高温叶片前缘内部旋流冷却的流动与传热机理研究

燃气透平叶片的前缘工作时处在高温燃气的强烈冲刷下，其热负荷极高，因此是叶片中最容易烧蚀的部位之一。为确保透平高温叶片高效可靠的工作和合理的运行寿命，必须采用有效的冷却技术对其进行保护。为此，本项目拟结合机理性实验和三维数值计算，深入研究叶片前缘旋流冷却的流动与传热机理。采用先进的可视化流动和传热测试技术以及包含湍流模型和转捩模型的对比等精确热流耦合数值模拟方法，通过详细研究不同气动参数和结构参数及动叶旋转状态下叶片前缘内部的旋流冷却特性，阐明各参数对旋流冷却的流动结构、阻力特征和传热特性的影响机制，揭示叶片前缘旋流冷却的流动和传热机理，探索叶片前缘内部旋流冷却结构的优化方向，以期建立叶片前缘内部旋流冷却的设计理论，为发展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。

As gas turbine blade’s leading edge is scoured by high temperature inflows, it witness very high heat flux. So the blade leading edge must be cooled effectively to make sure the gas turbine works safely. In order to improve the cooling efficiency of the cooling methods in the blade leading edge, it is very important to investigate the flow and heat transfer characteristics of the swirl cooling on turbine blade leading edge. Therefore, based on the applicant’s early study and aimed for the development of cooling technique with high efficiency and safety, this project plans to study the flow and heat transfer mechanism of swirl cooling in turbine blade leading edge numerically and experimentally with the help of visualization test technology and advanced CFD method, understand the effect of different flow, geometrical parameters, and rotor blade rotation on the flow structure, resistance and heat transfer characteristics of swirl cooling, reveal the flow and heat transfer mechanism of swirl cooling, subsequently 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.