Abstract: A fan case assembly adapted for use with a gas turbine engine includes a case at extends circumferentially at least partway about an axis of the gas turbine engine and a plurality of vanes. The case is formed to define a plenum that extends circumferentially at least partway about the axis. The plurality of vanes are arranged in the plenum and spaced apart circumferentially about the axis to define a plurality of inlet openings in fluid communication with the plenum.

Abstract: The disclosure describes braze tape coatings and technique to form articles with differing physical properties in different layers or regions of the article. An example method includes forming a braze tape defining at least one layer that includes a first segment and a second segment. A portion of the second segment in the plane is adjacent to a portion of the first segment in a plane of the layer. The method also includes positioning the braze tape on a surface of a substrate, the plane of the layer of the braze tape being parallel to the surface of the substrate. The method also includes heating the braze tape to melt a constituent of at least one of the first coating material and the second coating material to form a densified coating on the surface of the substrate.

Abstract: The disclosure describes example systems and techniques for controlling microstructure of a superalloy substrate by controlling temperature during forging and using multiple die forging stages to formation of grain boundary phases of the superalloy, and components formed by such example systems and techniques. The method includes heating a substrate to within a forging temperature range. The substrate includes a nickel-based superalloy, and the forging temperature range is below an eta phase solvus temperature of the substrate. The method includes applying a plurality of die forging stages to the substrate to form a component preform. The method includes maintaining the substrate within the forging temperature range during application of the plurality of die forging stages and cooling the component preform.

Abstract: An example article includes a substrate and a barrier coating on the substrate. The barrier coating includes a matrix including a rare-earth disilicate extending from an inner interface facing the substrate to an outer surface opposite the inner interface. The barrier coating includes a graded volumetric distribution of rare-earth oxide rich (REO-rich) phase regions in the matrix along a direction from the inner interface to the outer surface. The graded volumetric distribution defines a first volumetric density of the REO-rich phase regions at a first region of the matrix adjacent the outer surface. The graded volumetric distribution defines a second volumetric density of the REO-rich phase regions at a second region of the matrix adjacent the inner surface. The second volumetric density is different from the first volumetric density. An example technique includes forming the barrier coating on the substrate of a component.

Abstract: A voltage controlled aircraft electric propulsion system includes an electric propulsion system. The voltage controlled aircraft electric propulsion system may include electric propulsors providing thrust for the aircraft. In hybrid systems, a gas turbine engine may also be included. The electric propulsion system may include at least one electric generator power source, at least one propulsor motor load, and at least one stored energy power source, such as a battery. The propulsor motor load may be supplied power from a power supply bus. The voltage of the power supply bus may be adjusted according to an altitude of the aircraft while maintaining a substantially constant current flow to the propulsor motor load. Due to the adjustment to lower voltages at increased altitude, insulations levels may be lower.

Abstract: In examples of the disclosure, a device may be couple an electrical load to a power source. The device may have a first coupling configured to couple to the power source and a second coupling configured to couple to the electrical load. The device may have a plurality of strands electrically disposed between the first coupling and the second coupling. Each of the plurality of strands may have a coating having a resistivity greater than 1.8×10?8 ?-m and less than 1 ?-m and a center conductor wrapped, at least in part, by the coating.

Abstract: An acoustic panel for a gas turbine engine, includes a panel body, a panel-body cover, and a support bracket. The panel body is configured to dampen vibrations caused by the gas turbine engine. The forward support bracket is configured to mount the acoustic panel to portions of the gas turbine engine.

Abstract: A turbine engine may include a compressor section of the turbine engine. The turbine engine may include a combustion section of the turbine engine. The combustion section may be downstream of the compressor section. The turbine engine may include a turbine section of the turbine engine. The turbine section may be downstream of the combustion section. The turbine engine may include a sensor for speed detection. The sensor may be disposed at an upstream segment of the turbine section. The sensor may include a cooling jacket. The cooling jacket may encase at least a portion of the sensor. A cooling fluid may be in fluid communication with the cooling jacket and an outer surface of the sensor. The cooling jacket may be shaped to direct cooling fluid around the sensor.

Abstract: A method for manufacturing a turbine shroud segment with at least one undercut region. The method includes forming a removable insert including an external surface corresponding to at least a portion of a wall of the undercut region in the turbine shroud segment; placing the removable insert in a mold including a mold cavity corresponding to a shape of the turbine shroud segment; injecting a metal injection molding (MIM) feedstock into the mold cavity and around the removable insert to form a shroud green body with the at least one undercut region; and, sintering the shroud green body to form the shroud body.

Abstract: A fluid atomizer and methods of atomizing fluids are disclosed. The fluid atomizer may comprise an inner member and one or more outer members. The inner member defines an interior conduit for providing a first-fluid flowpath from a supply end of the atomizer to a discharge end of the atomizer along a central axis. The one or more outer members are positioned radially outward of the inner member from the central axis. The inner and outer members define a second-fluid flowpath extending from a second-fluid supply conduit to a second-fluid discharge plenum. The second-fluid flowpath comprises a tangential conduit spiraling along the axis from the second-fluid supply conduit to a terminal end; an annulus downstream from and in fluid communication with the tangential conduit; and a second-fluid discharge plenum downstream from and in fluid communication with the annulus.

