Failure Analysis of High-Pressure Compressor Blade in an Aero Gas Turbine Engine

被引：12

作者：

Mishra R.K. ^{[1
]}

Nandi V. ^{[2
]}

Raghavendra Bhat R. ^{[2
]}

机构：

[1] Centre for Military Airworthiness and Certification, Bangalore

[2] Central Material Processing Laboratory, Hindustan Aeronautics Limited, Bangalore

来源：

Journal of Failure Analysis and Prevention | 2018年 / 18卷 / 03期

关键词：

Fatigue; HP compressor; Platform ladder; Rotor blade; SEM;

D O I：

10.1007/s11668-018-0425-5

中图分类号：

学科分类号：

摘要：

Failure of high-pressure compressor rotor blade in an aero gas turbine engine is analyzed to determine its root cause. Forensic and metallurgical investigations are carried out on the blade and failed parts. The failure of the platform ladder is found to the first in the chain of events that led to the compressor blade failure. The mode of failure in the blade is found to be fatigue and has originated from the damaged region on the leading edge caused by dislodgement of platform ladder. The failure has caused extensive damages in high-pressure compressor module and also in downstream turbine blades as a secondary effect. © 2018, ASM International.

引用

页码：465 / 470

页数：5

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