Modern gas turbine blades are cooled using air bleeded from the compressor.In a rotor-stator system

the cooling air enters at the center of the stator and flows radially outward

then leaves through the discrete receiver holes in the rotor and the clearance between the rotor and the shroud.The temperature distribution was measured by Thermal Liquid Crystal(TLC) and thermocouples on the rotor surface to acquire the cooling effectiveness.The influence of rotating speed and cooling mass flow rate on cooling effectiveness were analyzed.The dimensionless average temperature and dimensionless temperature difference of rotor surface decrease with both of the dimensionless mass flow rate and rotational Reynolds number are increased.The existence of receiver holes is of advantage to cooling rotor.The experiments show that the bigger the size of receiver holes is

the higher of cooling effectiveness will be.