燃气透平高温叶片前缘旋流/气膜复合冷却气热性能与流热耦合机理研究

针对现代燃气透平高温叶片前缘热负荷过高、流场复杂且由于结构原因难以有效冷却等原因造成易于烧蚀的问题，本项目拟对叶片前缘旋流/气膜复合冷却气热性能与流热耦合作用机理开展研究，采用先进的可视化流动和传热测试技术以及精确的流热耦合数值模拟方法和理论分析，通过详细研究不同气动和结构参数及旋转状态等对叶片前缘旋流/气膜复合冷却的影响规律，阐明各参数对叶片前缘旋流/气膜复合冷却流动结构、传热特性和损失特征的作用机制，揭示叶片前缘旋流/气膜复合冷却的流热耦合作用机理，探索叶片前缘旋流/气膜复合冷却结构的优化方向，寻求利用冷却结构的合理布置控制叶片材料内部的温度梯度的方法，建立叶片前缘旋流/气膜复合冷却的设计方法，为发展先进的叶片前缘冷却设计技术，研发具有自主知识产权的燃气透平高温叶片奠定理论基础并提供技术支撑。

Modern gas turbine inlet temperature is pushed far beyond the material melt temperature, and correspondly turbine component, especially the leading edge of first stage turbine blade, is scoured by very high temperature inflows as well as very high heat flux. To make sure the safety works of gas turbine, high performance cooling technology must be applied to the blade leading edge. Therefore, this project plans to investigate experimentally and numerically the aero-thermal (fluid-heat) coupled mechanism of swirl and film composite cooling in turbine blade leading edge with the help of test visualization technology and advanced CFD method, to understand the effect of different flow, geometrical parameters, and blade rotation on the flow structure, resistance and conjugate heat transfer characteristics of swirl and film composite cooling, to reveal the fluid-heat coupling mechanism of swirl and film composite cooling, and subsequently to offer solid theoretical basis and experimental verification for the development of efficient blade leading edge cooling technology, thus providing related theoretical foundation for the research and development of our self-owned intellectual property in the high temperature gas turbine blade.