EFFECT OF SMALL RADIAL DISTORTION OF INLET FLOW ON STALL FLUTTER IN AXIAL FLOW COMPRESSOR
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EFFECT OF SMALL RADIAL DISTORTION OF INLET FLOW ON STALL FLUTTER IN AXIAL FLOW COMPRESSOR
Vol. 10, Issue 3, (1995)
作者机构:
北京航空航天大学
作者简介:
基金信息:
DOI:
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Published:1995
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Feng Yucheng, Zhao Xiuhua, Hu Zongan, et al. EFFECT OF SMALL RADIAL DISTORTION OF INLET FLOW ON STALL FLUTTER IN AXIAL FLOW COMPRESSOR[J]. 1995, 10(3).
DOI:
Feng Yucheng, Zhao Xiuhua, Hu Zongan, et al. EFFECT OF SMALL RADIAL DISTORTION OF INLET FLOW ON STALL FLUTTER IN AXIAL FLOW COMPRESSOR[J]. 1995, 10(3).DOI:
EFFECT OF SMALL RADIAL DISTORTION OF INLET FLOW ON STALL FLUTTER IN AXIAL FLOW COMPRESSOR
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.