Abstract: A cooling system includes a nozzle guide vane endwall. The nozzle guide vane endwall includes a first wall and a second wall. The first wall includes a first opening that extends completely through the first wall into a primary flow path of a high-pressure turbine. The second wall includes a second opening that extends completely through the second wall into an inner passageway of the nozzle guide vane endwall. The inner passageway is configured to direct a cooling fluid to the first opening and/or the second opening. The first and second opening are configured to receive a plug or a probe.

Abstract: A gas turbine engine includes a compressor, a combustor, and a turbine. The compressor compresses gases entering the gas turbine engine. The combustor receives the compressed gases from the compressor and mixes fuel with the compressed gases. The turbine receives the hot, high pressure combustion products created by the combustor by igniting the fuel mixed with the compressed gases. The turbine extracts mechanical work from the hot, high pressure combustion products to drive the compressor and a fan, shaft, or propeller.

Abstract: A power-generation system for a nuclear reactor includes a power unit, a heat exchanger, and a temperature control system. The power unit produces compressed air that is heated by the nuclear reactor via the heat exchanger. The temperature control system includes a heat transfer fluid and a heat exchanger fluidly connected with the compressed air to transfer heat between the compressed air and heat transfer fluid to control the power level of the power unit.

Abstract: A cooling system comprising a cooling circuit connecting a heat exchanger and a heat load. The cooling system comprising a first velocity fuse upstream of the heat exchanger or heat load and a second velocity fuse or valve downstream of the heat exchanger or heat load. The heat exchanger or heat load is dynamically isolated from the rest of the cooling system by the first velocity fuse or the second velocity fuse in response to a velocity of a flow of cooling fluid exceeding a respective velocity setting of the first velocity fuse or the second velocity fuse.

Abstract: Methods are provided for controlling thermal energy storage in a thermal energy management system that may operate in response to a variable or high transient heat load. Thermal energy management systems are also provided for controlling thermal energy storage that may operate in response to a variable or high transient heat load.

Abstract: The disclosure describes an apparatus for sealing a rotating machine, such as an electric machine or gas turbine engine. The apparatus includes a brush seal. The brush seal includes a plurality of first filaments and a plurality of electrically conductive filaments. The first filaments are configured to seal a lubricant within a bearing chamber or sump of the rotating machine. The plurality of electrically conductive filaments is configured to contact a shaft of the rotating machine and discharge a shaft voltage-induced current from the shaft to an external ground of the rotating machine.

Abstract: An airfoil for use in a gas turbine engine is formed to define a cavity formed in the airfoil. The airfoil further includes at least one obstructing member arranged within the cavity and a shear-thickening fluid disposed in the cavity. A viscosity of the shear-thickening fluid increases in response to the airfoil experiencing an aeromechanic response or vibrations such that the obstruction of the movement of the thicker fluid by the obstructing member dampens the vibrations of the airfoil and reduces negative effects of a dynamic response of the airfoil.

Abstract: An example thermal management system may include a first heat exchanger including a bleed air inlet configured to receive input bleed air from a gas turbine engine and a bleed air outlet configured to output cooled bleed air. A turbine including a turbine inlet may be fluidically coupled to the bleed air outlet. The turbine may be configured to drive a shaft mechanically coupled to the turbine in response to expansion of the cooled bleed air through the turbine. A second heat exchanger may include an expanded bleed air inlet fluidically coupled to a turbine outlet of the turbine. The second heat exchanger may be configured to extract heat from at least one heat source using the expanded bleed air.

Abstract: In some examples, an additive manufacturing technique including forming an as-deposited coating on a substrate by depositing a filament via a filament delivery device, wherein the filament includes a sacrificial binder and a powder; removing substantially all the binder from the as-deposited coating; and sintering the as-deposited coating to form a thermal coating; wherein the thermal coating is configured to ablate in response to absorption of energy from an external environment, and wherein the ablation of the thermal coating reduces the energy transferred to the substrate.

Abstract: Thermal management systems for cooling high-power, low-duty-cycle thermal loads by rejecting heat from the thermal loads to the ambient environment are provided. The thermal management systems include a two-phase pump loop in fluid communication with a vapor compression system loop, evaporators disposed in parallel between the two-phase pump loop and the vapor compression system loop, and a thermal energy storage loop including a cold-temperature tank and a warm-temperature tank thermally coupled to the two-phase pump loop and the vapor-compression system loop. Methods of transferring heat from one or more thermal loads to an ambient environment are also provided.

