某型航空发动机进气压力畸变试验研究

Experimental Study on Inlet Pressure Distortion of an Aeroengine

针对飞机在大攻角飞行时易引起进气道和发动机进口流场畸变的情况,对某型发动机的综合抗进气压力畸变能力进行了整机试验研究。试验采用插板式畸变模拟器研究发动机综合抗总压畸变能力,获得了各规定风扇换算转速下发动机临界畸变指数,完成了畸变条件下遭遇加速试验,发动机过渡态工作正常。结果表明:该试验方案可行、数据可靠、结果有效,该型发动机满足飞机/发动机相容性试验要求。

Aiming at the aircraft inlet and engine inlet flow distortion caused by the flight at high attack angle,the general anti-inlet pressure distortion capability of an engine was experimentally studied,which used inlet flashboard distortion simulation.The critical distortion indexes were obtained at the fan conversion speed.The engine transition operation was usual at the accelerated test under the distortion condition.The results show that the test plot is feasible,the data is reliable and the results is effective,which satisfy the aircraft/engine compatibility test requirement.