某高压涡轮盘裂纹扩展特性研究  

Study on Crack Propagation Characteristics of a High Pressure Turbine Disk

作　　者：张超[1] 宣海军[1] ZHANG Chao;XUAN Haijun(High-speed Rotating Machinery Laboratory, College of Energy Engineering, Zhejiang University, Hangzhou 310027, China)

机构地区：[1]浙江大学能源工程学院高速旋转机械实验室

出　　处：《机械工程师》2019年第6期1-3,9,共4页Mechanical Engineer

基　　金：中央高校基本科研业务费专项资金项目

摘　　要：通过三维裂纹扩展有限元仿真分析与低循环疲劳裂纹扩展试验相结合,研究了某高压涡轮盘损伤容限特征。基于有限元仿真分析获得的螺栓孔部位的应力和变形,开展了三维裂纹扩展寿命仿真计算,得到裂纹扩展速率的计算值。在轮盘低循环疲劳试验中,通过螺栓孔内壁面处定期荧光渗透检测和裂纹长度检测,记录了裂纹发展情况;在轮盘破裂后,通过疲劳断口扫描电镜观察,获得了裂纹扩展特征。结果表明,仿真计算与试验断口分析得到的裂纹前沿扩展历程、裂纹扩展寿命之间均存在较好的一致性。The damage tolerance characteristics of a high-pressure turbine disk are studied by the three-dimensional crack propagation finite element simulation analysis combined with the low cycle fatigue crack growth test. Based on the stress and deformation of the bolt hole obtained by finite element simulation analysis, a three-dimensional crack propagation life simulation calculation is carried out, and the calculated value of the crack propagation rate is obtained. In the low cycle fatigue test of disk, the crack propagation is recorded by periodic fluorescent penetrant inspection and crack length detection at the inner wall surface of the bolt hole. After the disk rupture, the crack propagation characteristics are obtained by scanning electron microscopy. The results show that there is a good agreement between the crack front propagation process and the crack propagation life obtained by the simulation calculation and the test fracture analysis.

关 键 词：高压涡轮盘 数值仿真 低循环疲劳试验 裂纹扩展 

分 类 号：V232[航空宇航科学与技术—航空宇航推进理论与工程]