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Film cooling is an effective way to protect solid surface to high temperature main stream and has been widely used in turbine blades. This thesis experimentally investigated the characteristic of flow and heat transfer with film cooling. A test facility had been built to employ the TLC for measuring temperature filed. A large number of pictures that indicated wall temperature field had been collected. All of these pictures were converted to temperature filed. The adiabatic wall temperatures, the effectiveness and heat transfer coefficients had been obtained. It was found that:For small blow ratio, the cooling intensity near by film cooling hole is larger than that of large blow ratio, but the effective length is shorter. For the large blow ratio, the film cooling air may penetrated through the main stream and could not form the protection layer between the hot gas and solid surface. The best blow ratio is about 0.7 for the film cooling hole inclined 30<0> along the flow direction.