This paper describes recently completed and current advanced liner research applicable to advanced small gas turbine engines. Research relating to the evolution of fuel efficient small gas turbine engines capable of meeting future commercial and military aviation needs is currently underway at NASA Lewis Research Center. As part of this research, a reverse-flow combustor geometry was maintained while different advanced liner wall cooling techniques were investigated and compared to a baseline combustor. The performance of the combustosr featuring counter-flow film-cooled liner (CFFC) panels, transpiration cooled liner walls (TRANS), and compliant metal/ceramic (CMC) walls was obtained over a range of simulated flight conditions of a 16:1 pressure ratio gas turbine engine and fuel air ratios up to 0.034. All the combustors featured an identical fuel injection system, identical geometric configuration outline, and similar designed internal aerothermodynamics.
Liner cooling research at NASA Lewis Research Center
Erforschung der Auskleidungskuehlung im NASA Lewis Research Center
AIAA-Papers ; Jul ; 1-16
1987
16 Seiten, 10 Bilder, 1 Tabelle, 9 Quellen
Conference paper
English
Liner cooling research at NASA Lewis Research Center
AIAA | 1987
|NASA/Lewis Research Center Icing Research Program
NTRS | 1981
|Composites Research at NASA Lewis Research Center
NTIS | 1994
|