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作 者:郑小梅[1] 范雨晴 杨旭峰 程昊 余嘉伟 汪全中 杨兴宇[1] 范天宇[1] Zheng Xiaomei;Fan Yuqing;Yang Xufeng;Cheng Hao;Yu Jiawei;Wang Quanzhong;Yang Xingyu;Fan Tianyu(Beijing Aeronautical Engineering Technical Research Center,Beijing 100076,China;AECC Hunan Aviation Powerplant Research Institute,Zhuzhou 412000,China)
机构地区:[1]北京航空工程技术研究中心,北京100076 [2]中国航发湖南动力机械研究所,湖南株洲412000
出 处:《航空科学技术》2024年第9期63-69,共7页Aeronautical Science & Technology
摘 要:航空发动机关键件采用模拟件开展试验可在一定程度上替代真实结构试验,从而大幅节省试验周期和成本。为满足某型发动机高压涡轮盘定寿需求,减少真实轮盘低循环疲劳的试验成本,本文采用考虑应力梯度影响的结构特征模拟件设计方法,设计了该发动机高压涡轮盘螺栓孔部位的结构特征模拟件,开展了特征模拟件及轮盘真实结构的低循环疲劳试验;对于模拟件试验结果,应用统计学方法得到了具有一定置信度和可靠度的模拟件寿命和分散度,采用该分散度计算得到的模拟件安全循环寿命和轮盘实际试验结果相比,模拟件安全循环寿命小于轮盘实际低循环疲劳寿命,误差为14.69%,该螺栓孔模拟件设计及低循环疲劳试验研究可用于指导实际轮盘的定寿工作,具有一定的工程参考价值。The use of simulating specimen for testing key components of aero-engines can replace real structural testing to some extent,thereby significantly saving testing cycles and costs.In order to meet the service life requirements of a turbofan engine's high pressure turbo disc and reduce the cost of the disc's low cycle fatigue experiments,this paper develops a simulating specimen design method which can consider the influence on stress gradient.With this method,the simulating specimen of the bolt hole is designed,and the low cycle fatigue tests of the simulating specimens and the real discs are also carried out;For the simulating specimens,the life and dispersity with certain confidence and reliability are obtained by using statistical methods.Compared with low-cycle fadigue life results of the disc,the safe life of the simulating specimen,which is calculated by using this dispersity,is less than the disc's with an error of 14.69%;The research on the design method of the bolt hole and the low cycle fatigue tests,which have engineering reference value,can be used to guide the life determination of actual wheel discs.
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]
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