外物损伤压气机叶片损伤容限分析  

Tolerance analysis of foreign object damage on compressor blade

作　　者：牟园伟 唐俊星[2] 赵勇铭 

机构地区：[1]中国航空发动机研究院,北京101304 [2]西北工业大学,西安710072 [3]中国航发湖南动力机械研究所,湖南株洲412002

出　　处：《燃气涡轮试验与研究》2017年第1期52-57,共6页Gas Turbine Experiment and Research

摘　　要：为研究外物损伤造成的初始裂纹对压气机叶片疲劳寿命的影响,开发了基于ANSYS平台的三维平片裂纹扩展整体参数化自动模拟通用技术。通过应力强度因子计算结果与文献结果对比,证明所开发裂纹扩展模型有较好的精度。利用该模型,研究了外物损伤初始裂纹位置、形态和方向对压气机叶片低周疲劳寿命的影响。研究表明,叶片后缘疲劳裂纹扩展寿命最长;裂纹短/长轴比越大,疲劳裂纹扩展寿命越长;当初始裂纹面垂直于最大主应力方向时,疲劳裂纹扩展寿命最短。In order to study the influence of initial crack caused by foreign object damage on compressorblade fatigue life, a total parameter-based and geometry independent general method was developed for au-tomatically simulating of 3D crack planar propagation on ANSYS platform. The accuracy of this crack mod-el was demonstrated by comparison with other analytical or experimental stress intensity factor results avail-able in the literature. The influence law of initial crack location, crack size, and crack direction on compres-sor blade fatigue life was studied by the model. The results show that the fatigue crack propagation life islonger in trailing edge than in other location and is longer as the short/length axis ratio increases. When theinitial crack surface was perpendicular to the direction of maximum principal stress, fatigue crack propaga-tion life is the shortest.

关 键 词：航空发动机 压气机叶片 外物损伤 三维裂纹 损伤容限 应力强度因子 裂纹扩展  北京101304 

分 类 号：V232.3[航空宇航科学与技术—航空宇航推进理论与工程]