Volume 28 Issue 7
Jul.  2013
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SHI Pei-jie, QIAO Wei-yang, WEI Zuo-jun, XU Kun-bo. Numerical calculation model of axial compressor stability enhancement bywith discrete tip injection[J]. Journal of Aerospace Power, 2013, 28(7): 1549-1556.
Citation: SHI Pei-jie, QIAO Wei-yang, WEI Zuo-jun, XU Kun-bo. Numerical calculation model of axial compressor stability enhancement bywith discrete tip injection[J]. Journal of Aerospace Power, 2013, 28(7): 1549-1556.

Numerical calculation model of axial compressor stability enhancement bywith discrete tip injection

  • Received Date: 2012-09-28
  • Publish Date: 2013-07-28
  • A numerical calculation model for axial compressor stability enhancement by tip injection was developed.The model solved Navier-Stokes equation with source terms for annulus duct without blades.The effect of blades,including the force and energy applied to the flow by the blades,was modeled by the source terms.The current source terms of every iteration step varied according to the inlet parameters.Variation of manual disturbance was introduced to the model to predict the compressor's stall margin.The performance and stall margin of a transonic single stage compressor were calculated by the model with/without tip jet.The performance and stall margin predicted by the model without tip jet agree well with the experiment result,and the difference between the massflow of the stall margin predicted by the model and that got by the experiment is less than 0.7%.The effect of stability enhancement by tip injection is obvious from the results of the model compared with the results in open literature,helping to verify the model.

     

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