US 12,392,490 B1
Combustor assembly including a fuel injection system for a turbomachine
Jason A. Ryon, Carlisle, IA (US); and Philip Buelow, West Des Moines, IA (US)
Assigned to COLLINS ENGINE NOZZLES, INC., Des Moines, IA (US)
Filed by Collins Engine Nozzles, Inc., Des Moines, IA (US)
Filed on Feb. 15, 2024, as Appl. No. 18/442,159.
Int. Cl. F23R 3/14 (2006.01); F02C 7/22 (2006.01); F23D 5/06 (2006.01); F23R 3/28 (2006.01)
CPC F23R 3/14 (2013.01) [F02C 7/22 (2013.01); F23D 5/06 (2013.01); F23R 3/286 (2013.01); F05D 2240/35 (2013.01)] 18 Claims
OG exemplary drawing
 
1. A combustor assembly for a turbomachine comprising:
a combustor housing defining a combustion chamber, the combustor housing including an inlet portion, an outlet portion, and an axial axis extending between the inlet portion and the outlet portion;
a first annular plenum arranged at the inlet portion, the first annular plenum including a first inlet and a first outlet; and
a second annular plenum, radially spaced from the first annular plenum, is arranged at the inlet portion, the second annular plenum including a second inlet, a second outlet, a vortex inducing member arranged between the second inlet and the second outlet, and a fuel outlet, the second outlet including a pre-filming surface that forms an annular ring of fuel that enters the second annular plenum through the fuel outlet of the second annular plenum and passes from the second annular plenum into a swirling fluid passing through the first outlet and the second outlet;
wherein the vortex inducing member comprises a guide ring arranged between the first annular plenum and the second annular plenum, the guide ring including a plurality of fuel guide slots that direct fuel from the fuel outlet along a pathway towards the pre-filming surface, the pathway including an axial component and a circumferential component.