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Thermal and flow analysis of a convection air-cooled ceramic coated porous metal concept for turbine vanesThe heat transfer and pressure drop through turbine vanes made of a sintered, porous metal coated with a thin layer of ceramic and convection cooled by spanwise flow of cooling air were analyzed. The analysis was made to determine the feasibility of using this concept for cooling very small turbines, primarily for short duration applications such as in missile engines. The analysis was made for gas conditions of approximately 10 and 40 atm and 1644 K and with turbine vanes made of felt type porous metals with relative densities from 0.2 to 0.6 and ceramic coating thicknesses of 0.076 to 0.254 mm.
Document ID
19810013526
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Stepka, F. S. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 4, 2013
Publication Date
January 1, 1981
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-TM-81749
E-815
Meeting Information
Meeting: Natl. Heat Transfer Conf.,
Location: Milwaukee, WI
Country: United States
Start Date: August 2, 1981
End Date: August 5, 1981
Sponsors: ASME, American Inst. of Chemical Engineers
Accession Number
81N22056
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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