高压气冷涡轮内冷通道换热系数准则式的研究  

STUDY ON INNER-COOLING CHANNEL'S HEAT TRANSFER COEFFICIENT CRITERIA FORMULA OF A HIGH PRESSURE AIR-COOLED TURBINE

作　　者：王振峰[1] 颜培刚[1] 唐洪飞[1] 黄洪雁[1] 韩万金[1] 

机构地区：[1]哈尔滨工业大学能源科学与工程学院,哈尔滨150001

出　　处：《工程热物理学报》2010年第2期247-250,共4页Journal of Engineering Thermophysics

基　　金：国家自然科学基金资助项目(No.50706009;No.50576017)

摘　　要：将应用最广的迪图斯-贝尔特和格尼林斯基管内对流换热实验准则式应用于NASA-MarkII高压燃气气冷涡轮叶栅气热耦合换热计算中,同时引入温度差和入口效应的修正因子。计算结果表明,在结构较简单的冷却通道、冷却孔等位置,采用进行修正的换热系数实验准则式能够得出与实验结果较为吻合的计算结果,准则式的应用省略了冷却通道流体域求解工作,避免了冷却通道流体与固体叶片的耦合计算误差和冷却通道边界条件不同给定带来的结果误差,此方法具有一定的工程应用价值。Dittus-Boelter criteria formula and Gnielinski criteria formula are adopted during the calculation of conjugate heat transfer analysis for the NASA-MarkII high pressure air-cooled gas turbine.The correct coefficients which consider the geometry and work conditions of inner-cooling channels include the temperature difference correct coefficient,the entry effect correct coefficient and the inner-cooling channel curvature correct coefficient etc.The results show that the application of heat transfer coefficient criteria formulas on the inner-cooling channel can give the results which have a good agreement with the experimental results.In addition,the application of heat transfer coefficient criteria formulas omits the calculation of inner-cooling channel fluid domain.It avoids the conjugate errors of inner-cooling channel fluid domain and solid blade domain and avoids the calculation errors of uncertain inner-cooling channel boundary conditions,so this method is feasible and effective.

关 键 词：气冷涡轮 气热耦合 换热系数准则公式 湍流模型 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]