Volume 32 Issue 6
Jun.  2017
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Numerical simulation on blade tip unsteady flow in transonic compressor rotor[J]. Journal of Aerospace Power, 2017, 32(6): 1481-1490. doi: 10.13224/j.cnki.jasp.2017.06.026
Citation: Numerical simulation on blade tip unsteady flow in transonic compressor rotor[J]. Journal of Aerospace Power, 2017, 32(6): 1481-1490. doi: 10.13224/j.cnki.jasp.2017.06.026

Numerical simulation on blade tip unsteady flow in transonic compressor rotor

doi: 10.13224/j.cnki.jasp.2017.06.026
  • Received Date: 2015-08-27
  • Publish Date: 2017-06-28
  • The detailed three-dimensional unsteady numerical study was conducted in a transonic compressor rotor to deepen the understanding of unsteady flow phenomenon in rotor blade tip region. Unsteady numerical simulations were studied in single rotor under different inlet conditions and different mass flows, so as to investigate the complex flow structure in rotor blade tip region and the development of blade tip unsteady flow. Results showed that the structure of blade tip flow field varied under different inlet conditions. When inlet direction was non-axial, signal passage periodical form emerged for unsteady flow at blade tip, while an unsteady flow phenomenon like “rotating instability”, spreading along circumferential direction, occurred in blade tip region under axial inlet condition. And with the decrease of mass flow, the structural flow field of blade tip region changed correspondingly.

     

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