Abstract: Rotor assemblies and methods for manufacturing airfoils for rotor assemblies are provided. For example, a rotor assembly comprises a rotary structure extending circumferentially about an axial centerline of a gas turbine engine and an airfoil having a root and a tip. The root is coupled to the rotary structure and has a bulbous shape. The airfoil is formed from a plurality of composite plies, a portion of which defines at the root first and second end surfaces, which are in contact with the rotary structure and together define a chisel-shaped end of the root. In another embodiment, a rotor assembly comprises an outer rotor extending circumferentially about an axial centerline of a gas turbine engine and a composite outer rotor blade having a root and a tip. The blade root is coupled to the outer rotor and extends inward along a radial direction toward the axial centerline.

Abstract: A system for hyperpolarizing a substance is provided. The system includes a cryostat and a polarizer. The cryostat is operative to generate radicals within the substance by exposing the substance to electromagnetic radiation. The polarizer is operative to hyperpolarize the substance via the radicals. Once the substance is polarized, the radicals contained within the substance are quenched by adjusting a temperature of the substance to greater than or equal to a melting point of the substance. In embodiments, the polarizer may then rapidly freeze the substance.

Abstract: The systems and methods described herein relate to a dome of a gas turbine assembly configured to suppress pressure pulsations. The systems and methods provide a dome having an aperture configured to surround an injector assembly of a combustor. The dome having a front panel extending radially from the aperture. The systems and methods couple a first cavity to the front panel. The first cavity includes a series of ducts. A first duct of the series of ducts is configured to receive airflow into the first cavity from a compressor and a second set of ducts of the series of ducts and a third duct of the series of ducts are configured to direct airflow to the combustor from the first cavity, wherein the third duct has a larger diameter than the second set of ducts.

Abstract: A binder jet printed article includes a part having a top portion, a bottom portion, and an overhang extending from the top portion and a support structure formed around the part that may block deformation of the part during post-printing thermal processing. The support structure includes a skid positioned adjacent to the bottom portion that may support the part, a first plurality of support features disposed along an outer perimeter of the skid, and a second plurality of support features disposed on the top portion of the printed part. The first and second plurality of support features form a lattice around the printed part such that the printed part is nested within the support structure.

Abstract: A planetary gear system can include a sun gear, an outer ring gear, and at least one planet gear driving the sun gear and planet gear. The planet gear can include an inner ring having an inner race, an outer ring having an outer race circumscribing and confronting the inner race. A plurality of rolling elements can be located between and in contact with the inner and outer races, which can include least one damper.

Abstract: A system and method for additively manufacturing a component including features for part identification are provided. The method includes selectively depositing a contrast agent on a cross sectional layer to define a component identifier of the component and directing energy from an energy source onto the contrast agent to fuse the contrast agent and the cross sectional layer. The contrast agent may be an x-ray emission contrast agent that is read using an x-ray emission spectroscopy method, an infrared contrast agent that is read using an infrared camera or an infrared scanner, or a radioactive contrast agent that is read using a gamma ray spectrometer.

Abstract: A turbine engine component includes: a body bounded by an end face; and a seal slot having an opening communicating with the end face, the seal slot including a receptacle defining a boundary configured to receive and position a spline seal, and an open chamber communicating with the seal slot and extending beyond the boundary.

Abstract: The present invention provides methods for the preparation of compounds useful in in vivo therapeutic and diagnostic applications. In particular, the present invention provides a method for the synthesis of 1,4,7,10-tetraazacyclododecane-1,4,7,10-tetraacetic acid (DOTA) and also methods for the preparation of metal chelates of DOTA.

Abstract: An accelerometer includes a membrane; a laser source, the laser source producing a laser beam, the laser beam directed at the membrane causing the membrane to vibrate; a transparent cap, the transparent cap disposed between the laser source and the membrane; an antireflecting film disposed on an outer surface of the transparent cap; and a detector sensing a reflected portion of the laser beam, the reflected portion including a modulated intensity. An acceleration signal is based in part on the frequency of the modulated intensity of the reflected portion of the laser beam.

