Fuel injectors for multipoint arrays
A combustor dome system includes an annular combustor dome defining a main axis therethrough. The combustor dome includes opposed upstream and downstream faces, wherein the upstream face is configured to face upstream toward a compressor discharge space, wherein the downstream face is configured to face downstream toward a combustor space. The downstream face has a curved cross-sectional profile. A plurality of nozzles extends at least partially through the combustor dome from the upstream face to the downstream face for injection of fuel into the combustor space. A fuel manifold is in fluid communication with the plurality of nozzles.
1. A combustor dome system comprising:
an annular combustor dome defining a main axis therethrough, the combustor dome including opposed upstream and downstream faces, wherein the upstream face is configured to face upstream toward a compressor discharge space, wherein the downstream face is configured to face downstream toward a combustor space, and wherein the downstream face has a curved cross-sectional profile;
a plurality of nozzles extending at least partially through the combustor dome from the upstream face to the downstream face for injection of fuel into the combustor space; and
a nozzle assembly defining a fuel circuit therethrough, wherein the nozzle assembly extends along an injection axis;
a plurality of supports extending from the nozzle assembly to engage the combustor dome wherein at least one of the supports includes a fuel feed passage fluidly connected with the fuel circuit of the nozzle assembly for fluid communication of fuel from a fuel manifold into the fuel circuit.
2. The system as recited in claim 1 , wherein the annular dome includes an upper cross-section and a lower-cross section, wherein in each of the upper and lower cross-sections, there is symmetry in the curved cross-sectional profile across a cylinder defined about the main axis and extending downstream from the downstream face of the combustor dome.
3. The system as recited in claim 1 , wherein a cylinder defined about the main axis and extending downstream from downstream face of the combustor dome divides the combustor space into an inner space inside the cylinder and an outboard space outside the cylinder, wherein some of the plurality of nozzles are radially inboard relative to the cylinder, and some of the plurality of nozzles are radially outboard relative to the cylinder.
4. The system as recited in claim 3 , wherein the nozzles of the plurality of nozzles that are radially inboard of the cylinder are angled outward toward the cylinder.
5. The system as recited in claim 3 , wherein the nozzles of the plurality of nozzles that are radially outboard of the cylinder are angled inward toward the cylinder.
6. The system as recited in claim 1 ,
wherein each support in the plurality of supports includes a side face, wherein the side faces are circumferentially spaced apart around an insertion axis that is oblique relative to the injection axis and parallel to the main axis.
7. The system as recited in claim 6 , wherein each side face is aligned with the insertion axis.
8. The system as recited in claim 6 , wherein each support in the plurality of supports is aerodynamically aligned with the injection axis.
9. The system as recited in claim 6 , wherein at least one of the supports is swept on a non-perpendicular angle relative to the injection axis.
10. The system as recited in claim 6 , wherein the combustor dome defines an outer air flow passage therethrough for each nozzle aligned with the injection axis thereof, wherein the nozzle assembly is suspended in an outer air flow passage of the combustor dome with an outer air circuit defined through the outer air flow passage outboard of the nozzle assembly.
11. The system of claim 6 , wherein the supports provide alignment and concentricity for the nozzles.
12. The system of claim 6 , wherein each support includes an end face that faces radially outward relative to the insertion axis, wherein each end face is contained in a respective plane that is parallel to the insertion axis and oblique to the injection axis.
13. The system as recited in claim 1 , wherein the fuel manifold is supported by fuel conduits that provide fluid communication from the fuel manifold to the plurality of nozzles, wherein the manifold holds the plurality of nozzles in place axially and forces the plurality of nozzles up against the dome to maintain a constant gap.
14. A combustor dome system comprising:
an annular combustor dome defining a main axis therethrough, the combustor dome including opposed upstream and downstream faces, wherein the upstream face is configured to face upstream toward a compressor discharge space, wherein the downstream face is configured to face downstream toward a combustor space, and wherein the downstream face has a curved cross-sectional profile;
a plurality of nozzles extending at least partially through the combustor dome from the upstream face to the downstream face for injection of fuel into the combustor space, each nozzle in the plurality of nozzles further comprising:
a nozzle assembly defining at least one of a fuel circuit and an air circuit therethrough, wherein the nozzle assembly extends along an injection axis; and
a plurality of supports extending from the nozzle assembly to engage the combustor dome, the supports being circumferentially spaced apart from one another about the injection axis, wherein each support in the plurality of supports includes a side face, wherein the side faces are circumferentially spaced apart around an insertion axis that is oblique relative to the injection axis and parallel to the main axis wherein at least one of the supports includes a fuel feed passage fluidly connected with a fuel circuit of the nozzle assembly for fluid communication of fuel from a manifold into the fuel circuit; and
a fuel manifold in fluid communication with the plurality of nozzles.
15. The system as recited in claim 14 , wherein the combustor dome defines an outer air flow passage therethrough for each nozzle aligned with the injection axis thereof, wherein the nozzle assembly is suspended in the outer air flow passage of the combustor dome with an outer second air circuit defined through the outer air flow passage outboard of the nozzle assembly.
16. The system of claim 14 , wherein the supports provide alignment and concentricity for the nozzles.
17. The system of claim 14 , wherein each support includes an end face that faces radially outward relative to the insertion axis, wherein each end face is contained in a respective plane that is parallel to the insertion axis and oblique to the injection axis.
18. The system as recited in claim 14 , wherein each side face is aligned with the insertion axis.
19. The system as recited in claim 14 , wherein each support in the plurality of supports is aerodynamically aligned with the injection axis.
20. The system as recited in claim 1 , wherein the fuel manifold is supported by fuel conduits that provide fluid communication from the fuel manifold to the plurality of nozzles, wherein the manifold holds the plurality of nozzles in place axially and forces the plurality of nozzles up against the dome to maintain a constant gap.