls of the planar and contoured passages. Coolant coverage from the upstream interface slot, however, was spread over a larger area of the contoured endwall in comparison to the flat endwalls as the interface slot was oriented closer to the plane of the contoured endwall. Seeking a fundamental understanding of interface slot coolant injection, further investigation into the effects of orientation and position of slot injection on secondary flows and the net heat flux experienced by a vane endwall was conducted. Results indicated that cooling effectiveness levels can be improved and the horseshoe vortex reduced in size by moving the interface slot closer to the passage inlet. At large injection rates, reducing the slot orientation resulted in the removal of the horseshoe vortex and a subsequent reduction in passage secondary flows leading to a reduction in the average heat load experienced by the endwall. Advisors/Committee Members: Karen Ann Thole, Dissertation Advisor/Co-Advisor, Cengiz Camci, Committee Member, Dr Eric Paterson, Committee Member, Domenic Adam Santavicca, Committee Member, Karen Ann Thole, Committee Chair/Co-Chair.

Subjects/Keywords: Gas Turbine Cooling; Endwall Contouring; Film Cooling; First Stage Vane

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APA (6^th Edition):

Thrift, A. A. (2011). Cooling of a Turbine Vane Endwall Through Contouring and Flow Injection . (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/12136

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):

Thrift, Alan Albright. “Cooling of a Turbine Vane Endwall Through Contouring and Flow Injection .” 2011. Thesis, Penn State University. Accessed January 23, 2021. https://submit-etda.libraries.psu.edu/catalog/12136.

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

MLA Handbook (7^th Edition):

Thrift, Alan Albright. “Cooling of a Turbine Vane Endwall Through Contouring and Flow Injection .” 2011. Web. 23 Jan 2021.

Vancouver:

Thrift AA. Cooling of a Turbine Vane Endwall Through Contouring and Flow Injection . [Internet] [Thesis]. Penn State University; 2011. [cited 2021 Jan 23]. Available from: https://submit-etda.libraries.psu.edu/catalog/12136.

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

Council of Science Editors:

Thrift AA. Cooling of a Turbine Vane Endwall Through Contouring and Flow Injection . [Thesis]. Penn State University; 2011. Available from: https://submit-etda.libraries.psu.edu/catalog/12136

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

Texas A&M University

19. Meador, Charles Michael. Massively-Parallel Direct Numerical Simulation of Gas Turbine Endwall Film-Cooling Conjugate Heat Transfer.

Degree: MS, Mechanical Engineering, 2011, Texas A&M University

URL: http://hdl.handle.net/1969.1/ETD-TAMU-2010-12-8952

► Improvements to gas turbine efficiency depend closely on cooling technologies, as efficiency increases with turbine inlet temperature. To aid in this process, simulations that consider… (more)

Subjects/Keywords: Parallel; Film; Cooling; Film Cooling; Conjugate; Heat Transfer; Gas; Gas Turbine; Endwall; Efficiency

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APA (6^th Edition):

Meador, C. M. (2011). Massively-Parallel Direct Numerical Simulation of Gas Turbine Endwall Film-Cooling Conjugate Heat Transfer. (Masters Thesis). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/ETD-TAMU-2010-12-8952

Chicago Manual of Style (16^th Edition):

Meador, Charles Michael. “Massively-Parallel Direct Numerical Simulation of Gas Turbine Endwall Film-Cooling Conjugate Heat Transfer.” 2011. Masters Thesis, Texas A&M University. Accessed January 23, 2021. http://hdl.handle.net/1969.1/ETD-TAMU-2010-12-8952.

MLA Handbook (7^th Edition):

Meador, Charles Michael. “Massively-Parallel Direct Numerical Simulation of Gas Turbine Endwall Film-Cooling Conjugate Heat Transfer.” 2011. Web. 23 Jan 2021.

Vancouver:

Meador CM. Massively-Parallel Direct Numerical Simulation of Gas Turbine Endwall Film-Cooling Conjugate Heat Transfer. [Internet] [Masters thesis]. Texas A&M University; 2011. [cited 2021 Jan 23]. Available from: http://hdl.handle.net/1969.1/ETD-TAMU-2010-12-8952.

Council of Science Editors:

Meador CM. Massively-Parallel Direct Numerical Simulation of Gas Turbine Endwall Film-Cooling Conjugate Heat Transfer. [Masters Thesis]. Texas A&M University; 2011. Available from: http://hdl.handle.net/1969.1/ETD-TAMU-2010-12-8952

Penn State University

20. Baek, Seung Il. EFFECTS OF OSCILLATIONS IN THE MAIN FLOW ON FILM COOLING AT VARIOUS FREQUENCIES AND BLOWING RATIOS.

Degree: 2018, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/15762sub208

► The objective of this study was to investigate the effects of oscillations in the main flow on gas turbine film cooling at various single frequencies… (more)

