高温度梯度轮盘低循环疲劳试验件设计方法  

Design Method for Low Cycle Fatigue Test Pieces of Large Temperature Gradient Turbine Disk

作　　者：高仁衡 曹廷云 沈莲 张根 林淑环 古远兴 GAO Ren-heng;CAO Ting-yun;SHEN Lian;ZHANG Gen;LIN Shu-huan;GU Yuan-xing(AECC Sichuan Gas Turbine Establishment,Chengdu 610500,China)

机构地区：[1]中国航发四川燃气涡轮研究院,成都610500

出　　处：《航空发动机》2021年第2期74-78,共5页Aeroengine

基　　金：航空动力基础研究项目资助。

摘　　要：针对航空发动机设计中高温度梯度轮盘低循环疲劳试验的需求,基于国内外航空发动机轮盘低循环疲劳试验件设计经验及国内现有轮盘试验器的试验条件,总结了该类高温度梯度航空发动机轮盘低循环疲劳寿命试验件设计的难点主要为轮盘热应力难在试验过程中模拟、轮盘寿命考核位置多、轮盘试验件试验转速高、轮盘试验件寿命限制位置容易转移等,并针对各难点给出了用离心载荷补偿热载荷、以损伤程度定考核位置、在不改变考核位置应力特征的前提下可以改变非考核位置局部结构特征等解决方案,形成了一套高温度梯度轮盘低循环疲劳寿命试验件设计方法。应用该方法设计了某航空发动机轮盘低循环疲劳寿命试验件并进行了试验,完成了寿命考核试验,结果表明:该方法是可行的。Aimed at the requirement of large temperature gradient LCF test of disk in aeroengine design,also based on the design experience of LCF test pieces and the existing test conditions at home and abroad,the design difficulties of the disk LCF test pieces was summarized which include the difficulty to simulate thermal stress,too many test positions,high test speed,the life limit displacement of test piece was easy to transfer,etc.In view of these difficulties,some solutions were given,such as compensating the thermal load with centrifugal load,determining the assessment position according to the damage degree,and changing the geometric structure of the non-assessment position without changing the stress characteristics of the assessment position.A design method for high temperature gradient LCF test pieces of disk was formed.By applying this method,one LCF life test pieces part of a disk was designed and the life test was completed,the results show that the method is feasible.

关 键 词：低循环疲劳试验 多考核位置 高温度梯度 设计方法 试验件设计 

分 类 号：V216.3[航空宇航科学与技术—航空宇航推进理论与工程]