CFD Simulation on Gas turbine blade and Effect of Hole Shape on leading edge Film Cooling Effectiveness
Journal Title: International Journal of Modern Engineering Research (IJMER) - Year 2013, Vol 3, Issue 4
Abstract
In order to raise thermal efficiency of a gas turbine, higher turbine inlet temperature (TIT) is needed. However, higher TIT increases thermal load to its hot-section components and reducing their life span. Therefore, very complicated cooling technology such as film cooling and internal cooling is required especially for HP turbine blades. In film cooling, relatively cool air is injected onto the blade surface to form a protective layer between the surface and hot mainstream gas. The highest thermal load usually occurs at the leading edge of the airfoil, and failure is likely to happen in this region. Film cooling is typically applied to the leading edge through an array of hole rows called showerhead. In this project initially benchmarks study the current state of heat transfer prediction for commonly used CFD software ANSYS Fluent. The predictions Reynolds-Averaged Navier-Stokes solutions for a baseline Flat film cooling geometry will be analyzed and compared with experimental data. The Fluent finite volume code will be used to perform the computations with the realizable k-ε turbulence model. The film hole is angled at 30° to the crossflow with a Reynolds number of 17,400. The focus of this investigation is to investigate advanced cooling hole geometries on film cooling effectiveness over flat surface. Three film-cooling holes with different hole geometries including a standard cylindrical hole and two holes with a diffuser shaped exit portion (i.e. a fanshaped and a laidback fanshaped hole) will be studied. Finally optimized shape of the hole configuration is included in NASA Mark II vane turbine geometry to study heat transfer characteristics of blade.
Authors and Affiliations
Shridhar Paregouda
Keywords
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