▼ The objective of this study was to investigate the effects of oscillations in the main flow on gas turbine film cooling at various single frequencies from 0 to 2144 Hz (non-dimensional frequencies F: 0 to 5.36). The single frequencies were identified as the dominant frequencies from a Fourier analysis of combustor instability data on combustor pressure fluctuations. Numerical simulations are carried out using ANSYS Fluent LES and URANS turbulence models. The results show that if the oscillation frequency of the main flow is increased from 0 to 180 Hz (F: 0 to 0.45) at low blowing ratio of M = 0.5, the film cooling effectiveness is decreased due to increase of jet lift off leading to entrainment of hot main flow under the jet. However, when the frequency goes from 180 to 268 Hz (F: 0.45 to 0.67), the film cooling effectiveness is dramatically increased because a thin coolant film near the wall is overlapped by large vortices of the coolant created during the higher velocity part of the cycle at 268 Hz. The large vortices prevent the thin film near the wall mixing with the hot main flow leading to decrease of the wall temperature. If the frequency changes from 268 to 1072 Hz (F: 0.67 to 2.68), the effectiveness drops because the large vortices start overlapping and moving away from the wall by the vertical component of the jet momentum resulting in entrainment of the hot main flow under the jet. If the frequencies exceed 1072 Hz (F: 2.68 to 5.36), the film cooling effectiveness is increased because the coolant jet cannot respond to these high frequencies and the coolant behavior returns to that at 0 Hz gradually. The trends of the effectiveness at high blowing ratio of M = 1.0 are similar with those at M = 0.5 except from 0 to 180 Hz. At M = 1.0, coolant jet lift off is created under the steady state conditions. However, if the oscillation frequency goes from 0 to 180 Hz, the coolant flapping is generated leading to lower wall temperature (also lower adiabatic wall temperature which is used in calculation of the film cooling effectiveness, this results in higher effectiveness) compared to the wall temperature or adiabatic wall temperature under the steady flow conditions. In terms of heat transfer coefficients, if the frequency is increased from 0 to 536 Hz (F: 0 to 1.34) at low blowing ratio of M = 0.5, spanwise-averaged Stanton number ratio is increased because of increase of the disturbances in the flows. However, if the frequency goes from 536 to 2144 Hz (F: 1.34 to 5.36), the spanwise-averaged Stanton number ratio is decreased since the coolant jet cannot respond to high frequency oscillations and return to that at 0 Hz. The trends of the spanwise-averaged Stanton number ratio at high blowing ratio are similar with those at M = 0.5 except from 0 to 180 Hz. If the frequency is increased from 0 to 180 Hz at M = 1.0, more entrainment of the hot main flow is induced leading to less mixing near the wall and decrease of the Stanton number ratio. Further, multi-frequency velocities are applied to the main and coolant… Advisors/Committee Members: Savas Yavuzkurt, Dissertation Advisor/Co-Advisor, Victor Ward Sparrow, Committee Chair/Co-Chair, Stephen Clarke Conlon, Committee Member, Robert Keolian, Committee Member, Savas Yavuzkurt, Outside Member.

Subjects/Keywords: Film cooling; Turbulent flows; Numerical simulation; Film cooling effectiveness; Stanton number ratio

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

APA (6^th Edition):

Baek, S. I. (2018). EFFECTS OF OSCILLATIONS IN THE MAIN FLOW ON FILM COOLING AT VARIOUS FREQUENCIES AND BLOWING RATIOS. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/15762sub208

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):

Baek, Seung Il. “EFFECTS OF OSCILLATIONS IN THE MAIN FLOW ON FILM COOLING AT VARIOUS FREQUENCIES AND BLOWING RATIOS.” 2018. Thesis, Penn State University. Accessed January 23, 2021. https://submit-etda.libraries.psu.edu/catalog/15762sub208.

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

MLA Handbook (7^th Edition):

Baek, Seung Il. “EFFECTS OF OSCILLATIONS IN THE MAIN FLOW ON FILM COOLING AT VARIOUS FREQUENCIES AND BLOWING RATIOS.” 2018. Web. 23 Jan 2021.

Vancouver:

Baek SI. EFFECTS OF OSCILLATIONS IN THE MAIN FLOW ON FILM COOLING AT VARIOUS FREQUENCIES AND BLOWING RATIOS. [Internet] [Thesis]. Penn State University; 2018. [cited 2021 Jan 23]. Available from: https://submit-etda.libraries.psu.edu/catalog/15762sub208.

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

Council of Science Editors:

Baek SI. EFFECTS OF OSCILLATIONS IN THE MAIN FLOW ON FILM COOLING AT VARIOUS FREQUENCIES AND BLOWING RATIOS. [Thesis]. Penn State University; 2018. Available from: https://submit-etda.libraries.psu.edu/catalog/15762sub208

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

University of Texas – Austin

21. Moore, Jacob Damian. Film effectiveness performance for a shaped hole on the suction side of a scaled-up turbine blade.