Abstract: Methods of pressure assisted melt infiltration of fiber preforms are provided. The fiber preform is provided inside of a pressure vessel. The pressure vessel projects into a molten material contained in a crucible. The pressure vessel has an opening located below a surface of the molten material through which the molten material enters the pressure vessel. An end of the fiber preform contacts the molten material within the pressure vessel. The pressure vessel and crucible are located in a furnace. The molten material is pulled within the pressure vessel by increasing a first pressure at a first port of the furnace so the first pressure is higher than a second pressure at a second port of the pressure vessel. The second port is located above the molten material located within the pressure vessel. The fiber preform is infiltrated with the molten material.

Abstract: A thermal management system for an energy storage system for an aircraft includes a pump circulating a thermal management fluid through the thermal management system and an energy storage device of the aircraft. A controller circuitry may control a variable pumping capacity of the pump based on sensing pressure or temperature of the thermal management fluid at the energy storage device. The controller circuitry may default operation of the pump to a first pumping capacity in response to the pressure or temperature being within a predetermined operating range and a predetermined failure condition or a power demand of an aircraft engine supply bus exceeding a predetermined threshold. The controller controlling operation of the pump to a second pumping capacity in response to absence of the power demand signal of the aircraft engine supply bus and the pressure or temperature being within the predetermined operating range.

Abstract: An example system includes a throttle control for managing power in a hybrid propulsion system that includes an electrical propulsion unit configured to operate using electrical energy sourced from an electrical energy storage system (ESS) and/or one or more electrical generators, the throttle control comprising: a control lever movable through a plurality of positions, the plurality of positions including: a regeneration position; an off position; a maximum electric only position; a maximum continuous dual source position; and a maximum non-continuous dual source position.

Abstract: A method for connecting or joining a first substrate and a second substrate across an interface between the first substrate and the second substrate. The method includes disposing a fastener precursor in the bore and sintering the fastener precursor in the bore. The fastener precursor densifies and shrinks in at least one dimension to mechanically interlock with a contour in the bore and form a mechanical fastener in the bore, and the mechanical fastener forms an interlock between the first substrate and the second substrate.

Abstract: A starter system for a gas turbine engine in, for example, a hybrid electric engine is provided. The hybrid electric engine may include the gas turbine engine, an electric machine, and an electrical energy storage. The starter system may include the electric machine, and a low-pressure shaft of the gas turbine engine may be mechanically coupled to a rotor of the electric machine. The electrical energy storage may electrically power the electrical machine and receive electrical power from the electrical machine. In addition, a clutch may selectively couple the low-pressure shaft to a high-pressure shaft of the gas turbine engine. The clutch may, when engaged, transfer mechanical power from the low-pressure shaft, which is mechanically coupled to the electric machine, to the high-pressure shaft. Further, the clutch may disengage if a rotational speed of the high-pressure shaft exceeds a rotational speed of the low-pressure shaft.

Abstract: A turbine shroud assembly includes a carrier segment, a blade track segment, and a retainer. The carrier segment is formed to include an attachment-receiving space. The blade track segment includes a shroud wall and attachment flanges that extends radially outward from the shroud wall into the attachment-receiving space of the carrier segment. The retainer couples the blade track segment to the carrier segment.

Abstract: An integrated circuit thermal management system includes an enclosure, a heat exchanger, an integrated circuit, a slide having a moveable slide body, an electromagnetic coil, a magneto caloric material and controller circuitry. The heat exchanger is positioned on a first side of the enclosure, and the integrated circuit is positioned on a second side of the enclosure with a temperature sensor configured to generate a temperature signal indicative of a temperature of the integrated circuit. The slide is disposed in the enclosure extending between the heat exchanger and the integrated circuit. The electromagnetic coil and the magnetocaloric material are included on the slide body. The controller is configured to control energization of the magnetic coil and movement of the magnetocaloric material on the slide body between the heat exchanger and the integrated circuit based on the temperature signal.

Abstract: A turbine section of a gas turbine engine includes a case, a plurality of flow path components, and a mounting system. The case extends circumferentially at least partway around an axis of the gas turbine engine. The plurality of flow path components includes a flow path segment and a turbine vane. The mounting system couples the flow path segment to the case to support the flow path segment radially relative to the axis of the gas turbine engine.

Abstract: A fan assembly includes a fan duct, an inlet fan, an outlet guide vane assembly, and a control system. The inlet fan includes fan blades adapted to rotate about a central axis to force fan exit air toward an aft end of the fan duct. The outlet guide vane assembly is located in the fan duct downstream of the inlet fan and is configured to adjust a direction of the fan exit air. The outlet guide vane assembly includes a plurality of guide vanes that extend radially relative to the central axis and are configured to rotate to a first vane-pitch angle. The control system is configured to rotate the guide vanes redirect the fan exit air, vary a pressure downstream of the fan inlet, minimize intake flow distortion experienced by the inlet fan, reduce inlet fan vibratory response and/or improve fan operability margins.

Abstract: In some examples, a method may include depositing, from a slurry comprising particles including silicon metal, a bond coat precursor layer including the particles comprising silicon metal directly on a ceramic matrix composite substrate. The method also may include locally heating the bond coat precursor layer to form a bond coat comprising silicon metal. Additionally, the method may include forming a protective coating on the bond coat. In some examples, an article may include a ceramic matrix composite substrate, a bond coat directly on the substrate, and a protective coating on the bond coat. The bond coat may include silicon metal and a metal comprising at least one of Zr, Y, Yb, Hf, Ti, Al, Cr, Mo, Nb, Ta, or a rare earth metal.