Abstract: A patient monitoring system includes at least two wireless sensing devices, each configured to measure a different physiological parameter from a patient and wirelessly transmit a parameter dataset. The system further includes a receiver that receives each parameter dataset, a processor, and a monitoring regulation module executable on the processor to assign one of the at least two wireless sensing devices as a dominant wireless sensing device and at least one of the remaining wireless sensing devices as a subordinate wireless sensing device. The physiological parameter measured by the dominant wireless sensing device is a key parameter and the parameter dataset transmitted by the dominant wireless sensing device is a key parameter dataset. The key parameter dataset from the dominant wireless sensing device is processed to determine a stability indicator. The subordinate wireless sensing device is then operated based on the stability indicator for the key parameter.

Abstract: A system-on-module (SOM) for controlling an unmanned vehicle (UV) is provided. The SOM comprises a circuit board, a first processing system in operative communication with the circuit board, and a second processing system in operative communication with the circuit board. The first processing system includes one or more first processing units and a volatile programmable logic array. The first processing system is configured to execute a first process for the UV. The second processing system includes one or more second processing units and a non-volatile programmable logic array. The second processing system is configured to monitor execution of the first process by the first processing system.

Abstract: An electric discharge machining (EDM) system includes an electrode set having a plurality of electrodes. Each electrode is electrically-isolated from the other electrodes. The EDM system includes a power supply configured to generate an electric discharge between a workpiece and the electrode set to remove material from the workpiece. The power supply includes a multi-loop driver system and an AC-to-DC component that outputs DC electric power. The multi-loop driver system includes a plurality of power loop circuits coupled to an output of the AC-to-DC component. Each power loop circuit is electrically-isolated from other power loop circuits and is coupled to at least one electrode. The multi-loop driver system includes a drive controller coupled to the power loop circuits. The drive controller is configured to transmit at least one control signal to at least one power loop circuit to drive the AC-to-DC component to generate the electric discharge.

Abstract: A method that includes acquiring image data, and determining a quality level for a measurement presented in a medical image. The quality level is based on the acquired image data. The method also includes generating the medical image including a measurement indicator based on the quality level, and displaying the medical image on a display device.

Abstract: A turbine shroud is disposed between stages of stationary turbine nozzles. The turbine shroud includes arcuate shroud segments sealingly engaged with one another. Each shroud segment includes a bottom panel with a radially inner surface and a radially outer surface and opposite ends. Each end includes an end face, an end cutback face spaced from the end face, and an intermediate surface extending between the end face and the end cutback face to define a recess. One or more seals overlap the recess of a circumferentially adjacent pair of shroud segments to produce a sealed joint.

Abstract: A system for performing ultrasonic procedures within a turbomachine. The system includes a bladder and a probe assembly. The bladder includes a bladder body for positioning within the turbomachine. Further, the bladder is inflatable to at least partially define an ultrasonic tank within the turbomachine for containing a fluid medium. The probe assembly includes an extension member and ultrasonic transmitter coupled to or positioned within the extension member. The extension member is insertable into the ultrasonic tank for positioning the ultrasonic transmitter within the ultrasonic tank.

Abstract: A method and system of determining or predicting a climb profile for an aircraft, includes receiving, by a controller module, an initial climb profile defining a portion of a flight plan for the aircraft between takeoff and a cruise profile, and an altitude climb constraint defining at least one altitude limitation of the aircraft, determining, by the controller module, that the initial climb profile does not satisfy the altitude constraint, and determining an updated climb profile based on a set of subsequent climb models.

Abstract: A combustor assembly lift system (200) comprises an exterior lift frame (220) comprising a base portion (222) and an arm portion (224), wherein the arm portion extends away from a base portion to form an interior, and, an interior combustor assembly engagement frame (240) at least partially disposed in the interior of the exterior lift frame and configured to temporarily secure to at least a portion of a combustor assembly. The interior combustor assembly engagement frame is connected to the base portion of the exterior lift frame.

