榫连接结构微动疲劳模拟件设计及试验
Design and experiment of simulated specimen for fretting fatigue of turbine attachment
鄢林 1胡殿印 2田腾跃 1毛建兴 2王荣桥3
作者信息
- 1. 北京航空航天大学能源与动力工程学院,北京 100191
- 2. 北京航空航天大学航空发动机研究院,北京 100191;中小型航空发动机联合研究中心,北京 100191;北京航空航天大学航空发动机结构强度北京市重点实验室,北京 100191
- 3. 北京航空航天大学能源与动力工程学院,北京 100191;中小型航空发动机联合研究中心,北京 100191;北京航空航天大学航空发动机结构强度北京市重点实验室,北京 100191
- 折叠
摘要
提出了基于损伤控制参量一致的榫连接结构微动疲劳模拟件设计方法.在几何相似的基础上,保证最大相对滑移距离与临界距离内等效应力分布的一致性,确定模拟件的二维结构尺寸;在此基础上,以临界裂纹长度内应力强度因子一致为目标,优化分析确定模拟件的三维结构尺寸;开展了某型发动机涡轮榫连接结构模拟件的微动疲劳试验,试验观测到裂纹萌生于接触面边缘,裂纹初期扩展方向垂直于接触面,断裂时的裂纹长度与仿真结果相比误差小于5％,由此验证模拟件设计方法的合理性.
Abstract
A method was proposed to design the simulated specimen for fretting fatigue of turbine attachment based on the consistency of damage control parameters.Afterwards,a simulated specimen for the turbine attachment of a certain aero-engine was designed.Firstly,based on geometric similarity,two-dimensional structural dimension of the simulated specimen was determined by ensuring the consistency of the maximum relative slip distance and the equivalent stress distribution within the critical distance;and then,three-dimensional structural dimension of the simulated specimen was determined by optimization analysis with the objective of consistency of the stress intensity factor within the critical crack length.Finally,fretting fatigue test of the simulated specimen was performed.It was found that the crack was initiated at the edge of the contact surface,the direction of the crack growth was perpendicular to the contact surface and the crack length at fracture was within 5％in error with the simulation,thus verifying the rationality of the design method of the simulated specimen.
关键词
榫连接结构/模拟件/微动疲劳/裂纹萌生/裂纹扩展Key words
turbine attachment/simulated specimen/fretting fatigue/crack initiation/crack growth引用本文复制引用
基金项目
国家自然科学基金(52022007)
国家科技重大专项(2017-Ⅳ-0004-0041)
国家科技重大专项(J2019-Ⅳ-0009-0077)
国家科技重大专项(J2019-Ⅳ0016-0084)
出版年
2024
NETL
NSTL
万方数据