Abstract: A self-cooled orifice structure that may be for a combustor of a gas turbine engine, and may further be a dilution hole structure, includes a hot side panel, a cold side panel spaced from the hot side panel, and a continuous inner wall extending between the hot and cold side panels and defining an orifice having a centerline and communicating axially through the hot and cold side panels. A plurality of end walls of the structure are in a cooling cavity that is defined in-part by the hot and cold side panels and the inner wall. Each end wall extends between and are engaged to the hot and cold side panels and are circumferentially spaced from the next adjacent end wall. A plurality of inlet apertures extend through the cold side panel and are in fluid communication with the cavity, and each one of the plurality of inlet apertures are proximate to a first side of a respective one of the plurality of end walls.

Abstract: A method of forming an engine component according to an exemplary aspect of the present disclosure includes, among other things, introducing molten metal into a cavity between a shell and a casting article in the shell. The casting article includes a ceramic portion and a plurality of fibers. The method further includes separately removing the ceramic portion and the fibers from an interior of the component.

Abstract: An abrasive profiling tool that may be part of a robotic machining system for machining a trailing edge of an airfoil, includes a shank extending along a rotational axis, a bearing guide rotationally secured to a distal end of the shank for riding upon the airfoil; and an abrasive profiler projecting radially and rigidly outward from the shank for grinding at least the trailing edge as the shank rotates. The profiler may include a round-over portion for grinding the trailing edge and a chamfered blending portion for grinding adjacent surfaces of the airfoil to produce a smooth transition from the adjacent surfaces and to the trailing edge.

Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a wall and a vascular engineered lattice structure formed inside of the wall. The vascular engineered lattice structure includes at least one of a hollow vascular structure and a solid vascular structure configured to communicate fluid through the vascular engineered lattice structure.

Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things a wall and a vascular engineered lattice structure formed inside of the wall. The vascular engineered lattice structure defines a hollow vascular structure configured to communicate a fluid through the vascular engineered lattice structure. The vascular engineered lattice structure has at least one inlet hole and at least one outlet hole that communicates the fluid into and out of the hollow vascular structure.

Abstract: A transpiration-cooled article includes a body wall that has first and second opposed surfaces. The first surface is adjacent a passage that is configured to receive a pressurized cooling fluid. At least a portion of the body wall includes a nanocellular foam through which the pressurized cooling fluid from the passage can flow to the second surface. The article can be an airfoil that includes an airfoil body that has an internal passage and an outer gas-path surface. At least a portion of the airfoil body includes a nanocellular foam through which cooling fluid from the internal passage can flow to the gas-path surface.

Abstract: An airfoil includes a suction surface, a pressure surface, a first showerhead cooling hole and a second showerhead cooling hole. The suction surface and the pressure surface both extend axially between a leading edge and a trailing edge, as well as radially from a root section to a tip section. The first showerhead cooling hole and the second showerhead cooling hole both extend into pressure surface near the leading edge. The first showerhead cooling hole and the second showerhead cooling hole are angled in opposing directions.

Abstract: A system includes a turbomachine having one or more inspection ports. An LWIR sensor is positioned in the inspection port of the turbomachine to sense thermal energy emitted by a turbomachine component. An imaging device can be operably connected to the LWIR sensor to convert signals from the LWIR sensor to a thermal image of the turbomachine component based on the sensed thermal energy. In some embodiments, the LWIR sensor configured to image a ceramic coated turbine blade.

Abstract: An impeller includes a plurality of vanes formed around a hub, each of the plurality of vanes defines an offset between a leading edge and a trailing edge.

Abstract: A combustor liner with an input end and an output end includes an annular inner wall and an annular outer wall. At least one of the inner wall and outer wall is three-dimensionally contoured. The inner wall and the outer wall form a combustion chamber with the contours creating alternating expanding and constricting regions inside the chamber causing combustion gases to flow in the circumferential and axial directions.

Abstract: A combustor liner with an input end and an output end includes an annular inner wall and an annular outer wall. At least one of the inner wall and outer wall is three-dimensionally contoured. The inner wall and the outer wall form a combustion chamber with the contours creating alternating expanding and constricting regions inside the chamber causing combustion gases to flow in the circumferential and axial directions.

Abstract: An airfoil includes a suction surface, a pressure surface, a first showerhead cooling hole and a second showerhead cooling hole. The suction surface and the pressure surface both extend axially between a leading edge and a trailing edge, as well as radially from a root section to a tip section. The first showerhead cooling hole and the second showerhead cooling hole both extend into pressure surface near the leading edge. The first showerhead cooling hole and the second showerhead cooling hole are angled in opposing directions.

Abstract: Turbomachinery, such as a gas turbine engine, has parts with opposed first and second surfaces and with a cavity between the surfaces and with the first surface moving relative to the second surface. The turbomachinery further has at least one feature for creating pressure variations incorporated into the first and second surfaces.

Abstract: An airfoil array includes a laterally extending endwall 56 with a series of airfoils such as 28 or 38 projecting from the endwall. The airfoils cooperate with the endwall to define a series of fluid flow passages 74. The endwall has a trough 100 toward a pressure side of the passage and a more elevated profile toward a suction side of the passage for reducing secondary flow losses.

Abstract: A dirt separator may be retrofit into existing gas turbine engines since it is formed of circumferentially separate pieces which may be assembled together in the gas turbine engine.

Abstract: Systems and methods involving variable throat area vanes are provided. In this regard, a representative gas turbine engine includes: a vane extending into a gas flow path and having: an interior operative to receive pressurized air; a pressure surface portion; and a first port communicating between the interior and pressure surface portion, the first port being operative to receive the pressurized air from the interior and emit the pressurized air, wherein the emitted pressurized air displaces the gas flow path such that a throat area defined, at least in part, by the vane is modified.

Abstract: An impeller includes a plurality of vanes formed around a hub, each of the plurality of vanes defines an offset between a leading edge and a trailing edge.

Abstract: A turbine section of a gas turbine engine includes an arcuate vane platform segment having a substantially flat surface over which a rotational turbine vane may swing.

Abstract: A turbine section includes a housing and a blade outer air seal to be mounted on the housing. A flex beam mounts the blade outer air seal onto the housing, with the flex beam being supported on the housing, but free to move relative to the housing. A pressure air chamber is formed on an opposed side of the flex beam from the blade outer air seal. A source of pressurized air is delivered into the chamber to cause the flex beam to move the blade outer air seal toward and away from a central axis of the housing.

Abstract: Gas turbine engine systems involving mechanically alterable vane throat areas are provided. In this regard, a representative vane for a gas turbine engine includes: a leading edge; a trailing edge; a suction side surface extending between the leading edge and the trailing edge; a cavity having an aperture located in the suction side surface; and a barrel located within the cavity and being moveable therein such that movement of the barrel alters an extent to which the barrel protrudes through the aperture.