大涵道比涡扇发动机高空台试验技术研究需求分析  

Technical research requirements for high bypass-ratio turbofan engine test at the simulated altitude test facility

作　　者：马前容[1] 苏金友[1] 侯鑫正 

机构地区：[1]中国燃气涡轮研究院航空发动机高空模拟技术重点实验室,四川江油621703

出　　处：《燃气涡轮试验与研究》2015年第1期39-44,共6页Gas Turbine Experiment and Research

摘　　要：分析了分开排气大涵道比涡扇发动机与小涵道比涡扇发动机,在结构、技术特点和对试验要求等方面的差异,并结合国内新建高空舱的设备特点和试验能力,提出了分开排气大涵道比涡扇发动机在该高空舱内试验前需开展的技术研究工作,明确了该大涵道比涡扇发动机开展首次高空台试验前应解决的技术问题。本研究对其他新型发动机高空台试验技术研究需求分析也具有重要的借鉴意义。The engine tests at the simulated altitude test facility （ATF） are necessary in engine develop？ment. The differences in configuration, technique and the test requirements between high bypass-ratio tur？bofan with separated flow nozzles and low bypass-ratio turbofan were analyzed firstly. Then taking into ac？count the structure and the test capability of a new ATF in China, the technical research requirements for high bypass-ratio turbofan engine with separated flow nozzles test at this ATF were offered, and the techni？cal problems that should be resolved before the first ATF test were also confirmed. It would be helpful for the analysis of technical research requirements on the other new-type engine test at the ATF.

关 键 词：分开排气喷管 大涵道比涡扇发动机 高空模拟试验 试验方法 需求分析 预先研究 

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]