燕尾榫连接结构微动疲劳全寿命预测方法

doi:10.13700/j.bh.1001-5965.2019.0471

北京航空航天大学学报 ›› 2020, Vol. 46 ›› Issue (10): 1890-1898.doi: 10.13700/j.bh.1001-5965.2019.0471

燕尾榫连接结构微动疲劳全寿命预测方法

徐可宁¹, 李雯¹, 黄勇², 余庆陶³, 马国佳³, 胡文颖¹

1. 中国航空发动机研究院, 北京 101304;
2. 北京航空航天大学航空科学与工程学院, 北京 100083;
3. 中国航空制造技术研究院, 北京 100024

收稿日期:2019-09-02 发布日期:2020-10-29
通讯作者: 李雯 E-mail:mosquato@buaa.edu.cn
作者简介:徐可宁女,博士,高级工程师。主要研究方向:航空发动机结构强度振动可靠性;李雯女,博士,研究员。主要研究方向:机械传动与摩擦学、微动损伤多尺度建模与仿真技术。
基金资助:
国家自然科学基金（51705490，5187600）；装备预研重点实验室基金（614290802081706）

A fretting fatigue total life prediction method for dovetail attachment

XU Kening¹, LI Wen¹, HUANG Yong², YU Qingtao³, MA Guojia³, HU Wenying¹

1. Aero Engine Academy of China, Beijing 101304, China;
2. School of Aeronautic Science and Engineering, Beihang University, Beijing 100083, China;
3. AVIC Manufacturing Technology Institute, Beijing 100024, China

Received:2019-09-02 Published:2020-10-29
Supported by:
National Natural Science Foundation of China (51705490,5187600); Pre-research Key Laboratory Fund for Equipment (614290802081706)

摘要/Abstract

摘要： 微动损伤使航空发动机榫连接结构疲劳寿命显著降低。以钛合金Ti-6Al-4V燕尾榫连接结构为例，提出一种适用于复杂结构微动疲劳全寿命预测方法。基于修正的Manson-McKnight方法和多轴疲劳理论，疲劳损伤参数由等效应力参数（ESP）表征，微动疲劳裂纹萌生位置和成核寿命通过有限元分析（FEA）和ESP预测。基于断裂力学理论和最大周向应力准则，提出微动疲劳裂纹扩展数值模拟方法，建立微动疲劳扩展寿命与裂纹长度函数关系，依据裂纹终值长度预测微动疲劳扩展寿命。结果显示：钛合金Ti-6Al-4V燕尾榫连接结构微动疲劳裂纹扩展角预测值与实验值均为18°，裂纹生长方向预测值与实验值相符；微动疲劳全寿命（成核寿命+扩展寿命）预测值在实验值的2倍分散带内；最大拉伸载荷对榫连接结构的微动疲劳全寿命影响显著，在相同应力比下，最大拉伸载荷从18 kN变化到24 kN，钛合金Ti-6Al-4V燕尾榫连接结构微动疲劳全寿命降低1个数量级。

关键词: 航空发动机, 燕尾榫连接结构, 微动损伤, 微动疲劳, 寿命预测

Abstract: Fatigue life of aero-engine dovetail attachment can be significantly reduced by fretting damage. Taking Ti-6Al-4V alloy aero-engine blade dovetail attachment as an example, a fretting fatigue total life prediction method for complex structure is proposed. A fatigue damage parameter was defined as an Equivalent Stress Parameter (ESP) based on modified Manson-McKnight method and multiaxial fatigue theory. Crack initiation position and nucleation life were evaluated by ESP and multiaxial stresses obtained from Finite Element Analysis (FEA). A numerical simulation method of fretting fatigue crack growth is proposed based on linear elastic fracture mechanics and maximum hoop stress criterion. From the simulated crack growth results, the function relationship between fretting fatigue propagation life and crack length was established, and the fretting fatigue propagation life was determined by the crack length at failure. The results show that the crack growth trajectory predicted by the simulation correlates well with that in a tested Ti-6Al-4V dovetail component-both have a crack kink angle of 18°. The estimated fretting fatigue total life (nucleation + propagation) of a dovetail under different fretting conditions by using the proposed numerical method matches well with test results, as the predicted total life is within 2 times of error range. Maximum tensile load has significant influence on crack nucleation and propagation life, and under the same stress ratio, the fretting fatigue total life of the Ti-6Al-4V dovetail attachment reduces one order of magnitude as the maximum tensile load increases from 18 kN to 24 kN.

