Abstract: A raw byte sequence payload describing a picture in slices, WPP substreams or tiles and coded using context-adaptive binary arithmetic coding is subdivided into tranches with continuing the context-adaptive binary arithmetic coding probability adaptation across tranche boundaries. Thereby, tranche boundaries additionally introduced within slices, WPP substreams or tiles do not lead to a reduction in the entropy coding efficiency of these entities. However, the tranches are smaller than the original slices, WPP substreams or tiles and accordingly they may be transmitted earlier, i.e. with lower delay, than the un-chopped original entities. According to another aspect combinable with the first aspect, substream marker NAL units are used within a sequence of NAL units of a video bitstream to enable a transport demultiplexer to assign data of slices within NAL units to the corresponding substreams or tiles so as to be able to, in parallel, serve a multi-threaded decoder with the corresponding substreams or tiles.

Abstract: Heat dissipation system, a power converter using such a heat dissipation system, and an associated method of thermal management of the power converter are disclosed. The heat dissipation system includes a condenser, a first cooling loop, and a second cooling loop. The first cooling loop is coupled to the condenser and includes a first two-phase heat transfer device. The second cooling loop is coupled to the condenser and includes a second two-phase heat transfer device. The condenser is disposed above the first and second two-phase heat transfer devices.

Abstract: A system and a method for identifying errors within a modular framework of a system comprising of a flight management system and an error reporting system. The modular components and correlating code modulars of the modular framework can be executed collectively or independently. Each modular component can be designed to incorporate independent modular updates or modifications.

Abstract: A thermal management system of a gas turbine engine, the thermal management system including: a thermal transport bus configured to have a heat exchange fluid flowing therethrough and including a pump including a plurality of bearings; an auxiliary thermal bus in thermal communication with the plurality of bearings; and an auxiliary heat exchanger in thermal communication with the auxiliary thermal bus.

Abstract: An electronic device for an aircraft. The electronic device comprising a memory associated with an Operating System (OS) and at least one application at least partially operable by way of the electronic device. The at least one application is further configured to establish a connection with at least one avionics system of an aircraft for receiving data from the at least one avionics system.

Abstract: A medium or high voltage electrical device and method of maintaining the composition of an insulating gas mixture in a medium or high voltage electrical device, where the device comprises a sealed chamber, said sealed chamber comprising electrical components; a gas mixture ensuring electrical insulation and/or extinguishing of electrical arcs produced in this chamber, wherein the gas mixture comprises at least one insulating gas and at least one dilution gas; and a receptacle, said receptacle comprising an opening, at least one wall, wherein at least one wall is a heatable wall, and wherein said receptacle is positioned to receive liquefied gas; the device further comprising a heating element for heating the heatable receptacle wall; and a dielectrically and thermally insulating layer located between the heatable receptacle wall and the chamber.

Abstract: A method for manufacturing a tower structure of a wind turbine at a wind turbine site. The method includes determining an optimized shape of the tower structure based on one or more site parameters. Further, the optimized shape of the tower structure is non-symmetrical. In a further step, the method include printing, via an additive printing device, the optimized shape of the tower structure of the wind turbine at the wind turbine site, at least in part, of a cementitious material. In addition, the method includes allowing the cementitious material to cure so as to form the tower structure of the wind turbine.

Abstract: An integrated combustor nozzle includes a combustion liner that extends radially between an inner liner segment and an outer liner segment. The combustion liner includes a forward end portion, an aft end portion, a first side wall, and a second side wall. The integrated combustor nozzle further includes an impingement cooling apparatus positioned within the cavity. The impingement cooling apparatus includes a flange. The impingement cooling apparatus further includes a plurality of impingement members that each extend from a respective opening defined in the flange to a respective closed end. Each impingement member defines a plurality of impingement apertures that direct air to impinge upon one of the first side wall and the second side wall. The impingement cooling apparatus further includes stand-offs extending from each impingement member of the plurality of impingement members. The stand-offs space apart each impingement member of the plurality of impingement members from surrounding surfaces.

Abstract: A gas turbine engine having a rotor blade stage with a plurality of circumferentially spaced rotors, a nozzle stage adjacent the rotor blade stage and including an outer nozzle end, at least one stop, and a shroud. The shroud having a forward end positioned radially outward from the circumferentially spaced rotor blades, and an aft end axially aft of the forward end. The at least one stop confronting at least a portion of the outer nozzle end.

Abstract: A fuel system including a fuel metering unit, a heat exchanger, a plurality of fuel nozzles, and a coke filtration system. The fuel metering unit is configured to meter a flow of a hydrocarbon fuel. The heat exchanger is fluidly connected to the fuel metering unit. The heat exchanger is configured to heat the hydrocarbon fuel to improve engine performance or efficiency. The plurality of fuel nozzles is fluidly connected to the heat exchanger downstream of the heat exchanger to receive the hydrocarbon fuel heated by the heat exchanger. The coke filtration system includes at least one filter to remove coke particles in the heated fuel. The coke filtration system is located upstream of the plurality of fuel nozzles and directly downstream of the heat exchanger.

Abstract: A radio frequency coil assembly for an MRI system. A support structure extends between a first end and a second end in a first direction and between an inner surface and an opposite outer surface in a second direction perpendicular to the first direction. The support structure has channels that extend into the support structure in the second direction. An RF coil is configured to transmit and/or receive RF signals. The RF coil is supported by the outer surface of the support structure. The channels are at least partially positioned between the support structure and the RF coil in the first direction and are configured to convey a cooling medium to cool the support structure in use.

