Analysis and comparison of wall cooling schemes for advanced gas turbine applications /
Raymond S. Colladay.

Description

Main Author

Colladay, Raymond S. (Raymond Strong)

Related Names

United States. National Aeronautics and Space Administration.
Lewis Research Center.

Language(s)

English

Published

Washington, D.C. : National Aeronautics and Space Administration, 1972.

Subjects

Cooling.
Turbines > Turbines / Cooling.
Gas-turbines.

Summary

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.

Note

Prepared at Lewis Research Center.
N72-14941.

Physical Description

41 p. : ill. ; 27 cm.

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