Volume 30 Issue 2
Feb.  2015
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ZHANG Chen-kai, HU Jun, WANG Zhi-qiang, YIN Chao, YAN Wei. Numerical study on three-dimensional optimization of low-speed axial compressor rotor blade[J]. Journal of Aerospace Power, 2015, 30(2): 483-490. doi: 10.13224/j.cnki.jasp.2015.02.028
Citation: ZHANG Chen-kai, HU Jun, WANG Zhi-qiang, YIN Chao, YAN Wei. Numerical study on three-dimensional optimization of low-speed axial compressor rotor blade[J]. Journal of Aerospace Power, 2015, 30(2): 483-490. doi: 10.13224/j.cnki.jasp.2015.02.028

Numerical study on three-dimensional optimization of low-speed axial compressor rotor blade

doi: 10.13224/j.cnki.jasp.2015.02.028
  • Received Date: 2013-09-18
  • Publish Date: 2015-02-28
  • To deepen the knowledge of endwall flow in the large-scale low-speed axial compressor, reduce accordingly its flow loss and improve its aerodynamic performance, numerical simulation and optimization were presented. With numerical tool, three-dimensional stacking principle was optimized to improve the design operation point aerodynamic performance for the prototype rotor of a large-scale low-speed axial compressor in low speed simulation. Results show that, near-hub region of the optimized rotor cannot undertake large blade loading; compared with the prototype rotor, the main region of performance improvement of optimized rotor locates near the hub region, and a certain degree of positive bend in this region effectively helps to reduce its flow loss. It shows the effect of “loaded leading edge”, which suppresses flow separation near the trailing edge; consequently nearly 19.4% of total pressure loss is reduced.

     

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