Investigation on full-coverage film cooling effectiveness of turbine vane with exit Mach number from 0.81 to 1.01

Heat transfer coefficient and film cooling effectiveness are investigated on a turbine vane employing the transient thermal couple technique.There are 1 3 rows of film cooling holes placed on the test blade.The cooling gas through film holes is supplied by two plenums,with mass flow ratio of 5.06% in the first plenum and 1.14% in the second.To match the real engine operating condition,the range of the inlet Reynolds number and the exit Mach number of the cur-rent experiment are 1.7×105~5.7×105 and 0.81~1.01,respectively.Heat transfer coefficient distribution is obtained,and effects of Reynolds number and Mach number to film cooling effec-tiveness distribution are investigated.The results show that heat transfer coefficient and film cooling effectiveness are higher in the near hole region.Film cooling effectiveness increases as in-let Reynolds number increases,especially on the pressure side and suction side,while the effect of exit Mach number to film cooling effectiveness is not obvious.