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作 者:郑杰[1] 张雅荣[2] 窦益华[1] 李明飞[1]
机构地区:[1]西安石油大学机械工程学院,西安710065 [2]西安交通大学数学与统计学院,西安710049
出 处:《汽轮机技术》2017年第4期261-264,共4页Turbine Technology
基 金:国家自然科学基金(5167041385);陕西省教育厅专项科研计划项目(16JK1611)
摘 要:针对涡轮叶片尾缘"冲击+扰流柱"复合典型冷却结构,通过分析内部流场和换热特性,揭示"冲击+扰流柱"冷却结构中流动发展的过程以及冲击对压力分布和流场分布的影响,揭示涡轮叶片尾缘区内射流冲击扰流柱排通道内换热机理,详细分析了冲击下各个表面的换热情况。结果表明,压比的增大能够有效改善冷却通道端壁的换热性能,但同时增大了压力损失;在两种冲击距离下,n=3d换热效果优于n=6d,但是n=6d的下游换热覆盖效果优于n=3d。顺排时,冲击孔的平均换热系数大约是扰流柱的1.5倍;叉排时,冲击孔的平均换热系数大约是扰流柱的3倍,而其它部位的平均换热系数受排列方式的影响很小。因此,"冲击+扰流柱"冷却结构的匹配,对于优化涡轮叶片尾缘区域的换热及其重要。This paper investigates the "impingement + cylinders" of the trailing edge of turbine blade and analyzes the flow fields and heat transfer characteristics. It reveals the flow development process on the "impingement + cylinders" cooling configuration, and it shows the flow fields and the pressure distributions and reveals the heat transfer mechanism of array jet impingement for the turbine blade trailing edge, and analyses the heat transfer on each surface in detail. The results have shown that the heat transfer characteristics can be effectively improved when the pressure ratios increase at the endwall, but the pressure loss is increased. At the two kinds of the impingement distance, the heat transfer of the n = 3d is better than n = 6d, but the downstream heat transfer coverage of n = 6d is better than n = 3d. The average heat transfer coefficient of the impingement hole is about 1.5 times that of the cylinders in in-line, but the average heat transfer coefficient of the impingement hole is about 3 times that of the cylinders in staggered, while the arrangement have a small influence for the average heat transfer coefficient of other parts. Therefore, it is important for matching the "impingement + cylinders" cooling structure to optimize the heat transfer in the turbine blade trailing edge region.
分 类 号:V231.1[航空宇航科学与技术—航空宇航推进理论与工程]
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