Abstract: A method for transmitting a set of conforming data frames in a specialized data network, the method comprising providing, from a data source, at least one specialized header frame to a data destination by way of the specialized data network, generating, at the data source, a set of conforming data frames, and providing at least a subset of the conforming data frames to the data destination by way of the specialized data network.

Abstract: A generator assembly includes a stator assembly coupled to an engine stator component of a propulsion engine, the stator assembly including: a stator support structure fixedly attached to the engine stator component; a stator disposed on a supporting surface of the stator support; a manifold coupled to the stator support, the manifold defining a connection volume and including at least one coolant opening at a connection end of the manifold; and an electrical connector extending between the stator and a connection device disposed on the connection end. The generator assembly also includes a rotor assembly comprising a rotor support structure connected to a shaft of the propulsion engine and a rotor attached to the rotor support structure, wherein the rotor rotates in conjunction with the shaft to generate a power signal that travels through the electrical connector to the connection device.

Abstract: A fuel nozzle for a combustor may include a primary fuel passage having a primary fuel outlet. A secondary fuel passage having a secondary fuel outlet. A valve located within the secondary fuel passage. The valve may include a stationary hub having a plurality of first angled surfaces. The valve may include a movable sleeve having a plurality of second angled surfaces. Each of the plurality of first angled surfaces aligns axially with a respective one of the plurality of second angled surfaces to define a slot therebetween. The valve is movable between a plurality of positions to open, to close, or to partially open the slots.

Abstract: A contrail suppression system includes a shell having an exhaust gas inlet, an exhaust gas outlet, a condensate drain and a flow chamber in fluid communication with the exhaust gas inlet, the exhaust gas outlet and the condensate drain. The exhaust gas inlet is in fluid communication with a jet exhaust nozzle of a gas turbine engine. A first tube bundle is disposed within the flow chamber downstream from the exhaust gas inlet. The first tube bundle includes an inlet and an outlet. The inlet of the first tube bundle is fluidly connected to a first cooling medium source. A second tube bundle is disposed within the flow chamber downstream from the first tube bundle and upstream from the exhaust gas outlet. The second tube bundle includes an inlet and an outlet. The inlet of the second tube bundle is fluidly connected to a second cooling medium source.

Abstract: A system comprises a gas turbine engine including a compressor, combustor, gas turbine, the combustor including a plurality of late lean fuel injectors; and wash system configured to be attached to and in fluid communication with the a plurality of late lean fuel injectors of the combustor. The wash system includes a water source supplying water; a first fluid source supplying a first fluid; a mixing chamber in communication with the water source and first fluid source; a water pump to pump water to the mixing chamber; a first fluid pump to pump the first fluid to the mixing chamber; a fluid line in fluid communication with the mixing chamber and at least one of the plurality of late lean fuel injectors so fluid from the mixing chamber is injected into the combustor at late lean fuel injectors. The wash system is operated with the gas turbine engine off-line.

Abstract: The present disclosure relates to a wind turbine comprising a wind turbine rotor with a plurality of blades supported on a support structure, a generator operatively coupled to the wind turbine rotor for generating electrical power, a power electronic converter for converting electrical power generated by the generator to a converted AC power of predetermined frequency and voltage, and a main wind turbine transformer having a low voltage side and a high voltage side for transforming the converted AC power to a higher voltage. One or more electric filters are connected to the high voltage side of the main transformer, wherein the electric filters are arranged in the support structure. The present disclosure also relates to wind farms, and particularly offshore wind farms, and to methods for operating wind farms.

Abstract: An aircraft defining a longitudinal direction and a lateral direction is provided. The aircraft includes: a fuselage; an engine mounted at a location spaced from the fuselage of the aircraft, the engine comprising a plurality of rotor blades; and a fuselage shield attached to or formed integrally with the fuselage at a location in alignment with the plurality of rotor blades along the lateral direction, the fuselage shield comprising a first layer defining a first density and a second layer defining a second density, the first density being different than the second density.

Abstract: A method of operating an aircraft engine coupled to a wing of an aircraft including: setting a pitch of a plurality of rotor blades of a rotor assembly of the aircraft engine at non-uniform pitch angles along a circumferential direction of the aircraft engine such that the plurality of rotor blades define a first pitch at a first position and a second pitch at a second position, wherein the second position is 180 degrees offset from the first position, and wherein the first pitch is different from the second pitch.

