Abstract: A method for predicting distortion of a part during sintering in an additive process includes receiving a computerized representation of a complex geometric part, discretizing the computerized representation of the complex geometric part into a plurality of elements, processing the plurality of elements of the computerized representation of the complex geometric part with a machine-learning model configured to predict a distorted geometry of the complex geometric part in response to a sintering process, wherein the machine-learning model is trained to predict distortion of a set of primitive geometric coupons represented by image data fed into the machine-learning model during training, the set of primitive geometric coupons having fewer geometries than the complex geometric part, the complex geometric part comprises a plurality of geometries corresponding to geometries associated with the set of primitive geometric coupons, and generating a computerized representation of the predicted distorted geometry of t

Abstract: A method for forming an object includes moving a recoat assembly over a build material, where the recoat assembly includes a first roller and a second roller that is spaced apart from the first roller, moving the second roller above the first roller in a vertical direction, rotating the first roller of the recoat assembly in a counter-rotation direction, such that a bottom of the first roller moves in a coating direction, contacting the build material with the first roller of the recoat assembly, thereby fluidizing at least a portion of the build material, while the second roller is spaced apart from the build material in the vertical direction, and moving the fluidized build material with the first roller, thereby depositing a second layer of the build material over an initial layer of build material positioned in a build area.

Abstract: There is provided markers, systems, and methods for creating and utilizing a marker containing identification information. The embodiments include an identifying marker comprised of high temperature material for tracking a component in a high temperature environment. The marker may be disposed on the component such that the marker is subject to high temperatures while affixed to the component. The marker may provide the ability to track a history of the component the marker is attached to for maintenance.

Abstract: Methods, apparatus and systems for generating verifiable conflict-free flight plans for aircraft are disclosed. In an embodiment, a server computer receives a set of air traffic flight plans for an airspace that includes elements, and receives at least two of aerodynamic constraint data, business constraint data and operational constraint data for an aircraft. The server computer then generates using a first constraint satisfaction solver, a plurality of candidate flight plans for the aircraft based on the at least two of the aerodynamic constraint data, the business constraint data and the operational constraint data. The server computer next checks, utilizing a second constraint solver, for conflicts with the elements of the air traffic flight plans for the airspace, and provides at least one verifiable conflict-free flight plan for the aircraft from the plurality of candidate flight plans when a candidate flight plan is conflict-free from all of the elements of the set of air traffic flight plans.

Abstract: A gearbox assembly includes a first gear and a second gear. The first gear includes a plurality of first gear teeth. The second gear includes a plurality of second gear teeth. The plurality of first gear teeth and the plurality of second gear teeth mesh with each other as the first gear and the second gear rotate. A profile shape of at least one first gear tooth of the first gear is characterized by a total profile modification between 66 micrometers and 120 micrometers.

Abstract: Various systems and devices are provided for facilitating communication in a healthcare setting. In one example, a system for providing medical information can include a processor that, in response to executing machine-readable instructions, can generate a patient dashboard comprising the medical information for a patient and a patient communication thread. The processor can also output the patient dashboard to a display, wherein the patient dashboard further comprises a first link proximate to a displayed parameter from the medical information and the processor can obtain communication among care providers monitoring the patient and virtual healthcare assistants configured to communicate on the communication thread. The processor can also output the communication from the care providers, the virtual healthcare assistances, or any combination thereof, in the patient communication thread of the patient dashboard provided by the display.

Abstract: Systems and methods for thermally processing composite components are provided. In one exemplary aspect, a system includes a thermal system, a mover device, and a control system. The system also includes a plurality of vessels in which one or more components may be placed. The vessels are similarly shaped and configured. A vessel containing the one or more components therein may be mounted into a chamber defined by the thermal system during thermal processing. The thermal system and vessels include features that allow components to be thermally processed, e.g., compacted, burnt-out, and densified via a melt-infiltration process, a polymer impregnation and pyrolyzing process, or a chemical vapor infiltration process. utilizing the same thermal system and common vessel design. The control system may control the thermal system and mover device to automate thermal processing of the composite components.

Abstract: An integrated fuel cell and combustor assembly includes a combustor that is fluidly coupled with at least one upstream compressor that generates compressed air. A fuel cell stack having a cathode and an anode is fluidly coupled to the combustor. The fuel cell stack is configured to receive intake fuel and a portion of the compressed air as intake air, to generate a fuel cell power output using the intake fuel and the intake air, and to direct a fuel and air exhaust from the fuel cell stack into the combustor. A self-reliant air supply system is fluidly coupled with the at least one upstream compressor and the fuel cell stack, and is configured to supply the intake air to the fuel cell stack. A fault-tolerant controller is configured to detect a transient event within the combustor and to control the self-reliant air supply system during the transient event.

Abstract: A combined cycle propulsion system for a flight vehicle includes a compressor-fed combustion engine, and a multi-mode supersonic engine. The multi-mode supersonic engine includes an adjustable inlet section, a combustion section arranged downstream of the adjustable inlet section and including a first combustor portion having at least one rotating detonation combustor and a second combustor portion having a supersonic combustion type combustor, and an adjustable exhaust nozzle section arranged downstream of the combustion section. The at least one rotating detonation combustor functions as a pilot for the supersonic combustion type combustor.