Degree: MSin Engineering, Mechanical Engineering, 2018, University of Texas – Austin

URL: http://hdl.handle.net/2152/71583

► Surface curvature has been shown to have significant effects on the film cooling performance of round holes, but the present literature includes very few studies… (more)

▼ Surface curvature has been shown to have significant effects on the film cooling performance of round holes, but the present literature includes very few studies dedicated to curvature’s effects on shaped hole geometries despite their prevalence in turbine blade and vane designs. Experiments were performed on two rows of holes placed on the suction side of a scaled-up gas turbine blade model in a low-Mach-number linear cascade wind tunnel. The test facility was set up to match a high-Mach-number pressure distribution without modifying the blade’s geometry or including contoured end walls to accelerate the flow. By adjusting the positions of the movable walls in the tunnel test section, the suction side pressure distribution could be matched to the design distribution. One row was placed in a region of high convex surface curvature; the other, in a region of low convex curvature. Other geometric and flow parameters near the rows were matched in the design of the experiment, including hole geometry and spacing. The hole geometry was a standard 7-7-7 shaped hole. In addition, local freestream conditions for the rows were measured and set to match as closely as possible. Comparison of the adiabatic effectiveness results from the two rows revealed trends similar to those seen in previous literature for round holes. The high curvature row outperformed the low curvature row at lower coolant injection rates, having wider jets and higher centerline effectiveness. But as the injection rate was increased, the low curvature row surpassed the high curvature row in effectiveness. The driver behind this behavior was the surface-normal pressure gradient that arose from the convex surface curvature. As flow traveled around the surface, centripetal acceleration produced a pressure gradient directed towards the surface, effectively pushing jets toward the blade wall. However, at higher blowing ratios, the jets’ high momenta overcame the effects of this pressure gradient. At these injection rates, the high curvature row’s jets’ trajectories did not follow the surface as it curved away. The high surface curvature exacerbated the adverse effects of jet separation on film cooling performance. Advisors/Committee Members: Bogard, David G. (advisor).

Subjects/Keywords: Film cooling; Shaped hole; Adiabatic effectiveness; Turbine blade; Experimental; Curvature; Effectiveness; Film; Turbine cooling

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APA (6^th Edition):

Moore, J. D. (2018). Film effectiveness performance for a shaped hole on the suction side of a scaled-up turbine blade. (Masters Thesis). University of Texas – Austin. Retrieved from http://hdl.handle.net/2152/71583

Chicago Manual of Style (16^th Edition):

Moore, Jacob Damian. “Film effectiveness performance for a shaped hole on the suction side of a scaled-up turbine blade.” 2018. Masters Thesis, University of Texas – Austin. Accessed January 23, 2021. http://hdl.handle.net/2152/71583.

MLA Handbook (7^th Edition):

Moore, Jacob Damian. “Film effectiveness performance for a shaped hole on the suction side of a scaled-up turbine blade.” 2018. Web. 23 Jan 2021.

Vancouver:

Moore JD. Film effectiveness performance for a shaped hole on the suction side of a scaled-up turbine blade. [Internet] [Masters thesis]. University of Texas – Austin; 2018. [cited 2021 Jan 23]. Available from: http://hdl.handle.net/2152/71583.

Council of Science Editors:

Moore JD. Film effectiveness performance for a shaped hole on the suction side of a scaled-up turbine blade. [Masters Thesis]. University of Texas – Austin; 2018. Available from: http://hdl.handle.net/2152/71583

NSYSU

22. Yeh, Yi-Fan. Spray Cooling Thermal and Flow Characteristics for High Power Electronic Devices.

Degree: Master, Mechanical and Electro-Mechanical Engineering, 2017, NSYSU

URL: http://etd.lib.nsysu.edu.tw/ETD-db/ETD-search/view_etd?URN=etd-0711117-201256

► The purpose of this experiment is to use the piezoelectric atomizer film as a nozzle, set up a high-power electronic devices (â¥ 100W COB LED)… (more)

Subjects/Keywords: LED cooling; Î¼PIV; Î¼IPI; High powered electronic devices; Spray cooling; Piezoelectric atomizer film

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APA (6^th Edition):

Yeh, Y. (2017). Spray Cooling Thermal and Flow Characteristics for High Power Electronic Devices. (Thesis). NSYSU. Retrieved from http://etd.lib.nsysu.edu.tw/ETD-db/ETD-search/view_etd?URN=etd-0711117-201256

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):

Yeh, Yi-Fan. “Spray Cooling Thermal and Flow Characteristics for High Power Electronic Devices.” 2017. Thesis, NSYSU. Accessed January 23, 2021. http://etd.lib.nsysu.edu.tw/ETD-db/ETD-search/view_etd?URN=etd-0711117-201256.

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

MLA Handbook (7^th Edition):

Yeh, Yi-Fan. “Spray Cooling Thermal and Flow Characteristics for High Power Electronic Devices.” 2017. Web. 23 Jan 2021.

Vancouver:

Yeh Y. Spray Cooling Thermal and Flow Characteristics for High Power Electronic Devices. [Internet] [Thesis]. NSYSU; 2017. [cited 2021 Jan 23]. Available from: http://etd.lib.nsysu.edu.tw/ETD-db/ETD-search/view_etd?URN=etd-0711117-201256.

