摘要
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.
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.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
1989年第4期371-372,共2页
Journal of Aerospace Power
