Effects of film cooling on the surface pressure distribution on composite air-cooled blades has been investigated experimentlly at medium temperatures and pressures.The effects of the ratio of cooling mass flow to gas mass flow K G,the ratio of gas temperature to coolant temperature K T,and the location of film cooling holes on the surface pressure distribution are discussed.It is found from the experimental results that the K G and the location of the film cooling holes have considerable effects on the surface pressure distribution.
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