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Analysis and Comparison of Wall Cooling Schemes for Advanced Gas Turbine Applications

Raymond Strong Colladay

出版	National Aeronautics and Space Administration, 1972
URL	http://books.google.com.hk/books?id=dWUAXxME4awC&hl=&source=gbs_api
EBook	FULL_PUBLIC_DOMAIN

註釋

The relative performance of (1) counterflow film cooling, (2) parallel-flow film cooling, (3) convection cooling, (4) adiabatic film cooling, (5) transpiration cooling, and (6) full-coverage film cooling was investigated for heat loading conditions expected in future gas turbine engines. Assumed in the analysis were hot-gas conditions of 2200 K (3500 F) recovery temperature, 5 to 40 atmospheres total pressure, and 0.6 gas Mach number and a cooling air supply temperature of 811 K (1000 F). The first three cooling methods involve film cooling from slots. Counterflow and parallel flow describe the direction of convection cooling air along the inside surface of the wall relative to the main gas flow direction. The importance of utilizing the heat sink available in the coolant for convection cooling prior to film injection is illustrated.