Simultaneous film and convection cooling of a plate inserted in the exhaust stream of a gas turbine combustor
by Cecil J. Marek and Albert J. Juhasz.

Description

Main Author

Marek, Cecil J.

Related Names

Juhasz, Albert J.
United States. National Aeronautics and Space Administration.
Lewis Research Center.

Language(s)

English

Published

Washington, D.C. : National Aeronautics and Space Administration ; 1973.

Subjects

Combustion chambers > Combustion chambers / Materials > Combustion chambers / Materials / Cooling.
Gas-turbines > Gas-turbines / Combustion.

Summary

Data were obtained on a parallel-flow film- and convection-cooled test section placed in the exhaust stream of a rectangular-sector combustor. The combustor was operated at atmospheric pressure and at exhaust temperatures of 589 and 1033 K (600 and 1400 F). The cooling air was at ambient pressure and temperature. Test results indicate that it is better to use combined film and convection cooling rather than either film or convection cooling alone for a fixed total coolant flow. An optimum ratio of film to convection cooling flow rates was determined for the particular geometry tested. The experimental results compared well with calculated results.

Note

Prepared at Lewis Research Center.
Cover title.

Physical Description

iii, 34 p. : ill. ; 27 cm.

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