Abstract: A turbine shroud assembly adapted for use with a gas turbine engine includes a carrier, a seal segment, and a mount assembly. The carrier is configured to be coupled to a turbine case. The seal segment is shaped to define a gas path boundary of the shroud assembly. The mounting assembly is configured to couple the seal segment to the carrier.

Abstract: A method of forming a bladder cast ceramic matrix composite (CMC) article including infiltrating a CMC substrate positioned in a cavity of a mold body with a slurry. The CMC substrate includes reinforcement material defining inner spaces. The slurry includes solid particles and a carrier material. During infiltration, the slurry at least partially fills at least a portion of the inner spaces of the CMC substrate. The method also includes inflating at least one bladder that is coupled to the mold body and disposed within the cavity such that a surface of the at least one bladder in an inflated configuration contacts at least one surface of the CMC substrate. The method also includes drying the slurry to remove at least a portion of the carrier material form an infiltrated CMC and deflating the at least one bladder.

Abstract: An assembly for a dual-walled component of a gas turbine engine and methods of forming and repairing a dual-walled component. The assembly includes a cold section part having an outer surface that defines a plurality of impingement apertures, a hot section part including a pre-sintered preform, the hot section part positioned over the outer surface of the cold section part, and a plurality of support structures including the pre-sintered preform, the plurality of support structures positioned between the hot section part and the cold section part, the plurality of support structures separating the hot section part from the cold section part to define at least one cooling channel therebetween.

Abstract: A turbine shroud assembly adapted for use with a gas turbine engine includes a shroud segment. The shroud segment includes a heat shield, an attachment flange, and a multi-layer coating. The heat shield extends circumferentially partway around the axis to define a portion of gas path for the gas turbine engine. The attachment feature extends radially outward from the heat shield. The multi-layer coating is applied to different surfaces of the heat shield and the attachment feature of the shroud segment.

Abstract: An example system includes a first gas-turbine engine configured to propel an aircraft, the first gas-turbine engine comprising a first electric starter, the first electric starter configured to rotate a spool of the first gas-turbine engine; and one or more controllers collectively configured to: cause, following operation of the first gas-turbine engine, the first electric starter to perform barring of the first gas-turbine engine; measure, during the barring of the first gas-turbine engine, values of one or more parameters of the first gas-turbine engine; and determine, based on the values of the one or more parameters, whether the first electric starter is available for use in performing mid-air restart of the first gas-turbine engine.

Abstract: There is provided a blower system for providing air to an airframe system, comprising a rotor configured to be mechanically coupled to a spool 440 of a gas turbine engine, wherein the rotor is configured to: in a blower mode, be driven to rotate by the spool to discharge air to an airframe discharge port for supply to an airframe system; and, in an engine drive mode, receive air from an external air source via an impingement port that is configured to direct the received air onto the rotor and thereby drive the rotor to rotate to drive the spool to.

Abstract: A gas turbine engine includes a fan and a fan case assembly. The fan includes a fan rotor configured to rotate about an axis of the gas turbine engine and a plurality of fan blades coupled to the fan rotor for rotation therewith. The fan case assembly extends circumferentially around the plurality of fan blades radially outward of the plurality of the fan blades.

Abstract: An electric machine adapted for use in a gas turbine engine includes a shaft extending along a central axis, a magnetic rotor drum, and a non-magnetic rotor hub rotatably coupled with the shaft and the magnetic rotor drum. The magnetic rotor drum includes a rotor and a plurality of magnets arranged circumferentially about the central axis.

Abstract: A battery pack core may include a cold plate comprising a plurality of apertures defined between a first major surface and a second major surface of the cold plate; a plurality of battery cells, a single battery cell positioned in each aperture of the plurality of apertures such that a first end of the battery cell projects beyond the first major surface and a second end of the battery cell projects beyond the second major surface; and a plurality of silicone bushings, a silicone bushing surrounding each battery cell of the plurality of battery cells and contacting a wall of the aperture in which the battery cell is positioned.

