Combustor assembly for a turbine engine
A combustor assembly for a gas turbine engine defining a radial direction and a circumferential direction includes a liner assembly at least partially defining a combustion chamber and including at least one liner formed of a ceramic matrix composite material and extending between a downstream end and an upstream end, the downstream end of the at least one liner defining an interface surface extending along the circumferential direction; and a seal member also formed of a ceramic matrix composite material and bonded to the interface surface of the at least one liner, the seal member defining a downstream surface for contacting an adjacent component to form a seal with the adjacent component.
1. A combustor assembly for a gas turbine engine defining an axial direction, a radial direction and a circumferential direction, the combustor assembly comprising:
a liner assembly at least partially defining a combustion chamber and comprising at least one liner formed of a ceramic matrix composite material and extending between a downstream end and an upstream end, the downstream end of the at least one liner defining an interface surface extending along the axial direction and extending along the circumferential direction; and
a seal member formed of a ceramic matrix composite material and bonded to the interface surface of the at least one liner at a body surface extending along the axial direction, the seal member defining a downstream surface for contacting an adjacent component to form a seal with the adjacent component,
wherein the body surface is a farthest inward surface in the radial direction of the seal member that extends in the axial direction.
2. The combustor assembly of claim 1 , wherein the at least one liner of the liner assembly is formed of a plurality of silicon carbide plies, and wherein the seal member is also formed of a plurality of silicon carbide plies.
3. The combustor assembly of claim 2 , wherein the seal member is bonded to the interface surface of the at least one liner using a silicone-based bonding material extending entirely across the body surface in the axial direction.
4. The combustor assembly of claim 1 , wherein the interface surface of the at least one liner extends continuously along the circumferential direction to form a complete loop.
5. The combustor assembly of claim 4 , wherein the at least one liner comprises a plurality of liners spaced along the circumferential direction, and wherein the plurality of liners together extend continuously along the circumferential direction.
6. The combustor assembly of claim 1 , wherein the at least one liner is an at least one outer liner, wherein the downstream surface of the seal member is positioned at least partially outward of the at least one outer liner along the radial direction and at least partially downstream of the at least one outer liner along the axial direction.
7. The combustor assembly of claim 1 , wherein the at least one liner defines a downstream edge, and wherein the interface surface of the at least one liner is positioned at the downstream edge.
8. The combustor assembly of claim 1 , wherein the seal member is a first seal member of a plurality of seal members bonded to the interface surface of the at least one liner, and wherein the plurality of seal members are arranged along the circumferential direction and together form a continuous circumferential seal ring.
9. The combustor assembly of claim 1 , wherein the seal member extends continuously along the circumferential direction to form a circumferential seal ring.
10. The combustor assembly of claim 1 , wherein the at least one liner comprises a plurality of liners spaced along the circumferential direction, and wherein the plurality of liners together define the interface surface.
11. The combustor assembly of claim 10 , wherein the interface surface of the plurality of liners extends continuously along the circumferential direction to form a complete loop.
12. A gas turbine engine defining an axial direction, a radial direction, and a circumferential direction, the gas turbine engine comprising:
a compressor section, a combustor section, and a turbine section arranged in serial flow order, the combustor section comprising a combustor assembly, the combustor assembly comprising:
a liner assembly at least partially defining a combustion chamber and comprising at least one liner formed of a ceramic matrix composite material and extending between a downstream end and an upstream end, the downstream end of the at least one liner defining an interface surface extending along the axial direction and extending along the circumferential direction; and
a seal member formed of a ceramic matrix composite material and bonded to the interface surface of the at least one liner at a body surface extending along the axial direction, the seal member defining a downstream surface for contacting an adjacent component to form a seal with the adjacent component,
wherein the body surface is a farthest inward surface in the radial direction of the seal member that extends in the axial direction.
13. The gas turbine engine of claim 12 , wherein the seal member is bonded to the interface surface of the at least one liner using a silicone-based bonding material extending entirely across the body surface in the axial direction.
14. The gas turbine engine of claim 12 , wherein the interface surface of the at least one liner extends continuously along the circumferential direction to form a complete loop.
15. The gas turbine engine of claim 14 , wherein the at least one liner comprises a plurality of liners spaced along the circumferential direction, and wherein the plurality of liners together extend continuously along the circumferential direction.
16. The gas turbine engine of claim 12 , wherein the at least one liner is an at least one outer liner, wherein the downstream surface of the seal member is positioned at least partially outward of the at least one outer liner along the radial direction and at least partially downstream of the at least one outer liner along the axial direction.
17. The gas turbine engine of claim 12 , wherein the at least one liner defines a downstream edge, and wherein the interface surface of the at least one liner is positioned at the downstream edge.
18. The gas turbine engine of claim 12 , wherein the seal member is a first seal member of a plurality of seal members bonded to the interface surface of the at least one liner, and wherein the plurality of seal members are arranged along the circumferential direction and together form a continuous circumferential seal ring.
19. The gas turbine engine of claim 12 , wherein the seal member extends continuously along the circumferential direction to form a circumferential seal ring.
20. The gas turbine engine of claim 12 , wherein the at least one liner comprises a plurality of liners spaced along the circumferential direction, wherein the plurality of liners together define the interface surface, and wherein the interface surface of the plurality of liners extend continuously along the circumferential direction to form a complete loop.