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

Council of Science Editors:

Yeh Y. Spray Cooling Thermal and Flow Characteristics for High Power Electronic Devices. [Thesis]. NSYSU; 2017. Available from: http://etd.lib.nsysu.edu.tw/ETD-db/ETD-search/view_etd?URN=etd-0711117-201256

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

Penn State University

23. Mensch, Amy. Using Conjugate Heat Transfer to Assess the Cooling Performance on a Turbine Endwall.

Degree: 2015, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/24899

► Advancements in cooling for applications such as gas turbines components require improved understanding of the complex heat transfer mechanisms and the interactions between those mechanisms.… (more)

▼ Advancements in cooling for applications such as gas turbines components require improved understanding of the complex heat transfer mechanisms and the interactions between those mechanisms. Turbine designers often rely on multiple thermal protection techniques, including internal cooling, external film cooling, and thermal barrier coatings to efficiently cool components and limit the use of coolant. Traditionally, the effectiveness of such cooling technologies is quantified by considering the convection and conduction heat transfer mechanisms separately. The current research considers the combined effects of both internal and external cooling in a single experiment or simulation using a conjugate heat transfer approach. The geometry used for this study is a turbine blade endwall, which is influenced by three-dimensional vortices generated by the passage flow. The experiments and computational simulations include impingement and film cooling as well as conduction through the endwall. Appropriate geometric and flow parameters are properly scaled to ensure engine relevant dimensionless temperatures are obtained. The overall effectiveness, which is a scaled wall temperature, is compared for multiple cases, including different cooling configurations and the implementation of endwall contouring, thermal barrier coatings, and contaminant deposition. The measurements showed that impingement cooling was a larger contributor to the combined overall effectiveness compared to film cooling. The area-averaged contoured endwall overall effectiveness was similar to the flat endwall despite local differences in film cooling effectiveness and impingement effectiveness. The thermal barrier coating significantly increased overall effectiveness by reducing the external heat transfer. Contaminant deposition increased surface roughness, which increased external heat transfer to the endwall. Computational simulations of conjugate heat transfer and time-resolved flowfield measurements helped to understand the complex mechanisms acting together to generate the overall cooling effectiveness. The predicted endwall temperature fields show the three-dimensional temperature gradients present in conjugate heat transfer. The flat and contoured endwall flowfield measurements show that film cooling jets and the passage vortex interact to generate the secondary flowfield impacting endwall heat transfer. Several recommendations for mitigating increased heat transfer and optimizing the cooling performance for gas turbine endwalls are given. Advisors/Committee Members: Karen Ann Thole, Committee Chair/Co-Chair, Stephen P Lynch, Committee Member, Jacqueline Antonia O'connor, Committee Member, Brent A Craven, Special Member.

Subjects/Keywords: gas turbine endwall; conjugate heat transfer; contoured endwall; film cooling; impingement cooling; thermal barrier coating

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APA (6^th Edition):

Mensch, A. (2015). Using Conjugate Heat Transfer to Assess the Cooling Performance on a Turbine Endwall. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/24899

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):

Mensch, Amy. “Using Conjugate Heat Transfer to Assess the Cooling Performance on a Turbine Endwall.” 2015. Thesis, Penn State University. Accessed January 23, 2021. https://submit-etda.libraries.psu.edu/catalog/24899.

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

MLA Handbook (7^th Edition):

Mensch, Amy. “Using Conjugate Heat Transfer to Assess the Cooling Performance on a Turbine Endwall.” 2015. Web. 23 Jan 2021.

Vancouver:

Mensch A. Using Conjugate Heat Transfer to Assess the Cooling Performance on a Turbine Endwall. [Internet] [Thesis]. Penn State University; 2015. [cited 2021 Jan 23]. Available from: https://submit-etda.libraries.psu.edu/catalog/24899.

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

Council of Science Editors:

Mensch A. Using Conjugate Heat Transfer to Assess the Cooling Performance on a Turbine Endwall. [Thesis]. Penn State University; 2015. Available from: https://submit-etda.libraries.psu.edu/catalog/24899

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

Penn State University

24. Topcuoglu, Ilker. Aerodynamic Loss Models and Multi-Dimensional Prediction of Discrete Hole Film Cooling on Gas Turbine Blades.

Degree: 2013, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/19150

► A detailed review of the literature on losses associated with film cooling is given. An experimental case with two different cooling-hole geometries (Round Cylindrical Hole… (more)

▼ A detailed review of the literature on losses associated with film cooling is given. An experimental case with two different cooling-hole geometries (Round Cylindrical Hole and Conical Diffused Hole) was selected in order to base numerical computations on and to determine the deficiencies in both numerical simulations and analytical methods. Two analytical loss prediction models were selected from literature, and they were compared to both the experimental results from the open literature and the computer simulations. These two analytical methods by Shapiro and Köllen gave different results. As a part of this study, a first set of simulations were performed modeling the transonic film cooling data on a symmetrical airfoil given in the reference, and they did not capture the effects of the oblique shockwaves at the trailing edge very accurately, which is possibly due to inaccuracies in the geometric model, flow conditions, and the mathematical model itself. For this case, the predictions from both the computer simulations and the analytical methods were quite different than the experimental values. In order to avoid the effects of these shockwaves, further simulations were carried out under high subsonic conditions. In these simulations, the losses were significantly lower than the transonic experiments, but they agreed remarkably well with the predictions from Köllen’s method. Shapiro’s method somewhat under-predicted the results. As a result of comparing three-dimensional computational results to the analytical methods by Shapiro where constant pressure one-dimensional mixing is assumed, and by Köllen where one-dimensional mixing with the mixing-layer concept is adopted, while taking the experimental results of Jackson et.al. into account, it was found that both Shapiro’s and Köllen’s methods captured the order of magnitude for the total pressure losses for a cooled blade, while Köllen’s method provided much more accurate results. Advisors/Committee Members: Cengiz Camci, Thesis Advisor/Co-Advisor.

