Combustor assembly including a fuel injection system for a turbomachine

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 includes a plurality of guide vanes extending between the second inlet and the second outlet;
• wherein the plurality of guide vanes are arranged in an annular array;
• wherein the fuel outlet of the second plenum is arranged between the plurality of guide vanes and the second outlet;
• wherein the combustor assembly further includes:
• a fuel injector extending into the fuel outlet of the second annular plenum, the fuel injector including a first portion extending radially relative to the axial axis and a second portion extending from the first portion at a non-zero angle relative to the axial axis;
• wherein the plurality of guide vanes extend at a first non-zero angle relative to the axial axis and the second portion of the fuel injector extends at a second non-zero angle relative to the axial axis, the second non-zero angle being substantially identical to the first non-zero angle.

A turbomachine comprising:

• a compressor;
• a turbine mechanically connected to the compressor;
• and
• a combustor assembly fluidically connected to the compressor and the turbine, the combustor assembly 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.

A turbomachine comprising:

• a compressor;
• a turbine mechanically connected to the compressor;
• and
• a combustor assembly fluidically connected to the compressor and the turbine, the combustor assembly 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 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 includes a plurality of guide vanes extending between the second inlet and the second outlet;
• wherein the plurality of guide vanes are arranged in an annular array,
• wherein the fuel outlet is arranged between the plurality of guide vanes and the second outlet;
• wherein the turbomachine further includes a fuel injector extending into the fuel outlet of the second annular plenum, the fuel injector including a first portion extending radially relative to the axial axis and a second portion extending from the first portion at a non-zero angle relative to the axial axis;
• and
• wherein the plurality of guide vanes extend at a first non-zero angle relative to the axial axis and the second portion of the fuel injector extends at a second non-zero angle relative to the axial axis, the second non-zero angle being substantially identical to the first non-zero angle.