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Volume 3: Heat Transfer; Electric Power; Industrial and Cogeneration
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 thedoi:10.1115/99-gt-421 fatcat:45l35tvmgrhotcqxgvkmdmls34