Integrated control for supersonic inlet/engine

SUN Feng-yong; ZHANG Hai-bo; YE Zhi-feng

doi:10.13224/j.cnki.jasp.2014.10.002

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Integrated control for supersonic inlet/engine

更新时间：2026-07-07

- Integrated control for supersonic inlet/engine
- Issue 10, (2014)
- 作者机构：
  
  南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室,南京,210016
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2014.10.002
  CLC：
- Published：2014
- 稿件说明：
移动端阅览
孙丰勇, 张海波, 叶志锋. 超声速进气道/发动机一体化控制[J]. 航空动力学报, 2014, (10): 2279-2287. doi: 10.13224/j.cnki.jasp.2014.10.002

SUN Feng-yong, ZHANG Hai-bo, YE Zhi-feng. Integrated control for supersonic inlet/engine[J]. 2014, (10).
孙丰勇, 张海波, 叶志锋. 超声速进气道/发动机一体化控制[J]. 航空动力学报, 2014, (10): 2279-2287. doi: 10.13224/j.cnki.jasp.2014.10.002 DOI：

SUN Feng-yong, ZHANG Hai-bo, YE Zhi-feng. Integrated control for supersonic inlet/engine[J]. 2014, (10). DOI： 10.13224/j.cnki.jasp.2014.10.002.

摘要

为了解决超声速进气道/发动机一体化问题，建立了可进行放气调节的超声速进气道部件级数学模型，而后将其与某双轴涡扇发动机部件级模型匹配，实现进气道与发动机共同工作.基于该进气道/发动机一体化部件级模型，分析计算了超声速进气道内流、外流特性，并研究了在超声速工作状态下进气道放气特性，验证了在超声速飞行时，发动机在中间状态与加力状态下，通过进气道放气调节，发动机安装推力提升了3%.

Abstract

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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