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A combustor assembly for a gas turbine engine is provided. The combustor assembly includes a liner at least partially defining a combustion chamber and extending between an aft end a forward end generally along an axial direction. The combustor assembly also includes an annular dome including an enc

A combustor assembly for a gas turbine engine is provided. The combustor assembly includes a liner at least partially defining a combustion chamber and extending between an aft end a forward end generally along an axial direction. The combustor assembly also includes an annular dome including an enclosed surface defining a slot for receipt of the forward end of the liner. A cap is positioned at the forward end of the liner and at least partially positioned within the slot defined by the enclosed surface of the annular dome. The cap includes a surface configured to contact at least one of the enclosed surface of the annular dome and the forward end of the liner. Such a configuration may form a substantially airtight seal between the forward end of the liner and the annular dome despite a relative thermal expansion between the components.

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1. A combustor assembly for a gas turbine engine defining an axial direction, the combustor assembly comprising: a liner at least partially defining a combustion chamber and extending between an aft end and a forward end generally along the axial direction;an annular dome including an enclosed surfa

1. A combustor assembly for a gas turbine engine defining an axial direction, the combustor assembly comprising: a liner at least partially defining a combustion chamber and extending between an aft end and a forward end generally along the axial direction;an annular dome including an enclosed surface defining a slot for receipt of the forward end of the liner;a cap positioned at the forward end of the liner and at least partially positioned within the slot defined by the enclosed surface of the annular dome, the cap including a first surface configured to contact at least one of the enclosed surface of the annular dome or the forward end of the liner, wherein the cap is positioned over the forward end of the liner, and wherein the first surface of the cap is an end surface configured to contact the enclosed surface of the annular dome; anda resilient member positioned in a gap defined between the cap and the forward end of the liner, wherein the resilient member is configured to form a first seal between the cap and the forward end of the liner, and wherein the resilient member is also configured to press the first surface of the cap against the enclosed surface of the annular dome to form a second seal between the cap and the enclosed surface,wherein the cap further comprises: a first arm extending axially;a second arm extending substantially parallel with the first arm; anda base extending radially between the first arm and second arm and defining an inside surface and an outside surface,wherein the first and second arms together define the radially inner and radially outer boundaries of the gap in which the resilient member is positioned, and wherein the first arm and the second arm each define one or more cap openings for receiving a mounting assembly for mounting the forward end of the liner to the annular dome. 2. The combustor assembly of claim 1, wherein the resilient member is a rope seal including a silicone core. 3. The combustor assembly of claim 1, wherein the liner is an outer liner and wherein the annular dome is an outer annular dome. 4. The combustor assembly of claim 1, wherein the liner is an inner liner and wherein the annular dome is an inner annular dome. 5. The combustor assembly of claim 2, wherein the liner is comprised of a ceramic matrix composite material. 6. The combustor assembly of claim 5, wherein the annular dome is comprised of a metal material. 7. The combustor assembly of claim 5, wherein the annular dome includes a base plate and a yoke, the base plate and the yoke extending parallel to one another, the enclosed surface of the annular dome including a second surface of the base plate and a third surface of the yoke. 8. The combustor assembly of claim 7, further comprising: the mounting assembly extending through the yoke of the annular dome, through the forward end of the liner, and through the base plate of the annular dome, wherein the mounting assembly attaches the liner to the annular dome. 9. The combustor assembly of claim 8, wherein the mounting assembly includes a pin and a bushing, wherein the pin extends through the yoke, the forward end of the liner, and the base plate, and wherein the bushing is positioned around the pin within the slot and pressed between the yoke and the base plate. 10. The combustor assembly of claim 1, wherein the first arm, the second arm, and the base are all formed integrally of a metal material or a ceramic matrix composite (CMC) material. 11. The combustor assembly of claim 1, further comprising a plurality of fuel air mixers spaced along a circumferential direction within the annular dome. 12. The combustor assembly of claim 9, further comprising a metal grommet positioned around the bushing within a liner opening defined in the forward end of the liner. 13. A gas turbine engine defining an axial direction, the gas turbine engine comprising: a compressor section;a turbine section mechanically coupled to the compressor section through a shaft; anda combustor assembly disposed between the compressor section and the turbine section, the combustor assembly includinga liner at least partially defining a combustion chamber and extending between an aft end and a forward end generally along the axial direction;an annular dome including an enclosed surface defining a slot for receipt of the forward end of the liner;a cap positioned at the forward end of the liner and at least partially positioned within the slot defined by the enclosed surface of the annular dome, the cap including a first surface configured to contact at least one of the enclosed surface of the annular dome or the forward end of the liner, wherein the cap is positioned over the forward end of the liner, and wherein the first surface of the cap is an end surface configured to contact the enclosed surface of the annular dome; anda resilient member positioned in a gap defined between the cap and the forward end of the liner, wherein the resilient member is configured to form a first seal between the cap and the forward end of the liner, and wherein the resilient member is also configured to press the first surface of the cap against the enclosed surface of the annular dome to form a second seal between the cap and the enclosed surface,wherein the cap further comprises: a first arm extending axially;a second arm extending substantially parallel with the first arm; anda base extending radially between the first arm and second arm and defining an inside surface and an outside surface,wherein the first and second arms together define the radially inner and radially outer boundaries of the gap in which the resilient member is positioned, and wherein the first arm and the second arm each define one or more cap openings for receiving a mounting assembly for mounting the forward end of the liner to the annular dome.