首页> 外文会议>ASME turbo expo: turbine technical conference and exposition >EXPERIMENTAL STUDY ON THE EFFECT OF NON-UNIFORM INLET VELOCITY PROFILE ON INTERNAL COOLING IN RECTANGULAR CHANNELS WITH MULTI-FEATURES
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EXPERIMENTAL STUDY ON THE EFFECT OF NON-UNIFORM INLET VELOCITY PROFILE ON INTERNAL COOLING IN RECTANGULAR CHANNELS WITH MULTI-FEATURES

机译:矩形进气道内非均匀入口速度分布对内部冷却影响的实验研究

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Experiments were conducted to investigate the overall thermal performance of rectangular channels with a non-uniform inlet velocity profile. Two test sections with multiple internal cooling features had been used. One test section was implemented with two circular staggered pin-fin arrays with different pin diameters. The other one was implemented with a combination of a staggered pin-fin array and a perforated blockage array. The average surface heat transfer coefficient of the pedestal and perforated blockage and the local distribution of heat transfer coefficient on endwall were measured by the lumped capacitance method and transient liquid crystal method, respectively. The pressure drop across each array was measured. The heat transfer coefficients were measured over the Reynolds number range from 9,000 to 17,000. The spanwise pitches of the upstream pin-fin arrays were 2.33 and 4.66 for the channel with the multiple pin-fin array and the channel with perforated blockage, respectively. The effect of a non-uniform velocity profile on local heat transfer pattern and row-resolved heat transfer coefficient has been investigated.
机译:进行实验以研究具有非均匀入口速度曲线的矩形通道的整体热性能。使用了具有多个内部冷却功能的两个测试部分。一个测试部分由两个具有不同引脚直径的圆形交错的引脚-翅片阵列实现。另一个是通过交错的针鳍阵列和穿孔的阻塞阵列实现的。用集总电容法和瞬态液晶法分别测量了基座和穿孔堵塞物的平均表面传热系数以及端壁上传热系数的局部分布。测量了每个阵列上的压降。在9,000至17,000的雷诺数范围内测量了传热系数。具有多个针翅阵列的通道和具有穿孔阻塞的通道的上游针翅阵列的翼展方向间距分别为2.33和4.66。研究了非均匀速度分布对局部传热模式和行解析传热系数的影响。

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