Combustor assembly for a turbine engine

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 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, the seal member defining a downstream surface for contacting an adjacent component to form a seal with the adjacent component.