In modern aircraft engines

different kind of cooling techniques such as film showerhead

film spills internal heat transfer enhancement and pin-fin with impingement were used together to keep the turbine blades and guide vanes operating safely.Design and experimental research of compound air-cooled turbine guide vane were presented.The overall cooling characteristics of a real vane was tested and calculated at elevated pressures and temperatures.Experimental results show that the cooling characteristics of the vane are superior while the cooling mass flow ratios varies between 6% and 16%

and the calculation results are in good agreement with the experiments.