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首页> 外文会议>ASME(American Society of Mechanical Engineers) Turbo Expo vol.3 pt.A; 20050606-09; Reno-Tahoe,NV(US) >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：移动端壁的大型涡轮叶栅中的叶尖传热和空气动力学

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摘要

High resolution Nusselt number (Nu) distributions were measured on the blade tip surface of a large, 1.0 meter-chord, low-speed cascade representative of a high-pressure turbine. Data was obtained at a Reynolds number of 4.0 x 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 blade chord. An infrared camera, looking through the hollow blade, made detailed temperature measurements on a constant heat flux tip surface. The relative motion between the endwall and the blade tip was simulated by a moving belt. The moving belt endwall significantly to shifts the region of high Nusselt number distribution and reduces the overall averaged Nusselt number on the tip surface by up to 13.3%. The addition of a suction side squealer tip significantly reduced local tip heat transfer and resulted in a 32% reduction in averaged Nusselt number. Analysis of pressure measurements on the blade airfoil surface and tip surface along with PIV velocity flow fields in the gap give an understanding of the heat transfer mechanism.
机译：在代表高压涡轮的大型1.0米弦低速叶栅的叶片尖端表面上测量了高分辨率Nusselt数（Nu）分布。基于出口速度和叶片轴向弦，在雷诺数为4.0 x 10〜5时获得数据。刀尖间隙水平为设计弦的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，在恒定的热通量尖端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。移动的皮带端壁可显着改变高努氏数分布的区域，并使尖端表面上的总体平均努氏数降低多达13.3％。吸力侧尖叫器尖端的添加大大减少了局部尖端的传热，并导致平均Nusselt数降低了32％。对叶片翼型表面和叶尖表面的压力测量值以及间隙中的PIV速度流场进行分析，可以了解传热机理。

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