EXPERIMENTAL INVESTIGATION ON PATTERNED BLADES OF COMPRESSOR

Miao Runtian; Wang Liangui; Qian Luhong; Tang Zhiming; Gao Ge

Volume 8 Issue 2

Apr. 1993

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Article Navigation > Journal of Aerospace Power > 1993 > 8(2): 155-157,204

Miao Runtian, Wang Liangui, Qian Luhong, Tang Zhiming, Gao Ge. EXPERIMENTAL INVESTIGATION ON PATTERNED BLADES OF COMPRESSOR[J]. Journal of Aerospace Power, 1993, 8(2): 155-157,204.

Citation:

Miao Runtian, Wang Liangui, Qian Luhong, Tang Zhiming, Gao Ge. EXPERIMENTAL INVESTIGATION ON PATTERNED BLADES OF COMPRESSOR[J]. Journal of Aerospace Power, 1993, 8(2): 155-157,204.

Miao Runtian, Wang Liangui, Qian Luhong, Tang Zhiming, Gao Ge. EXPERIMENTAL INVESTIGATION ON PATTERNED BLADES OF COMPRESSOR[J]. Journal of Aerospace Power, 1993, 8(2): 155-157,204.

Citation:

Miao Runtian, Wang Liangui, Qian Luhong, Tang Zhiming, Gao Ge. EXPERIMENTAL INVESTIGATION ON PATTERNED BLADES OF COMPRESSOR[J]. Journal of Aerospace Power, 1993, 8(2): 155-157,204.

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EXPERIMENTAL INVESTIGATION ON PATTERNED BLADES OF COMPRESSOR

1.
Shenyang LIMING Engine Manufactu ring Company
2.
Beijing University of Aeronautics and Astronautics

Received Date: 1992-05-01
Rev Recd Date: 1992-08-01
Publish Date: 1993-04-28

Abstract

Abstract

The presented experimental investigation on patt erned blades of compressor opens up a new way for improving performance of compressor.The experiments were carried out with a HP compres sor of a twin spool turbojet engine in a multistage compressor rig.The HP compressor consists of three stages(named the 4th,5th and 6th stage).Two kinds of pattern presented in the paper,as two design,are all engraved on the surfaces of the existent 4th and 5th stage stator blades.The pattern Ⅰ is 45° cross grooves and the pattern Ⅱ is streamwards grooves.The experimental data of the efficiency η and surge margin SM are listed below as compared with the reference compressor for uniform inlet flow: [WT6BZ]Pattern ⅠPattern Ⅱ[WX(!3KG2,4KG2,5KG2,4KG2,5]△η(%)△SM(%)△η(%)△SM(%)0 9+2 5+2 2+3 5+1 31 0+2 9-0 1+3 1+2 81 05+1 1-2 1+3 7+3 31 1+1 2-3 0+1 9+3 6 The performance with circumferential distorted inlet flow is kept the same with the reference compressor.The above experimental results show that the efficiencies and surge margines of the compressor with appro priately patterned stator blades can increase significantly.