Volume 29 Issue 10
Oct.  2014
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SUN Feng-yong, ZHANG Hai-bo, YE Zhi-feng. Integrated control for supersonic inlet/engine[J]. Journal of Aerospace Power, 2014, (10): 2279-2287. doi: 10.13224/j.cnki.jasp.2014.10.002
Citation: SUN Feng-yong, ZHANG Hai-bo, YE Zhi-feng. Integrated control for supersonic inlet/engine[J]. Journal of Aerospace Power, 2014, (10): 2279-2287. doi: 10.13224/j.cnki.jasp.2014.10.002

Integrated control for supersonic inlet/engine

doi: 10.13224/j.cnki.jasp.2014.10.002
  • Received Date: 2013-06-17
  • Publish Date: 2014-10-28
  • A component-level mathematical model of supersonic inlet with bleeding adjustment was developed to study of integrated performance for supersonic inlet/engine. Meanwhile, a coupling mathematical model of supersonic inlet and turbofan engine was built via a biaxial turbofan engine component-level models and inlet component-level models to describe their collaborate relationship. The properties of outside and inside flux of the intake were calculated base on this integrated component-level model for inlet/engine. Inlet bleeding properties in supersonic working mode were also analyzed. At last, the engine installed thrust was verified to be effectively enhanced 3% by the bleeding adjustment of inlet when the aircraft worked at supersonic flight in the middle and afterburner states.

     

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