Subjects/Keywords: Film cooling; gas turbine cooling; aerodynamic loss prediction; total pressure loss model

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

APA (6^th Edition):

Topcuoglu, I. (2013). Aerodynamic Loss Models and Multi-Dimensional Prediction of Discrete Hole Film Cooling on Gas Turbine Blades. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/19150

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):

Topcuoglu, Ilker. “Aerodynamic Loss Models and Multi-Dimensional Prediction of Discrete Hole Film Cooling on Gas Turbine Blades.” 2013. Thesis, Penn State University. Accessed January 23, 2021. https://submit-etda.libraries.psu.edu/catalog/19150.

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

MLA Handbook (7^th Edition):

Topcuoglu, Ilker. “Aerodynamic Loss Models and Multi-Dimensional Prediction of Discrete Hole Film Cooling on Gas Turbine Blades.” 2013. Web. 23 Jan 2021.

Vancouver:

Topcuoglu I. Aerodynamic Loss Models and Multi-Dimensional Prediction of Discrete Hole Film Cooling on Gas Turbine Blades. [Internet] [Thesis]. Penn State University; 2013. [cited 2021 Jan 23]. Available from: https://submit-etda.libraries.psu.edu/catalog/19150.

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

Council of Science Editors:

Topcuoglu I. Aerodynamic Loss Models and Multi-Dimensional Prediction of Discrete Hole Film Cooling on Gas Turbine Blades. [Thesis]. Penn State University; 2013. Available from: https://submit-etda.libraries.psu.edu/catalog/19150

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

University of Oxford

25. Thomas, Mitra. Optimization of endwall film-cooling in axial turbines.

Degree: PhD, 2014, University of Oxford

URL: http://ora.ox.ac.uk/objects/uuid:e369eb63-0c99-4ded-ab05-6b050004ce4c ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.629557

► Considerable reductions in gas turbine weight and fuel consumption can be achieved by operating at a higher turbine entry temperature. The move to lean combustors… (more)

Subjects/Keywords: 621.43; Aerodynamics and heat transfer; aerodynamics; heat transfer; film cooling; turbine endwall cooling

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

APA (6^th Edition):

Thomas, M. (2014). Optimization of endwall film-cooling in axial turbines. (Doctoral Dissertation). University of Oxford. Retrieved from http://ora.ox.ac.uk/objects/uuid:e369eb63-0c99-4ded-ab05-6b050004ce4c ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.629557

Chicago Manual of Style (16^th Edition):

Thomas, Mitra. “Optimization of endwall film-cooling in axial turbines.” 2014. Doctoral Dissertation, University of Oxford. Accessed January 23, 2021. http://ora.ox.ac.uk/objects/uuid:e369eb63-0c99-4ded-ab05-6b050004ce4c ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.629557.

MLA Handbook (7^th Edition):

Thomas, Mitra. “Optimization of endwall film-cooling in axial turbines.” 2014. Web. 23 Jan 2021.

Vancouver:

Thomas M. Optimization of endwall film-cooling in axial turbines. [Internet] [Doctoral dissertation]. University of Oxford; 2014. [cited 2021 Jan 23]. Available from: http://ora.ox.ac.uk/objects/uuid:e369eb63-0c99-4ded-ab05-6b050004ce4c ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.629557.

Council of Science Editors:

Thomas M. Optimization of endwall film-cooling in axial turbines. [Doctoral Dissertation]. University of Oxford; 2014. Available from: http://ora.ox.ac.uk/objects/uuid:e369eb63-0c99-4ded-ab05-6b050004ce4c ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.629557

Loughborough University

26. Krawciw, Jason. Optimisation techniques for combustor wall cooling.

Degree: PhD, 2017, Loughborough University

URL: http://hdl.handle.net/2134/25030

► In a drive to increase the thermal efficiency of modern gas turbine engines, the turbine entry temperature (TET) has been steadily increasing over time to… (more)

