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首页> 外文会议>ASME turbo expo >DERIVATION OF TEMPERATURE-ESTIMATION EQUATION BASED ON MICROSTRUCTURAL CHANGES IN COATINGS OF IN-SERVICE BLADES OF GAS TURBINES
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DERIVATION OF TEMPERATURE-ESTIMATION EQUATION BASED ON MICROSTRUCTURAL CHANGES IN COATINGS OF IN-SERVICE BLADES OF GAS TURBINES

机译：基于微结构变化的燃气轮机在用叶片涂层温度估算方程的推导

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摘要

A CoNiCr AlY-coated blade of an in-service gas turbine is analyzed, and a diffusion layer is formed along the boundary between the coating and the substrate due to the interdiffusion in the middle and tip of the blade. Such a layer is not observed in the vicinity of the blade root because of a comparatively low temperature during the operation. Coated specimens are prepared from the portions of the blade devoid of the diffusion layers, and the specimens are exposed to a high temperature in air. On the basis of the increase in the diffusion layer thickness, an equation for estimating the temperature of the blade is derived. Analysis of another in-service blade with a thermal barrier coating (TBC) is carried out. The aluminum-content decreases below the bond coat surface due to Al diffusion caused by the Al-oxide formation. This results in the formation of an Al-decreased layer (ADL) along the leading and trailing edges. The ADL is not observed at the center of the blade chord. The specimens are extracted from the portions of the blade that are devoid of ADL, and they are subjected to a high temperature in air. On the basis of the increase in the ADL thickness, a temperature-estimation equation is derived.
机译：分析了使用中的燃气轮机的涂有CoNiCr AlY涂层的叶片，由于叶片中部和尖端之间的相互扩散，沿涂层和基材之间的边界形成了扩散层。由于在操作期间温度较低，因此在叶片根部附近未观察到这样的层。从叶片的没有扩散层的部分制备涂覆的样品，并且将样品暴露于空气中的高温。基于扩散层厚度的增加，推导出用于估计叶片温度的方程式。对另一个带有隔热涂层（TBC）的在用刀片进行了分析。由于由铝氧化物形成引起的铝扩散，铝含量在粘结涂层表面以下降低。这导致沿前缘和后缘形成Al减少层（ADL）。在桨叶弦的中心未观察到ADL。从没有ADL的叶片部分中提取样品，然后在空气中对其进行高温处理。基于ADL厚度的增加，推导出温度估计方程。

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