Research on flow and heat transfer characteristics of supersonic film cooling with different hole-configurations
Author:
Affiliation:
1. School of Aeronautics and Astronautics, Sichuan University, Chengdu, P.R. China
2. Aircraft Strength Research Institute of China, Xi’an, P.R. China
3. Shenyang Aircraft Design and Research Institute, P.R. China
Funder
National Natural Science Foundation of China
Aeronautical Science Foundation of China
Publisher
Informa UK Limited
Link
https://www.tandfonline.com/doi/pdf/10.1080/10407782.2024.2384619
Reference29 articles.
1. A Review of Shaped Hole Turbine Film-Cooling Technology
2. Influence of Cooling-Gas Properties on Film-Cooling Effectiveness in Supersonic Flow
3. Fan-Shaped Hole Effects on the Aero-Thermal Performance of a Film Cooled Endwall
4. A. Kohli and D. G. Bogard “Effects of hole shape on film cooling with large angle injection ” ASME Paper 99-GT-165 1999. DOI: 10.1115/99-GT-165.
5. J. R. Dorrington D. G. Bogard and R. S. Bunker “Film effectiveness performance for coolant holes embedded in various shallow trench and crater depressions ” ASME Paper GT2007-27992 2007. DOI: 10.1115/GT2007-27992.
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