Abstract: A cover plate for enclosing a cooling cavity of a ceramic matrix composite (CMC) component of a turbine engine may include a base plate dimensioned to cover an open cooling cavity of the CMC component. The base plate has a first side facing the cooling cavity and at least one feature plate is attached to the first side of the base plate. At least one heat transfer augmentation feature is formed on the at least one feature plate and extends into the cooling cavity, wherein the at least one heat transfer augmentation feature is configured to cause turbulence in a cooling air flow within the cooling cavity. Thus, rather than forming complex heat transfer augmentation features on the cooling cavity of the CMC component itself, such features can be easily provided using metal plate or sheet material or separately-formed CMC elements on the cover plate.

Abstract: Acoustic structures for a gas turbine engine are disclosed. In various embodiments, the acoustic structures comprise a panel in the form of a cellular structure having a plurality of cells; and a housing configured to house the cellular structure, the housing including a first rail configured for attachment to a static structure within the gas turbine engine and a second rail configured for attachment to the static structure. In various embodiments, the acoustic structures comprise a liner in the form of a non-segmented or two-piece structure configured to extend about the inner barrel of a nacelle structure. The disclosed panels and liners are configured to maximize the operational area of the acoustic structures by eliminating obstructions from adjacent flow paths.

Abstract: A method includes laying-up a fabric made of ceramic tows to form a fiber preform that has a repeating pattern of seal arc sections, densifying the fiber preform with a ceramic matrix material to form a densified ceramic matrix composite body, and then either before or after the densifying, cutting the fiber preform or the densified ceramic matrix composite body, respectively, along boundaries between the seal arc sections to separate the seal arc segments from each other.

Abstract: An assembly is provided for an aircraft powerplant. This assembly includes a vane structure, a first electric device and a cooling system. The first electric device is disposed within the vane structure. The first electric device includes a first device housing and first electrical circuitry. The first electrical circuitry is housed within an interior of the first device housing. The cooling system is configured to cool the first electrical circuitry. The cooling system includes a first heat exchanger and an air circuit. The first heat exchanger is disposed within the vane structure and thermally coupled to the first electric device. The air circuit extends within the vane structure from an airflow inlet into the air circuit, through the first heat exchanger, to an airflow outlet from the air circuit. The airflow inlet fluidly couples the air circuit to a volume external to the vane structure.

Abstract: A method and apparatus for applying a controlled thickness patch of repair material to a damaged surface adjacent a filleted surface disposed between a case surface and a strut is disclosed. A spacer is positioned on the case surface adjacent the filleted surface, with an outermost surface of the spacer dimensioned to intersect the filleted surface at a predetermined drop height from the case surface. Repair material is applied to the damaged surface by screeding with a straight edge. The straight edge is positioned with a first end against the outermost surface of the spacer and the filleted surface at the drop height, and a second end positioned against the strut or a guide mask disposed thereon so as to form a controlled thickness patch of repair material to the strut and filleted surface when the repair material is screeded.

Abstract: An assembly is provided for an aircraft. This assembly includes a propulsion system and a control system. The propulsion system includes an open propulsor rotor and a turbine engine configured to drive rotation of the open propulsor rotor about an axis. The control system includes a first sensor, a second sensor and a controller in signal communication with the first sensor and the second sensor. The first sensor is configured to provide first sensor data indicative of a first environmental parameter. The second sensor is mounted to the propulsion system and is configured to provide second sensor data indicative of a second environmental parameter. The controller is configured to monitor and/or control operation of the propulsion system using the first sensor data. The controller is also configured to monitor the first sensor data using the second sensor data.

Abstract: An accessible debris separator for a gas turbine engine is provided. The accessible debris separator including a chamber formed by a entrance wall, an exit wall, an inner wall, and an outer wall; a plurality of inlet openings in the entrance wall; a plurality of outlet openings in the exit wall; and a component within the chamber, the component forcing cooling air with debris particulates entering the chamber via an inlet opening of the plurality of inlet openings to take a circuitous path thereby separating the debris particulates from the cooling air prior to the cooling air exiting the chamber via an outlet opening of the plurality of outlet openings.

Abstract: A heat exchanger is provided that includes a heat exchanger core, an inlet manifold, and a turbulence generating structure. The inlet manifold is in fluid communication with the heat exchanger core. The inlet manifold has a fluid inlet and outlet. The turbulence generating structure is disposed adjacent to the fluid inlet, and a separation distance from the fluid outlet. The heat exchanger is configured with a fluid flow path through which a fluid flow enters the heat exchanger through the fluid inlet, encounters the turbulence generating structure and passes through the fluid outlet, and into the heat exchanger core. The turbulence generating structure is configured to produce turbulence in the fluid flow. The separation distance is long enough such that the fluid flow entering the heat exchanger core is substantially free of the turbulence.

Abstract: A method for forming a CMC article includes wrapping first ceramic fibers around a mandrel to form inner fabric layers on the mandrel, depositing a first interface coating material on the first ceramic fibers, densifying the inner fabric layers to a partially-densified state with first ceramic matrix material, wrapping second ceramic fibers around the inner fabric layers to form outer fabric layers around the mandrel, depositing a second interface coating material on the second ceramic fibers, and densifying both the inner fabric layers and the outer fabric layers to a final-densified state with second ceramic matrix material.

