燃气轮机作为现代能源与动力领域的核心装备在我国科技发展领域具有十分重要的地位，不断提升燃气轮机透平叶片冷却性能是提升燃气轮机效率的关键举措。透平叶片的尾缘高温耐受度低、结构狭窄空间有限，是冷却结构设计的难点。本文采用实验测量与数值模拟有机结合理论分析的手段，研究多种叶片尾缘冷却结构的强化换热机制，发展基于连续伴随方法的尾缘内部冷却流动与换热耦合的拓扑优化方法，揭示尾缘冷却典型几何构型对流体形态和强化换热的作用机制，提出新型高效尾缘冷却结构。针对串联倾斜冲击冷却结构，分析了其内的强化换热机制以及通流率对其流动换热特性的影响。结果表明，倾斜冲击射流和射流孔内压力梯度诱导产生的通道二次流共同强化了其内部换热；由多股冷却射流之间及与壁面的交互作用产生的射流背侧低速回流区增大了腔室内流动损失。更进一步的实验研究表明增加通流率能明显降低该结构的流动阻力，提升综合冷却效能。针对倾斜冲击与柱肋组合冷却结构，分析了冲击孔倾斜角度及通流率对其流动换热特性的影响。结果表明，随着冲击孔倾斜角度增大，冷却通道中柱肋换热机制与冲击射流强化换热相互制衡，导致换热强度呈现非单调性变化，在组合结构中存在最优倾斜冲击角度。适当扩大倾斜冲击孔的通流率有助于降低该组合冷却结构的流动阻力，并对换热强度造成一定损失。以降低流动损失为目标，提出了扁平腔室串联倾斜冲击冷却结构，采用实验和数值的方法分析了其内的流动换热特性。结果表明扁平腔室有效限制了冲击射流的发展，保持了冲击区域较高的速度核心，从而限制了低速回流区的产生，相对于贯通腔室结构换热能力提升了9%，流动阻力降低了21%。为充分挖掘尾缘狭窄通道的强化换热潜力，发展了基于连续伴随方法的流动换热拓扑优化方法，建立了基于开源软件的尾缘内部冷却拓扑优化平台，实现了非参数化的尾缘冷却结构优化。以二维通道和模化的尾缘结构为例验证了该方法的有效性，获得了换热能力较强的非参数化尾缘冷却结构。综合多种尾缘冷却结构中的流动换热特性，归纳了加速、滞止、折转、稳定、贴附这五种典型作用机制。基于此，提出了折转冲击通道冷却结构，通过实验证明该结构相对于平直小通道总换热能力提升了93%，流阻系数仅增加55%，从而表明其具有进一步提升叶片尾缘冷却特性的潜力。

As a core equipment in the field of modern energy and power industry, gas turbines have a very important position in the field of scientific and technological development in China. Continuously improving the design of the turbine blade cooling structure of gas turbines is a key measure to improve the efficiency of gas turbines. The trailing edge of the turbine blade has a low temperature tolerance and a narrow structure with limited space, which makes it difficult to design cooling structures. In this paper, based on the analysis of the main heat transfer mechanism of the existing blade trailing edge cooling structure, the experimental measurement and numerical simulation method are used to explore the cooling structure of the blade trailing edge, establish the topology optimization method of the cooling structure of the trailing edge based on the continuous adjoint method, reveal the fluid morphology and the mechanism of the cooling structure of the trailing edge, and propose a new cooling structure of the trailing edge.For the series inclined impingement cooling structure, which is also known as blockages with inclined holes, the effect of its enhanced heat transfer mechanism and the flow characteristics are analyzed. The results show that the secondary flow induced by the oblique impinging jet and the pressure gradient in the orifice strengthens its internal heat transfer; the low-velocity recirculation zone on the back side of the oblique impinging jet increases the flow loss in the chamber. Further experimental studies have shown that increasing the opening ratio significantly reduces the flow resistance of the structure.Aiming at the combined cooling structure of inclined impingement and pin-fin, the influence of the inclination angle and opening ratio of the impingement hole on its flow heat transfer characteristics is analyzed. The results show that as the inclination angle of the impingement hole increases, the heat transfer mechanism of the pin-fin and the impingement jet heat transfer check and balance each other, resulting in a non-monotonic change in heat exchange intensity, and there is an optimal inclined impact angle. Properly expanding the opening ratio of the inclined impact holes helps to reduce the flow resistance of the structure and at the same time, cause some loss on the heat exchange capacity.In order to reduce the flow loss, a series inclined impingement cooling structure with flat cavity was proposed. The flow and heat transfer characteristics were analyzed by experimental and numerical methods. The results show that the flat chamber effectively limits the development of the impinging jet, maintains the high velocity core in the impinging region, and thus limits the generation of the low-speed recirculation zones. Compared with the through chamber structure, the heat transfer capacity is increased by 9%, and the flow resistance is reduced by 21%.In order to fully exploit the heat transfer enhancement potential of the narrow channel of the trailing edge, a flow heat transfer topology optimization method based on the continuous adjoint method was developed, and a topology optimization platform for internal cooling of the trailing edge based on open source software was established. Aiming at the wedge-shaped space of the modeled trailing edge, the topology optimization method was used to obtain the cooling structure of the trailing edge with higher heat transfer capability.Combining the characteristics of flow heat transfer in various trailing edge cooling structures, five typical action mechanisms of acceleration, stagnation, turning, stabilization and attachment are summarized. Based on this, the cooling structure of the reversing impact channel is proposed, and it is proved by experiments that the total heat transfer capacity of the structure is increased by 93% compared with the straight small channel, and the flow resistance coefficient is only increased by 55%, thus indicating that it has further improved blade trailing edge cooling.