Film cooling of gas turbine baldes using new geometry-holes

新一代高性能飞机涡轮机喷气发动机的发展要求燃气涡轮机在非常高的涡轮机转子入口气体温度下操作。这就需要开发更创新的燃气涡轮机叶片冷却技术。本提案的目的有两个。第一个是开发一个数值模型来预测非常规形状的孔，不同的布局排布置和内部冷却剂供应配置，和喷射角，光滑平板和测试叶片模型的薄膜冷却效率。各种湍流模型，包括先进的大涡模拟（LES）模型与各种亚网格尺度（SGS）模型将在其捕获的流动的主要特征和所需的计算成本，这样的冷却系统建模的能力方面进行研究。第二是设计和开发一个实验装置，以调查膜冷却和传热从宏观和微观形状的孔和槽，在不同的主流流量，冷却剂流量，和表面条件下的平板和测试叶片模型。试验叶片模型的轮廓形状将设计为反映实际涡轮机叶片上雷诺数和加速度参数的真实分布。

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.