Abstract: A gas turbine engine is provided. The gas turbine engine includes a turbomachine having a compressor section, a combustor, and a turbine section arranged in serial flow order, the turbomachine further including an outer casing and, during operation of the gas turbine engine, an exhaust gas flow from the turbine section; and a fuel cell assembly positioned within the outer casing of the turbomachine, the fuel cell assembly having a fuel cell defining an inlet positioned to receive a portion of the exhaust gas flow, an outlet positioned to provide output products directly to the exhaust gas flow, or both.

Abstract: An airfoil for a turbine engine includes a body defining a pressure side and a suction side, the body extending between a leading edge and a trailing edge and also extending radially to define an outer edge. A radially-extending plenum can be disposed at the outer edge of the airfoil. A flared portion can be disposed at the outer edge of the body extending from the suction side.

Abstract: Provided is a system and method that can safely generate and execute an outage plan for a power grid based on severe weather-driven events. In one example, the method may include receiving predicted or current operational power system state data from a power grid and weather conditions associated with the power grid, identifying one or more nodes on the power grid to de-energize based on the operational state data and the current weather conditions, determining a sequence of instructions to perform to de-energize the one or more identified nodes based on the operational state data and the current weather conditions associated with the power grid, and generating an outage plan including mitigation steps for ensuring the stability and security of the power grid which includes the determined sequence of instructions to be executed and store the outage plan in the memory.

Abstract: A thermal management system includes a thermal circuit having a thermal transport bus with a thermal fluid flowing therethrough. The thermal transport bus includes first and second bus segments. First and second thermal loads are on the first and second bus segments, respectively, and have different first and second inlet temperature requirements. The thermal management system includes a plurality of heat exchangers in thermal communication with the first and second thermal loads. The heat exchangers include a first heat exchanger and one or more second heat exchangers. The first heat exchanger is on one of the first or second bus segments for rejecting heat to engine fuel. The thermal fluid is split between each of the first and second bus segments such that only a portion of the thermal fluid flows through the first heat exchanger to accommodate the different first and second inlet temperature requirements.

Abstract: A gas turbine engine oil flow control system can include a variable flow oil pump useful to provide oil at varying rates to a variety of oil consumers, such as, power gearboxes, engine shaft bearings, electrical generators, etc. Oil flow control valves that have an ability to provide a variable flow of oil can be used in conjunction with the variable flow oil pump. Flow sensors can be used along with an oil flow controller to measure a flow of oil at various points in the gas turbine engine oil flow control system. The oil flow controller can use information from the flow sensors along with a variable consumption demand association with one or more of the oil consumers (either provided to the oil controller or calculated based upon an operational need of the oil consumer) to change operation of the variable flow oil pump and/or oil flow control valve.

Abstract: An engine component with an abradable material and treatment is disclosed herein. An example engine component includes a substrate having a first thickness and defining at least a first substrate surface, the substrate extending along an axial direction, an abradable material on the first substrate surface, the abradable material defining a first abradable material surface, a second abradable material surface spaced radially apart from the first abradable material surface and defining a second thickness, and a treatment, the treatment extending from the first abradable material surface through at least a portion of the first thickness of the substrate.

Abstract: Disclosed herein are example variable flowpath casings for blade tip clearance control. An example casing for a turbine engine includes an annular substrate extending along an axial direction, the annular substrate including a first surface and a second surface that is radially inward relative to the first surface; an actuator structure coupled to the second surface of the annular substrate; and a smart structure cantilevered from the second surface of the annular substrate, the smart structure including: a support structure, a first region of the support structure coupled to the second surface of the annular substrate, a second region of the support structure coupled to the actuator structure; and a radially inward surface defining a variable surface, the support structure to move the variable surface in a radial direction.

Abstract: A rotary machine seal assembly (200) includes seal segments (102) configured to circumferentially extend around a rotor (108) between a stator (106) and the rotor (108) of a rotary machine. One or more seal segments include a shoe plate (110, 410, 710, 910), a seal base (112, 412, 712, 912), and at least one intermediate member (114, 414, 714). The shoe plate is disposed along the rotor. The seal base is disposed radially outward of the shoe plate. At least one intermediate member is coupled to and disposed between the seal base and the shoe plate. The at least one intermediate member includes an actuator portion (302, 402, 702, 902) having first coefficient of thermal expansion and a constrictor portion (304, 404, 704, 904) having a different, second coefficient of thermal expansion.

Abstract: A furnace system includes at least one wall that defines a workspace. The workspace includes an aircraft part to be cleaned. One or more vacuum pumps are configured to achieve a predetermined vacuum level in the workspace. A gas purifier is configured to remove impurities in a gas to create a purified gas, the purified gas being directed from the gas purifier into the workspace, the purified gas being of a purity and composition that is effective to disassociate oxides on a surface or in a crack of the aircraft part to be cleaned when the workspace is heated to a predetermined temperature and the predetermined vacuum level is achieved in the workspace.

Abstract: An additive manufacturing apparatus, a computing system, and a method for operating an additive manufacturing apparatus are provided. The method includes obtaining two or more images corresponding to respective build layers at a build plate, wherein each image comprises a plurality of data points comprising a feature and corresponding location at the build plate; removing variation between the features of the plurality of data points; and normalizing each feature to remove location dependence in the plurality of data points.

