NASA Technical Reports Server (NTRS) : Analysis pdf

NASA Technical Reports Server (NTRS) : Analysis

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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

• Creator/s: NASA Technical Reports Server (NTRS
• Date: 1/1/1972
• Year: 1972
• Book Topics/Themes: NASA Technical Reports Server (NTRS), FILM COOLING, GAS TURBINES, SWEAT COOLING, HEAT SINKS, HIGH PRESSURE, HIGH TEMPERATURE, Colladay, R. S

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