Combustor assembly
A combustor assembly for a gas turbine engine is includes a liner and a combustor dome formed of a ceramic matrix composite material. The combustor dome and liner together define at least in part a combustion chamber. The combustor dome extends along a circumferential direction and defines one or more openings, the combustor dome is configured to receive one or more fuel-air injector hardware assemblies in or through the one or more openings.
1. A combustor assembly for a gas turbine engine defining a circumferential direction, the combustor assembly comprising:
a liner;
a combustor dome formed of a ceramic matrix composite material, the combustor dome and the liner together defining at least in part a combustion chamber, the combustor dome defining an opening; and
a fuel-air injector hardware assembly attached directly to the combustor dome and extending into or through the opening;
wherein the combustor dome includes a raised boss extending around the opening in the combustor dome for mounting the fuel-air injector hardware assembly directly to the combustor dome.
2. The combustor assembly of claim 1 , wherein the fuel-air injector hardware assembly comprises a plurality of fuel-air injector hardware assemblies, and wherein at least one fuel-air injector hardware assembly is attached directly to the combustor dome independently of an adjacent fuel-air injector hardware assembly.
3. The combustor assembly of claim 1 , wherein the fuel-air injector hardware assembly comprises a plurality of fuel-air injector hardware assemblies, and wherein each fuel-air injector hardware assembly is attached directly to the combustor dome independently of the adjacent fuel-air injector hardware assemblies.
4. The combustor assembly of claim 1 , wherein the combustor dome defines a hot side and a cold side, and wherein the fuel-air injector hardware assembly is attached directly to the hot side of the combustor dome and directly to the cold side of the combustor dome.
5. The combustor assembly of claim 1 , wherein the combustor dome extends continuously along the circumferential direction and is formed integrally of a continuous piece of ceramic matrix composite material.
6. The combustor assembly of claim 1 , wherein the combustor dome further defines a plurality of openings, and wherein the plurality of openings are substantially evenly spaced along the circumferential direction.
7. The combustor assembly of claim 1 , wherein the combustor dome defines a hot side and a cold side, and wherein the combustor dome defines a plurality of cooling holes extending through the combustor dome from the cold side to the hot side to allow for a flow of cooling air.
8. The combustor assembly of claim 7 , wherein the plurality of cooling holes includes a plurality of cooling holes extending around the opening for receiving the fuel-air injector hardware assembly.
9. The combustor assembly of claim 1 , wherein the combustor dome comprises a transition portion and a back wall, wherein the transition portion extends from the back wall of the combustor dome towards the liner, and wherein the transition portion defines an angle greater than 90 degrees and less than 180 relative to the back wall.
10. A combustor assembly for a gas turbine engine defining a circumferential direction, the combustor assembly comprising:
a liner; and
a combustor dome formed of a ceramic matrix composite material, the combustor dome and the liner together defining at least in part a combustion chamber, the combustor dome defining a plurality of openings for receiving a respective plurality of fuel-air injector hardware assemblies,
wherein the combustor dome extends along the circumferential direction and is formed integrally of a continuous piece of ceramic matrix composite material;
wherein the combustor dome includes a raised boss extending around each of the plurality of openings in the combustor dome for mounting a respective fuel-air injector hardware assembly directly to the combustor dome.
11. The combustor assembly of claim 10 , wherein the combustor dome extends continuously along the circumferential direction to define an annular shape.
12. The combustor assembly of claim 10 , wherein the plurality of openings are substantially evenly spaced along the circumferential direction.
13. The combustor assembly of claim 10 , further comprising:
a plurality of fuel-air injector hardware assemblies, each fuel-air injector hardware assembly attached directly to the combustor dome at a respective one of the plurality of openings.
14. The combustor assembly of claim 13 , wherein each fuel-air injector hardware assembly is attached directly to the combustor dome independently of an adjacent fuel-air injector hardware assembly.
15. The combustor assembly of claim 13 , wherein at least one fuel-air injector hardware assembly is attached directly to the combustor dome independently of an adjacent fuel-air injector hardware assembly.
16. The combustor assembly of claim 10 , wherein the combustor dome defines a hot side facing the combustion chamber and a cold side opposite the hot side, and wherein the combustor dome includes an environmental protective coating on at least one of the hot side or the cold side.
17. The combustor assembly of claim 10 , wherein the combustor dome defines a hot side and a cold side, and wherein the combustor dome defines a plurality of cooling holes extending through the combustor dome from the cold side to the hot side to allow for a flow of cooling air.
18. The combustor assembly of claim 10 , wherein the combustor dome includes a groove extending around each of the plurality of openings in the combustor dome on the hot side of the combustor dome, wherein the raised boss and the groove of the combustor dome are configured for assisting with mounting the fuel-air injector hardware assemblies directly to the combustor dome.