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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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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：最后阶段的涡轮刀片失效以660兆瓦的两个单位经历。这些单元具有一个高压涡轮机和两个串联化合物低压涡轮机，具有44英寸的最后阶段叶片。失效的叶片在连接到高压（LP）涡轮机（LP1）和连接到发电机（LP2）的LP涡轮机中的低压（LP）涡轮机中。失败的刀片在其根部的裂缝引发在后缘，陡峭最外面的圆角半径的凹面。裂缝的实验室评估表明失效机制是高循环疲劳（HCF）。进行了最后阶段的刀片故障评估。调查包括裂纹叶片的金相分析，自然频率试验和分析，叶片应力分析，单位的操作参数和事件分析历史，裂缝力学和裂纹传播分析。本文概述了这种故障调查，导致叶片造成叶片扭转近120Hz的扭转振动，以及低负荷低载荷的操作周期作为对观察到的故障的主要贡献。

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