民用航空发动机高空模拟试验排气扩压器特性分析  

Characteristic analysis on exhaust diffuser of civil aviation engine in altitude simulation test

作　　者：郑舒桐[1] 陈廷千 文晓武 

机构地区：[1]中国燃气涡轮研究院,四川江油621703

出　　处：《燃气涡轮试验与研究》2015年第6期9-13,20,共6页Gas Turbine Experiment and Research

摘　　要：基于射流理论分析了民用航空发动机高空模拟试验时的排气流场,应用喷射器模型建立了针对民用航空发动机排气扩压器气动性能的计算方法,并完成了民用航空发动机试验的排气扩压器性能计算。分析了排气扩压器出口的增压比、马赫数、总温、体积流量,与排气扩压器内径和二股流流量之间的关系。基于计算分析结果,建议民用航空发动机高空模拟试车台排气采用直接喷水冷却方式,高空模拟试验时尽可能控制二股流流量。Based on the jet flow theory, the exhaust flow field of civil aviation engine in altitude simulation test was analyzed. The method used for aerodynamic performance calculation of civil aviation engine exhaust diffuser was established with ejector model, and the performance calculation of a civil aviation engine exhaust diffuser was completed with the method. The changes of pressure ratio, Mach number, total temperature, volume flow of the exhaust diffuser with the secondary flow and inner diameter of the exhaust diffuser inner diameter were summarized. Based on the calculating analysis, the outflow of altitude test facility for high bypass ratio turbofan engine should be cooled by spraying water and the flux of secondary flow should be reduced at full steam.

关 键 词：高空模拟试车台(高空台) 排气扩压器 增压比 大涵道比涡扇发动机 分开排气 

分 类 号：V263.4[航空宇航科学与技术—航空宇航制造工程]