Abstract: Embodiments of a combustor assembly for a turbine engine are generally provided. The combustor assembly includes a first separable portion defining a dome assembly, and a second separable portion defining a deflector assembly. The first separable portion and the second separable portion are coupled together at a fitted interface.

Abstract: 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.

Abstract: 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.

Abstract: Embodiments of a combustor assembly for a turbine engine are generally provided. The combustor assembly includes a first separable portion defining a dome assembly, and a second separable portion defining a deflector assembly. The first separable portion and the second separable portion are coupled together at a fitted interface.

Abstract: A heat engine including a wall assembly is generally provided. The wall assembly includes a plurality of radial walls coupled together via a connecting member. The radial wall defines a flow opening therethrough. A flow cavity is defined between the plurality of radial walls and the connecting member.

Abstract: The present subject matter provides a combustion system which comprising: a cowl; a deflector configurated to include a ring body, a plurality of swirlers integrated on the ring body and a plurality of arms integrally extending outward from the ring body; an annular inner liner attached with the cowl; and an annular outer liner attached with the cowl. The deflector is positioned between the inner liner and the outer liner; the deflector, the inner liner and the outer line define a combustion chamber thereamong. The deflector is attached to the cowl via the plurality of arms, but the arms are rigid enough to work together to fix the deflector with the cowl while allowing for thermal expansion flexibility therebetween at the same time.

Abstract: A combustor includes an outer liner, an inner liner, an annular cowl joining upstream ends of the outer and inner liners, and an annular deflector configured to shield the cowl from hot combustion gases in a combustion chamber defined between the outer liner, the inner liner and the deflector. The cowl has at least one opening for introduction of fuel and compressed air. The deflector includes at least one swirler. The cowl defines at least one axial cowl hole, and the deflector defines at least one corresponding axial deflector hole, wherein the corresponding deflector hole and cowl hole are configured to receive a fastener for fastening together the cowl and the deflector.

Abstract: 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.

Abstract: Embodiments of a combustor assembly for a turbine engine are generally provided. The combustor assembly includes a first separable portion defining a dome assembly, and a second separable portion defining a deflector assembly. The first separable portion and the second separable portion are coupled together at a fitted interface.

Abstract: A heat engine including a wall assembly is generally provided. The wall assembly includes a plurality of radial walls coupled together via a connecting member. The radial wall defines a flow opening therethrough. A flow cavity is defined between the plurality of radial walls and the connecting member.

Abstract: The present subject matter provides a combustion system which comprising: a cowl; a deflector configurated to include a ring body, a plurality of swirlers integrated on the ring body and a plurality of arms integrally extending outward from the ring body; an annular inner liner attached with the cowl; and an annular outer liner attached with the cowl. The deflector is positioned between the inner liner and the outer liner; the deflector, the inner liner and the outer line define a combustion chamber thereamong. The deflector is attached to the cowl via the plurality of arms, but the arms are rigid enough to work together to fix the deflector with the cowl while allowing for thermal expansion flexibility therebetween at the same time.

Abstract: A combustor includes an outer liner, an inner liner, an annular cowl joining upstream ends of the outer and inner liners, and an annular deflector configured to shield the cowl from hot combustion gases in a combustion chamber defined between the outer liner, the inner liner and the deflector. The cowl has at least one opening for introduction of fuel and compressed air. The deflector includes at least one swirler. The cowl defines at least one axial cowl hole, and the deflector defines at least one corresponding axial deflector hole, wherein the corresponding deflector hole and cowl hole are configured to receive a fastener for fastening together the cowl and the deflector.

Abstract: Flow path assemblies and gas turbine engines are provided. In one exemplary embodiment, a flow path assembly comprises an inner wall and a unitary outer wall including a combustor portion extending through a combustion section and a turbine portion extending through at least a first turbine stage of a turbine section. The combustor portion and the turbine portion are integrally formed as a single unitary structure. The inner wall and the unitary outer wall define a combustor of the combustion section. In another exemplary embodiment, a flow path assembly comprises a unitary inner wall defining an inner boundary of a flow path and extending from a forward end of a combustor through a nozzle portion of a first turbine stage, and a unitary outer wall defining an outer boundary of the flow path and extending from the forward end of the combustor through at least the first turbine stage.

Abstract: Flow path assemblies and gas turbine engines are provided. A flow path assembly may comprise a combustor dome positioned at a forward end of a combustor of a combustion section of a gas turbine engine, and a unitary outer wall including a combustor portion extending through the combustion section and a turbine portion extending through at least a first turbine stage of a turbine section of the gas turbine engine. The combustor portion and the turbine portion are integrally formed as a single unitary structure. The flow path assembly also comprises an inner wall extending from the forward end of the combustor through at least the combustion section. The combustor dome extends radially from the unitary outer wall to the inner wall and is configured to move axially with respect to the inner wall and the unitary outer wall. Other flow path assemblies and gas turbine engine configurations are provided.

Abstract: Flow path assemblies and gas turbine engines are provided. In one exemplary embodiment, a flow path assembly comprises an inner wall and a unitary outer wall including a combustor portion extending through a combustion section and a turbine portion extending through at least a first turbine stage of a turbine section. The combustor portion and the turbine portion are integrally formed as a single unitary structure. The inner wall and the unitary outer wall define a combustor of the combustion section. In another exemplary embodiment, a flow path assembly comprises a unitary inner wall defining an inner boundary of a flow path and extending from a forward end of a combustor through a nozzle portion of a first turbine stage, and a unitary outer wall defining an outer boundary of the flow path and extending from the forward end of the combustor through at least the first turbine stage.

Abstract: Flow path assemblies and gas turbine engines are provided. A flow path assembly may comprise a combustor dome positioned at a forward end of a combustor of a combustion section of a gas turbine engine, and a unitary outer wall including a combustor portion extending through the combustion section and a turbine portion extending through at least a first turbine stage of a turbine section of the gas turbine engine. The combustor portion and the turbine portion are integrally formed as a single unitary structure. The flow path assembly also comprises an inner wall extending from the forward end of the combustor through at least the combustion section. The combustor dome extends radially from the unitary outer wall to the inner wall and is configured to move axially with respect to the inner wall and the unitary outer wall. Other flow path assemblies and gas turbine engine configurations are provided.