Abstract: A method and system, the method including receiving semantic descriptions of features of an asset extracted from a first set of images; receiving a model of the asset, the model constructed based on a second set of a plurality images of the asset; receiving, based on an optical flow-based motion estimation, an indication of a motion for the features in the first set of images; determining a set of candidate regions of interest for the asset; determining a region of interest in the first set of images; iteratively determining a matching of features in the set of candidate regions of interest and the determined region of interest in the first set of images to generate a record of matches in features between two images in the first set of images; and displaying a visualization of the matches in features between two images in the first set of images.

Abstract: There is provided a method for optimizing a manufacturing process of a new part. The method includes executing, by a system configured to drive the manufacturing process, a set of manufacturing functions. Executing these functions include receiving data associated with one or more field parts similar to the new part, and generating, based on the data, a forecast representative of a longevity of the one or more parts. The method further includes generating a digital thread forming a surrogate model for the new part, based on the forecast. Further, the method includes creating the set of manufacturing functions based on the surrogate model and manufacturing the new part according to the set of manufacturing functions.

Abstract: A modular power system includes a plurality of electronic modules, the plurality of modules is arranged in a manner that each of the modules is detachable from the others, and adjacent modules are in fluid communication with each other through a passage, and at least one thermally activated element is disposed within each said passage. In normal operation, the thermally activated element is in an unexpanded state, and fluid communication between the plurality of modules is allowable through a space between the thermally activated element and the passage, and in a failure event when at least one of the modules fails, the thermally activated element is activated and expanded to block the passage between the failed module and the other modules. A method of mitigating failure propagation between a plurality of modules in the modular power system is also described.

Abstract: Systems and methods for managing and/or exchanging aviation records are provided. One example aspect is directed to a method that includes receiving, at one or more processors, an aviation record in a first format from a first computing system. The method includes performing, at the one more processors, a quality assurance procedure on the aviation record in the first format based on historical data. The method includes determining, at the one or more processors, whether the aviation record in the first format is valid based on the quality assurance procedure. The method includes selectively translating, at the one or more processors, the aviation record into a standardized format based on whether the aviation record in the first format is valid. The method includes storing, at the one or more processors, the aviation record in the standardized format if the aviation record in the first format is valid.

Abstract: A gas turbine engine and combustor assembly is generally provided. The gas turbine engine may include an outer casing while the combustor assembly may include a liner and a damper assembly. The liner may at least partially define a combustion chamber extending between an aft end and a forward end generally along an axial direction within the outer casing. The liner may include an inner surface facing the combustion chamber and an outer surface facing away from the combustion chamber. The damper assembly may extend between the outer casing and the outer surface of the liner. The damper assembly may include a selectively separable support and damper spring. The damper spring may be disposed between the support and the liner.

Abstract: The subject matter disclosed herein relates to wide band gap semiconductor power devices and, more specifically, to high-energy implantation masks used in forming silicon carbide (SiC) power devices, such as charge balanced (CB) SiC power devices. An intermediate semiconductor device structure includes a SiC substrate layer having a first conductivity type and silicon carbide (SiC) epitaxial (epi) layer having the first conductivity type disposed on the SiC substrate layer. The intermediate device structure also includes a silicon high-energy implantation mask (SiHEIM) disposed directly on a first portion of the SiC epi layer and having a thickness between 5 micrometers (?m) and 20 ?m. The SiHEIM is configured to block implantation of the first portion of the SiC epi layer during a high-energy implantation process having an implantation energy greater than 500 kiloelectron volts (keV).

Abstract: Methods for preparing an environmental barrier coating and the resulting coating are provided. The methods and products include the incorporation of a continuous ceramic inner layer and a segmented ceramic outer layer on a CMC component. The segmented ceramic outer layer may be formed by thermal spray techniques. The coating is more stable at higher temperatures and provides for a longer lifetime of the coated component.

Abstract: The present application provides a combustor. The combustor may include a fuel supply line, a fuel nozzle, and a number of flow-device pathways connecting the fuel supply line and the fuel nozzle. The flow-device pathways may include a counter-swirl configuration.

