某型飞机进气道对发动机性能和台架点的影响  

Effect of inlet on the engine performance and platform point for aircraft

作　　者：张发启[1] 江勇[2] 桑增产[2] 孔卫东[2] 

机构地区：[1]西安交通大学机械工程学院,陕西西安710049 [2]空军工程大学工程学院,陕西西安710038

出　　处：《推进技术》2001年第2期137-138,146,共3页Journal of Propulsion Technology

摘　　要：对某双转子涡喷发动机装与不装飞机进气道进行了台架对比实验 ,测量了发动机的状态参数和进口压力场。根据实验结果 ,分析了飞机进气道引起发动机的进气畸变和对发动机台架性能及台架点的影响 ,并讨论了造成变化的原因。实验结果对于正确使用该类型双转子涡喷发动机具有重要的现实意义。In the experimental research, a twin-rotor turbojet with aircraft's inlet was contrasted with the case without aircraft's inlet, and the state parameter and inlet's pressure field of the engine were measured. Based on the experimental result, the inlet distortion caused by aircraft's inlet, the effect of aircraft's inlet on the performance and platform point of the engine was analyzed as well as the relevant causes. The experimental result has practical significance for correctly using the twin-rotor turbojet.

关 键 词：进气道-发动机匹配 进气道畸变 进气道试验 台架试验 飞机 

分 类 号：V235.113[航空宇航科学与技术—航空宇航推进理论与工程]