In order to study the film cooling performance of impingement-effusion structure, it is important to study its adiabatic film cooling effectiveness. To improve the adiabatic film cooling effectiveness of the vane’s surface, some rows of the cylindrical hole of the effusion hole are changed into fan-shaped holes. The experiment measured the adiabatic film cooling effectiveness of the double-walled structure on the suction surface via the Pressure Sensitive Paint (PSP) technique. After the adiabatic cooling effectiveness (measured by PSP) processed into the heat transfer equation, the transient liquid crystal technique (TLC) technique is used to solve the heat transfer coefficient. It reduced the time of experiment and improved the efficiency of the experiment. The heat transfer coefficient ratio is used to evaluate the level of heating transfer. Two experimental vanes’ (A and B) film holes are both arranged in 6 rows of holes. There are 15 holes in each row. And only the position of the fan-shaped hole is different. Experimental conditions include the mainstream Reynolds number (Re=151,000) based on chord length and inlet velocity, the turbulence intensities (Tu=0.77%, 16.9%), and the mass flux ratios ( = 0.4%, 0.8%, 1.6%).

The findings show that when the mass flux ratio increases to a point, the film cooling effectiveness does not improve. Increasing the turbulence intensity leads to a decrease in the film cooling effectiveness except for Vane B. Using the coupling of PSP and TLC to solve the heat transfer coefficient can get credible results. The turbulence intensity and the arrangement of the film holes have obvious effects on the distribution of the heat transfer coefficient ratio.


Experimental Investigation on Cooling Performance of Impingement-Effusion Full Coverage Film on Suction Surface for Vane

Division / Sponsor:
International Gas Turbine Institute (IGTI)

Paper Proceedings: https://asmedigitalcollection.asme.org/GT/GT2020/volume/84058

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