Reduction of end wall loss in axial compressor by using non-axisymmetric profiled end wall: A new design approach based on end wall velocity modification-Reference-Cited by-同舟云学术

Reduction of end wall loss in axial compressor by using non-axisymmetric profiled end wall: A new design approach based on end wall velocity modification

Published:2016-08 Issue: Volume:55 Page:76-91
ISSN:1270-9638
Container-title:Aerospace Science and Technology
language:en
Short-container-title:Aerospace Science and Technology

Author:

Chu Wuli,Li Xiangjun,Wu Yanhui,Zhang Haoguang

Funder

National Natural Science Foundation of China

Northwestern Polytechnical University

Publisher

Elsevier BV

Subject

Aerospace Engineering

Reference25 articles.

1. A criterion for axial compressor hub-corner stall;Lei;J. Turbomach.,2008

2. Leakage and secondary flows in compressor cascades;Lakshminarayana,1967

3. Three-dimensional separations in axial compressors;Gbadebo;J. Turbomach.,2005

4. Experimental and numerical investigation of corner stall in a highly-loaded compressor cascade;Zhang,2014

5. Experimental study of corner stall in a linear compressor cascade;Ma;Chin. J. Aeronaut.,2011

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