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
19850057552
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)