涡轮盘疲劳寿命评估流程及应用  

Fatigue life evaluation procedure and its application for turbine disk

作　　者：李宏新[1,2,3] 王延荣 石亮[1,2] 钟波 魏大盛[1,2] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191 [2]先进航空发动机协同创新中心,北京100191 [3]中国航空发动机集团有限公司沈阳发动机研究所,沈阳110015

出　　处：《航空动力学报》2017年第10期2419-2426,共8页Journal of Aerospace Power

基　　金：国家自然科学基金(51475022;50571004)

摘　　要：建立了较完整的涡轮盘疲劳寿命评估流程,并以一个涡轮转子模型的分析实例给出了寿命评估流程的实施过程,同时探索了涡轮盘考核部位模拟试验件设计的方法。结果表明:所建立的涡轮盘寿命评估流程具有较强的工程实用性,所发展的寿命方程参数确定方法可有效利用现有材料手册中各种材料基础试验数据并能获得一组物理意义明确的参数,此寿命方程预测的寿命精度在2倍分散带之内;通过涡轮盘计算分析发现应力梯度是影响涡轮盘中心孔、螺栓孔边以及过渡圆角等部位寿命的关键因素,需在设计过程中重点关注;通过带缺口的平板模型算例模拟了涡轮盘危险部位的应力梯度特征,实现试验件缺口部位的应力梯度与涡轮盘考核部位的相对梯度特征接近,并提供了缺口模拟试验件设计方法,为使用简单缺口试验件评估涡轮盘考核点的寿命提供了技术途径。A fatigue life evaluation procedure of a turbine disk was established,and illustrated with a turbine rotor model,meanwhile a simulating test design method of turbine disk assessment sites was explored.The results show that the established life evaluation procedure has good engineering practicability.The developed method of determining the equation parameters could take advantage of the material experimental data effectively,and a group of parameters could be obtained by this method.Precision of the prediction life by using the method lied in two times scatter band.The stress gradient was the key influential factor to the fatigue life near the bore,bolt hole and transitional fillet of the turbine disk,for which enough attention should be paid in the design stage.Stress gradient features of thecritical positions in the turbine disk were simulated using aplate model with notches,and the simulation results agreed well with the test results.A modeling test design method was provided for life evaluation of the turbine disk test pieces with notches.

关 键 词：涡轮盘 疲劳寿命 应力梯度 缺口设计 工程应用 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]