Investigations on fretting fatigue in aircraft engine compressor blade

被引：48

作者：

Lee, Bok-Won ^{[3
]}

Suh, Jungjun ^{[3
]}

Lee, Hongchul ^{[3
]}

Kim, Tae-gu ^{[1
,2
]}

机构：

[1] INJE Univ, Dept Safety Engn, Gimhae 621749, Gyeongnam, South Korea

[2] INJE Univ, AEI, Gimhae 621749, Gyeongnam, South Korea

[3] ROKAF, ATRI, Failure Anal Div, Daegu Si 701799, South Korea

来源：

ENGINEERING FAILURE ANALYSIS | 2011年 / 18卷 / 07期

关键词：

Blade tang; Engine compressor; Fretting fatigue; Fractography; Finite element method; TI-6AL-4V;

D O I：

10.1016/j.engfailanal.2011.07.021

中图分类号：

TH [机械、仪表工业];

学科分类号：

0802 ;

摘要：

An investigation of several cracked blade tangs in the military aircraft engine compre was conducted to identify the root cause of the failure. These cracks were found during scheduled maintenance with fluorescent penetration inspection. The engine compre blade made of Ti-6Al-4V is attached to compressor rotor by means of inserting retai pin through rotor and blade tang. By analyzing the fracture surface of the failed blade t it is found that the crack in the blade tang was initiated by fretting fatigue and propag under low cycle fatigue. Stress analysis of the blade using a non-linear finite eler method is coincident with the results of fractography. The clearance between retai pin and tang hole caused small amplitude of sliding motion leading to fretting wear du engine operation. Consequently, the damaged area due to fretting wear acts as a stress ser inside tang hole and contributes to accelerate fretting fatigue. (C) 2011 Elsevier Ltd. All rights reser

引用

页码：1900 / 1908

页数：9

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