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Advanced liner-cooling techniques for gas turbine combustorsComponent research for advanced small gas turbine engines is currently underway at the NASA Lewis Research Center. As part of this program, a basic reverse-flow combustor geometry was being maintained while different advanced liner wall cooling techniques were investigated. Performance and liner cooling effectiveness of the experimental combustor configuration featuring counter-flow film-cooled panels is presented and compared with two previously reported combustors featuring: splash film-cooled liner walls; and transpiration cooled liner walls (Lamilloy).
Document ID
19850012805
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
September 5, 2013
Publication Date
January 1, 1985
Subject Category
Aerodynamics
Report/Patent Number
E-2475
NASA-TM-86952
NAS 1.15:86952
Meeting Information
Meeting: Joint Propulsion Conf.
Location: Monterey, CA
Country: United States
Start Date: July 8, 1985
End Date: July 10, 1985
Sponsors: SAE, AIAA, ASME
Accession Number
85N21115
Funding Number(s)
PROJECT: RTOP 535-06-12
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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