畸变条件下航空发动机喘振/失速适航符合性方法  

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

作　　者：郭重佳 傅文广 孙鹏 白杰[1] GUO Chongjia;FU Wenguang;SUN Peng;BAI Jie(College of Aeronautical Engineering,Civil Aviation University of China,Tianjin 300300,China;College of Safety Science and Engineering,Civil Aviation University of China,Tianjin 300300,China)

机构地区：[1]中国民航大学航空工程学院,天津300300 [2]中国民航大学安全科学与工程学院,天津300300

出　　处：《航空动力学报》2022年第12期2875-2886,共12页Journal of Aerospace Power

基　　金：天津市教委科研计划项目(2021KJ060);天津市多元投入基金项目青年项目(21JCQNJC00930)。

摘　　要：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。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.

关 键 词：民用涡扇发动机 进气畸变 喘振/失速特性 适航 符合性方法 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]