降低燃气涡轮叶栅的表面换热系数，可以减少涡轮叶栅的冷气用量，提高涡轮功率和效率，改善燃气轮机的性能。燃气与叶栅表面的换热特性取决于边界层流动状态，其转捩位置和转捩区长度的影响至关重要。正确认识叶栅表面换热的流体动力学机理，并建立流动与换热两者的复合反问题模型，主动弱化叶栅表面换热，对先进燃气轮机设计具有重要的理论意义。.基于边界层稳定性理论，在曲面喷管模型上，研究曲面边界层转捩过程对叶栅表面传热特性的影响，建立边界层状态参数与表面换热特征参数之间的关联。在平面叶栅上，研究叶栅气动造型对叶片型面和叶栅端壁换热特性的影响，建立叶栅表面的弱化换热模型。.基于"场协同"理论，研究建立高负荷燃气涡轮叶栅的气热复合反问题设计模型。通过构造流动与温度梯度场的"协同函数"，解决多目标反问题的边值问题不适定的难题，对涡轮叶栅气动性能与表面换热性能的复合设计，实现主动控制。

When the heat transfer flux on turbine cascade surface is reduced, the coolant flow rate can be also reduced. Therefore, gas turbine thermal performance is improved through the increases of shaft power and efficiency. Heat transfer between the gas and turbine cascade depends on the states of boundary layer flow. Especially important is the occurance and length of the transition. It is of theoritical importance in the design of advanced gas turbine technology to understand the correct dynamic mechanism of surface heat transfer and to solve inverse problem of hybrid aero-thermal model for active blocked heat transfer. . Based upon the theory of boundary layer stability, it is studied upon a curved nozzle model the effect of boundary layer transition on surface heat transfer. Correlation between heat flux and boundary layer parameters is analyzed. Upon a linear cascade, the effects of aero-profiling is investigated for the heat transfer on blade surfaces and endwalls to build allevated heat transfer model. . Based on the theory of field synergy, it is investigated for the hybrid inverse formulation of aero-flow and heat transfer for highly loaded turbine cascade. Syneritc function is proposed to combine flow velocities with temperature gradient. Nonfited boundary value problem of inverse multi-object problem is then resolved. Active control of cascade flow performance and heat transfer becomes available.