Film cooling of gas turbine baldes using new geometry-holes

新一代高性能飞机涡轮喷气发动机的发展要求燃气轮机在非常高的涡轮转子入口气体温度下运行。这就需要为燃气轮机叶片开发更创新的冷却技术。本建议的目标是双重的。首先是建立一个数值模型，以预测光滑平板和试验叶片模型在非常规形状孔、不同布置排排和内部冷却剂供应配置以及喷射角度下的气膜冷却效果。各种湍流模型，包括先进的大涡模拟（LES）模型和各种子网格尺度（SGS）模型，将根据其捕获流动的主要特征的能力和建模所需的计算成本来研究这些冷却系统。二是设计和开发实验装置，研究平板和试验叶片模型在不同主流流量、冷却剂流量和表面条件下，宏观和微观形状孔和槽的气膜冷却和换热。测试叶片模型的外形将被设计成反映实际涡轮叶片上雷诺数和加速度参数的真实分布。这项研究的长期目标是扩展知识，建立技术专长和工具，从而设计和测试新的创新型燃气轮机叶片冷却技术。此外，该项目将为建立一个跨学科的研究项目铺平道路，以调查冷却配置的制造技术对膜冷却效率的影响。拟议的研究计划对加拿大航空航天工业的意义在于它对开发新一代高性能飞机涡轮喷气发动机的贡献。这对于加拿大工业保持其生产最好的飞机和燃气涡轮发动机的竞争力至关重要。

The development of a new generation of high performance aircraft turbine jet engines requires gas turbines to be operated at very high turbine rotor inlet gas temperatures. This necessitates the development of more innovative cooling techniques for gas turbine blades. The objective of the present proposal is two-fold. The first is to develop a numerical model to predict the film cooling effectiveness for unconventional shaped-holes, different layout row arrangements and internal coolant supply configurations, and injection angles, for smooth flat plate and test blade models. Various turbulence models, including the advanced Large-Eddy Simulation (LES) model with various subgrid scale (SGS) models will be investigated in terms of their ability to capture the main features of the flow and the required computing cost for modeling of such cooling systems. The second is to design and develop an experimental setup to investigate film cooling and heat transfer from macro and micro shaped holes and slots, under different mainstream flow, coolant flow, and surface conditions for flat plate and test blade models. The profiled shapes of the test blade models will be designed to reflect realistic distributions of the Reynolds numbers and acceleration parameters over actual turbine blades.The long-term objectives of the research are to expand the knowledge and establish the technical expertise, and tools, that lead to the design and testing of new innovative cooling techniques for gas turbine blades. Moreover, this project will pave the way for establishing an interdisciplinary research program to investigate the effects of manufacturing techniques of cooling configurations on the film cooling effectiveness. The significance of the proposed research program for the Canadian aerospace industry is its contribution towards the development of a new generation of high performance aircraft turbine jet engines. This is essential for the Canadian industry to maintain its competitiveness to produce the best in aircraft, and gas turbine engines.