APPROACH TO BLADE END-BEND MECHANISM

Jul. 1988

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Article Navigation > Journal of Aerospace Power > 1988 > 3(3): 219-222,281-282

Huang Lixi, Wei Xinglu, Peng Zeyan. APPROACH TO BLADE END-BEND MECHANISM[J]. Journal of Aerospace Power, 1988, 3(3): 219-222,281-282.

Citation:

Huang Lixi, Wei Xinglu, Peng Zeyan. APPROACH TO BLADE END-BEND MECHANISM[J]. Journal of Aerospace Power, 1988, 3(3): 219-222,281-282.

Huang Lixi, Wei Xinglu, Peng Zeyan. APPROACH TO BLADE END-BEND MECHANISM[J]. Journal of Aerospace Power, 1988, 3(3): 219-222,281-282.

Citation:

Huang Lixi, Wei Xinglu, Peng Zeyan. APPROACH TO BLADE END-BEND MECHANISM[J]. Journal of Aerospace Power, 1988, 3(3): 219-222,281-282.

Abstract

Blade end-bend is a new technique to improve the performance of compressors. A comprehensive study of two multistage compressors has been completed with numerical calculation, theoretical analysis and experimental investigation.It is shown that the end-bend causes redistribution of the whole flowfield,and the changes of characteristics in main flow region may be a vital factor to improve the engine performance. A comparative study of several end-bend patterns shows that the character of redistribution differs for each from other. It is important to choose the end-bend pattern suitable for the specific compressor.