涡轮叶片冷却技术是发展现代高性能航空发动机的关键技术之一，对流冷却在先进涡轮叶片冷却技术中占主导地位，增强涡轮叶片冷却通道内的对流换热可以有效提升涡轮叶片的整体冷却效果，因此研究冷却通道内的对流换热是发展先进涡轮叶片冷却技术的关键。本项目通过数值模拟研究涡轮叶片冷却通道中的冷却气体和叶片之间的共轭传热问题，探索冷却通道内冷却气体的流动对涡轮叶片温度场分布的影响。首先，建立涡轮叶片共轭传热问题的耦合计算模型，形成全场统一求解的耦合方法，避免需要预先给定流固交界面处热边界条件的困难；其次，采用直接数值模拟法计算涡轮叶片冷却通道中复杂的湍流运动，该方法对湍流的流动无需做任何假设和简化，可以精确捕捉湍流的全部流动与换热细节；最后，建立涡轮叶片和内部冷却气体整场耦合求解的POD降阶模型，通过求解降阶后的离散模型可以快速预测涡轮叶片的温度场分布。本研究将为发展先进的涡轮叶片冷却技术提供理论和技术支持。

Turbine blade cooling technology is one of the key technologies for development the modern aero-engine. Convection cooling plays a leading role in advanced turbine blade cooling technology, and enhancing convective heat transfer in the cooling channel of turbine blades can effectively improve the cooling effect of turbine blades. Therefore, study on convection heat transfer in the cooling channel is very important to development the advanced turbine blade cooling technology.. In this project, the conjugate heat transfer between the cooling gas and the blade in the cooling channel of turbine blade is studied by numerical simulation, and the influence of the flow of cooling gas in the cooling channel on the temperature distribution of the turbine blade is analyzed. Firstly, the coupling calculation model of the conjugate heat transfer problem of turbine blade is established, and the coupling method of the whole field is formed to avoid the difficulty of determining the thermal boundary conditions at the fluid-solid interface in advance. Secondly, the direct numerical simulation method is used to calculate the complex turbulent motion in the cooling channel of turbine blades. This method can accurately capture all the details of turbulent flow and heat transfer without making any assumptions and simplifying the turbulent flow. Finally, the POD reduced-order model coupled with the whole field of turbine blade and internal cooling gas is established. By solving the reduced-order discrete model, the temperature field distribution of turbine blade can be predicted quickly. This study can provide theoretical and technical support for the development of advanced turbine blade cooling technology. Firstly, the coupling calculation model of the conjugate heat transfer problem of turbine blade is established, and the coupling method of the whole field is formed before to avoid the difficulty of determining the thermal boundary conditions at the fluid-solid interface. Secondly, the direct numerical simulation method is used to calculate the complex turbulent motion in the cooling channel of turbine blades. The method can accurately capture all the details of turbulent flow and heat transfer without making any assumptions and simplifying the turbulent flow. Finally, a POD reduced-order model coupled the whole field of turbine blade with the cooling gas is established, the temperature field of turbine blade can be predicted quickly by solving the reduced-order discrete model. The research can provide theoretical and technical support for development the advanced turbine blade cooling technology.