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Failure analysis of a gas turbine compressor

机译：燃气轮机压缩机的故障分析

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摘要

During the shut down period, a 32 MW gas turbine experienced a severe failure accompanied by a loud noise near its second natural frequency at 4200 rpm. After opening the turbine casing, it was revealed that the disks of stages 16 and 17 of the compressor had been fractured and all of the stationary and rotary blades of stages 14-18 of the compressor had been detached from the dovetail region of the disks. The degree of damage was such that repairing the compressor was not economical, and thus, the compressor was no longer able to be used. Diagnostic work was carried out using different finite element models and frac-tography analysis. Analysis showed that multiple cracks had been initiated in the interface of the disks and shaft by the fretting fatigue mechanism and had been propagated by fatigue mechanism. Finally, unexpected and/or excessive forces or impact loads had led to the final brittle fracture of the disks. Some recommendations are proposed for preventing similar failures in the future.
机译：在停机期间，一台32 MW的燃气轮机发生了严重故障，并在4200 rpm的第二自然频率附近发出很大的噪音。在打开涡轮机壳体之后，揭示出压缩机的级16和17的盘已经断裂，并且压缩机的级14-18的所有固定叶片和旋转叶片已经从盘的燕尾区域分离。损坏程度使得维修压缩机不经济，因此不再能够使用压缩机。诊断工作是使用不同的有限元模型和分数维分析进行的。分析表明，微动疲劳机制在盘与轴的界面处引发了多个裂纹，并通过疲劳机制扩展了裂纹。最后，意想不到的和/或过大的力或冲击负载导致了磁盘的最终脆性断裂。提出了一些建议，以防止将来发生类似的故障。

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