航空发动机轮盘中心孔模拟试验件设计方法及试验验证  

Design method and test verification of simulated specimen of aeroengine disc center hole

作　　者：魏大盛[1,2] 冯俊淇 马梦弟 姚利信 王延荣 WEI Dasheng;FENG Junqi;MA Mengdi;YAO Lixin;WANG Yanrong(School of Energy and Power Engineering,Beihang University,Beijing 100191,China;Jiangxi Research Institute,Beihang University,Nanchang 330096,China)

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]北京航空航天大学江西研究院,南昌330096

出　　处：《航空动力学报》2022年第10期2157-2166,共10页Journal of Aerospace Power

基　　金：国家科技重大专项(J2019-Ⅳ-0012-0080)。

摘　　要：依据涡轮盘有限元计算结果,确定盘心考核位置处的应力状态,并将周向应力和轴向应力比值以及轮盘中心孔处周向应力沿径向的应力梯度作为设计指标,保证模拟件应力状态与实际轮盘一致。针对轮盘中心孔考核位置,本文共设计两类模拟件:一是反映双轴应力状态的多轴模拟件,二是反映应力梯度的平板缺口模拟件。分别采用两种试验件,结合轮盘实际载荷条件开展低循环疲劳试验,并对试验结果进行统计分析。进而,采用多轴疲劳寿命预测模型及考虑应力梯度影响的寿命预测模型对两种试验件的疲劳寿命进行评估,双轴模拟件的预测结果均在2倍分散带内,平板缺口模拟件的预测结果均在3倍分散带内,此寿命预测结果对实际轮盘设计具有参考价值。According to the finite element simulation results of the turbine disc,the stress state at the inspection position of the disk center was determined,and the ratio of the circumferential stress and axial stress and the radial stress gradient of the circumferential stress at the disc center hole were taken as the design indexes to ensure the consistency of stress state of the simulated specimen with the actual disc.Two kinds of simulators,namely,the multi axial simulators reflecting the biaxial stress state,and the plate notch simulators reflecting the stress gradient,were designed for the inspection position of the center hole of the wheel disc.Low cycle fatigue tests were carried out by using these two kinds of specimens under actual load conditions of the disc,and the test results were statistically analyzed.Furthermore,the multi-axial fatigue life prediction model and the life model considering the influence of stress gradient were used to evaluate the fatigue life of these two simulated specimens.The scatter bands of the prediction results of biaxial simulated specimen were within 2 and those of the flat notch simulated specimen were within 3.The results could provide engineering reference for the life evaluation of aeroengine structures.

关 键 词：涡轮盘 模拟试验件 结构强度 多轴疲劳 应力梯度 

分 类 号：V231.95[航空宇航科学与技术—航空宇航推进理论与工程]