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首页> 外文会议>ASME(American Society of Mechanical Engineers) Power Conference; 20070717-19; San Antonio,TX(US) >LAST-STAGE BLADE FAILURE EVALUATION
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LAST-STAGE BLADE FAILURE EVALUATION

机译：最后阶段刀片故障评估

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摘要

A last stage turbine blades failure was experienced in two units of 660 MW. These units have one high-pressure turbine and two tandem-compound low-pressure turbines with 44-inch last-stage blades. The blades that failed were in a low pressure (LP) turbine connected to the high pressure (HP) turbine (LP1) and in LP turbine connected to the generator (LP2). The failed blades had cracks in their roots initiating at the trailing edge, concave side of the steeple outermost fillet radius. Laboratory evaluation of the cracking indicates the failure mechanism to be high cycle fatigue (HCF). The last-stage blades failure evaluation was carried out. The investigation included a metallographic analysis of the cracked blades, natural frequency test and analysis, blade stress analysis, unit's operation parameters and history of events analysis, fracture mechanics and crack propagation analysis. This paper provides an overview of this failure investigation, which led to the identification of the blades torsional vibrations near 120 Hz and some operation periods with low load low vacuum as the primary contribution to the observed failure.
机译：在两个660 MW的机组中，最后一级的涡轮叶片发生故障。这些装置具有一台高压涡轮和两台串联式低压复合涡轮，带有44英寸末级叶片。发生故障的叶片位于连接到高压（HP）涡轮（LP1）的低压（LP）涡轮和连接到发电机（LP2）的LP涡轮中。失效叶片的根部有裂纹，始于尖顶最外圆角半径的后缘，即凹面。实验室对开裂的评估表明，失效机理为高循环疲劳（HCF）。最后阶段进行了叶片故障评估。调查包括裂纹叶片的金相分析，固有频率测试和分析，叶片应力分析，机组的运行参数和事件历史分析，断裂力学和裂纹扩展分析。本文概述了这种故障研究，从而确定了120 Hz附近的叶片扭转振动以及一些低负荷，低真空的运行周期，这是导致观察到故障的主要原因。

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