Abstract: A hybrid-electric aircraft propulsion system includes an engine, a first electric machine assembly, and a second electric machine assembly. The engine includes a first rotational assembly and a second rotational assembly. The first electric machine assembly includes a first electric machine, a first control unit, first electrical cables, and a first cable conduit. The first electric machine is coupled with the first rotational assembly. The first electrical cables extend between and electrically connect the first electric machine and the first control unit through the first cable conduit. The second electric machine assembly includes a second electric machine, a second control unit, second electrical cables, and a second cable conduit. The second electric machine is coupled with the second rotational assembly. The second electrical cables extend between and electrically connect the second electric machine and the second control unit through the second cable conduit.

Abstract: A machine has: an outer member; an inner member having an outer diameter (OD) surface; and a seal system. A seal housing is mounted to the outer member and has first and second walls; a first seal stage contacting the OD surface and the first wall; a second seal stage contacting the OD surface and the second wall; and a wave spring biasing the seal stages axially apart from each other. The seal stages each have a plurality of seal segments interfitting end to end and each having: a first end; a second end circumferentially opposite the first end; a first face; a second face axially opposite the first face; an inner diameter (ID) face; and an outer diameter (OD) face having a radially protruding lug. The housing has an inner diameter (ID) surface having recesses receiving the lugs of the seal stages to circumferentially retain the seal stages.

Abstract: A craft has: a body including an engine bay; and an engine having an installed condition at least partially in the engine bay. The engine has a heat exchanger having an inlet manifold; and in the installed condition an air flowpath passes through the inlet manifold to the heat exchanger and exits the heat exchanger to the engine bay.

Abstract: A composite vane with a locking feature including a leading edge and a trailing edge opposite chordwise from the leading edge; a radially inner attachment region opposite spanwise from a radially outer attachment region; a span dimension extending between the radially inner attachment region and the radially outer attachment region; a chord dimension extending between the leading edge and the trailing edge; a pressure side opposite a suction side of the composite vane; a dovetail section formed within the composite vane proximate the radially outer attachment region; a shoe member in operative communication with the dovetail section; a boot in operative communication with an inner portion opposite spanwise from the dovetail portion; and a failsafe fastener in operative communication with the boot and the inner portion of the composite vane.

Abstract: An assembly is provided for a turbine engine with a flowpath. This turbine engine assembly includes a fuel injection system. The fuel injection system includes a first fuel injector and a second fuel injector. The fuel injection system is configured to provide the first fuel injector with first fuel and provide the second fuel injector with second fuel. The first fuel may be or include ammonia. The second fuel is different than the first fuel. The second fuel may be or include hydrogen gas. The first fuel injector is configured to direct the first fuel into the flowpath for combustion. The second fuel injector is configured to direct the second fuel into the flowpath for combustion.

Abstract: An assembly is provided for a turbine engine. This assembly includes a stationary structure, a rotating structure, a magnetic-foil bearing and a cooling system. The rotating structure is rotatable about an axis. The magnetic-foil bearing radially supports the rotating structure within the stationary structure. The magnetic-foil bearing includes a magnetic bearing stator, a magnetic bearing rotor and a foil bearing. The foil bearing is disposed radially between the magnetic bearing stator and the magnetic bearing rotor. The cooling system includes a cooling circuit configured to deliver cooling air to at least a first bearing component. The first bearing component is configured as or otherwise includes one of the magnetic bearing stator, the magnetic bearing rotor and the foil bearing.

Abstract: A combustor for rich-quench-lean combustion includes a combustor shell, a combustion chamber delimited by the combustor shell, and fuel injectors. The combustion chamber includes a primary zone, a quench zone, a secondary zone, and an outlet arranged in axial flow series. Openings through the combustor in the quench zone provide a quench air flow into the quench zone. A method for rich-quench-lean combustion for the combustor includes contemporaneously injecting a rich air-fuel mixture into the primary zone and injecting a second air flow into the quench zone in which the second air flow is equal to or less than four times the primary air flow.

Abstract: Disclosed herein is a ceramic matrix composite comprising a preform comprising a plurality of plies; a ceramic matrix encompassing the plies and distributed through the plies; and thermally conducting particles distributed through the ceramic matrix. Disclosed herein is a method comprising distributing thermally conducting particles between plies in a preform; infiltrating chemical vapors of a ceramic precursor into the plies; and reacting the ceramic precursor to form a matrix.

Abstract: A steam injected turbine engine includes a core engine section that generates a first gas flow, a burner where an inlet flow is mixed with fuel and ignited to generate thermal energy, and an evaporator where thermal energy from at least the first gas flow is used to transform water into a first steam flow. The first steam flow is injected into a core flow through the core engine.

Abstract: A combustor liner for a gas turbine engine is disposed about an axis and defines a combustion chamber. The combustor liner includes a plurality of attachment elements circumferentially spaced about an outer wall of the combustor liner opposite the combustion chamber and a plurality of support elements connecting the plurality of attachment elements to combustor liner such that the plurality of attachment elements is radially spaced from the outer wall of the combustor liner. Each of the plurality of attachment elements includes an opening configured to slidingly receive a pin.

Abstract: A method for repairing a gas turbine engine component, comprising: providing at least one gas turbine engine component comprising a surface area having a portion comprising an aperture including a first size and corrosion; removing the corrosion from the aperture to form an aperture free of corrosion and comprising a second size; treating the aperture free of corrosion and comprising a second size to form an aperture free of corrosion; disposing an amount of at least one anti-corrosion agent on the treated aperture free of corrosion to form an anti-corrosion agent-coated treated aperture free of corrosion; and removing at least a portion of the anti-corrosion agent from the anti-corrosion agent-coated treated aperture free of corrosion to form an aperture free of corrosion comprising the first size and a residual amount of the anti-corrosion agent.