航空科学技术2024，Vol.35Issue(9)：63-69,7.DOI:10.19452/j.issn1007-5453.2024.09.007
高压涡轮盘螺栓孔疲劳模拟件设计及试验
Design and Experimental of Fatigue Simulating Specimen for Bolt Holes of High Pressure Turbine Disc
郑小梅 1范雨晴 2杨旭峰 2程昊 2余嘉伟 2汪全中 2杨兴宇 1范天宇1
作者信息
- 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
- 折叠
摘要
Abstract
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.关键词
高压涡轮盘/低循环疲劳/模拟件/试验/安全寿命Key words
high pressure turbo disc/low cycle fatigue/simulating specimen/experiment/safe life分类
航空航天引用本文复制引用
郑小梅,范雨晴,杨旭峰,程昊,余嘉伟,汪全中,杨兴宇,范天宇..高压涡轮盘螺栓孔疲劳模拟件设计及试验[J].航空科学技术,2024,35(9):63-69,7.