Abstract: A particle separator includes a separator body in a primary fluid passageway of a machine. The primary fluid passageway includes one or more bleed holes through which a diverted portion of the fluid flowing in the primary fluid passageway toward a volume of the machine is diverted into an auxiliary flow passageway that bypasses the volume and directs the diverted portion of the fluid toward one or more other components of the machine. The separator body is coupled with the inner wall and/or outer wall of the primary fluid passageway. The separator body includes an upstream edge positioned to separate at least some particles carried by the fluid from the fluid as the diverted portion of the fluid bends around and flows over the at least one upstream edge of the separator body and into the auxiliary flow passageway.

Abstract: A combustor liner for a gas turbine has a cold side liner segment, and a hot side liner segment, with a baffle cavity between the cold side liner segment and the hot side liner segment. At least one cooling airflow dispersing member is arranged within the baffle cavity. The at least one cooling airflow dispersing member includes a main cavity portion, and at least one peripheral cavity portion surrounding the main cavity portion. The main cavity portion includes a main cavity inlet side having a cooling airflow opening, a main cavity outlet side having plurality of hot side cooling airflow openings, and at least one peripheral cavity outlet flow passage providing fluid communication between the main cavity portion and the at least one peripheral cavity portion. The at least one peripheral cavity portion includes a peripheral cavity outlet side having a plurality of hot side cooling airflow openings.

Abstract: A method and system for monitoring neuromuscular blockade in patients during surgical procedures. A stimulator provides stimulation to a nerve of the patient, such as train-of-four (TOF). Following such stimulation, the system and method creates a predicted recovery trend for the patient that is based upon measured recovery trend and a recovery model. The recovery model estimates a recovery trend for the patient based on initial model parameter values. The recovery model creates a predicted recovery trend that is used to estimate a recovery time for the patient. The trend values from the patient are monitored and compared to the predicted trend values throughout the operation as long as the NMT measurement is on. During recovery, the recovery model and recovery time estimates are updated based on the recovery trend being formed from measurements of the patient.

Abstract: An additive manufacturing apparatus includes a first print module includes a first stage configured to hold a first component and a first radiant energy device. The resin support is configured to be positioned between the first stage and the first radiant energy device. A second print module includes a second stage configured to hold a second component and a second radiant energy device. The resin support is configured to be positioned between the second stage and the second radiant energy device. A control system is configured to translate the resin support based on a condition of the first print module and the second print module through the first print module and the second print module.

Abstract: A hybrid electric propulsor equipped with a hydraulic coupling is provided. In one aspect, a propulsor includes a gas turbine engine and an electric machine operatively coupled thereto. The gas turbine engine includes a fan spool and a core spool. The electric machine is operatively coupled with the fan spool. A hydraulic coupling defines a sealed volume in which hydraulic transmission fluid is provided. The hydraulic coupling encases at least a portion of the fan spool and at least a portion of the core spool. The hydraulic coupling hydraulically couples the fan spool and the core spool and allows for power transmission between the fan spool and the core spool.

Abstract: A method may include receiving a request for a first set of data to be gathered by an unmanned aircraft system. A first unmanned aircraft system may be identified that is capable of gathering the first data. A request may be transmitted to the first unmanned aircraft system to gather the first set of data. The first set of data gathered by the first unmanned aircraft system may be received.

Abstract: A load adaptive linear electrical generator system is provided for generating DC electrical power. The electrical generation system includes one or more power generation modules which will be selectively turned on or off and additively contribute power depending on the DC power demand. Each power generating module includes a pair of linear electrical generators connected to respective ones of a pair of internal combustion piston based power assemblies. The piston in the internal combustion assembly is connected to a magnet in the linear electrical generator. The piston/magnet assembly oscillates in a simple harmonic motion at a frequency dependent on a power load of the electrical generator. A stroke limiter constrains the piston/magnet assembly motion to preset limits.

Abstract: A gas turbine engine includes a turbomachine and a thermal management system. The thermal management system includes a heat source heat exchanger configured to collect heat from the turbomachine during operation; a heat sink heat exchanger; and a thermal transport bus having a heat exchange fluid configured to flow therethrough at a pressure within an operational pressure range. The thermal management system defines an operational temperature range for the heat exchange fluid, the operational temperature range having a lower temperature limit less than about zero degrees Fahrenheit at a pressure within the operational pressure range and an upper temperature limit of at least about 1000 degrees Fahrenheit at a pressure within the operational pressure range.

