Turbine Blade Surface Film Cooling Experimental Research

Film cooling of the surface of a gas turbine blade was studied in a large-scale low-speed opening wind tunnel according to actual requirement of the design of aero-engine. The surface of a gas turbine blade was cooled by four rows of cylindrical holes in the experiment.The mass flow rate coefficients, the heat transfer coefficients and the film effectiveness of cylindrical holes of different part of a gas turbine blade were studied experimentally in the different mainstream Reynolds number. The distribution of the mass flow rate, the heat transfer coefficients and the film effectiveness of cylindrical holes was measured. The influence of mainstream Reynolds number, blowing ratio and the position of holes on flow rate, the heat transfer coefficients and the film effectiveness was studied greatly. The ranges of test parameters are: mainstream Reynolds numbers of 100000,150000,200000,236900 and blowing ratio from 0 to 2. Results show that the influence of mainstream Reynolds numbers on discharges coefficients and film effectiveness is little but on the heat transfer coefficients is obvious. The mass flow rate coefficients increase and achieve a constant at last with increasing blowing ratio. The influence of blowing ratio on the heat transfer coefficients and film effectiveness is complex.