Computational research on film cooling performance of different shaped holes with backward and forward injection
Author:
Affiliation:
1. Air Force Engineering University, Xi’an 710038, China
2. Unit 32035 of PLA, Xi’an 7106002, China
3. Unit 95910 of PLA, Jiuquan 735000, China
Funder
National Natural Science Foundation of China
Publisher
AIP Publishing
Subject
General Physics and Astronomy
Link
http://aip.scitation.org/doi/pdf/10.1063/1.5091573
Reference45 articles.
1. Effect of High Freestream Turbulence on Flowfields of Shaped Film Cooling Holes
2. Numerical assessment of round-to-slot film cooling performances on a turbine blade under engine representative conditions
3. Film-cooling performance of converged-inlet hole shapes
4. Film Cooling
5. Heat transfer on a film-cooled rotating blade
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