采用流热耦合方法分别对内部冷却的超跨音直列叶栅和环形叶栅进行数值模拟。其中直列叶栅为径向圆孔内冷的NASA MARK II叶片,通过数值解与实验值的对比,验证流热耦合方法的准确性,并讨论层流、不同湍流及转捩模型在流热耦合模拟中的特...采用流热耦合方法分别对内部冷却的超跨音直列叶栅和环形叶栅进行数值模拟。其中直列叶栅为径向圆孔内冷的NASA MARK II叶片,通过数值解与实验值的对比,验证流热耦合方法的准确性,并讨论层流、不同湍流及转捩模型在流热耦合模拟中的特点。在此基础上选用考虑和不考虑转捩模型的SST湍流模型,以采用径向成形内冷通道的某高压级导叶环形叶栅为研究对象,讨论其复杂流场与换热之间的相互作用。结果表明:为准确预测流热耦合作用下的温度分布,需要选择合理的湍流模型,并考虑转捩的影响,不同热边界同样会影响气动效果如分离再附等;三维超跨音流场中激波、分离以及通道涡、角隅涡等涡系结构与温度场之间存在复杂的相互作用;内部换热对于降低叶片表面温度有着重要作用,通过数值解可指导冷却结构优化设计。展开更多
The present investigation analyzes the effects of major geometrical modifications to the interior of a convectioncooled gas turbine rotor blade. The main focus lies on the flow of the leading edge channels and the imp...The present investigation analyzes the effects of major geometrical modifications to the interior of a convectioncooled gas turbine rotor blade. The main focus lies on the flow of the leading edge channels and the impact on theheat transfer. An experimental approach is performed with flow visualization via paint injection into water. Alsonumerical calculations are carried out in two sets, on the one hand water calculations accompanying the experimentsand on the other hand conjugate heat transfer calculations under realistic engine conditions. The latter calculationsare still ongoing delivering preliminary results.Five geometry configurations are investigated, three of them with differing turbulator arrangements in the leadingedge channels. The operating point of the base configuration is set to Re = 50,000 at the inlet while for the modifiedgeometries the pressure ratio is held constant compared to the base.Among several investigated configurations one could be identified that leads to a heat transfer enhancement inone leading edge channel 7 % larger compared to the base.展开更多
文摘采用流热耦合方法分别对内部冷却的超跨音直列叶栅和环形叶栅进行数值模拟。其中直列叶栅为径向圆孔内冷的NASA MARK II叶片,通过数值解与实验值的对比,验证流热耦合方法的准确性,并讨论层流、不同湍流及转捩模型在流热耦合模拟中的特点。在此基础上选用考虑和不考虑转捩模型的SST湍流模型,以采用径向成形内冷通道的某高压级导叶环形叶栅为研究对象,讨论其复杂流场与换热之间的相互作用。结果表明:为准确预测流热耦合作用下的温度分布,需要选择合理的湍流模型,并考虑转捩的影响,不同热边界同样会影响气动效果如分离再附等;三维超跨音流场中激波、分离以及通道涡、角隅涡等涡系结构与温度场之间存在复杂的相互作用;内部换热对于降低叶片表面温度有着重要作用,通过数值解可指导冷却结构优化设计。
基金supported by the AG Turbo with funds of the Federal Ministry of Eco- nomics and Technology BMWi (FKZ 0327715G)
文摘The present investigation analyzes the effects of major geometrical modifications to the interior of a convectioncooled gas turbine rotor blade. The main focus lies on the flow of the leading edge channels and the impact on theheat transfer. An experimental approach is performed with flow visualization via paint injection into water. Alsonumerical calculations are carried out in two sets, on the one hand water calculations accompanying the experimentsand on the other hand conjugate heat transfer calculations under realistic engine conditions. The latter calculationsare still ongoing delivering preliminary results.Five geometry configurations are investigated, three of them with differing turbulator arrangements in the leadingedge channels. The operating point of the base configuration is set to Re = 50,000 at the inlet while for the modifiedgeometries the pressure ratio is held constant compared to the base.Among several investigated configurations one could be identified that leads to a heat transfer enhancement inone leading edge channel 7 % larger compared to the base.