▼ In a drive to increase the thermal efficiency of modern gas turbine engines, the turbine entry temperature (TET) has been steadily increasing over time to the point where the hot gasses contained within the combustion chamber have temperatures well in excess of the melting point of the materials used in its construction. As a result compressor exit air is widely used to cool these components. However, the use of this air is detrimental to the cycle efficiency. Therefore an important area of study is in optimising the use of this cooling flow in order to minimise the amount of air diverted from the main cycle. Effusion cooling techniques involving the use of a number of holes arrayed on the combustor liner wall are widely used and with additive manufacturing techniques such as direct laser deposition (DLD) gaining maturity, the design space of the cooling passages has become much wider. Therefore methods of assessing the performance of these newly enabled designs must be developed. This thesis describes a number of methodologies used to evaluate the performance of effusion cooling systems. Experimental methods are employed to determine both overall effectiveness using infrared (IR) thermography and adiabatic film effectiveness using pressure sensitive paint (PSP) and the heat-mass transfer analogy. These measurement techniques are carried out using a single near-ambient conditions wind tunnel and a single set of metal test plates. These methods are used to determine the relative performance of six coolant passage geometries ranging from a simple cylindrical angled effusion design to more exotic helical flow passages. Computational techniques are also used to evaluate the relative film performance of the same six geometries utilising a simplification technique which splits the effusion calculation up and uses a single-passage computation to determine the through-hole flow field then extracts flow properties on a plane near the passage exit. These data are then used as boundary conditions for the effusion array, reducing the mesh size dramatically as only a small region near each hole exit is included in the computation. A conjugate simulation is also carried out on the single-passage geometry to investigate the heat transferred through the passage walls. These techniques are used to investigate the performance of the six cooling geometries at various conditions of liner pressure drop and freestream turbulence levels. The PSP tests indicate that increasing the momentum ratio beyond 6 has little effect on the adiabatic effectiveness performance for the majority of the designs considered, the only exception being a design which utilises densely packed rows of cooling slots while increasing the distance xii between successive rows. These tests also indicated that the main effect of increasing freestream bulk turbulence is to increase the turbulent mixing, resulting in wider coolant traces in the lateral direction while reducing the streamwise trace length. Sensitivity to bulk turbulence levels generally decreases with…

Subjects/Keywords: Engineering not elsewhere classified; Film cooling; Effusion cooling; Pressure sensitive paint; Infrared thermography; CFD

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

APA (6^th Edition):

Krawciw, J. (2017). Optimisation techniques for combustor wall cooling. (Doctoral Dissertation). Loughborough University. Retrieved from http://hdl.handle.net/2134/25030

Chicago Manual of Style (16^th Edition):

Krawciw, Jason. “Optimisation techniques for combustor wall cooling.” 2017. Doctoral Dissertation, Loughborough University. Accessed January 23, 2021. http://hdl.handle.net/2134/25030.

MLA Handbook (7^th Edition):

Krawciw, Jason. “Optimisation techniques for combustor wall cooling.” 2017. Web. 23 Jan 2021.

Vancouver:

Krawciw J. Optimisation techniques for combustor wall cooling. [Internet] [Doctoral dissertation]. Loughborough University; 2017. [cited 2021 Jan 23]. Available from: http://hdl.handle.net/2134/25030.

Council of Science Editors:

Krawciw J. Optimisation techniques for combustor wall cooling. [Doctoral Dissertation]. Loughborough University; 2017. Available from: http://hdl.handle.net/2134/25030

Northeastern University

27. Yao, Yuan. An Experimental Film Cooling Effectiveness Introducing A New Film Hole Geometry Using Pressure Sensitive Paint Technique.

Degree: MS, Department of Mechanical and Industrial Engineering, 2019, Northeastern University

URL: http://hdl.handle.net/2047/D20317909

► Since the invention of the gas turbine technology, countless engineers and scientists have been trying their best to refine this type of machine. One of… (more)

Subjects/Keywords: Anti-counter-rotating vortices; Blowing ratio; Film cooling; Film cooling effectiveness; Pressure Sensitive Paint; 'V-shaped' film cooling hole; Mechanical engineering; Aerospace engineering

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

APA (6^th Edition):

Yao, Y. (2019). An Experimental Film Cooling Effectiveness Introducing A New Film Hole Geometry Using Pressure Sensitive Paint Technique. (Masters Thesis). Northeastern University. Retrieved from http://hdl.handle.net/2047/D20317909

Chicago Manual of Style (16^th Edition):

Yao, Yuan. “An Experimental Film Cooling Effectiveness Introducing A New Film Hole Geometry Using Pressure Sensitive Paint Technique.” 2019. Masters Thesis, Northeastern University. Accessed January 23, 2021. http://hdl.handle.net/2047/D20317909.

MLA Handbook (7^th Edition):

Yao, Yuan. “An Experimental Film Cooling Effectiveness Introducing A New Film Hole Geometry Using Pressure Sensitive Paint Technique.” 2019. Web. 23 Jan 2021.

Vancouver:

Yao Y. An Experimental Film Cooling Effectiveness Introducing A New Film Hole Geometry Using Pressure Sensitive Paint Technique. [Internet] [Masters thesis]. Northeastern University; 2019. [cited 2021 Jan 23]. Available from: http://hdl.handle.net/2047/D20317909.

