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: An apparatus relating to a component for a turbine engine which generates a hot gas fluid flow, and provides a cooling fluid flow. The component having a wall separating the hot gas fluid flow from the cooling fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow. At least one cooling hole including a connecting passage extending from a first inlet located at the cooled surface, to a first outlet located at the heated surface, the connecting passage defining a downstream flow direction from the first inlet to the first outlet, the connecting passage comprising a metering section fluidly coupled to the first inlet and defining a metered centerline and a diffusing section, downstream of the metering section, defining a diffused centerline, and fluidly coupling the metering section to the first outlet.

Abstract: An apparatus and method relating to a cooling hole of a component of a turbine engine. The component can include a wall separating the hot gas fluid flow from the cooling fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow and at least one cooling hole comprising at least one inlet at the cooled surface, at least one outlet at the heated surface, with the outlet having a modified outlet shape.

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 method for additively manufacturing a component includes generating, via imaging software, a plurality of slices of a support structure of the component based on component geometry. The method also includes melting or fusing, via the additive manufacturing system, layers of material to a build platform of the component so as to form the support structure according to the plurality of slices. The support structure includes a lattice configuration having of a plurality of support members arranged together to form a plurality of cells. Further, the method includes melting or fusing, via the additive manufacturing system, a component body to the support structure. After the component body solidifies, the method includes removing all of the support structure from the component body to form the component.

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: An apparatus and method relating to a cooling hole of a component of a turbine engine. The component can include a wall separating the hot gas fluid flow from the cooling fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow and at least one cooling hole comprising at least one inlet at the cooled surface, at least one outlet at the heated surface, with the outlet having a modified outlet shape.

Abstract: An apparatus and method relating to a cooling hole of a component of a turbine engine. The component can include a wall separating the hot gas fluid flow from the cooling fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow and at least one cooling hole comprising at least one inlet at the cooled surface, at least one outlet at the heated surface, with the outlet having a modified outlet shape.

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 method for additively manufacturing a component includes generating, via imaging software, a plurality of slices of a support structure of the component based on component geometry. The method also includes melting or fusing, via the additive manufacturing system, layers of material to a build platform of the component so as to form the support structure according to the plurality of slices. The support structure includes a lattice configuration having of a plurality of support members arranged together to form a plurality of cells. Further, the method includes melting or fusing, via the additive manufacturing system, a component body to the support structure. After the component body solidifies, the method includes removing all of the support structure from the component body to form the component.

Abstract: An apparatus and method relating to a cooling hole of a component of a turbine engine. The component can include a wall separating the hot gas fluid flow from the cooling fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow and at least one cooling hole comprising at least one inlet at the cooled surface, at least one outlet at the heated surface, with the outlet having a modified outlet shape.

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: An apparatus and method relating to a cooling hole of a component of a turbine engine. The cooling hole can extend from an inlet to an outlet to define a passage. The cooling hole can include a laid back section where a coating can be applied. The method can include forming the cooling hole in the component and applying the coating to the component to maintain a specific geometry.

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: Upper and lower P-clamps secured to a structure by a fastener, upper and lower legs attached to upper and lower annular clamp bodes of the P-clamps, the upper leg on top of the lower leg, and a support plate secured to the structure between the upper P-clamp and the structure. The fastener may be disposed through holes in the upper and lower legs. Circular or rounded annular clamp bodies may secure articles therein and be attached to the upper and lower legs. A loop portion of the clamp body may be encased by an elastomeric sheath. Each of the upper and lower legs may include upper and lower flanges outside of the elastomeric sheath and extending away from upper and lower portions respectively of the loop portion. The upper and lower legs may be parallel or angled with respect to each other.