摘要
本篇文章依据《航空涡轮螺桨和涡轮轴发动机通用规范》(GJB242—87)及某型涡轴发动机外物损伤试验要求,制定了试验方案。针对如何实现外物损伤模拟进行了详细的分析研究,确定了叶片损伤缺口的位置、深度和最优试制方法,并通过多轮试制和分析,确定了缺口宽度,最终顺利完成了整机外物损伤试验验证。该项试验的完成为发动机研制提供了有力的试验支撑,同时文中提出的叶片缺口设计试制方法及试验程序可为以后同类试验提供参考。
This paper formulates the test scheme according to The General Specification for Aviation Turbine Propeller and Turboshaft Engine(GJB242-87)and the external object damage test requirements of a turboshaft engine.The detailed analysis and research on how to realize foreign object damage simulation are carried out,the position,depth and optimal trial production method of blade damage notch are determined,and the notch width is determined through multiple rounds of trial production and analysis.Finally,the foreign object damage test verification of the whole machine is successfully completed.The completion of this test provides a strong test support for engine development.At the same time,the blade notch design and trial production method and test procedure proposed in this paper can provide reference for similar tests in the future.
作者
岳洋
杜玉庆
王璐
袁先圣
杨艳美
YUE Yang;DU Yuqing;WANG Lu;YUAN Xiansheng;YANG Yanmei(AECC Hunan Aviation Powerplant Research Institute,Zhuzhou,Hunan,412002,China)
关键词
整机试验
涡轴发动机
外物损伤
complete machine test
turboshaft engine
foreign object damage
