Increasing Surge Margin in an Axial Flow Compressor Using “End-Bend” Airfoils PUBLIC ACCESS

[+] Author Affiliations
Y. J. Cai, Y. L. Zhong, L. H. Qian, S. Z. He, Q. H. Pang

Shenyang Aeroengine Company, China

Paper No. 85-IGT-25, pp. V001T02A009; 8 pages
  • ASME 1985 Beijing International Gas Turbine Symposium and Exposition
  • Volume 1: Aircraft Engine; Turbomachinery
  • Beijing, People’s Republic of China, September 1–7, 1985
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7942-9
  • Copyright © 1985 by ASME


This paper concentrates solely on the effect of end bend airfoil on performance of an axial flow compressor. The purpose is to reduce flow loss in the region of endwall boundary layer and to enlarge surge margin of an axial flow compressor by employing end bend airfoil on the stator blades in the last stages of the compressor. The experimental results show that surge margin is increased by 4.9–5.2 percent, efficiency by 2.6–3.2 percent at operational speed n=1.0–1.1.

Copyright © 1985 by ASME
Topics: Axial flow , Surges , Airfoils
This article is only available in the PDF format.



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