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Small gas turbine combustor study - Combustor liner evaluationA reverse flow combustor liner constructed of Lamilloy (a multilaminate transpiration type material) is compared both analytically and experimentally with a conventional splash film-cooled design with the same combustor configuration. Comparison of selected critical combustor panels indicated that it was possible to maintain the liner temperature similar between the two configurations using 50 percent less coolant for the Lamilloy as compared with the reference film-cooled combustor. Additional benefits indicated improvement in outlet temperature distribution and NOx emission level.
Document ID
19830035445
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Norgren, C. T.
(NASA Lewis Research Center Cleveland, OH, United States)
Riddlebaugh, S. M.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 11, 2013
Publication Date
January 1, 1983
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 83-0337
Meeting Information
Meeting: American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting
Location: Reno, NV
Start Date: January 10, 1983
End Date: January 13, 1983
Accession Number
83A16663
Distribution Limits
Public
Copyright
Other

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