EFFECT OF SMALL RADIAL DISTORTION OF INLET FLOW ON STALL FLUTTER IN AXIAL FLOW COMPRESSOR

Feng Yucheng; Zhao Xiuhua; Hu Zongan; Ji Tu; Wang Yunwei

Volume 10 Issue 3

Jul. 1995

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Article Navigation > Journal of Aerospace Power > 1995 > 10(3): 213-216,307

Feng Yucheng, Zhao Xiuhua, Hu Zongan, Ji Tu, Wang Yunwei. EFFECT OF SMALL RADIAL DISTORTION OF INLET FLOW ON STALL FLUTTER IN AXIAL FLOW COMPRESSOR[J]. Journal of Aerospace Power, 1995, 10(3): 213-216,307.

Citation:

Feng Yucheng, Zhao Xiuhua, Hu Zongan, Ji Tu, Wang Yunwei. EFFECT OF SMALL RADIAL DISTORTION OF INLET FLOW ON STALL FLUTTER IN AXIAL FLOW COMPRESSOR[J]. Journal of Aerospace Power, 1995, 10(3): 213-216,307.

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EFFECT OF SMALL RADIAL DISTORTION OF INLET FLOW ON STALL FLUTTER IN AXIAL FLOW COMPRESSOR

4th Dept.Beijing University of Aeronautics and Astronautics,Beijing 100083

Received Date: 1994-05-01
Rev Recd Date: 1994-06-01
Publish Date: 1995-07-28

Abstract

Abstract

The effect of small radial stagnation pressure distortion of inlet flow on the stall flutter has been investigated experimentally.The results of experiments show that the small radial distortion of the inlet flow at blade tip can eliminate the stall flutter.This phenomenon is verified by computation with three dimensional actuator disk method.The computed results conform with the experimental data.