Loss reduction in the compressor corner region via blade cooling-Reference-Cited by-同舟云学术

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Loss reduction in the compressor corner region via blade cooling

Published:2024-01 Issue: Volume:261 Page:108676
ISSN:0020-7403
Container-title:International Journal of Mechanical Sciences
language:en
Short-container-title:International Journal of Mechanical Sciences

Author:

Wang Mingyang,Lu Xin'gen^ORCID,Yang Chengwu^ORCID,Han Ge,Zhao Shengfeng,Zhang Yanfeng

Funder

China Postdoctoral Science Foundation

National Major Science and Technology Projects of China

National Natural Science Foundation of China

Publisher

Elsevier BV

Subject

Mechanical Engineering,Mechanics of Materials,Condensed Matter Physics,General Materials Science,Civil and Structural Engineering,Ocean Engineering,Aerospace Engineering,Applied Mathematics

Reference77 articles.

1. Competing three-dimensional mechanisms in compressor flows;Taylor;J Turbomach,2017

2. Investigation of endwall effect on transitional flow inside compressor cascade passage at low reynolds number;Li;Phys Fluids,2021

3. Parameter study on numerical simulation of corner separation in Lmfa-Naca65 linear compressor cascade;Gao;Chin J Aeronaut,2017

4. Unsteady aerodynamics of compact axial compressors;Hutchings,2022

5. Reynolds number effects in axial compressors;Wassell;J Eng Power,1968

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