非均匀激波-辐射加热作用下涡轮叶片复合冷却结构耦合传热机制

项目名称： 非均匀激波-辐射加热作用下涡轮叶片复合冷却结构耦合传热机制

项目编号： No.51276088

项目类型： 面上项目

立项/批准年度： 2013

项目学科： 能源与动力工程

项目作者： 杨卫华

作者单位： 南京航空航天大学

项目金额： 80万元

中文摘要： 本课题拟考虑高温激波和辐射交互作用，深入开展航空发动机涡轮复合冷却结构非均匀加热机制与特性研究，掌握冷却结构高温侧激波对流和辐射加热热流的特性规律；考虑非定常、非均匀的热-流边界条件，构建涡轮叶片复合冷却结构内多场耦合传热数理模型，发展相应的算法；并通过开展跨音速叶栅层板全气膜复合冷却结构的流动换热实验研究为相应的机理分析、数值模拟方法和算法验证提供部分支持；最终形成非均匀激波-辐射加热作用下涡轮叶片复合冷却结构热环境及耦合传热特性的系统分析技术。 该问题的研究不仅对优化航空发动机涡轮区热防护设计、增强冷却结构可靠性和寿命具有重要的科学与工程价值，也可以为超燃冲压发动机喷管、航空发动机尾喷管冷却结构的优化设计提供参考；同时，从学术角度看，这一问题的研究涉及激波、导热、辐射传递、对流换热等多个学科领域，具有明显的学科交叉性，对促进相关学科发展也具有重要价值。

中文关键词： 涡轮叶片；复合冷却；耦合换热；辐射；激波

英文摘要： The non-uniform heating mechanism of compound-cooling configurations of turbine blade is studied by the influence of interaction of high temperature shock wave and radiation, the characteristics of shock convection and radiation heat transfer on the heated side of the compound-cooling configurations is obtained. The unsteady and non-uniform heat flow boundary conditions is considered, the multiple fields heat transfer mathematical models and calculation methods is obtained. And the analytical models and numerical method is validated by the flow and heat transfer experimental study of transonic turbine blade of compound-cooling configuration. The systemic method for analyzing the coupled heat transfer characteristics of compound-cooling configurations of turbine blade heated by non-uniform shock wave and radiation. The study results of the project is not only used to design the compound-cooling configurations of turbine blade and increase the reliability and life of turbine blade, but also provide the references for designing the nozzle of ramjet and aeroengine. From the position of science, the problem relates to multiple science of shock wave, radiation transfer, convection heat transfer, conduction heat transfer, which has a evident characteristics of across of different science. And it has a important values

英文关键词： turbine blade；compound cooling；coupled heat transfer；radiation；shock wave