Abstract: A turbomachine blade, and a coupon for a turbomachine blade, are disclosed. The blade may include an airfoil body having a pressure side and a suction side connected by a leading edge and a trailing edge, a coolant feed passage defined in the airfoil body, and a coolant reuse passage defined in the airfoil body. The blade may also include a first cooling circuit defined in the airfoil body. The first cooling circuit may include a rearward passage extending toward the trailing edge from and fluidly coupled to the coolant feed passage, and a radially spreading return passage extending away from the trailing edge toward and fluidly coupled to the coolant reuse passage. The cooling circuit may also include a radially extending turn passage coupling the rearward passage and the radially spreading return passage. A first set of obstructions may be positioned in the radially extending turn passage.

Abstract: A method, medium, and system to receive an indication of an assembly including a plurality of different components to produce by additive manufacturing (AM), determine based on a forward search process that starts with individual components of the plurality of components and iteratively adds other components of the plurality of components thereto in combinations until an entirety of the assembly is accounted for, determine based on a reverse search process that starts with the entirety of the assembly and iteratively removes components of the plurality of components therefrom in combinations until a two-component set is reached, automatically select an optimal combination of the plurality of components from the combinations determined by the forward search and reverse search processes; and transmit the selection of the optimal combination of the plurality of components to an AM controller.

Abstract: A turbomachine defining a flowpath therethrough at which a fluid is compressed is provided, in which the turbomachine includes a first compressor in serial flow arrangement upstream of a second compressor. The second compressor includes a port at the flowpath and is configured to receive at least a portion of the fluid from the flowpath from the second compressor. The first compressor includes a vane positioned at the flowpath and the vane includes an opening at the flowpath configured to egress the portion of the fluid from the port into the flowpath.

Abstract: A turbine nozzle assembly includes at least one airfoil and an outer endwall coupled to a radial outer end of the at least one airfoil. A mounting rail is coupled to the outer endwall and extends at least partially radially outward from the outer endwall and at least partially circumferentially along the outer endwall. A stress relief structure is defined in the mounting rail. The stress relief structure includes an end opening defined in a radial outer surface of the mounting rail, a slot defined through the rail thickness of the mounting rail and coupled to the end opening, and an oblong opening defined through the rail thickness of the mounting rail and coupled to a radial inner end of the slot. The oblong opening is arranged asymmetrically in a circumferential direction relative to the slot to relieve stress where prevalent in the mounting rail.

Abstract: A turbine engine that includes an engine core having at least a compressor section and a combustion section. The combustion section includes a combustor. The combustor section or combustor includes a fuel-air mixing assembly fluidly coupled to the compressor section. The fuel-air mixing assembly includes an outer wall, a center body at least partially circumscribed by the outer wall, and an annular flow passage between the outer wall and center body. At least one fuel orifice includes a fuel outlet fluidly coupled to the annular flow passage.

Abstract: Various systems are provided for a power supply system. In one example, the system includes a power distribution unit configured to receive power from a main power source and an uninterruptible power supply (UPS), wherein the UPS is configured to directly power an output AC load, the UPS is further configured to power an output DC load after coupled through one or more transformers.

Abstract: The present invention relates to a method of processing a component, wherein the component comprises at least one opening in a surface thereof, the method comprising: placing the component in an electrophoretic fluid comprising particles of a masking material as an electrode, applying a voltage to the component and a counter electrode of the component, depositing particles of the masking material in the electrophoretic fluid into the at least one aperture through electrophoresis to mask the at least one aperture; processing a surface of the component; and removing the masking material in the at least one opening.

Abstract: A turbomachine diaphragm including a sealing section having a first end portion that extends to a second end portion through an intermediate portion; and at least one rail member including a first end section that extends from the first end portion of the sealing section to a second end section through an intermediate section having an inner surface section and an outer surface section, the second end section including multiple weld passes disposed on opposed sides of the second end section for mitigation of thermal tensions on the diaphragm, the multiple weld passes forming a cladding welded to the diaphragm, wherein the cladding includes a stainless austenitic steel.

