MAXIMUM BLADE SURFACE TEMPERATURE ESTIMATION FOR ADVANCED STATIONARY GAS TURBINES IN NEAR-INFRARED (WITH REFLECTION)
    21.
    发明申请
    MAXIMUM BLADE SURFACE TEMPERATURE ESTIMATION FOR ADVANCED STATIONARY GAS TURBINES IN NEAR-INFRARED (WITH REFLECTION) 审中-公开
    近红外(带反射)先进静止气轮机叶片表面温度最大值估算

    公开(公告)号:WO2008051441A3

    公开(公告)日:2008-07-03

    申请号:PCT/US2007022243

    申请日:2007-10-18

    Abstract: Methods for maximum scene surface temperature estimation for blades with reflective surface properties in advanced stationary gas turbines are disclosed. The approach utilizes high speed infrared imagery provided by an online monitor system using a focal plan array (FPA) for near-infrared monitoring during engine runtime up to base load. The one waveband method for temperature estimation is assumed as starting point. A lower surface emissivity and higher surface reflectance of thermal barrier coating (TBC) in near-infrared can cause systematic estimation errors. Methods using the one wave band method, with the purpose to reduce estimation errors for maximum temperatures are also disclosed. Theoretical results, data from numerical simulations, and real data from engine test are provided. A system for performing temperature estimation methods is also disclosed.

    Abstract translation: 公开了用于在先进固定燃气轮机中对具有反射表面特性的叶片进行最大景物表面温度估计的方法。 该方法利用由在线监测系统提供的高速红外图像,该系统使用焦平面阵列(FPA)在发动机运行期间的近红外监测直至基本负载。 温度估算的一种波段方法被认为是起点。 近红外热障涂层(TBC)的较低表面发射率和较高表面反射率可能导致系统估计误差。 还公开了使用单波段方法的方法,其目的是减少最大温度下的估计误差。 提供了理论结果,数值模拟的数据和发动机测试的实际数据。 还公开了一种用于执行温度估计方法的系统。

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