Film cooling of gas turbine baldes using new geometry-holes

使用新几何孔对燃气轮机叶片进行薄膜冷却

• 批准号: 311579-2007
• 负责人: Jubran, Bassam
• 金额: $ 1.31万
• 依托单位: Ryerson University
• 依托单位国家: 加拿大
• 项目类别: Discovery Grants Program - Individual
• 财政年份: 2011
• 资助国家: 加拿大
• 起止时间: 2011-01-01 至 2012-12-31
• 项目状态: 已结题
• 来源: https://www.nserc-crsng.gc.ca/ase-oro/Details-Detailles_eng.asp?id=480919
• 关键词: Film; cooling; gas; turbine; baldes

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.

新一代高性能飞机涡轮喷气发动机的开发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具创新性的冷却技术。本提案的目标有两个。第一个是开发一个数值模型来预测光滑平板和测试叶片模型的非常规形状孔、不同布局行布置和内部冷却剂供应配置以及喷射角度的气膜冷却效率。将研究各种湍流模型，包括先进的大涡模拟 (LES) 模型和各种次网格尺度 (SGS) 模型，以了解其捕获流动主要特征的能力以及此类冷却系统建模所需的计算成本。第二个是设计和开发一个实验装置，以研究在平板和测试叶片模型的不同主流流量、冷却剂流量和表面条件下，宏观和微观形状的孔和槽的薄膜冷却和传热。测试叶片模型的轮廓形状将被设计为反映实际涡轮叶片上雷诺数和加速度参数的真实分布。