Abstract: The disclosure describes articles and techniques that include an airfoil having a hybrid coating system to provide improved particle impact resistance and improve CMAS attack resistance on the pressure side of the airfoil and improved thermal load protection on the suction side of the airfoil. An example article for a gas turbine engine may include a substrate, and a hybrid environmental barrier coating (EBC) including a relatively dense EBC layer on a first portion of the substrate and a relatively porous EBC layer on a second portion of the substrate, where the first portion of the substrate is different from the second portion of the substrate, and wherein at least a portion of the relatively porous EBC layer overlaps at least a portion of the relatively dense EBC layer in an overlap region.

Abstract: A fan case assembly adapted for use with a gas turbine engine includes a fan track liner and an annular case. The fan track liner extends circumferentially at least partway about a central axis of the gas turbine engine. The annular case is configured to support the fan track liner at a radial position relative to the central axis. The fan case assembly further includes an air recirculation duct configured to redirect air around the fan track liner.

Abstract: A vane assembly for a gas turbine engine is disclosed in this paper. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil. The ceramic-containing airfoil extends between the inner platform and the outer platform. A reinforcement spar extends between the inner platform and the outer platform through a hollow core of the ceramic-containing airfoil.

Abstract: An engine section stator for a gas turbine engine having a compressor, a combustor, and a turbine. The engine section stator includes an inner band, an outer band spaced radially outwardly from the inner band, and a series of spaced apart aerofoils extending the inner and outer bands. The engine section stator includes a stiffness feature that extends away from one of the inner and outer bands of the engine section stator. The stiffness feature configured to increase the high cycle fatigue strength of the aerofoils without impeding airflow passing between the inner and outer bands.

Abstract: An engine that may comprise a first rotatable shaft, a second rotatable shaft, and a turnbuckle shaft. The first shaft rotatable may be disposed about a centerline axis and have threads disposed thereon. The second shaft rotatable may be disposed about the centerline axis and have threads disposed thereon. The turnbuckle shaft may be axially disposed between the first and second shafts, rotatable about the centerline axis, and have threads disposed thereon for engaging the threads of the first and second shafts. The first and second shafts may be drawn together by a force acting on the threads of at least one of the first and second shafts created by a rotation of the turnbuckle shaft relative to the at least one of the first and second shafts. The turnbuckle shaft may rotationally connect the first shaft and second shaft.

Abstract: A fan case assembly extend along and around a center axis. The fan case assembly may comprise a barrel extending along and around the center axis, the barrel configured to fasten to a flange of an engine case. The fan case assembly may comprise a fan track liner disposed radially inward of the barrel and a containment hook, wherein the containment hook is a discrete component separate from the barrel. The containment hook may include a front segment configured to fasten to the flange, and an axial segment disposed radially inward of the barrel. The axial segment may extend between the flange and the fan track liner and the front segment may extend radially outward from an end of the axial segment. The containment hook may also include a protruding segment extending radially inward from the axial segment.

Abstract: In some examples, an additive manufacturing technique for forming a vacuum insulator. For example, a method including forming an article including a first layer, a second layer, and at least one support member extending between the first and second layer by depositing a filament via a filament delivery device, wherein the filament includes a sacrificial binder and a powder, and wherein the first layer, second layer, and at least one support member define an open cavity within the article; removing the binder; and sintering the article to form the vacuum insulator, wherein the vacuum insulator defines a vacuum environment in the cavity.

Abstract: A cooling system includes a first cooling loop, a second cooling loop and a heat exchanger configured to transfer heat from the first cooling loop to the second cooling loop. The first cooling loop includes a flow restrictor, an inertial separator, and a pressure relief valve cooperating to effect diversion of vapor present in the first cooling loop due to a leak between the first cooling loop and the second cooling loop.

Abstract: A redundant oil and fuel pumping system for use with a gas turbine engine. The pumping system includes a plurality of power sources, a fuel system and an oil system. The fuel system pump being driven by electric motors controlled via variable frequency drives powered by the plurality of power sources. The oil system pump being driven by electric motors controlled via variable frequency drives powered by the plurality of power sources.

Abstract: A fan case assembly adapted for use with a gas turbine engine includes a fan track liner and an annular case. The fan track liner extends circumferentially at least partway about a central axis of the gas turbine engine. The annular case is configured to support the fan track liner at a radial position relative to the central axis. The fan case assembly further includes an air recirculation duct configured to redirect air around the fan track liner.