Abstract: A method is provided for casting a component. Accordingly, a casting core is provided within a cavity of a component mold. The casting core defines an inner component shape and includes a core wall. The core wall defines a core outer surface and a core inner surface disposed opposite the core outer surface. The core inner surface defines a core cavity. The casting core also includes a removal facilitation feature. The component is cast within the cavity of the component mold with the casting core positioned therein. The cast component is removed from the component mold and the casting core is removed from the cast component.

Abstract: A box-shaped air intake silencer with vertical baffles for a gas turbine system. The box-shaped silencer has a silencer housing having opposing ends with a first end closed and a second end opened to permit passage of air. Opposing sidewalls extend between the first end and the second end with each of the sidewalls operative to receive a perpendicular flow of intake air. A silencer having vertically, spaced baffles are disposed within the housing. A first end of the baffles face the first end of the housing and a second end of the baffles faces the second end of the housing. Each of the baffles extend horizontally between the first end and the second end of the housing. The baffles receive the perpendicular flow of intake air proximate the first end of the housing and direct the intake air towards the second end of the housing for passage therethrough.

Abstract: In a jet engine having a core that sources a first flow of fluid and a component (such as a fan, a pump, and/or a bleed line) that sources a second flow of fluid, and where the first flow of fluid will typically have, at least during ordinary operation, a higher temperature than the second flow of fluid, at least one flow aperture formed by a first passageway to receive at least a portion of the aforementioned second flow of fluid, wherein that first passageway is comprised of at least one material that (by design and intent) deflects as a function of temperature such that a flow of the second flow of fluid through the at least one flow aperture is thereby desirably modulated.

Abstract: A method of additively printing an extension segment on a workpiece includes pretreating a workpiece-interface of the workpiece using an energy beam emitted from an energy beam source of an additive manufacturing machine, providing a pretreated workpiece-interface having received a pretreatment, with the pretreatment remediating an aberrant feature of the workpiece and/or the workpiece-interface. The method further includes additively printing an extension segment on the pretreated workpiece-interface using an energy beam emitted from the energy beam source of the additive manufacturing machine. The aberrant feature includes one or more aberrant regions of the workpiece-interface having been determined from a digital representation of the workpiece-interface captured by a vision system. The pretreatment includes heat-conditioning at least a portion of the workpiece-interface including the one or more aberrant regions of the workpiece-interface.

Abstract: Partial integrated core-shell investment casting molds that can be assembled into complete molds are provided herein. Each section of the partial mold may contain both a portion of a core and portion of a shell. Each section can then be assembled into a mold for casting of a metal part. The partial integrated core-shell investment casting molds and the complete molds may be provided with filament structures corresponding to cooling hole patterns on the surface of the turbine blade or the stator vane, which provides a leaching pathway for the core portion after metal casting. Core filaments that can be used to supplement the leaching pathway, for example in a core tip portion of the mold are also provided herein.

Abstract: Methods, apparatus, systems, and articles of manufacture to provide damping of an airfoil are disclosed. An example airfoil is disposed in a flow path, the airfoil including a shell defining an exterior surface of the airfoil and forming a cavity in an interior surface of the airfoil, and a lattice damper disposed in the cavity, the lattice damper to reduce vibrational loads exerted on the airfoil.

Abstract: It is provided methods of installing a mechanical damper apparatus to an external surface of a tower of a wind turbine, the tower being in an erect state.

Abstract: A decentralized electrical power allocation system is provided. The system includes a power bus, electric power consumers, and at least two power source assemblies. Each power source assembly includes a power controller and a power source. Each power controller is configured to execute an adaptive droop control scheme so as to cause their respective power sources to output power to meet a power demand on the power bus applied by the power consumers. The power output of a given power source is controlled based at least in part on correlating a power feedback of the given power source with a droop function that represents an efficiency of the given power source to generate electrical power for a given power output. The droop functions are collaboratively defined so that one power source shares more output at lower power levels while another power source shares more output at higher power levels.

Abstract: A dispatch advisor for operating a power plant having at least one gas turbine with flexibility is described. The dispatch advisor can generate a representation of a flexible base load map for operating the power plant. The representation can include an aggregation of a primary base load operating space and an expanded portion of the base load operating space. The representation offers a range of operating values for operational parameters of the power plant during base load at various base load settings at predetermined ambient conditions and corresponding power output and efficiency values that are attained while operating the power plant at the range of operating values. This offers an operator of the power plant with flexibility in controlling the plant during base load.

