过热蒸汽射流冷却叶片热耦合数值模拟  

Numerical simulation of jet impingement cooling of turbine steam-cooling vane

作　　者：董瑜[1] 郑洪涛[1] 谭智勇[1] 穆勇[1] 李智明[1] 

机构地区：[1]哈尔滨工程大学动力与能源工程学院,哈尔滨150001

出　　处：《航空动力学报》2008年第2期237-243,共7页Journal of Aerospace Power

摘　　要：在对射流冷却平板模型和射流冷却凹板模型数值模拟的基础上,设计了射流冲击冷却式蒸汽冷却叶片,并对其进行了热耦合数值模拟.通过改变平板和凹板的进口雷诺数,射流孔与靶板间距和凹板曲率,对靶板的冷却传热进行了对比研究,得到传热量与各个参数的变化规律.然后根据上面得到的变化规律设计出射流冲击冷却式蒸汽冷却叶片,应用ANSYS CFX 10.0数值程序,对冲击冷却的流动和传热过程进行了三维热耦合数值模拟,得到叶片表面温度和对流换热系数分布.The present study numerically investigated a conceptual type of internal steam cooling vane with the impingement cooling technology on the basis of plane model and concave model. By changing the inlet Re, distance between the jet and target board and curvature of concave board, a series of temperature value and heat transfer coefficient are obtained. Based on these Results, an impingement cooling vane was designed, which worked on the ANSYS workbench, and the conjugated heat transfer was studied by means of ANSYS CFX Navier-Stokes code using κ-ε two-equation turbulence model for gas field and cooling field. The numerical results of the effects of cooling flow heat transfer in the vane were obtained to evaluate the damage of the vane during steady state operation conditions.

关 键 词：蒸汽冷却 射流冲击 燃气轮机 数值模拟 热耦合 

分 类 号：TK471[动力工程及工程热物理—动力机械及工程] V231.4[航空宇航科学与技术—航空宇航推进理论与工程]