Key words: aero-engine, dovetail attachment, fretting damage, fretting fatigue, life prediction

中图分类号:

V231.91

徐可宁, 李雯, 黄勇, 余庆陶, 马国佳, 胡文颖. 燕尾榫连接结构微动疲劳全寿命预测方法[J]. 北京航空航天大学学报, 2020, 46(10): 1890-1898.

XU Kening, LI Wen, HUANG Yong, YU Qingtao, MA Guojia, HU Wenying. A fretting fatigue total life prediction method for dovetail attachment[J]. Journal of Beijing University of Aeronautics and Astronautics, 2020, 46(10): 1890-1898.

参考文献

[1] WATERHOUSE R B.Fretting fatigue[M].London:Applied Science Publishers Ltd.,1981.
[2] NOWELL D,DINI D,HILLS D A.Recent developments in the understanding of fretting fatigue[J].Engineering Fracture Mechanics,2006,73(2):207-222.
[3] 俞树荣,王洁璐,李淑欣,等.Ti-6Al-4V燕尾榫结构微动疲劳裂纹萌生及扩展行为研究[J].中国机械工程,2015,26(24):3386-3390.YU S R,WANG J L,LI S X,et al.Study on the initiation and propagation of fretting fatigue crack on the Ti-6Al-4V alloy dovetail joint[J].China Mechanical Engineering,2015,26(24):3386-3390(in Chinese).
[4] GOLDEN P J,NICHOLAS T.The effect of angle on dovetail fretting experiments in Ti-6Al-4V[J].Fatigue & Fracture of Engineering Materials & Structures,2005,28(12):1169-1175.
[5] GOLDEN P J.Development of a dovetail fretting fatigue fixture for turbine engine materials[J].International Journal of Fatigue,2009,31(4):620-628.
[6] GOLDEN P J,CALCATERRA J R.A fracture mechanics life prediction methodology applied to dovetail fretting[J].Tribology International,2006,39(10):1172-1180.
[7] SHI L,WEI D S,WANG Y R,et al.An investigation of fretting fatigue in a circular arc dovetail assembly[J].International Journal of Fatigue,2016,82(2):226-237.
[8] MANGARDICH D,ABRARI F,FAWAZ Z.A fracture mechanics based approach for the fretting fatigue of aircraft engine fan dovetail attachments[J].International Journal of Fatigue,2019,129(12):105213.
[9] WEI D S,WANG Y R.Analysis of fretting fatigue life of dovetail assemblies based on fracture mechanics method[J].Engineering Failure Analysis,2012,25:144-155.
[10] WEI D S,SHI L,WANG Y R.Cyclic plastic behavior of dovetail under fretting load[J].Engineering Failure Analysis,2015,55:100-114.
[11] 石炜,温卫东,崔海涛.榫连接结构微动疲劳寿命研究[J].航空动力学报,2014,29(1):104-110.SHI W,WEN W D,CUI H T.Research on fretting fatigue life of dovetail joints[J].Journal of Aerospace Power,2014,29(1):104-110(in Chinese).
[12] HU C,WEI D S,WANG Y R,et al Experimental and numerical study of fretting fatigue in dovetail assembly using a total life prediction model[J].Engineering Fracture Mechanics,2019,205:301-318.
[13] GALLAGHER J P,VAN STONE R H,DELANEUVILLE R E.Improved high-cycle fatigue (HCF) life prediction:AFRL-ML-WP-TR-2001-4159[R].Dayton:Universal Technology Corporation,2001.
[14] GALLAGHER J P,NICHOLAS T,GUNDERSON A,et al.Advanced high cycle fatigue (HCF) life assurance:AFRL-ML-WP-TR-2005-4102[R].Dayton:Universal Technology Corporation,2004.
[15] GARCIA D B,GRANDT A F.Application of a total life prediction model for fretting fatigue in Ti-6Al-4V[J].International Journal of Fatigue,2007,29(7):1311-1318.
[16] GOLDEN P J,GRANDT A F.Fracture mechanics based fretting fatigue life predictions in Ti-6Al-4V[J].Engineering Fracture Mechanics,2004,71(15):2229-2243.
[17] MURTHY H,RAJEEV P T,FARRIS T N,et al.Fretting fatigue of Ti-6Al-4V subjected to blade/disk contact loading[C]//50th Anniversary of Japan Society of Materials Science,2001:41-48.
[18] 王建明,刘伟,吕鹤婷.复合型裂纹的扩展路径模拟及疲劳寿命预测[J].哈尔滨工程大学学报,2015,36(8):1086-1091.WANG J M,LIU W,LV H T.Numerical simulation of crack propagation path and fatigue life prediction for mixed mode cracks[J].Journal of Harbin Engineering University,2015,36(8):1086-1091(in Chinese).
[19] 魏大盛,王延荣.榫连结构的高应力梯度及破坏分析[J].北京航空航天大学学报,2010,36(10):1184-1188.WEI D S,WANG Y R.On the high stress gradient and failure analysis of dovetail attachments[J].Journal of Beijing University of Aeronautics and Astronautics,2010,36(10):1184-1188(in Chinese).
[20] GARCIA D B,GRANDT A F.Fractographic characteristics associated with fretting fatigue cracks in turbomachinery alloys:AIAA-2003-1682[R].Reston:AIAA,2003.