Abstract: A turbine shroud assembly includes a first shroud segment, a second shroud segment, and a damping strip seal. The first shroud segment has a first carrier segment arranged circumferentially at least partway around a central axis and a first blade track segment supported by the first carrier segment. The second shroud segment is arranged circumferentially adjacent the first shroud segment about the central axis. The damping strip seal extends circumferentially into the first shroud segment and the second shroud segment to block gases from passing between the first shroud segment and the second shroud segment.

Abstract: A dual walled component includes a spar comprising a plurality of pedestals; a coversheet attached to a first set of pedestals from the plurality of pedestals; and a repaired coversheet portion attached to a second set of pedestals from the plurality of pedestals and to the coversheet, where the repaired coversheet portion includes a braze material.

Abstract: A turbine shroud assembly for use with a gas turbine engine includes a first shroud segment, a second shroud segment, and a damping strip seal assembly. The first shroud segment has a first carrier segment arranged circumferentially at least partway around a central axis and a first blade track segment supported by the first carrier segment. The second shroud segment is arranged circumferentially adjacent the first shroud segment. The damping strip seal assembly includes an axial seal member, a forward seal, and an aft seal member.

Abstract: Turbine shroud structures and a method of assembling a turbine shroud into a turbine are disclosed. The method includes arranging turbine shroud segments into a full ring and inserting the full ring into a turbine case as a single unit.

Abstract: An additive manufacturing system may include an energy source, an optical system to modify and direct an energy beam from the energy source toward a component to form a melt pool, and a material delivery device to deliver material to the melt pool. The optical system may form an annular energy beam, direct the annular energy beam toward the component, receive at least a portion of thermal emissions produced by the annular energy beam and the melt pool, and direct the portion of the thermal emissions toward an imaging device, which may be used to control the energy source.

Abstract: The disclosure describes acoustic panels (such as for gas turbine engines) and techniques for forming acoustic panels. In some examples, the acoustic panel comprises a coversheet comprising an outer face, an inner face, and a plurality of apertures extend from the outer face to the inner face. The acoustic panel also comprises a 3D printed support layer comprising a polymer and defining a plurality of cell openings, wherein a first side of the support layer opposite the cell openings is coincident with the inner face of the coversheet, and wherein the 3D printed support layer is 3D printed directly onto the inner face of the coversheet.

Abstract: An additive manufacturing technique may include depositing, via a filament delivery device, a filament onto a surface of a substrate. The filament includes a binder and a powder including at least one metal or alloy and at least one braze alloy. The technique also includes sacrificing the binder to form a preform. The technique also includes sintering the preform to form a component including the at least one metal or alloy and the at least one braze alloy.

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 around a central axis of the gas turbine engine. The plurality of flow path components includes a turbine vane, a turbine blade, and a flow path ring. The mounting system is configured to couple the flow path ring to the case.

Abstract: A gas turbine nozzle guide vane structure includes a vane shaped as an airfoil and having a vane trailing edge, an endwall including an opening to receive an end of the vane, and an element securing the endwall and the vane to each other. Clearance remaining between the endwall and the vane defines a plenum to feed cooling air to the vane at a location adjacent the vane trailing edge. Certain arrangements may have a purge groove defined in at least one of the endwall and the vane and located between the endwall and the vane to receive cooling fluid supplied. In certain arrangements, the structure may include a cover sheet on the endwall defining a gap with the vane, the purge groove configured to receive cooling fluid that exits through the gap.

Abstract: An example system includes a common electric starter controller configured to control electric starters of a plurality of gas-turbine engines that are configured to propel an aircraft, wherein the common electric starter comprises: a driver configured to generate, using electrical energy sourced from a battery of the aircraft, power signals that control the electric starters; and a plurality of bus bars configured to directly connect the common electric starter controller to the battery and transport the electrical energy from the battery to the common electric starter controller.

Abstract: A method may include applying a layer comprising a carbon source on a surface of a substrate including silicon; applying a layer comprising silicon on the layer comprising elemental carbon; and heat treating at least the layer comprising the carbon source to cause carbon from the layer comprising the carbon source to react with at least one of silicon from the substrate or silicon from the layer comprising silicon to form silicon carbide.