Abstract: A system for modulating turbine blade tip clearance is provided. The system may comprise an actuation control system having at least one actuator configured to modulate turbine blade tip clearance between a turbine blade tip and a blade outer air seal (BOAS). Each actuator may be coupled to the BOAS. Each actuator may comprise a solid-state motion amplification device such as a flextensional actuator. The actuators may be configured to move the BOAS in a radial direction from a first position to a second position to control tip clearance.

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. A method for producing a component is also disclosed.

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: A turbine casing may comprise a casing body a heat pipe disposed in the casing body. The heat pipe may include a vaporization section and a condensation section. The vaporization section may be located forward the condensation section. The vaporization section may be located in a high pressure turbine region of the casing body. The condensation section may be located in a low pressure turbine region of the casing body.

Abstract: A method of preparing a casting article for manufacturing a gas turbine engine part according to an exemplary aspect of the present disclosure includes communicating a powdered material to an additive manufacturing system, the powdered material including at least one of a silica material, an alumina material, and a refractory metal material. The method includes using the additive manufacturing system to manufacture a casting article layer by layer, the casting article including a plurality of circuit forming portions, at least one of the circuit forming portions including an interior channel that establishes a hollow opening through the circuit forming portion.

Abstract: The present disclosure relates to combustor configurations, panels and components for a gas turbine engine. In one embodiment, a combustor for a gas turbine engine includes a support structure including a plurality of openings and a plurality of panels mounted to the structure. The plurality of panels define a combustion cavity of the combustor. Each panel includes a first wall configured to receive cooling air and a second wall configured to provide air flow for the cavity. The first and second walls form a cavity and include one or more elements for controlling the cooling effectiveness of each panel. Another embodiment is directed to a combustor panel including one or more elements for controlling cooling effectiveness. Another embodiment is directed to a support structure for a combustor of a gas turbine engine. Another embodiment is directed to configurations of panels including single walled portions or single walled panels.

Abstract: A casting article according to an exemplary aspect of the present disclosure includes, among other things, a circuit forming portion and an interior channel formed inside of the circuit forming portion. The interior channel defines a leaching path that extends at least partially through the circuit forming portion.

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 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: 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 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: 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: A tangential on-board injector (TOBI) for a gas turbine engine is provided. The TOBI includes a body having an entrance and an exit, the body having an outer curved wall and defining an air passageway between the entrance and the exit and a purge cavity configured on an exterior surface of the body with a purge cavity entry fluidly connecting the air passageway to the purge cavity. The purge cavity is configured such that particles in an airflow through the passageway will enter the purge cavity.

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: The present disclosure relates to combustor configurations, panels and components for a gas turbine engine. In one embodiment, a combustor for a gas turbine engine includes a support structure including a plurality of openings and a plurality of panels mounted to the structure. The plurality of panels define a combustion cavity of the combustor. Each panel includes a first wall configured to receive cooling air and a second wall configured to provide air flow for the cavity. The first and second walls form a cavity and include one or more elements for controlling the cooling effectiveness of each panel. Another embodiment is directed to a combustor panel including one or more elements for controlling cooling effectiveness. Another embodiment is directed to a support structure for a combustor of a gas turbine engine. Another embodiment is directed to configurations of panels including single walled portions or single walled panels.

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: A casting article according to another exemplary aspect of the present disclosure includes, among other things, a circuit forming portion including an interior channel and an outer shell body that surrounds the interior channel. An engineered failure feature is formed in the outer shell body and is configured to increase compressibility of the casting article during a casting process.

Abstract: A casting article according to an exemplary aspect of the present disclosure includes, among other things, a circuit forming portion and an interior channel formed inside of the circuit forming portion. The interior channel defines a leaching path that extends at least partially through the circuit forming portion.

Abstract: A method of locating a surface feature for a geometrically segmented coating on a contoured surface comprising providing an article having a contoured surface; overlaying an assembly of ligaments on the contoured surface; and locating a surface feature at a predetermined location relative to each ligament.