Abstract
The performance of film cooling used for gas turbine first vanes or blades depends on various factors. This paper discusses the effects of film-hole geometry on film cooling effectiveness distributions obtained by experiment and numerical analysis. In experiment, Laser-induced Fluorescence (LIF) has been utilized to measure film cooling effectiveness on the basis of heat/mass transfer analogy. Three-dimensional spatial distributions of film cooling air injected into the boundary layer on flat surface were investigated by using a low-speed wind tunnel. In numerical analysis, film cooling effectiveness was obtained with the standard k-ε model. Comparison of the film cooling effectiveness distribution between experimental results and numerical one shows qualitative agreement.
