Patent ID: 11913645
Assignee: GENERAL ELECTRIC COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 0:
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.