Heat Transfer in a Rotating Radial Channel With Swirling Internal Flow
Heat Transfer in a Rotating Radial Channel With Swirling Internal Flow
复制标题
具有旋流内流的旋转径向通道中的传热
DOI：
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发表时间：
1998
期刊：
影响因子：
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通讯作者：
G. Guenette
中科院分区：
文献类型：
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作者：
B. Glezer;H. Moon;J. Kerrebrock;J. Bons;G. Guenette
本文介绍了旋流内部换热的两种实验结果。利用试验台模拟了旋转叶片前缘内通道的加热壁面和通过离散切槽引入的气流产生的螺旋形冷却旋流。利用红外辐射计在旋转装置中测量了表面传热系数的空间分辨变化。在实际发动机环境中测试的叶片具有类似的前缘冷却通道几何形状。叶片表面温度在发动机中用热漆绘制，并与传统的对流冷却配置进行比较。在实际壁面与冷却剂温度比下，将旋转钻机和发动机测量数据与热叶栅中非旋转传热结果进行了比较。结果给出了实际的旋转数，范围从0到0.023，以及基于通道直径的代表性雷诺数20,000。随着旋转方向的改变，科里奥利力的作用是明显的。在钻机试验结果中记录了横向流的轻微负面影响，横向流向通道外半径方向增加。所提出的结果将有助于更好地理解螺旋形涡流冷却技术，为下一步在涡轮叶片前缘应用这种高效的内部冷却方法提供帮助。©1998 asme
This paper presents experimental results for heat transfer in swirling internal flow, obtained in two ways. A test rig simulated a rotating blade’s leading edge internal passage with heated walls and screw-shaped cooling swirl generated by flow introduced through discrete tangential slots. Spatially resolved variations of the surface heat transfer coefficients were measured in the rotating rig using an IR radiometer.A blade tested in the actual engine environment had similar geometry of the leading edge cooling passage. The blade surface temperatures were mapped in the engine with thermal paints and compared with a traditional convective cooling configuration. The data from the rotating rig and engine measurements are also compared with non-rotating heat transfer results obtained in the hot cascade using a traversing pyrometer at a realistic wall-to-coolant temperature ratio.The results are presented for realistic rotational numbers, ranging from 0 to 0.023, and for representative Reynolds number of 20,000 based on the channel diameter. The effect of Coriolis forces is evident with the change of direction of the rotation. A slight negative influence of the crossflow, which increased toward the outer radius of the channel, was recorded in the rig test results.The results presented will assist in better understanding of the screw-shaped swirl cooling technique, providing the next step toward the application of this highly-effective internal cooling method for the leading edges of turbine blades.© 1998 ASME