Abstract: A dome-deflector assembly for a combustor of a gas turbine includes a dome portion having a dome-side swirler opening therethrough, and a deflector portion having a deflector-side swirler opening therethrough. The dome portion and the deflector portion are connected together to form a dome-deflector cavity therebetween. The deflector portion includes a first-side surface and a second-side surface, the second-side surface being arranged within the dome-deflector cavity, and the second-side surface including a plurality of stress-relief contours arranged in a pattern about the deflector-side swirler opening.

Abstract: A combustor assembly for a gas turbine engine including an outer casing, the gas turbine engine defining an axial direction, the combustor assembly includes a liner at least partially defining a combustion chamber extending between an aft end and a forward end generally along the axial direction within the outer casing, the liner including an inner surface facing the combustion chamber and an outer surface facing away from the combustion chamber, and a damper assembly extending between the outer casing and the outer surface of the liner, the damper assembly including a selectively separable support and a damper spring, the damper spring being disposed between the support and the liner.

Abstract: A turbine engine comprising an engine core having a rotor and a stator, and a floating seal assembly sealing at least portions of the rotor and the stator relative to a higher-pressure area and a lower-pressure area. The floating seal assembly can comprise a carriage assembly at least partially defining a seal cavity and a seal body floating within the seal cavity. The floating seal assembly can further include at least one of a seal located between the seal body and the carriage assembly, and a seal face located between the seal body and the carriage assembly.

Abstract: This disclosure is directed to seal assemblies for a turbomachine. The seal assemblies include stationary and rotating components and at least one interface between the stationary and rotating components. The seal assembly further includes a self-lubricating lattice element made of carbon or a carbon-based material. The self-lubricating lattice element may have a porous and compressible microstructure capable of retaining a liquid substance. During engine operation, the self-lubricating lattice element can compress and expel some portion of the liquid substance to form a liquid-containing layer between the rotating and stationary components of the seal assembly. Also described herein are self-lubricating wear sleeves for use in other portions of the turbomachine.

Abstract: The present disclosure relates to use of a workflow for automatic prescription of different radiological imaging scan planes across different anatomies and modalities. The automated prescription of such imaging scan planes helps ensure contiguous visualization of the different landmark structures. Unlike prior approaches, the disclosed technique determines the necessary planes using the localizer images itself and does not explicitly segment or delineate the landmark structures to perform plane prescription.

Abstract: A fan assembly for an engine has a fan blade, a disk having a disk segment, a trunnion mechanism having a trunnion extending at least partially through the disk segment, and first and second attachment systems. The trunnion has a platform and a shaft. The fan blade is adjacent to the platform of the trunnion. The trunnion is attached to the disk segment using the first attachment system along a preload path. The first and second attachment systems further include first and second retention features, respectively, separate from the preload path. During normal operation of the fan assembly, the first attachment system retains the trunnion within the disk along a first load path. Upon a failure in the trunnion, the first and second retention features together retain the trunnion within the disk segment along a second load path, the first load path being different than the second load path.

Abstract: Apparatuses and systems are provided herein for unducted propulsion systems. The system includes an aft housing for low drag for high subsonic sustained flight. A plurality of blades are affixed to the aft housing, wherein the housing defines a flowpath curve extending from the axial extent of the aft blade root to the aft end of the aft housing. The flowpath curve is described by an axial direction parallel to an axis of rotation and a radius from the axis of rotation. The flowpath curve includes first point having a first radius where the radius reaches a maximum aft of the aft blade root and a second point forward of the first point having a second radius where the radius stops decreasing. The ratio of the first radius to the second radius is greater than or equal to 1.081.

Abstract: A heat exchanger is provided. The heat exchanger includes one or more exchanger units that each have a core and manifolds. The core of an exchanger unit is formed by multiple unit cells coupled together in flow communication to create a flow distribution grid. Each unit cell has at a first primary channel, a second primary channel, a first secondary channel in flow communication with the first primary channel, and a second secondary channel in flow communication with the second primary channel. The first secondary channel traverses through the second primary channel and the second secondary channel traverses through the first primary channel. Each manifold includes two chambers for separating fluids flowing through the heat exchanger, with one chamber being in flow communication with one of the primary channels and having one or more tubes traversing therethrough to provide flow communication between the other primary channel and the other chamber.

Abstract: Damping devices, turbomachines, and methods of damping vibration are provided. For example, a damping device for damping vibration of a shaft rotatable about an axis of rotation is provided. The damping device defines radial and axial directions. The damping device comprises a bearing, a housing, and a damper element. The housing and damper element define a cavity therebetween for receipt of a damping fluid. The cavity has a length along the axial direction that is curved away from the axis of rotation. As another example, a turbomachine comprising a shaft rotatable about an axis of rotation includes a damping device positioned annularly about the shaft. The damping device comprises a housing and a damper element defining a cavity therebetween for receipt of a damping fluid that has a curved shape. The cavity is curved in a plane extending along the radial and axial directions and including the axis of rotation.

Abstract: A system for coating ceramic fibers for use in manufacturing a ceramic matric composite (CMC) article includes a frame having a plurality of frame members arranged so as to create a void therebetween. At least one of frame members includes a hollow body and at least one perforated hole defined in the hollow body. Thus, the ceramic fibers are securable at respective ends of the frame and extend across the void. The frame also includes an inlet in fluid communication with the perforated hole(s) so as to allow a coating material to flow into and through the hollow body and out of the perforated hole(s) at a location of at least a portion of one of the ceramic fibers. As such, the coating material is configured to cause the portion of one of the ceramic fibers to separate from the frame such that the portion is uniformly coated with the coating material.