燕尾榫连接结构微动疲劳全寿命预测方法

A fretting fatigue total life prediction method for dovetail attachment

RichHTML

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 15

编辑推荐

Metrics

本文评价

[1]	王超, 张帅, 李亚东, 贾林. 基于静电互相关灵敏度加权的气路碎片监测[J]. 北京航空航天大学学报, 2020, 46(3): 457-464.
[2]	孙浩, 郭迎清, 赵万里. 航空发动机传感器与执行机构信息重构算法[J]. 北京航空航天大学学报, 2020, 46(2): 331-339.
[3]	叶宇隆, 金捷, 刘睿, 高翔, 王方. 直连式甩油盘非均匀流动特性[J]. 北京航空航天大学学报, 2019, 45(8): 1560-1568.
[4]	吴诗彤, 闫勇, 钱相臣. 静电传感器测量固体颗粒质量流量实验研究[J]. 北京航空航天大学学报, 2019, 45(8): 1575-1581.
[5]	王岩, 王晓晴, 郭生荣, 卢岳良, 刘胜. 航空柱塞泵缸体疲劳分析及寿命预测方法[J]. 北京航空航天大学学报, 2019, 45(7): 1314-1321.
[6]	谭治学, 钟诗胜, 林琳. 多源数据融合的民航发动机修后性能预测[J]. 北京航空航天大学学报, 2019, 45(6): 1106-1113.
[7]	单睿斌, 李秋红, 何凤林, 冯海龙, 管庭筠. 基于ADMM算法的航空发动机模型预测控制[J]. 北京航空航天大学学报, 2019, 45(6): 1240-1247.
[8]	樊嘉杰, 李磊, 钱诚, 胡爱华, 樊学军, 张国旗. 循环电载荷下大功率LED金引线疲劳断裂寿命预测[J]. 北京航空航天大学学报, 2019, 45(3): 478-485.
[9]	李超, 金福艺, 张卫浩. 航空发动机转子结构布局优化设计方法[J]. 北京航空航天大学学报, 2019, 45(2): 266-276.
[10]	张振良, 刘君强, 黄亮, 张曦. 基于半监督迁移学习的轴承故障诊断方法[J]. 北京航空航天大学学报, 2019, 45(11): 2291-2300.
[11]	潘慕绚, 曹良进, 黄金泉. 基于增益调度的航空发动机分散鲁棒控制[J]. 北京航空航天大学学报, 2018, 44(9): 1964-1973.
[12]	金海, 刘继兴, 张大义, 洪杰. 连接界面变形对转子动力特性影响的力学模型[J]. 北京航空航天大学学报, 2018, 44(6): 1294-1302.
[13]	车畅畅, 王华伟, 倪晓梅, 洪骥宇. 基于深度学习的航空发动机故障融合诊断[J]. 北京航空航天大学学报, 2018, 44(3): 621-628.
[14]	何大伟, 彭靖波, 胡金海, 宋志平. 改进BA优化的MKSVDD航空发动机工作状态识别[J]. 北京航空航天大学学报, 2018, 44(10): 2238-2246.
[15]	张建, 李艳军, 曹愈远, 张丽娜. 免疫支持向量机用于航空发动机磨损故障诊断[J]. 北京航空航天大学学报, 2017, 43(7): 1419-1425.