This paper documents a computational investigation of the aerodynamic impact of filmcooling on a linear turbine airfoil cascade. The simulations were for single row injection on both the pressure and suction surfaces, downstream of the leading edge region. The cases match experimental efforts prey iouslydocumented in the open literature. Results were obtained for density ratio equal to 1.0 and 2.0, and a blowing ratio range from 0.91 to 6.6. The domain included the passage flow as well as the

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... lm-hole and blade interior. The simulation used a dense, high-quality. unstructured hybrid-topology grid, comprised of hexahedra, tetrahedra. prisms and pyramids. The processing was performed with a pressurecorrection solution procedure and a second-order discretization scheme. Turbulence closure was obtained using standard, RNG, and "realizable" k-E models, as well as a Reynolds stress model. Results were compared to experimental data in terms of total pressure loss downstream of the blade row. Flow mechanisms responsible for the variation of aerodynamic losses due to suction and pressure surface coolant injection are documented. The results demonstrate that computational methods can be used to accurately predict losses on film-cooled airfoils. Downloaded From: http://proceedings.asmedigitalcollection.asme.org/ on 08/21/2017 Terms of Use: http://www.asme.org/about-asme/terms-of-use