某发动机涡轮盘裂纹扩展研究  

STUDY ON CRACK GROWTH OF AN ENGINE TURBINE

作　　者：刘宗晖 成晓鸣 单晓明 郭小军 LIU ZongHui;CHENG XiaoMing;SHAN XiaoMing;GUO XiaoJun(AECC Hunan Aviation Powerplant Research Institute, Zhuzhou 412002, China)

机构地区：[1]中国航发湖南航空动力机械研究所,株洲412002

出　　处：《机械强度》2018年第2期462-466,共5页Journal of Mechanical Strength

摘　　要：根据发动机限寿件损伤容限的设计要求,对某发动机涡轮盘(高强GH4169材料)开展了小样及整盘裂纹扩展试验研究,试验获得了涡轮盘裂纹扩展特性及其分散度;同时,开展了三维裂纹扩展仿真分析,并与试验结果进行了对比,结果表明涡轮盘裂纹扩展仿真结果具有较高精度,分析方法具备工程应用价值。According to the damage tolerance design requirements to the engine life-limited parts,research on the fatigue crack growth tests of an engine power turbine（ high-strength GH4169） is carried out in this article. The crack growth behaviors of the turbine and the dispersion are obtained. Meanwhile,the three-dimension crack growth simulation is conducted and the results are compared with the test results. The result demonstrates that the crack propagation simulation result of the turbine has high accuracy,the analysis method has the value of engineering application.

关 键 词：涡轮盘 裂纹扩展 试验 仿真 

分 类 号：V215.6[航空宇航科学与技术—航空宇航推进理论与工程]