飞机进气道/ 发动机台架联合试验及匹配特性研究

为了确定发动机地面装机条件下的进气畸变大小,对1种全尺寸进气道与发动机地面台架开展进发联合试验研究。试验速度条件为飞机静止状态,对应飞机迎角为0°,马赫数为0。参试进气道为2元外压式超声速进气道,参试发动机为大推力双转子带加力涡轮风扇发动机。采用地面台架联合试车的方法,获得了不同进气道条件下的进发匹配特性数据,包括在发动机不同工作转速下进气道出口流场的稳态总压特性、动态畸变特性等参数,并与进气道缩比模型风洞试验结果进行了对比分析。结果表明:全尺寸进气道的出口畸变随发动机空气流量增加而增大,与风洞试验结果一致,但防护网对于畸变的影响效果相反。

Combination Test and Match Characteristics Research of an Aircraft Inlet / Engine Testbed

In order to determine the distortion under the engine installed conditions, a combination test were studied on a full scale inlet and an engine ground testbed. The speed condition of the test was simulated at the aircraft stationary state, the corresponding angle of attack was 0° and mach was 0. The tested inlet was a two-dimensional external-compression supersonic inlet, the tested engine was a large thrust double spod turbofan with afterburer. Using the ground testbed combined test method,the test got the inlet characteristic parameters including steady-state pressure distortion, time-variant distortion at the Aerodynamic Interface Plane (AIP) in various engine rotating speed, and test results were compared with the wind-tunnel. Results show that the distortion of full scale inlet increases with the engine air flow increases, which is consistent with the results of scale model test in the wind-tunnel, but the effect of the protective net on the distortion is opposite against the wind-tunnel.