Volume 29 Issue 3
Mar.  2014
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SHI Lei, ZHU Yu, ZHAO Su. Inlet and engine compatibility in transonic speed low-flow state[J]. Journal of Aerospace Power, 2014, 29(3): 631-636. doi: 10.13224/j.cnki.jasp.2014.03.021
Citation: SHI Lei, ZHU Yu, ZHAO Su. Inlet and engine compatibility in transonic speed low-flow state[J]. Journal of Aerospace Power, 2014, 29(3): 631-636. doi: 10.13224/j.cnki.jasp.2014.03.021
shu

Inlet and engine compatibility in transonic speed low-flow state

doi: 10.13224/j.cnki.jasp.2014.03.021

  • 1. Shenyang Engine Design and Research Institute, Aviation Industry Corporation of China, Shenyang 110015, China;

  • 2. Shenyang Aircraft Design and Research Institute, Aviation Industry Corporation of China, Shenyang 110035, China

  • Received Date: 2013-01-14
  • Publish Date: 2014-03-28
    Abstract
  • The compatibility analysis of the inlet and engine was conducted,according to the phenomenon of surge and stall in state of transonic speed and low-flow during flight test.The research indicates that,the instability boundaries of the engine from flight tests agree with those of the inlet from the wind tunnel tests,proving there is something wrong in the compatibility of the inlet and engine.Two methods from the perspective of the inlet and engine were presented.One was used to adjust the inlet regulation of the ramp to enlarge the instability boundary of supersonic speed and low-flow.The other was used to increase the minimum fuel flow and the nozzle area to improve the flow and the stability margin.The validated results show that the methods can relieve the problem of inlet and engine compatibility in low-flow.In future,the rules of inlet and engine compatibility in transonic low-flow state should be built.

     

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