Abstract: Methods of forming a cooling passage on a turbine component having a component wall with an internal surface and an external surface, are disclosed. An opening is formed passing through the component wall and fluidly connecting the internal and external surfaces. The opening includes a metering section extending from the internal surface to a metering end, and a diffuser area extending from the metering end to the external surface. A preformed cap element is added to close a portion of the diffuser area to form the cooling passage with a diffusion section extending from the metering end to the external surface. The preformed metal cap element includes a projection extending internally of the external surface and into the diffusion area to define an internally facing section of the diffusion section. The cooling passage extends through the component wall and fluidly connects the internal surface and the external surface.

Abstract: According to some embodiments, a system to facilitate hierarchical data exchange may include an aggregation platform data store containing electronic records. A data aggregation platform may collect, from a plurality of data source devices, information associated with a plurality of data sources and store the collected information into the aggregation platform data store. The data aggregation platform may also receive a data request from a data consumer device, and, responsive to the received data request, determine a precision tier associated with the data request. The data aggregation platform may then automatically calculate a resource value for the data request based on the precision tier. It may then be arranged for information from the aggregation platform data store to be modified and transmitted to the data consumer device.

Abstract: A turbine blade is described herein, the turbine blade including a blade root, a blade tip, and an airfoil extending between the blade root and the blade tip. The airfoil has opposite pressure and suction sides extending between a forward leading edge and an aft trailing edge of the airfoil, and a maximum thickness located between the leading edge and the trailing edge. The blade tip includes a winglet extending laterally outward from at least one of the pressure side and the suction side from a leading point between the leading edge and the maximum thickness aftward to a trailing point between the maximum thickness and the trailing edge.

Abstract: A turbine blade tip cooling system includes a turbine blade having a tip cavity, a tip rail surrounding at least a portion of the tip cavity and at least one internal cooling cavity. The tip rail has an inner rail surface, an outer rail surface, an end surface and at least one tip rail pocket open at the end surface and fluidly connected to the at least one internal cooling cavity that carries a coolant. A tip rail cooling insert attaches to the at least one tip rail pocket, and has insert cooling channel(s) and a coolant collection plenum for directing coolant from the at least one internal cooling cavity to the insert cooling channel(s).

Abstract: A compressor bleed slot apparatus includes: an annular compressor casing; a stator vane row disposed inside the compressor casing; a blade row mounted for rotation about a centerline axis inside the compressor casing, axially downstream of the stator row; a bleed slot passing through the compressor casing, wherein the bleed slot is bounded by inboard and outboard walls defined within the compressor casing, the bleed slot having an inlet positioned axially between the stator vane row and the blade row, the bleed slot extending along a slot axis, at least a portion of the bleed slot lying within an axial extent of the blade row; an annular array of struts interconnecting the inboard and outboard walls; and an annular supplemental flange extending radially outward from the compressor casing, wherein at least a portion of the supplemental flange is axially positioned within an axial extent of the bleed slot.

Abstract: An axial flow turbine comprising a casing, a rotor having an axial rotational axis and rotatably mounted into the casing, at least one set of a plurality of moving blades supported by the rotor; and at least one diaphragm having an outer ring, an inner ring, concentric to the outer ring, and a plurality of static blades mounted therebetween, at least the outer ring being split in an upper half and a lower half along a vertical joint plane. The turbine diaphragm comprises an assembly system for assembling the upper half to the lower half while allowing the upper half and the lower half to move axially relative to each other.

Abstract: An approach relates to manipulation of tools or instruments in the performance of a task by a robot. In accordance with this approach, sensor data is acquired and processed to identify a subset of instruments initially susceptible to manipulation. The instruments are then manipulated in the performance of the task based on the processed sensor data.

Abstract: A hydrogen storage system includes a pressure-sealed sleeve defining an interior and having an outlet, a shaft extending through the interior of the sleeve, a set of porous chambers arranged axially along and concentric to the shaft, and a hydrogen storage, wherein at least some hydrogen gas is supplied to the outlet.

Abstract: The present invention relates to a power control method and device in a wireless power transmission system. According to the present invention, even if a CEP packet is not transmitted from a wireless power reception device over a certain period of time, a wireless power transmission device may additionally determine whether the wireless power reception device is located in a charging area and sustainably perform charging.