Abstract: Systems and methods are provided for computed tomography (CT) imaging. In one embodiment, a method comprises adaptively blending at least two input image volumes with different spatially-variant noise characteristics to generate an output image volume with uniform noise throughout the output image volume. In this way, images may be reconstructed from projection data with data redundancy without introducing image artifacts from stitching images or variance in image noise due to the data redundancy.

Abstract: An electric power source includes: a battery defining a state of charge; a converter in electrical communication with the battery; and a controller in operable communication with the converter, the controller including a compensation toggle circuit configured to provide a compensation toggle value based on a power output of the battery; a dynamic droop control circuit configured to receive the compensation toggle value and switch an output droop value of the dynamic droop control circuit from an upper output droop measurement to a lower output droop measurement, wherein the lower output droop measurement is based on the state of charge of the battery.

Abstract: A runner for a hydraulic machine comprising a band, a crown, a plurality of blades extending between the crown and the band, wherein the runner comprises a plurality of runner segments which together define the runner, each runner segment comprising a band portion, a crown portion and a blade, which portions are integrally formed with one another, each runner segment being attachable to another segment at a band joining edge and a crown joining edge, wherein the band joining edge and the crown joining edge are each spaced apart from the blade of the segment.

Abstract: A favorable merging or grouping of simply connected regions into which the array of information samples is sub-divided, is coded with a reduced amount of data. To this end, a predetermined relative locational relationship is defined enabling an identifying, for a predetermined simply connected region, of simply connected regions within the plurality of simply connected regions which have the predetermined relative locational relationship to the predetermined simply connected region. Namely, if the number is zero, a merge indicator for the predetermined simply connected region may be absent within the data stream. In other embodiments, spatial sub-division is performed depending on a first subset of syntax elements, followed by combining spatially neighboring simply connected regions depending on a second subset of syntax elements, to obtain an intermediate sub-division.

Abstract: An impedance-based respiration monitoring system for apnea detection includes at least three surface electrodes configured to record impedance respiration data from a patient's torso, a signal processing system, and an apnea detection module. The signal processing system is configured to generate a first respiration lead formed by a first set of surface electrodes from the at least three surface electrodes, the first respiration lead providing a first series of impedance measurements, and to generate a second respiration lead formed by a second set of surface electrodes attached to the patient's torso, the second lead providing a second series of impedance measurements. The apnea detection module is executable on a processor to calculate a first apnea metric based on the first series of impedance measurements, and calculate a second apnea metric based on the second series of impedance measurements. An apnea event is then detected based on the first apnea metric and the second apnea metric.

Abstract: The rotor for a squirrel-cage asynchronous rotating electrical machine comprises two compaction elements clamping a cylindrical magnetic mass, short-circuit rings facing the face of the compaction elements opposite that in contact with the magnetic mass, and conductive bars housed in recesses in the magnetic mass and distributed evenly over at least one diameter of the magnetic mass such that the short-circuit rings and the conductive bars form a squirrel cage. Retaining means distributed over at least one diameter of each short-circuit ring and over at least one diameter of each compaction element interact so as to secure the short-circuit rings and the compaction elements together, the pitch circle diameters of the retaining means on the rings and the compaction elements being smaller than the pitch circle diameter of the conductive bars.

Abstract: Methods and systems are provided for a single element ultrasound transducer. In one embodiment, a method for the transducer comprises laminating a comb structure and a conductive base package into an acoustic stack with a non-conductive glue, grinding the acoustic stack, and dicing the ground acoustic stack along a plane extending from the top surface of the second fin of the conductive base package to the bottom surface of the acoustic stack. The resulting transducer may have a flat front face with a non-conductive groove separating a ground pad formed by the conductive base package from a signal pad formed by a matching layer of the comb structure.

Abstract: A method for image segmentation includes receiving an input image. The method further includes obtaining a deep learning model having a triad of predictors. Furthermore, the method includes processing the input image by a shape model in the triad of predictors to generate a segmented shape image. Moreover, the method includes presenting the segmented shape image via a display unit.

