涡轴发动机压气机盘裂纹扩展寿命研究  

Research on Crack Growth Life of the Compressor Disk of a Turbo-shaft Engine

作　　者：张权 艾书民 唐广 ZHANG Quan;AI Shu-min;TANG Guang(AECC Hunan Aviation Powerplant Research Institute,Zhuzhou Hunan 412002;AECC Key Laboratory of Aero-engine Vibration Technology,Zhuzhou Hunan 412002)

机构地区：[1]中国航发湖南动力机械研究所,湖南株洲412002 [2]中国航空发动机集团航空发动机振动技术重点实验室,湖南株洲412002

出　　处：《长沙航空职业技术学院学报》2023年第1期1-4,共4页Journal of Changsha Aeronautical Vocational and Technical College

摘　　要：为提高发动机关键件的损伤容限设计水平,对涡轴发动机压气机第一级叶片盘裂纹扩展寿命开展了系统的计算分析和试验研究。建立了轮盘的裂纹扩展有限元分析模型,对轮盘工作状态下的应力、裂纹扩展几何历程和裂纹扩展寿命进行了计算分析。在立式轮盘试验器上分多阶段开展了一级叶片盘的裂纹扩展试验,试验后对轮盘及其断口进行了宏观、微观检查,对断口裂纹扩展寿命进行了定量计算。试验结果证明三维裂纹扩展仿真分析方法有效、可靠且精度较高。为涡轴发动机压气机典型零件裂纹扩展分析积累了宝贵的经验。In order to improve the level of damage tolerance design,the crack growth life of a compressor disk was studied by simulation analysis and experiment.A finite element model of the impeller was established.Stress,crack growth geometry progress and crack growth life of the impeller under working condition are calculated and analyzed.Crack growth experiments were carried out on a vertical disk tester.After test,the fracture was observed macroscopically and microscopically.The fracture crack growth life was quantitatively calculated.Valuable experience in crack growth analysis of typical turboshaft compressor parts was provided in this research.

关 键 词：损伤容限 压气机盘 裂纹扩展 疲劳寿命 仿真分析 断口分析 

分 类 号：V231.95[航空宇航科学与技术—航空宇航推进理论与工程]