Abstract: 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.

Abstract: A gas turbine engine and combustor assembly are provided, the combustor assembly including a first liner and a second liner together defining at least in part a combustion chamber, wherein the first liner and the second liner are separated by a gap along the longitudinal direction, and wherein the first liner is forward of the second liner relative to a flow of fluid through the combustion chamber along the longitudinal direction, and wherein the gap is extended along the circumferential direction.

Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber; and an intermediate member disposed at least partially between the forward and aft liner segments and extending in the circumferential direction.

Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a liner at least partially defining a combustion chamber of the gas turbine engine, wherein the liner comprises a looped feature.

Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a liner at least partially defining a combustion chamber, the liner further defining a gap; and an intermediate member disposed at least partially within the gap of the liner and in fluid communication with the combustion chamber, wherein the intermediate member is retained at a relatively fixed position with respect to the liner by a support extending between the intermediate member and a case of the gas turbine engine.

Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a liner at least partially defining a combustion chamber, the liner including a dilution slot in fluid communication with the combustion chamber; and one or more guides configured to redirect cooling medium into the dilution slot.

Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; and an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber, wherein the forward and aft liner segments are coupled together at a moveable interface.

Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber; and a fence disposed between the forward and aft liner segments, wherein the fence extends in the circumferential direction, and wherein the fence extends into the combustion chamber along the radial direction.

Abstract: A mixer assembly having a plurality of mixer vanes, each of the plurality of mixer vanes having a first end, a second end, and a body portion extending between the first end and the second end, the body portion having a length, a width, a thickness, a cross-sectional area, a curvature, and a twist, wherein each of the plurality of mixer vanes has a 3-dimensional shape defined by the length, width, thickness, cross-sectional area, curvature, and twist of the body portion, and wherein at least one of the plurality of mixer vanes has a non-uniform 3-dimensional shape.

Abstract: 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.

Abstract: 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.

Abstract: A combustor for a gas turbine engine includes an inner liner and an outer liner positioned outward of the inner liner along the radial direction such that a combustion chamber is defined between the inner and outer liners. Furthermore, the combustor includes a fuel nozzle configured to supply fuel to the combustion chamber. Moreover, the combustor includes a bristle pack having a base plate and a plurality of bristles extending outward from the base plate such that the bristle pack forms at least a portion of at least one of a heat shield coupled to the fuel nozzle, a deflector of the combustor, or a flare of the combustor.

Abstract: A fluid manifold assembly for a gas turbine engine, the fluid manifold assembly including a walled conduit assembly defining a fluid passage therewithin. The fluid passage defines a pair of ends separated by a length. A connecting conduit is coupled to the end of the fluid passage and to the length of the fluid passage.

Abstract: A gas turbine engine combustor includes a liner defining at least in part a combustion chamber, a first side exposed to the combustion chamber, a second side opposite the first side, and a dilution hole extending from the second side to the first side. The liner includes an airflow feature on the first side of the liner adjacent to the dilution hole and extending into the combustion chamber to increase a cooling of the liner.

Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly includes a liner defining a combustion chamber therewithin and a pressure plenum surrounding the liner. The liner defines an opening. The liner includes a walled chute disposed at least partially within the opening. The walled chute defines an inner surface at least partially defining a jet destabilizer.

Abstract: A fluid manifold assembly for a gas turbine engine, the fluid manifold assembly including a walled conduit assembly defining a fluid passage therewithin. The fluid passage defines a pair of ends separated by a length. A connecting conduit is coupled to the end of the fluid passage and to the length of the fluid passage.

Abstract: A gas turbine engine combustor includes a liner defining at least in part a combustion chamber, a first side exposed to the combustion chamber, a second side opposite the first side, and a dilution hole extending from the second side to the first side. The liner includes an airflow feature on the first side of the liner adjacent to the dilution hole and extending into the combustion chamber to increase a cooling of the liner.

Abstract: A deflector for a gas turbine engine combustor. The combustor includes a liner defining a combustion zone and a mixer assembly configured to supply the combustion zone with a predetermined mixture of fuel and air. The deflector includes a deflector body configured to couple to the liner. The deflector body includes a first surface configured to reflect thermal radiation to a predetermined focal area, and an aperture extending through the deflector body and configured to receive the mixer assembly therethrough.