Abstract: The subject matter disclosed herein relates to semiconductor power devices, such as silicon carbide (SiC) power devices. In particular, the subject matter disclosed herein relates to shielding regions in the form of body region extensions for that reduce the electric field present between the well regions of neighboring device cells of a semiconductor device under reverse bias. The disclosed body region extensions have the same conductivity-type as the body region and extend outwardly from the body region and into the JFET region of a first device cell such that a distance between the body region extension and a region of a neighboring device cell having the same conductivity type is less than or equal to the parallel JFET width. The disclosed shielding regions enable superior performance relative to a conventional stripe device of comparable dimensions, while still providing similar reliability (e.g., long-term, high-temperature stability at reverse bias).

Abstract: One example aspect of the present disclosure is directed to a method for operating a gas turbine engine. One example aspect of the present disclosure is directed to a method for operating a gas turbine engine, the gas turbine engine including at least a high pressure spool and a low pressure spool. The method includes causing, by one or more control devices, electrical power to be drawn from the high pressure spool and the low pressure spool into a power distribution system. The method includes determining, by the one or more control devices, a power adjustment event associated with the high pressure spool. The method includes initiating, by the one or more control devices, a power assist operation to redirect electrical power to the high pressure spool based at least in part on the power adjustment event.

Abstract: A component for a gas turbine engine including a core and an outer enclosure. The core includes an exterior surface extending along a length between a first end and a second end and at least partially defines a cooling cavity on the exterior surface extending from the first end along at least a portion of the length. The cooling cavity is fluidly coupled to an air supply at the first end. The outer enclosure includes an outer surface. The outer enclosure is positioned outside the core and extends from the first end of the core along at least a portion of the length of the core and at least partially defines the cooling cavity.

Abstract: A centralized monitoring unit (CMU) receiving patient monitoring data from multiple patient monitoring devices includes at least two monitoring technician stations and an assignment management module. Each monitoring technician station is configured to present alarms for each patient in the group of patients to a CMU technician. The assignment management module is executable by a processing system to calculate a load index for each monitoring technician station based on alarms for patients in the group of patients. The load index for each monitoring technician station is calculated based on at least one of a number of alarms, an alarm type of each alarm, a severity of each alarm, and a duration of continuous alarming at the monitoring technician station. Assignment of the multiple patients amongst the at least two monitoring technician stations is then distributed based on the load indexes.

Abstract: The present disclosure is directed to an engine component for a gas turbine engine, the engine component including a substrate that includes a composite fiber and defines a surface. An energy harvesting fiber is positioned within the substrate.

Abstract: A nuclear medicine (NM) multi-head imaging system is provided that includes a gantry, plural detector units mounted to the gantry, and at least one processor operably coupled to at least one of the detector units. The detector units are mounted to the gantry. Each detector unit defines a detector unit position and corresponding view oriented toward a center of the bore. Each detector unit is configured to acquire imaging information over a sweep range corresponding to the corresponding view. The at least one processor is configured to, for each detector unit, determine plural angular positions along the sweep range corresponding to boundaries of the object to be imaged, generate a representation of each angular position for each detector unit position, generate a model based on the angular positions using the representation, and determine scan parameters to be used to image the object using the model.

Abstract: Various methods and systems are provided for a water collection feature of an imaging probe assembly. In one example, a medical imaging probe assembly includes an electrical connector, an imaging probe, and an electrical cable including a first end connected to the electrical connector and a second end coupled to the imaging probe, the cable including a water collection feature arranged at an outer surface of the cable, proximate to the first end. The water collection feature may have converging edges extending outward from the cable, toward the first end, shaped to draw water droplets away from the cable.

Abstract: An apparatus includes a multi-channel DC bus assembly comprising a first channel and a second channel, a first electromechanical device coupled to a positive DC link of the first channel, and a second electromechanical device coupled to a positive DC link of the second channel. A first DC-to-AC voltage inverter is coupled to the positive DC link of the first channel and a second DC-to-AC voltage inverter is coupled to the positive DC link of the second channel. The apparatus further includes a bi-directional voltage modification assembly coupled to the positive DC link of the second channel and a first energy storage system electrically coupled to the first electromechanical device.

