Short-length annular combustor for turbojet engines eliminates change of exit temperature profile. Individual scoops of full annular height control air distribution so that shifts in the radial velocity profile of air entering the combustor will not affect combustion process or alter exit temperature profile.
Gas turbine combustor insensitive to compressor outlet distortion
01.06.1970
Sonstige
Keine Angabe
Englisch
NTRS | 2011
|NTIS | 1969
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