Combustor assembly for a turbine engine

A combustor assembly for a gas turbine engine defining a centerline, an axial direction, and a radial direction, the combustor assembly comprising:

• a dome defining a slot;
• a liner formed of a ceramic matric composite material and at least partially defining a combustion chamber, the liner extending between an aft end and a forward end, the forward end of the liner configured to be received within the slot of the dome, the forward end comprising an opening, a radial interface surface, and an axial interface surface;
• an axial gap located between a forward surface of the dome and the radial interface surface;
• a radial gap located between an inner surface of the dome and the axial interface surface;
• and
• at least one mounting assembly configured to secure the liner to the dome, the at least one mounting assembly comprising:
• a grommet located in the opening in the liner, the grommet configured to reduce wear on the forward end of the liner;
• a bushing installed in the opening of the liner and within the grommet;
• a collar adjacent an outer surface of the liner;
• a pin inserted through the bushing and extending through the dome and the opening in the liner;
• and
• a nut adjacent the inner surface of the dome and configured to tighten on the pin.