Film cooling of gas turbine baldes using new geometry-holes

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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.