Abstract: Four typical configurations of laminate plates for ultra-high temperature turbine blade were made and tested in a large scale low speed close-looped wind tunnel.The internal flow resistance and the cooling effectiveness were obtained.The experimental results showed that very high cooling effectiveness can be achieved by using laminate plates and the ratio of the hole area to the plate area plays the most important role in determination of the cooling effectiveness and the internal flow resistances,the higher the ratio,the smaller the resistance and the higher cooling effectiveness.The research results are of reference value for the application of the laminate plates to aero-engine turbine blade.