Abstract: A transceiver system may include a transmitter, a receiver, an antenna port that is connectable to the transmitter or to the receiver, a filter send port, and a filter return port. The filter ports may be antenna-side or receiver-side, and connectable across at least one filter between the antenna port and the receiver. A transceiver apparatus may include a housing including the transmitter, the receiver, a transceiver switch, and a filter switch assembly in a chamber of the housing. The ports may be accessible through a wall of the housing. A method for filtering a signal include switching, in response to a first signal, a receiver or a transceiver of a transceiver system from an unfiltered path connected to the antenna port to a filtered path connected to the antenna port. The method may further include switching, in response to a second signal, the receiver to the unfiltered path.

Abstract: A status indicator for a capacitor may include first and second indicator plates, each respectively defining a first face and a second face visually distinct from the first face. The first face of each of the first and second indicator plates is displayed during nominal operation of the capacitor. The second face of only one of the first and second indicator plates is displayed in response to a partial failure of the capacitor. The second face of each of the first and second indicator plates is displayed in response to a complete failure of the capacitor. A system may include a capacitor, and the status indicator coupled to the capacitor. A method for visually indicating a status of a capacitor may include controlling, by a controller, first and second indicator plates to display selected faces indicating nominal operation, partial failure, or complete failure of the capacitor.

Abstract: A joined part comprises a first portion and a second portion. The first portion comprises a guide slot at least partially defined by a porous structure. A joint material is disposed within the porous structure. The second portion is disposed within the guide slot and contacts the porous structure and the joint material disposed therein to form an interfacial joint between the first portion and the second portion. A method of manufacturing the joined part includes disposing a joint material into a porous structure of a guide slot of a first portion, inserting a second portion into the guide slot, and contacting the porous structure and the joint material disposed therein to form an interfacial joint between the first portion and the second portion.

Abstract: A system for melting, sintering, or heat treating a material is provided. The system includes a cathode, an anode, and a focus coil assembly having a quadrupole magnet. The quadrupole magnet includes four poles and a yoke. The four poles are spaced apart and surround a beam cavity. Each of the four poles includes a pole face proximate the beam cavity and an end opposite the pole face. The first and third poles are aligned along an x-axis and configured to have a first magnetic polarity at their respective pole faces and a second magnetic polarity opposite the first magnetic polarity at their respective ends. The second and fourth poles are aligned along a y-axis and configured to have the second magnetic polarity at their respective pole faces and the first magnetic polarity at their respective ends. The yoke surrounds the poles and is coupled to the poles.

Abstract: A differential gearbox assembly for a turbine engine having a fan shaft and a drive shaft. The differential gearbox assembly includes an epicyclic gear assembly coupling the fan shaft to the drive shaft. The epicyclic gear assembly includes a sun gear, a planet gear constrained by a planet carrier, and a ring gear. The sun gear is coupled to the drive shaft and the planet carrier is coupled to the fan shaft. The sun gear, the planet gear, and the ring gear all rotate about the drive shaft. The differential gearbox assembly includes an electric machine assembly that includes an input coupled to the epicyclic gear assembly. The electric machine assembly provides mechanical power to the fan shaft through the epicyclic gear assembly.

Abstract: A sealing system for sealing between components. The sealing system includes a first component, a second component, and a seal assembly including a seal member. The first component includes a first component surface, and the second component includes a second component surface. The second component surface is oriented in a direction transverse to the first contact surface. The seal member has a plurality of contact surfaces including a first contact surface and a second contact surface. The first contact surface is configured to contact the first component surface and to slide relative to the first component surface. The second contact surface is configured to contact the second component surface and to slide relative to the second component surface. The second contact surface is oriented in a direction transverse to the first contact surface.

Abstract: Core-shell microparticles, along with methods of their fabrication and use, are provided. The core-shell microparticles may include a core comprising a first metallic material having a first chromium content and a shell surrounding the core and comprising a second metallic material having a second chromium content that is less than the first chromium content. For example, the first chromium content may be 5% by weight or greater of elemental chromium within the first metallic material.

Abstract: A gas turbine engine includes: a turbomachine including a combustion section and an exhaust assembly arranged in serial flow order; and a fuel system. The fuel system includes: a hydrogen fuel tank for holding a hydrogen fuel in a liquid phase; and a hydrogen delivery assembly in thermal communication with the exhaust assembly. The hydrogen delivery assembly includes: a liquid hydrogen line in fluid communication with the hydrogen fuel tank; a gaseous hydrogen line in fluid communication with the combustion section of the gas turbine engine; and a heat exchanger tubing positioned within the exhaust assembly downstream of the liquid hydrogen line and upstream of the gaseous hydrogen line.

Abstract: A system for diagnosing an additive manufacturing device is provided. The system includes a first module configured to: obtain one or more parameters for a digital twin of a component of the additive manufacturing device based on raw data from the component of the additive manufacturing device; and generate physics features for the digital twin of the component of the additive manufacturing device based on the one or more parameters and one or more transfer functions, a second module configured to obtain one or more classifiers for classifying the component as a first condition or a second condition based on physics features; and a third module configured to: determine a health of the component based on the generated physics features of the first model and the one or more classifiers.

