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首页> 外文期刊>Journal of turbomachinery >Blade Tip Heat Transfer and Aerodynamics in a Large Scale Turbine Cascade With Moving Endwall
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Blade Tip Heat Transfer and Aerodynamics in a Large Scale Turbine Cascade With Moving Endwall

机译：带有活动端壁的大型涡轮机叶栅中的叶尖传热和空气动力学

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摘要

High resolution Nussell number distributions were measured on the blade lip surface of a large, 1.0 m chord, low-speed cascade representative of a high-pressure turbine. Data were obtained at a Reynolds number of 4.0 × 10~5 based on exit velocity and blade axial chord. Tip clearance levels ranged from 0.56% to 1.68% design span or equally from 1% to 3% of the blade chord. An infrared camera, looking through the hollow blade, made detailed temperature measurements on a constant heat flux lip surface. The relative motion between the endwall and the blade tip was simulated by a moving belt. The moving belt endwall significantly shifts the region of high Nusselt number distribution and reduces the overall averaged Nusselt number on the lip surface by up to 13.3%. The addition of a suction side squealer tip significantly reduced local lip heat transfer and resulted in a 32% reduction in averaged Nusselt number. Analysis of pressure measurements on the blade airfoil surface and lip surface along with panicle image velocimetry velocity flow fields in the gap gives an understanding of the heal transfer mechanism.
机译：在代表高压涡轮的大型1.0 m弦低速叶栅的叶片唇表面上测量了高分辨率Nussell数分布。基于出口速度和叶片轴向弦，在雷诺数为4.0×10〜5时获得数据。刀尖间隙水平的范围为设计弦的0.56％至1.68％，或相等于叶片弦的1％至3％。红外摄像机透过空心叶片观察，在恒定热通量唇缘表面上进行了详细的温度测量。端壁和叶片尖端之间的相对运动是通过移动皮带来模拟的。移动的皮带端壁会显着改变高Nusselt分布的区域，并使嘴唇表面的总体平均Nusselt数量减少多达13.3％。吸力侧置声器尖端的添加显着减少了局部唇部的热传递，并使平均努塞尔数降低了32％。对叶片翼型表面和唇表面的压力测量值以及间隙中的圆锥图像测速仪速度流场进行分析，可以了解愈合传递的机理。

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