Abstract: A system and method for evaluating blood flow in a vessel of a patient includes a catheter containing a first pressure sensor and a second pressure sensor and configured to simultaneously measure pressure data within a vessel on either side of a stenosis. Pressure data generated by the catheter includes a first series of pressure measurements from the first pressure sensor a second series of pressure measurements from the second pressure sensor. The system and method further includes a fractional flow reserve (FFR) calculation module executable on one or more processors and configured to calculate a stability index for each of two or more portions of the pressure data, wherein each stability index indicates at least one of heart rate stability and catheter stability for the respective portion of the pressure data. An optimal time window is identified based on the stability indexes for calculation of FFR based on the pressure data.

Abstract: A passive clearance control limits thermal expansion between stator components relative to rotor components. A control ring controls clearance in a passive manner and is located on or adjacent to stationary components which thermally expand during engine operation. The control ring is formed of material having low coefficient of thermal expansion such as CMCs (Ceramic Matrix Composites) and therefore limits, inhibits or restrains expansion of the adjacent stator components as temperatures increase. Limiting expansion of the stator component reduces rotor/stator clearances and limits parasitic leakage of fluid along the flow path through the engine core.

Abstract: A composite blade assembly for a turbine engine. The composite blade assembly having a core, a first skin and a second skin. The core having a composite structure. The first skin having at least one composite ply. The second skin having at least one composite ply. The first skin having a first radius. The second skin having a second radius.

Abstract: An airfoil structure including an airfoil and a spring and damper system. The airfoil including a longitudinal axis. The spring and damper system is connected to the airfoil to rotate the airfoil about the longitudinal axis to change airfoil pitch in response to a load applied to the airfoil.

Abstract: A turbine engine for an aircraft. The turbine engine includes a combustor and a steam system. Fuel and steam are injected into the combustor to mix with compressed air to generate a fuel and air mixture. The fuel and air mixture is combusted in the combustor to generate combustion gases. The steam system is fluidly coupled to the combustor as the steam source to provide steam to the combustor. The steam system includes a hot gas path and a steam hot gas path component. The hot gas path is fluidly coupled to the combustor to receive the combustion gases and to route the combustion gases through the steam system. The steam hot gas path component includes a wall having a combustion-gas-facing surface facing the hot gas path and a hydrophobic coating formed on the combustion-gas-facing surface.

Abstract: A turbine engine includes a turbomachine having a compressor section, a combustion section, and a turbine section in serial flow order and together defining a working gas flow path; a thermal system operable with the turbomachine; a heat exchanger in fluid communication with the thermal system; and a plurality of elongated delivery devices in fluid communication with the compressor section of the turbomachine. The plurality of elongated delivery devices are configured to deliver a fluid from the compressor section to a surface of the heat exchanger.

Abstract: A system for detecting hydrogen leaks within a vehicle includes a hydrogen sensor for generating data indicative of a level of hydrogen present within a compartment of the vehicle and a computing system. The computing system determines at least one of the level of hydrogen present within the compartment or a rate of change of the level of hydrogen present within the compartment and compares the determined at least one of the level of hydrogen present within the compartment or the rate of change of the level of hydrogen present within the compartment to a threshold value. When the determined at least one of the level of hydrogen present within the compartment or the rate of change of the level of hydrogen present within the compartment exceeds the threshold value, the computing system initiates a control action for reducing the level of hydrogen present within the compartment.

Abstract: An electric power system for a vehicle includes at least one electric machine, one or more power rectifiers, and a plurality of DC channels. The at least one electric machine includes a plurality of tooth-wound multi-phase windings that are substantially magnetically decoupled, and the at least one electric machine is mechanically balanced even if one of the plurality of windings is de-energized. The one or more power rectifiers are configured to produce rectified power from the power generated by the at least one electric machine. The plurality of DC channels are formed after the at least one power rectifier and are configured to provide DC power to one or more loads within a vehicle.

Abstract: Methods, apparatus, systems and articles of manufacture for mounting a gas turbine engine are described. An apparatus for mounting a gas turbine engine to a pylon, the gas turbine including an upstream section and a downstream section, the gas turbine defining a roll axis, a yaw axis, and a pitch axis, the apparatus including: a first mount to couple the upstream section of the gas turbine engine to the pylon; a second mount to couple the upstream section of the gas turbine engine to the pylon, the second mount downstream of the first mount; a thrust linkage to couple the upstream section to the pylon, wherein the downstream section is decouplable from the upstream section without decoupling the first mount, the second mount, and the thrust linkage.

Abstract: Structures for reducing forward loads in compressors are described. A compressor includes inner and outer circumferential support structures positioned concentrically around a central axis, and an aft-most stage including a vane extending radially inward from the outer circumferential support structure. An axial length of the aft-most stage is defined by a spacer arm of the inner circumferential support structure. The vane includes a root, a tip, and a trailing edge extending between the root and the tip. A ratio of a first radial distance between a first point located at an intersection of the tip of the vane and the trailing edge to a radially inner wall of the spacer arm of the inner circumferential support structure to a second radial distance between the first point and a second point located at an intersection of the root of the vane and the trailing edge is between 0.95 and 4.5.

Abstract: An additive manufacturing (AM) system includes a housing defining a chamber, a build platform disposed within the chamber, and an upper gas inlet configured to supply an upper gas flow in a first direction parallel to the build platform. The AM system includes a lower gas inlet disposed in the chamber and configured to supply a lower gas flow in a second direction toward a bottom wall of the chamber, and a flow directing system configured to receive the lower gas flow and redirect the lower gas flow in the first direction parallel to the build platform. The AM system includes one or more gas delivery devices fluidly coupled to the upper and lower gas inlets and configured to regulate one or more flow characteristics of the upper and lower gas flows and a gas outlet configured to discharge the upper and lower gas flows from the chamber.