邹煜申1,宣海军1,范梦龙1,郭小军2,单晓明2,洪伟荣1.某动力涡轮盘裂纹扩展寿命研究[J].航空发动机,2018,44(6):
某动力涡轮盘裂纹扩展寿命研究
Study on Crack Growth Life of a Power Turbine Disk
  
DOI:
中文关键词:  动力涡轮盘  裂纹扩展速率  仿真分析  低循环疲劳试验  涡轴发动机
英文关键词:power turbine disk  crack growth rate  simulation analysis  low cycle fatigue (LCF)test  turboshaft engine
基金项目:民机专项研究项目(MJ-2014-D-19)资助
作者单位E-mail
邹煜申1,宣海军1,范梦龙1,郭小军2,单晓明2,洪伟荣1 1. 浙江大学高速旋转机械实验室杭州3100272. 中国航发湖南动力机械研究所湖南株洲412002 chongyangcy_99@163.com 
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中文摘要:
      为研究某动力涡轮盘GH4169 合金的疲劳裂纹扩展特性,基于Paris 公式建立裂纹扩展模型,完成3 维裂纹扩展过程的 有限元仿真分析,确定试验方案;采用电火花加工工艺在轮盘不同考核部位预制模拟裂纹,以缩短裂纹萌生时间;在高速旋转试验 台上进行高温低循环疲劳裂纹扩展试验,试验过程中,在20500 r/min 上限转速下进行9000 次循环未发现裂纹,提速10%后进行 3000 次循环发现裂纹;又进行1700 次循环,轮盘破裂。试验结束后,利用扫描电镜对疲劳断口进行观察,获得断口宏观、微观特征。 将仿真结果与试验结果进行对比,表明仿真分析计算得到的裂纹扩展速率与试验结果有较好的符合性。
英文摘要:
      In order to study the fatigue crack growth characteristics of a power turbine disk GH4169 alloy,a crack growth model based on Paris formula was established,and the finite element analysis of the 3D crack growth process was completed. The test scheme was determined. In order to shorten the crack initiation time,simulation cracks were prefabricated at different parts of the wheel by EDM technology. High temperature and low cycle fatigue crack growth tests were carried out on a high speed rotating test rig. During the test,no cracks were found in 9000 cycles at the upper limit speed of 20500 r/min,and cracks were found in 3000 cycles after 10% increase in speed. Disk ruptured after another 1700 cycles. After the test,the fatigue fracture was observed by SEM,and the macroscopic and microscopic characteristics of the fracture were obtained. By comparing the simulation results with the test results,it is shown that the crack growth rate obtained by the simulation analysis is in good agreement with the test results.
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