Fracture of a Compressor Stator Blade in a Gas Turbine Engine

被引：0
|
作者：
Neidel, A. [1 ]
Matijasevic-Lux, B. [1 ]
机构：
[1] Siemens AG, Energy Sect, Gasturbinenwerk Berlin, Werkslab, D-10548 Berlin, Germany
来源：
PRAKTISCHE METALLOGRAPHIE-PRACTICAL METALLOGRAPHY | 2013年 / 50卷 / 01期
关键词：
D O I：
10.3139/147.110196
中图分类号：
TF [冶金工业];
学科分类号：
0806 ;
摘要：
On the occasion of the revision of a gas turbine power plant in Northern Germany, a surface crack was detected in one of the 44 stage 0 compressor stator blades during a routine non-destructive testing of the blades. By then the engine had completed more than 38,000 h of operation. The damaged blade was precision drop-forged and copy-milled of X20Cr13 and for some time was wearing a subsequently applied corrosion protection coating containing aluminium pigments. The blade's condition before the subsequent coating was applied is unknown. The metallurgical investigation found that the cause of failure was corrosion fatigue.
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页码：43 / 49
页数：7
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