Volume 30 Issue 1
Jan.  2015
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LI Yan-kai, HUANG Tian-hao, MENG De-jun, MIAO Yu-lu, YU Wen-sheng, TENG Jin-fang. Low-speed modeling design for tip flow field of compressor rotor blade[J]. Journal of Aerospace Power, 2015, 30(1): 237-247. doi: 10.13224/j.cnki.jasp.2015.01.031
Citation: LI Yan-kai, HUANG Tian-hao, MENG De-jun, MIAO Yu-lu, YU Wen-sheng, TENG Jin-fang. Low-speed modeling design for tip flow field of compressor rotor blade[J]. Journal of Aerospace Power, 2015, 30(1): 237-247. doi: 10.13224/j.cnki.jasp.2015.01.031

Low-speed modeling design for tip flow field of compressor rotor blade

doi: 10.13224/j.cnki.jasp.2015.01.031
  • Received Date: 2013-09-09
  • Publish Date: 2015-01-28
  • A low-speed compressor is designed for tip flow field of first stage rotor in the high-speed compressor with an inlet guide vane. It was prepared for subsequent experiments of the low-speed compressor stall and blade tip flow loss. The design used blade design and numerical simulation methods to ensure similar distribution of blade surface pressure coefficient and blade inlet and outlet main aerodynamic parameters of high- and low-speed compressors. High-speed prototype compressor was taken as research object to design a low-speed compressor. It included adjustment of flow-path geometry, iterative design of blade profiles and breakthrough the limitation of the geometric similar principle for inlet guide vane and first-stage rotor blade design. Finally, the comparative analyzed of geometry, aerodynamic parameters and flow-field structure of high- and low-speed compressor proved that the low-speed modeling design is useful. This design guarantees the similarity of processing capacity factor and rotor diffuser factor is 98.16%, 94.95%, respectively, which is under the same flow coefficient.

     

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