Abstract: Various methods and systems are provided for selecting sensors for acquiring physiological data of a patient. In one embodiment, a system comprises a plurality of sensors, a dynamic selection switch communicatively coupled to the plurality of sensors, a plurality of acquisition channels communicatively coupled to the dynamic selection switch, and a processor communicatively coupled to the dynamic selection switch and configured with executable instructions in non-transitory memory that when executed cause the processor to: select a subset of sensors; control the dynamic selection switch to connect the subset of sensors to the plurality of acquisition channels; and acquire, from the subset of sensors via the plurality of acquisition channels, physiological data of a patient. In this way, a subset of sensors in a plurality of sensors may be dynamically selected in real-time for acquiring physiological data of the patient.

Abstract: A bucket includes a pair of radially-inner part-span shrouds, and a pair of radially-outer part-span shrouds. The buckets also include a dovetail, an airfoil and a platform extending between the airfoil and the dovetail. The airfoil includes a pressure side and an opposite suction side. The radially-inner part-span shrouds extend outward from the airfoil such that each of the radially-inner part-span shroud is spaced a distance from the leading edge and a distance from the airfoil trailing edge. The radially-outer part-span shrouds extend outward from the airfoil such that each of the radially-outer part-span shrouds is spaced a distance from the airfoil leading edge and a distance from the airfoil trailing edge, and such that the radially-inner part-span shrouds are between the radially-outer part-span shrouds and the platform. At least one of the airfoil and the dovetail includes at least one aerodynamic feature that facilitates mode shape adjustment of the bucket.

Abstract: An integrated lubrication system and an engine that includes the integrated lubrication system. The system has a first and a second lubrication supply line and one or more spray bars. The first lubrication supply line extends radially inward toward a central axis of the engine, has a first plurality of jet outlets, and is configured to deliver a lubrication fluid to a first location on one or more engine components. The second lubrication supply line extends parallel to the central axis, has a second plurality of jet outlets, and is configured to deliver the lubrication fluid to a second location on the one or more engine components. The first lubrication supply line is configured to lubricate the one or more engine components in a first engine power condition and the second lubrication supply line is configured to lubricate the one or more engine components in a second engine power condition.

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 defining a cavity at a radially inward surface of the annular substrate, and a smart structure coupled to the annular substrate, the smart structure including a support structure; an actuator structure to at least one of expand or contract in response to a change in temperature of the actuator structure, and a variable surface coupled to the support structure, the support structure to move the variable surface in a radial direction.

Abstract: A turbomachine engine includes a fan section having a fan shaft, and a core engine having one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections. The turbomachine engine includes a low-speed shaft coupled to the power turbine and having a midshaft that extends from a forward bearing to an aft bearing. The low-speed shaft is characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. The low-speed shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). The turbomachine engine includes a gearbox assembly that couples the fan shaft to the low-speed shaft and characterized by a gearbox assembly mode less than 95% of a midshaft mode of the midshaft or greater than 105% of the midshaft mode.

Abstract: Certain examples provide an image data processing system including an anatomy detector to detect an anatomy in an image and to remove items not included in the anatomy from the image. The example system includes a bounding box generator to generate a bounding box around a region of interest in the anatomy. The example system includes a voxel-level segmenter to classify image data within the bounding box at the voxel level to identify an object in the region of interest. The example system includes an output imager to output an indication of the object identified in the region of interest segmented in the image.

Abstract: Various methods and systems are provided for individually analyzing a plurality of subregions within an ultrasound image for acoustic shadowing. In one embodiment, a method includes acquiring ultrasound data along a plurality of receive lines, generating an ultrasound image based on the ultrasound data, dividing the ultrasound image into a plurality of subregions, and individually analyzing each of the plurality of subregions for acoustic shadowing. The method includes detecting acoustic shadowing in one or more of the plurality of subregions, displaying the ultrasound image, and graphically indicating the one or more of the plurality of subregions in which the acoustic shadowing was detected on the ultrasound image while the ultrasound image is displayed on a display device.

Abstract: A method of operating an aircraft interface device may comprise receiving a request for a data dictionary from an electronic flight bag application and transmitting the data dictionary to the electronic flight bag application. The data dictionary may comprise a mapping between a plurality of parameters associated with an aircraft and a plurality of parameter identifiers. Values of the parameters may be retrieved by the aircraft interface device. The method may also include receiving a request for values of one or more of the parameters from the electronic flight bag, retrieving values of the parameters, and transmitting the values of the parameters to the electronic flight bag application.