Abstract: A shroud hanger assembly is provided for hangers and shrouds defining dimensionally incompatible components such as those which are press or frictionally fit to engage one another. The shroud hanger assembly includes a multi-piece hanger and a shroud that is pinned to the hanger assembly by at least one axially extending pin and which locates the shroud relative to the hanger to control motion in one or both of circumferential (tangential) and radial directions relative to the engine.

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: A shroud hanger assembly is provided for hangers and shrouds defining dimensionally incompatible components such as those which are press or frictionally fit to engage one another. The shroud hanger assembly includes a multi-piece hanger and a shroud that is pinned to the hanger assembly by at least one axially extending pin and which locates the shroud relative to the hanger to control motion in one or both of circumferential (tangential) and radial directions relative to the engine.

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 shroud hanger assembly (30) or shroud assembly is provided for dimensionally incompatible components wherein the assembly includes a multi-piece hanger (32), for example having a forward hanger portion (34) and a rearward hanger portion (36). A cavity (46) is formed between the parts; wherein a shroud (50) may be positioned which is formed of a low coefficient of thermal expansion material. The hanger (32) and shroud (50) may be formed of the same material or differing materials in order to better match the thermal growth between the hanger and the shroud. When the shroud (50) is positioned within the hanger opening or cavity (46), one of the forward (34) and rearward hanger (36) portions may be press fit or otherwise connected into the other of the forward (34) and rearward (36) hanger portion.

Abstract: A shroud hanger assembly or shroud assembly is provided for dimensionally incompatible components wherein the assembly includes a multi-piece hanger, for example having a forward hanger portion and a rearward hanger portion. A cavity is formed between the parts; wherein a shroud may be positioned which is formed of a low coefficient of thermal expansion material. The hanger and shroud may be formed of the same material or differing materials in order to better match the thermal growth between the hanger and the shroud. When the shroud is positioned within the hanger opening or cavity, one of the forward and rearward hanger portions may be press fit or otherwise connected into the other of the forward and rearward hanger portion.

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: A shroud hanger assembly is provided for hangers and shrouds defining dimensionally incompatible components such as those which are press or frictionally fit to engage one another. The shroud hanger assembly includes a multi-piece hanger and a shroud that is pinned to the hanger assembly by at least one axially extending pin and which locates the shroud relative to the hanger to control motion in one or both of circumferential (tangential) and radial directions relative to the engine.

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 shroud hanger assembly is provided for hangers and shrouds defining dimensionally incompatible components such as those which are press or frictionally fit to engage one another. The shroud hanger assembly includes a multi-piece hanger and a shroud, which is pinned to the hanger assembly by at least one axially extending pin and which locates the shroud relative to the hanger to control motion in one or both of circumferential (tangential) and radial directions relative to the engine.

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 example device for mounting for a solar array may include a solar panel carrier configured to receive a solar array to form a panel assembly; a pivot configured to pivotably secure the solar panel carrier with respect to a support structure; and/or a restoring moment element operatively connected to the solar panel carrier and configured to exert a restoring moment on the solar panel carrier opposite in direction and approximately equal in magnitude to a gravitational moment of the panel assembly when the solar panel carrier is tilted to various angular positions. When the solar panel carrier is at a nominal angular position, a center of gravity of the panel assembly may be above and substantially vertically aligned with the pivot axis.

Abstract: An example device for mounting for a solar array may include a solar panel carrier configured to receive a solar array to form a panel assembly; a pivot configured to pivotably secure the solar panel carrier with respect to a support structure; and/or a restoring moment element operatively connected to the solar panel carrier and configured to exert a restoring moment on the solar panel carrier opposite in direction and approximately equal in magnitude to a gravitational moment of the panel assembly when the solar panel carrier is tilted to various angular positions. When the solar panel carrier is at a nominal angular position, a center of gravity of the panel assembly may be above and substantially vertically aligned with the pivot axis.

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: 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 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.