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.

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