Council of Science Editors:

Yao Y. An Experimental Film Cooling Effectiveness Introducing A New Film Hole Geometry Using Pressure Sensitive Paint Technique. [Masters Thesis]. Northeastern University; 2019. Available from: http://hdl.handle.net/2047/D20317909

University of Maryland

28. Adamson, Colin Sawyer. Heat Transfer Measurements in a Supersonic Film Flow.

Degree: Aerospace Engineering, 2016, University of Maryland

URL: http://hdl.handle.net/1903/18424

► This thesis presents measurements of wall heat flux and flow structure in a canonical film cooling configuration with Mach 2.3 core flow in which the… (more)

Subjects/Keywords: Aerospace engineering; Film Cooling; Heat Flux Measurements; Heat Transfer; Supersonic Film Cooling; Supersonic Flow; Supersonic Heat Transfer

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

APA (6^th Edition):

Adamson, C. S. (2016). Heat Transfer Measurements in a Supersonic Film Flow. (Thesis). University of Maryland. Retrieved from http://hdl.handle.net/1903/18424

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):

Adamson, Colin Sawyer. “Heat Transfer Measurements in a Supersonic Film Flow.” 2016. Thesis, University of Maryland. Accessed January 23, 2021. http://hdl.handle.net/1903/18424.

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

MLA Handbook (7^th Edition):

Adamson, Colin Sawyer. “Heat Transfer Measurements in a Supersonic Film Flow.” 2016. Web. 23 Jan 2021.

Vancouver:

Adamson CS. Heat Transfer Measurements in a Supersonic Film Flow. [Internet] [Thesis]. University of Maryland; 2016. [cited 2021 Jan 23]. Available from: http://hdl.handle.net/1903/18424.

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

Council of Science Editors:

Adamson CS. Heat Transfer Measurements in a Supersonic Film Flow. [Thesis]. University of Maryland; 2016. Available from: http://hdl.handle.net/1903/18424

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

The Ohio State University

29. Kheniser, Issam E. Film Cooling Experiments in a Medium Duration Blowdown Facility.

Degree: MS, Mechanical Engineering, 2010, The Ohio State University

URL: http://rave.ohiolink.edu/etdc/view?acc_num=osu1276540410

► As gas turbine engines are driven to be more efficient, quiet, and to produce less pollutant the turbine inlet temperature has a tendency to… (more)

▼ As gas turbine engines are driven to be more efficient, quiet, and to produce less pollutant the turbine inlet temperature has a tendency to be driven upwards. The life of a turbine engine component decreases dramatically as the metal temperature increases. Because film cooling of high-pressure turbine airfoils has become common practice, improving the ability to predict film-cooling effectiveness is a critical problem of interest. Finding better, more efficient ways to use the cooling air is far preferable to using more of it. However, even if a given cooling-hole configuration proves to be effective in a flat-plate environment (which is the test article of interest in this thesis), it may not be effective on a turbine blade that is exposed to dynamic conditions that cannot be easily replicated. The goal of the experiment reported here is to measure the film effectiveness for a blowing ratio, temperature ratio and free stream Mach number, all similar to those experienced by the pressure surface of a rotating blade turbine blade with the same cooling-hole configuration, but for the flat-plate test article noted above. The cooling gas flow will be initiated earlier than the main flow to allow for proper setup of the cooling flow. This data will be used as a comparison to simulation results obtained using the CFD code Fine TURBO. It is shown in this work that the cooling-gas supply system interaction with the external gas supply associated with the blowdown facility process is not simple, and the current model used to design the experiment is not as good as it could have been. The effect of cooling was observed and the data closely resembled the simulations done using the CFD code Fine TURBO. Unfortunately, due to problems with the double-sided Kapton heat-flux gauges, heat flux data was not obtained in the immediate vicinity of the cooling holes. Solutions to the problems encountered in this experiment are relatively straightforward and are presented. Advisors/Committee Members: Dunn, Michael (Advisor).

Subjects/Keywords: Mechanical Engineering; Blowdown; Film; cooling; film-cooling

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

APA (6^th Edition):

Kheniser, I. E. (2010). Film Cooling Experiments in a Medium Duration Blowdown Facility. (Masters Thesis). The Ohio State University. Retrieved from http://rave.ohiolink.edu/etdc/view?acc_num=osu1276540410

Chicago Manual of Style (16^th Edition):

Kheniser, Issam E. “Film Cooling Experiments in a Medium Duration Blowdown Facility.” 2010. Masters Thesis, The Ohio State University. Accessed January 23, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=osu1276540410.

MLA Handbook (7^th Edition):

Kheniser, Issam E. “Film Cooling Experiments in a Medium Duration Blowdown Facility.” 2010. Web. 23 Jan 2021.

Vancouver:

Kheniser IE. Film Cooling Experiments in a Medium Duration Blowdown Facility. [Internet] [Masters thesis]. The Ohio State University; 2010. [cited 2021 Jan 23]. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=osu1276540410.

Council of Science Editors:

Kheniser IE. Film Cooling Experiments in a Medium Duration Blowdown Facility. [Masters Thesis]. The Ohio State University; 2010. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=osu1276540410

30. Lambert, Océane. Solutions architecturées par fabrication additive pour refroidissement de parois de chambres de combustion : Architectured materials fabricated by additive manufacturing for surface cooling of combustion chambers.

