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Turbine blade crack detection using vibration testing methods

机译:使用振动测试方法检测涡轮叶片裂纹

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摘要

Turbine blades are the most common cause of failures in gas turbines. Failure modes are typically cracking from foreign object damage (FOD), high cycle stress (HCF), blade rubbing, degradation from erosion and corrosion. Fault detection of blades is important function in reducing blade related failures. This study involved the use of vibration analysis and dynamic testing of blades for failure detection. Current field inspections of blades are based on visual inspections only, and the intent here was to use impact testing of the blades during these inspections to determine cracked blade (from the vibration response). Vibration impact tests were undertaken using decommissioned turbine blades with and without cracks in the laboratory. Four common crack patterns were deliberately induced to the turbine blades to investigate changes in the blades normal mode response. Finite element analysis (FEA) of the blades was also undertaken. FEA results were correlated to experimental results and these results showed that each crack pattern was unique and significant changes were found in higher modes. Dynamic vibration analysis was also undertaken in a laboratory testrig fitted with rotating model straight blades. Vibration measurements were undertaken on a baseline test case and other test conditions where the blades had induced cracks. Steady state and transient vibration responses were obtained from the controlled tests. Vibration measurements were on the machine casing and on a blade (with an accelerometer surfaced mounted onto a rotating blade). Order tracking analysis and continuous wavelet analysis were performed to the measured data. Both techniques showed ability in detecting changes in vibration response on the blades and casing for blades with cracks. Results showed that significant changes were detected during transient analysis as compared to the steady state. Changes were noted in the vibration response corresponding to the machine running speed and blade passing frequencies. Changes in wavelet maps were however qualitative in nature, which suggested that more work need to be undertaken for cracks severity assessment using wavelet maps.
机译:涡轮叶片是燃气涡轮机故障的最常见原因。失效模式通常是由于异物损坏(FOD),高循环应力(HCF),刀片摩擦,腐蚀和腐蚀引起的退化而导致的。刀片的故障检测是减少刀片相关故障的重要功能。这项研究涉及使用振动分析和叶片动态测试进行故障检测。当前叶片的现场检查仅基于目视检查,此处的目的是在检查期间使用叶片的冲击测试来确定破裂的叶片(根据振动响应)。在实验室中,使用退役的涡轮叶片进行了振动冲击测试,无论有无裂纹。故意将四个常见的裂纹模式引入涡轮叶片,以研究叶片正常模式响应的变化。还对叶片进行了有限元分析(FEA)。 FEA结果与实验结果相关,这些结果表明,每个裂纹模式都是唯一的,并且在较高模式下发现了显着变化。在装有旋转模型直叶片的实验室测试台中也进行了动态振动分析。振动测量是在基准测试用例和叶片引起裂纹的其他测试条件下进行的。从控制测试中获得稳态和瞬态振动响应。振动测量在机器机壳和叶片上进行(加速度计表面安装在旋转叶片上)。对测量数据进行了订单跟踪分析和连续小波分析。两种技术都显示出能够检测出带有裂纹的叶片在叶片和壳体上的振动响应变化的能力。结果表明,与稳态相比,在瞬态分析过程中检测到了显着变化。记录了与机器运行速度和刀片通过频率相对应的振动响应的变化。然而,小波图的变化本质上是定性的,这表明使用小波图评估裂缝的严重性还需要做更多的工作。

著录项

  • 作者

    Guai Yeu Kae;

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  • 年度 2009
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  • 原文格式 PDF
  • 正文语种 {"code":"en","name":"English","id":9}
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