Abstract: The present disclosure is directed to a system for monitoring wear on a gearbox of a wind turbine. A controller of the system is configured to determine a torque exerted on a rotor shaft of the wind turbine or a generator shaft of the wind turbine based on measurement signals received from a first sensor of the system. The controller is also configured to determine an accumulated wear value for the gearbox based on the torque.

Abstract: A lubrication system for a main bearing positioned around a main shaft of a wind turbine includes a seal ring positioned around the shaft adjacent to the bearing, at least one gear adjacent to the seal ring, a mechanical lubricant pump arranged to engage the at least one gear, and at least one lubricant for providing lubrication to the bearing. Thus, as the shaft rotates, the gear(s) drives the lubricant pump such that the pump continuously provides the lubricant to the bearing so long as the shaft is rotating.

Abstract: An aircraft includes an electric power source having a combustion engine and an electric generator. The electric generator is powered by the combustion engine. The aircraft also includes a propulsion assembly including a propulsor and an electric motor, the electric motor configured for rotating the propulsor. The aircraft also includes an electrical outlet configured for connection with an outside power sink. The electrical outlet and the propulsion assembly are selectively in electrical communication with the electric power source such that the electric power source selectively provides electrical power to one of the electrical outlet or the propulsion assembly.

Abstract: A fuel nozzle for a gas turbine engine is generally provided. The fuel nozzle includes an outer sleeve extended circumferentially around a fuel nozzle centerline and extended along a longitudinal direction substantially co-directional to the fuel nozzle centerline. The outer sleeve defines a plurality of first radially oriented air inlet ports through the outer sleeve in circumferential arrangement relative to the fuel nozzle centerline. The fuel nozzle further includes a centerbody positioned radially inward of the outer sleeve. The centerbody is extended along the longitudinal direction substantially co-directional to the fuel nozzle centerline and wherein the centerbody is concentric to the fuel nozzle centerline and the outer sleeve. The centerbody defines a plurality of second radially oriented air inlet ports through the centerbody in circumferential arrangement relative to the fuel nozzle centerline.

Abstract: A double submodule for a modular multilevel converter comprising a first and second submodule coupled to the first. Each submodule comprises an asymmetric H bridge circuit with two parallel bridges branches, connected between a first and a second direct voltage node of the submodule. Each bridge branch is formed by a series connection from a controllable power semiconductor switch and a diode. A storage capacitor is connected in parallel to the asymmetric H bridge circuit between the first and the second direct voltage node of the submodule. The first and the second submodule are interconnected in such a way that a power semiconductor switch or a diode is part of a bridge branch of the first submodule as well as part of a bridge branch of the second submodule. A modular multilevel converter, comprises a series connection of such double submodules in each of its converter branches, is also disclosed.

Abstract: The present invention relates to an ultrasonic diagnosis apparatus and a power supply device. The ultrasonic diagnosis apparatus comprises: an ultrasonic host including a pluggable main battery pack; a backup power supply device including a plurality of pluggable backup battery packs, for powering the ultrasonic host; and a trolley for carrying the ultrasonic host and the backup power supply device; wherein a specification of each of the plurality of backup battery packs is identical to that of the main battery pack.

Abstract: A gas turbine engine including core engine is provided. Air may enter the core engine through an inlet and travel through and engine air flowpath extending through the core engine, e.g., generally along an axial direction of the gas turbine engine. The gas turbine engine additionally includes a cooling air flowpath extending outwardly generally along the radial direction of the gas turbine engine. The cooling air flowpath extends between an inlet in flow communication with engine air flowpath and an outlet defined by an opening in an outer casing of the core engine. Moreover, the gas turbine engine includes a heat exchanger positioned at least partially within the outer casing the core engine with the cooling air flowpath extending over or through the heat exchanger.

Abstract: Methods and systems for generating a tunable or customizable activated product composition are related. In certain embodiments, one or more of electric pulse parameters, flow rate, or sample container size are varied so as to generate the activated product composition. The activated product composition may be customized or optimized based for a particular patient or procedure.