Combustor Assembly For A Turbine Engine

Abstract: A combustor assembly (100) for a gas turbine engine is provided. The combustor assembly (100) includes a liner at least partially defining a combustion chamber (114) and extending between an aft end a forward end generally along an axial direction. The combustor assembly (100) also includes an annular dome including an enclosed surface defining a slot (122) 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 (122) 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. Fig.l

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