大涵道比涡扇发动机进气畸变测量耙风洞校准试验

摘要

The inlet distortion rake used in flight test of the high bypass ratio turbofan engine for C919 was developed based on dynamic and static pressure tests as well as total temperature parameters tests. The in-let distortion rake was adjusted in wind tunnel in order to analyze velocitymeasurement characteristic with different angles and Mach number. Then the test data was selected and calculated. At last it can be conclud-ed that the pressure loss coefficient was less than 0.5%with angles within-20°~20°and Mach numberwithin 0.2~0.6. So the inlet distortion rake can meet the measurement requirements of inlet flowfield and flow of high bypass ratio turbofan engine.%以国产大型客机C919配装的大涵道比涡扇发动机飞行试验为应用背景，研制了基于动态、稳态压力和总温参数集成测试的大尺寸进气道畸变测量耙。为评估和验证其角度、速度测量特性及参数测量精确度，进行了全尺寸量级的进气道测量耙风洞校准试验研究。结果表明：在马赫数0.2~0.6、攻角和侧滑角-20°~20°范围内，耙体压力测量相对误差小于0.5%，满足对大涵道比涡扇发动机进口流场品质和流量的测试技术需求。