Small gas turbine combustor experimental study - Compliant metal/ceramic liner and performance evaluationCombustor research relating to the development of fuel efficient small gas turbine engines capable of meeting future commercial and military aviation needs is currently underway at NASA Lewis. As part of this combustor research, a basic reverse-flow combustor has been used to investigate advanced liner wall cooling techniques. Liner temperature, performance, and exhaust emissions of the experimental combustor utilizing compliant metal/ceramic liners were determined and compared with three previously reported combustors that featured: (1)splash film-cooled liner walls; (2) transpiration cooled liner walls; and (3) counter-flow film cooled panels.
Document ID
19860064873
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Acosta, W. A. (NASA Lewis Research Center; U.S. Army, Propulsion Directorate, Cleveland OH, United States)
Norgren, C. T. (NASA Lewis Research Center Cleveland, OH, United States)