畸变条件下航空发动机喘振/失速适航符合性方法

为研究畸变条件下航空发动机对喘振/失速特性适航条款的符合性验证方法，将用于发动机稳定性评定的畸变试验方法应用于适航领域。以某型大涵道比涡扇发动机为研究对象，采用数值模拟方法研究了其在0°～30°迎角条件下的部件特性，并依据所得畸变图谱设计了不同结构的畸变发生器。结果表明:所设计的畸变发生器可以在一定程度上较好地模拟出不同迎角工况的畸变图谱、风扇的气动特性及流场特征，喘振裕度最大偏差4.32%。总结出发动机喘振裕度与不同迎角和畸变发生器之间的变化关系，用以确定适航条款要求的稳定工作范围。依据中国民用航空规章，发展了一种进气畸变条件下航空发动机喘振/失速特性符合性验证方法，并明确了其在型号合格审定过程的任务阶段。 

Airworthiness compliance method for aero-engine on surge/stall with distortion conditions

In order to study the verification method of aero-engine’s compliance with the airworthiness terms of surge/stall characteristics under distortion conditions, the distortion test method for engine stability evaluation was applied to the airworthiness field. And a turbofan engine with large bypass ratio was taken as the object, the component characteristics at 0°—30° attack angles were simulated, and the distortion generators with different structures were designed according to the obtained distortion map. The results showed that the designed distortion generator can better simulate the distortion map, aerodynamic performance and flow field characteristics of the fan at different attack angles to a certain extent, and the maximum deviation of stability margin was 4.32%. The relationship between engine surge margin, different attack angles and distortion generator was summarized to determine the stable working range required by airworthiness terms. According to China Civil Aviation Regulations, a method for verifying the compliance of aero-engine surge/stall characteristics with inlet distortion was developed, and its task stage in the model qualification process was defined.