| 高压涡轮动叶气膜冷却的数值模拟 |
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| 引用本文： | 杨晓军.高压涡轮动叶气膜冷却的数值模拟[J].机械设计与制造,2011(1). |
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| 作者姓名： | 杨晓军 |
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| 作者单位： | 中国民航大学,航空工程学院,天津,300300 |
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| 基金项目： | 中国民航大学科研启动基金(07QD04); 青年骨干教师培养计划 |
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| 摘 要： | 为研究旋转造成的非稳定性对高压涡轮动叶气膜冷却的影响,建立了3维涡轮叶栅通道模型,应用周期性边界条件数值模拟了不同转速下涡轮动叶表面气膜冷却效率和换热系数的分布,冷气进口与涡轮前总压比为1.07,温度比为0.5。转速增加,叶片前缘滞止线从压力面移向吸力面,气膜出流从吸力面移向压力面;压力面气膜冷却效率上升,换热系数下降;吸力面冷却效率先上升后降低;换热系数下降。与静止相比,旋转不稳定性增大了叶片表面气膜覆盖面积。
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| 关 键 词： | 涡轮动叶 气膜冷却 冷却效率 换热系数 数值模拟 |
Numerical simulation of film cooling on high pressure turbine rotor blade |
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| YANG Xiao-jan.Numerical simulation of film cooling on high pressure turbine rotor blade[J].Machinery Design & Manufacture,2011(1). |
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| Authors: | YANG Xiao-jan |
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| Affiliation: | YANG Xiao-jun(College of Aeronautical Engineering,Civil Aviation University of China,Tianjin 300300,China) |
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| Abstract: | One high pressure turbine stage model was constructed to analyze the unsteady effect of rotation on the film cooling.The periodic condition together with the shear stress transport turbulence model is used in the simulation.The total pressure ratio of the cooling inlet to the turbine entry is 1.07 and the temperature ratio is 0.5.A Frozen Rotor interface technique is employed for information transfer between stator and rotor domains.With increasing rotating speed,the stagnation line moves from the pressure ... |
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| Keywords: | Turbine rotor Film cooling Cooling effectiveness Heat transfer coefficient Numerical simulation |
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