This paper presents the experimental study of effusion wall film heat transfer coefficients for impingement/effusion double wall cooling method

which is one of the advanced cooling methods of combustor liner in aeroengine.The investigation focused on the factors affecting the heat transfer coefficients

which are main flow Reynolds number

blowing ratio and configurations.The heat transfer coefficients were studied using the comparing method

and the basic heat transfer coefficients were compared with classical heat transfer result

showing that the difference was within ±7%.The experimental results showed that the main flow Reynolds number had no effect on the effusion wall film heat transfer coefficient

while the blowing ratio and configurations were the main factors.The more the rows of cooling film

the higher the heat transfer coefficient along the flowing direction.The experimental results were correlated

and the correlation can be used in the heat transfer design and validation of cooling schemes.