Degree: Docteur es, 2MGE : Matériaux, Mécanique, Génie civil, Electrochimie, 2017, Université Grenoble Alpes (ComUE)

URL: http://www.theses.fr/2017GREAI048

►

En vue de leur refroidissement, les parois de chambres de combustion aéronautiques sont perforées de trous à travers lesquels de l’air plus froid est injecté.… (more)

▼

En vue de leur refroidissement, les parois de chambres de combustion aéronautiques sont perforées de trous à travers lesquels de l’air plus froid est injecté. La paroi est ainsi refroidie par convection et un film isolant est créé en surface chaude (film cooling). Cette thèse a pour objectif d’utiliser les possibilités de la fabrication additive pour proposer de nouvelles solutions architecturées qui permettraient d’augmenter les échanges de chaleur internes et d’obtenir ainsi de meilleures efficacités de refroidissement.La première approche consiste à élaborer de nouveaux designs de plaques multiperforées par Electron Beam Melting (EBM) et Selective Laser Melting (SLM) aux limites de résolution des procédés. Les architectures sont caractérisées en microscopie, en tomographie X et en perméabilité. Des simulations aérothermiques permettent de mettre en évidence l’effet de ces nouveaux designs sur l’écoulement et les échanges de chaleur, et de proposer des voies d’amélioration de la géométrie.La deuxième approche consiste à élaborer de façon simultanée une pièce architecturée par EBM, avec des zones denses et poreuses. A partir d’analyse d’images associée à une cartographie EBSD grand champ, il est possible de remonter aux mécanismes de formation du matériau poreux et de relier la perméabilité et la porosité aux paramètres procédé. Afin de favoriser le film cooling, il pourrait être avantageux que les zones microporeuses soient orientées dans le sens de l’écoulement. Pour ce faire, un nouveau procédé dénommé Magnetic Freezing, où des poudres métalliques forment une structure orientée par un champ magnétique, est mis au point.Les diverses solutions développées durant cette thèse sont testées sur un banc aérothermique. Les essais montrent qu’elles offrent un refroidissement plus efficace et plus homogène que la référence industrielle. Enfin, de premiers tests en combustion sur l’une des structures retenues, plus légère et plus perméable que la référence, montrent qu’il s’agit d’une solution aussi efficace à un débit traversant donné, et donc a priori plus efficace à une surpression donnée.

Combustion chamber walls are perforated with holes so that a cooling air flow can be injected through them. The wall is cooled by convection and an insulating film is created on the hot surface (film cooling). This PhD thesis aims to use the possibilities of additive manufacturing to provide new architectured solutions that could enhance the internal heat exchanges, and lead to a higher cooling effectiveness.The first approach is to develop new designs of multiperforated walls by Electron Beam Melting (EBM) and Selective Laser Melting (SLM) used at the resolution limits of the processes. They are characterized by microscopy, X-ray tomography and permeability tests. Some aerothermal simulations help understanding the effects of these new designs on the flow and on heat exchanges. These results lead to a geometry adaptation.The second approach is to simultaneously manufacture an architectured part with dense and porous zones by EBM.…

Advisors/Committee Members: Dendievel, Rémy (thesis director).

Subjects/Keywords: Fabrication additive; Electron Beam Melting; Matériaux poreux; Refroidissement par transpiration; Film cooling; Additive manufacturing; Electron Beam Melting; Porous materials; Transpiration cooling; Film cooling; 600

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

APA (6^th Edition):

Lambert, O. (2017). Solutions architecturées par fabrication additive pour refroidissement de parois de chambres de combustion : Architectured materials fabricated by additive manufacturing for surface cooling of combustion chambers. (Doctoral Dissertation). Université Grenoble Alpes (ComUE). Retrieved from http://www.theses.fr/2017GREAI048

Chicago Manual of Style (16^th Edition):

Lambert, Océane. “Solutions architecturées par fabrication additive pour refroidissement de parois de chambres de combustion : Architectured materials fabricated by additive manufacturing for surface cooling of combustion chambers.” 2017. Doctoral Dissertation, Université Grenoble Alpes (ComUE). Accessed January 23, 2021. http://www.theses.fr/2017GREAI048.

MLA Handbook (7^th Edition):

Lambert, Océane. “Solutions architecturées par fabrication additive pour refroidissement de parois de chambres de combustion : Architectured materials fabricated by additive manufacturing for surface cooling of combustion chambers.” 2017. Web. 23 Jan 2021.

Vancouver:

Lambert O. Solutions architecturées par fabrication additive pour refroidissement de parois de chambres de combustion : Architectured materials fabricated by additive manufacturing for surface cooling of combustion chambers. [Internet] [Doctoral dissertation]. Université Grenoble Alpes (ComUE); 2017. [cited 2021 Jan 23]. Available from: http://www.theses.fr/2017GREAI048.

Council of Science Editors:

Lambert O. Solutions architecturées par fabrication additive pour refroidissement de parois de chambres de combustion : Architectured materials fabricated by additive manufacturing for surface cooling of combustion chambers. [Doctoral Dissertation]. Université Grenoble Alpes (ComUE); 2017. Available from: http://www.theses.fr/2017GREAI048

Open Access Theses and Dissertations