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Performance of semi-transportation-cooled liner in high-temperature-rise combustorsResults from tests with the Lamilloy combustor liner are compared with results obtained from a conventionally designed, film cooled, step-louver liner. Operation of the Lamilloy liner with counterrotating swirl combustor fuel modules with mixing venturis was possible to a fuel-air ratio of 0.065 without obtaining excessive liner metal temperatures. At the 0.065 fuel-air condition the average liner metal temperature was 140 K and the maximum local temperature 280 K above the inlet air temperature. Combustion efficiency, pattern factor, and smoke data are discussed.
Document ID
19810012548
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Wear, J. D. (NASA Lewis Research Center Cleveland, OH, United States)
Trout, A. M. (NASA Lewis Research Center Cleveland, OH, United States)
Smith, J. M. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 4, 2013
Publication Date
March 1, 1981
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
E-494
NASA-TP-1806
Report Number: E-494
Report Number: NASA-TP-1806
Accession Number
81N21077
Funding Number(s)
PROJECT: RTOP 505-32-32
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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