Abstract: A fuel delivery system for a gas turbine engine includes a fuel source; a draw pump downstream of the fuel source for generating a liquid fuel flow from the fuel source; a main fuel pump downstream of the draw pump; and a fuel oxygen reduction unit downstream of the draw pump and upstream of the main fuel pump.

Abstract: This disclosure provides systems, devices, apparatus and methods, including computer programs encoded on storage media, for a wireless power transmission apparatus that supports charging of one or more wireless power receiving apparatuses. The wireless power transmission apparatus may include multiple primary coils organized in groups (referred to as zones). Each zone may have a local controller for managing operation of one primary coil in the zone at a time. A master controller may selectively couple the primary coils to the local controllers. When a first primary coil is coupled to the local controller for a zone, the other primary coils in that zone may be disabled. The master controller may manage which primary coils from neighboring zones are coupled to their respective local controllers. Thus, when the first primary coil is activated, the adjacent primary coils (near the first primary coil) can be muted or disabled to mitigate undesirable interference.

Abstract: A combustor assembly is generally provided. The combustor assembly includes a volute wall extended annularly around a combustor centerline. The volute wall is extended at least partially as a spiral curve from a circumferential reference line around the combustor centerline. The volute wall defines a combustion chamber therewithin. An annular inner wall is extended at least partially along a lengthwise direction from the volute wall. An annular outer wall is extended at least partially along the lengthwise direction from the volute wall. The inner wall and the outer wall are each separated along a radial direction from the combustor centerline. A primary flow passage is defined between the inner wall and the outer wall in fluid communication from the combustion chamber.

Abstract: A liner support system for an exhaust liner in an aircraft engine. The liner support system includes a plurality of posts that space the exhaust liner from the exhaust duct, the plurality of posts spacing the exhaust liner from the exhaust duct further supporting the exhaust liner. Each post includes an interface region adjacent to the back side of the exhaust liner sealed to the back side of the exhaust liner, a shank extending to a low pressure region, and a hollow passageway internal to the shank, providing fluid communication between the interface region and the low pressure region. The low pressure region results in pressure against the liner, pulling the liner adjacent the post interface region against the post while preventing fluid leakage between the exhaust liner and the interface region. The posts create a pattern of alternating pressures in the liner allowing for elimination of hangers.

Abstract: A component for a turbine engine includes a body having an outer surface confronting a combustion air flow path and defining an interior, as well as a first cooling passage having at least a portion supplying cooling air to the interior of the body. The component also includes a cyclone separator having a cooling air inlet, a clean air outlet, and a dirty air outlet.

Abstract: Partition damper seal configurations for segmented internal cooling hardware apparatus are disclosed. An example apparatus includes an inner wall and an outer wall, the outer wall spaced apart from the inner wall in a radial direction, a space between the inner and outer walls defining a flow passage, and a body positioned between the inner and outer walls, the body traversing the inner and outer walls in an axial direction and attached to an inner surface of the outer wall and an outer surface of the inner wall, the body to detach from the inner and outer surfaces and to at least partially seal the flow passage in response to the outer wall moving relative to the inner wall.

Abstract: Devices, systems, and methods for providing software to aircraft using a distributed ledger are disclosed. A software delivery system includes aircraft having an engine control system configured to verify and install software utilized by components of the aircraft, an electronic distribution system coupled to the aircraft, an edge manager coupled to the electronic distribution system, and computing devices acting as nodes in a distributed ledger base maintaining a distributed ledger. The electronic distribution system verifies a request for software, requests software, and initiates an installation protocol with the engine control system. The edge manager maintains software. The distributed ledger base is coupled to the aircraft, the electronic distribution system, and the edge manager.

Abstract: An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion. The fuel nozzle can include both a primary and secondary fuel passage, and an additional air passage to provide for greater flame control, fuel provision, or local fuel and air mixing prior to combustion.

Abstract: A turbomachinery engine comprises a ducted fan, a high-pressure compressor, a low-pressure turbine, a gearbox, and a ducted engine correlation parameter (DECP). The DECP is within a range of 0.10-0.25 and is defined as 10*D/GR/NLPT/NHPC, where D is a fan blade tip diameter at a leading edge of the ducted fan measured in feet, GR is a gear ratio of the gearbox, NLPT is a stage count of the low-pressure turbine, and NHPC is a stage count of the high-pressure compressor.

Abstract: In the field of high voltage direct current (HVDC) power transmission networks there is a need for an improved sensor failure detector. A sensor failure detector, for use in HVDC power transmission networks, includes an intelligent electronic device. The intelligent electronic device has a first input to receive in-use a number of first sample values from a first sensor measuring a given operational characteristic, and a second input to receive in-use a number of second sample values from a second sensor measuring the same given operational characteristic. The intelligent electronic device also includes a comparator module that is programmed to compare the first and second sample values with one another, and to establish a sensor failure when the first and second sample values differ from one another by more than a primary threshold for a predetermined first number of samples.