A sleeve assembly for a combustion system is provided. The sleeve assembly includes a liner defining a combustion chamber having a flow axis and a primary combustion zone. The liner has a forward end and an aft end such that the liner circumscribes the flow axis. The sleeve assembly also includes a shell circumscribing the liner such that a cooling duct is defined between the liner and the shell. The shell includes a unisleeve having a forward end and an aft end. The aft end of the unisleeve is positioned axially upstream of the aft end of the liner, defining a gap between the aft end of the liner and the aft end of the unisleeve. The unisleeve is mounted to the liner at circumferentially spaced locations along an axial plane between the forward end and the aft end of the unisleeve.

A combustor assembly for a gas turbine engine is provided. The combustor assembly generally includes a liner at least partially defining a combustion chamber and having an inner wall defining an inner opening and an outer wall defining an outer opening. A boss is defined by the inner wall and extends around the inner opening toward the outer wall. A body of a ferrule extends along an axial direction through the outer opening and defines a central bore in fluid communication with the combustion chamber. A radial flange extends from the body along a radial direction and is positioned between the inner wall and the outer wall. The flange defines a flange diameter that is greater than an internal diameter of the outer opening such that the ferrule may slide along the radial direction but is restrained in the axial direction.

A combustor assembly for a gas turbine engine defining a radial direction and a circumferential direction includes a liner assembly at least partially defining a combustion chamber and including at least one liner extending between a downstream end and an upstream end, the downstream end of the at least one liner defining a radial opening and an interface surface extending along the circumferential direction and along the radial direction; and a seal member including a body, a flange, and a radial element, the body defining a body surface extending along the radial direction and positioned adjacent the interface surface of the at least one liner, the flange extending forward from the body, and the radial element coupled to the flange and extending into the radial opening defined by the at least one liner.

A turbomachine includes a compressor and a turbine with a burner and a combustor between the compressor and the turbine. The burner is downstream of the compressor and upstream of the turbine. The burner is connected to the combustor at a front panel of the burner. The front panel includes a frame, a rim extending around a central aperture within the frame, and a seal segment. The frame, the rim, and the seal segment are all integrally formed as a single unitary body.

A combustor for a gas turbine engine includes a forward liner segment and an aft liner segment positioned downstream from the forward liner segment relative to a direction of flow through the combustor. The forward and aft liner segments at least partially define a combustion chamber. Furthermore, the combustor includes a dilution slot frame positioned between the forward and aft liner segments along a longitudinal centerline of the gas turbine engine. Moreover, the dilution slot frame defines a plurality of dilution slots spaced apart from each other along a circumferential direction of the gas turbine engine such that the plurality of dilution slots provides an annular ring of dilution air to the combustion chamber.

An embodiment of a combustor for a gas turbine engine includes a combustor case, a combustor liner disposed within the combustor case, a fuel nozzle, and a torch igniter within the combustor case. The torch igniter includes a combustion chamber, a cap defining the upstream end of the combustion chamber, a tip defining the downstream end of the combustion chamber, an annular igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, and an outlet passage within the tip that fluidly connects the combustion chamber to the combustor. The tip is mounted through the combustor liner, the cap is downstream of the tip, and the torch igniter is downstream of the fuel nozzle and disposed radially between the combustor liner and the combustor case.

A sleeve assembly for a combustion system includes a first duct including a first circumferential surface and a second duct including a second circumferential surface. The first circumferential surface radially overlaps the second circumferential surface such that the first duct and the second duct collectively define a continuous combustion chamber therein. The continuous combustion chamber is configured to receive high temperature gases flowing therethrough. The sleeve assembly further includes a wear insert removably coupled to the first circumferential surface and extending radially therefrom to engage the second circumferential surface.

A guide plate for a swirler assembly is disclosed. In various embodiments, the guide plate includes a guide plate flange configured for engagement with a swirler body having a swirler inlet; and a guide plate collar, the guide plate collar having an aft protrusion with respect to an axial direction extending through the swirler body, the aft protrusion having an aft protrusion tip position configured to be equal to or extend downstream of a swirler inlet forward position with respect to the axial direction and a radially outer surface that forms a radially outer surface angle greater than ninety degrees with respect to a radial direction.

A combustor assembly for a heat engine is generally provided. The combustor assembly includes a liner wall defining a combustion chamber, and a deflector assembly. The deflector assembly includes a radially extended first wall disposed adjacent to the combustion chamber, and further an axially extended second wall disposed forward of the first wall and adjacent thereto. The second wall is coupled to the liner wall.

A combustion chamber for a gas turbomachine. The combustion chamber comprising inner and outer walls, a chamber bottom, and a heat shield arranged downstream of the chamber bottom, to protect it thermally. The inner and outer walls and the heat shield form a one-piece unit.