Abstract: Methods and systems are provided for adaptive scan control. In one embodiment, a method includes processing acquired projection data of a monitoring area of a subject to measure a contrast signal of a contrast agent delivered to the subject, determining a hemodynamic marker of the subject based on the contrast signal, generating a scan prescription based on the determined hemodynamic marker of the subject, and performing a multi-phase contrast scan according to the scan prescription.

Abstract: Diffuser apparatus for turbine frames and outlet guide vanes are disclosed. An example diffuser is integrated into a turbine engine. The example diffuser includes a plurality of struts extending between an inner portion and an outer portion of the turbine engine; and a plurality of flowpath surfaces supported by the plurality of struts. The example plurality of flowpath surfaces extends circumferentially within the turbine engine at a plurality of radial spans to control diffusion of air flow within the turbine engine.

Abstract: Systems and methods of servicing engines including a method of servicing an engine, the method including navigating at least a portion of a robotic assembly to a location associated with the engine; applying, from the robotic assembly, a medium to one or more adjustable components of the engine while the engine is at an elevated temperature; waiting a duration of time; and with the robotic assembly, operating on the one or more adjustable components.

Abstract: A gear assembly for an aeronautical engine includes a first gear disposed at a centerline axis of the gear assembly, a second gear coupled to the first gear in adjacent radial arrangement to form a first mesh between the first gear and the second gear, a static portion coupled to the second gear in adjacent circumferential arrangement, the static portion defining a pocket, and a spraybar disposed within the static portion such that a supply opening of the spraybar is directed at the first mesh between the first gear and the second gear. The supply opening provides a flow of lubricant to the first mesh between the first gear and the second gear and at least a portion of the flow of lubricant is collected by the pocket. The flow of lubricant is continuously released from the pocket to the gear system.

Abstract: An integrated combustor nozzle includes a combustion liner that extends radially between an inner liner segment and an outer liner segment, the combustion liner includes a forward end portion, an aft end portion, a first side wall, and a second side wall. The aft end portion of the combustion liner defines a turbine nozzle. The combustion liner defines a cavity forward of the turbine nozzle. The cavity extends between the first side wall and the second side wall. An impingement cooling apparatus positioned within the cavity. The impingement cooling apparatus includes a flange. The impingement cooling apparatus further includes a plurality of impingement members configured to direct coolant to impinge upon the first side wall and the second side wall. Each impingement member extends from a respective inlet defined within the flange to a respective closed end. A plurality of impingement apertures are defined on each impingement member.

Abstract: A combustor includes a skeleton mesh structure having a plurality of structural elements configured to mesh together to form the skeleton mesh structure, each of the plurality of structural elements including a frame and, a plurality of louvers connected to the frame. The combustor also includes an inner liner mounted to the skeleton mesh structure to define a combustion chamber. The inner liner includes a plurality of inner planks mounted to the skeleton mesh structure, each of the plurality of inner planks being mounted to a corresponding one of the plurality of structural elements.

Abstract: A swirler assembly includes a swirler having primary swirler with a primary swirler venturi, a swirler ferrule plate connected to the primary swirler, and a fuel nozzle disposed in the swirler ferrule plate. The swirler ferrule plate has an aft wall, an annular conical wall, and an annular cavity wall that together form an annular cavity. The annular cavity includes a plurality of inlet orifices, and at least one outlet orifice. A flow of oxidizer through the plurality of inlet orifices into the annular cavity incurs a first pressure drop from a first pressure of a pressure plenum to a second pressure lower than the first pressure, and a flow of the oxidizer from the annular cavity through the at least one outlet orifice into the primary swirler venturi incurs a second pressure drop from the second pressure to a third pressure lower than the second pressure.

Abstract: A lubricant supply system for a squeeze film damper. The lubricant supply system includes a fluid passage configured to supply a lubricant to the squeeze film damper of a bearing assembly. The fluid passage includes a first flow path for lubricant into the lubricant supply system and into the squeeze film damper of the bearing assembly and a second flow path for lubricant into the squeeze film damper of the bearing assembly. The lubricant supply system includes a valve assembly configured to allow the fluid passage to move from the first flow path to the second flow path in response to an interruption of the first flow path.

Abstract: An annular combustor includes a combustion liner defining a combustion chamber, the combustion liner having an outer liner and an inner liner and a plurality of dimples in the combustion liner. The combustion liner is characterized by a performance factor greater than or equal to one and less than or equal to seven. An engine includes the annular combustor.

Abstract: A method for determining the flow rate of combustible fluid injected into a combustion chamber (120) of a turbine (100) includes determining the cross section of the orifice of the at least one injector (112, 113, 114, 115) through which the combustible fluid is injected into the combustion chamber (120). The pressure of the combustible fluid upstream of the orifice of the injector (112, 113, 114, 115) is determined. The pressure downstream of the orifice of the injector (112, 113, 114, 115) is determined. The flow rate of combustible fluid flowing through the orifice of the at least one injector (112, 113, 114, 115) is determined.

Abstract: Additive manufacturing apparatus, along with methods of forming an object therewith, are provided. The additive manufacturing apparatus may include at least one build unit; a build platform (such as a rotating build platform); and a pair of collectors positioned on the apparatus such that a first collector contacts an outer surface of an object as it is formed on the build platform and a second collector contacts an inner surface of the object as it is formed on the build platform.

Abstract: Systems and methods are provided for a valve shut-off system of a medical device. In one embodiment, the valve shut-off system of the medical device includes a first pin movable between a first position where a valve is opened and a second position where the valve is closed, the first pin including a slot, and a second pin having a mating geometry with the slot of the first pin, the second pin adjustable between a locked position that holds the first pin in the first position and an unlocked position that enables movement of the first pin between the first position and the second position.

Abstract: A heat exchanger for a hydrogen fuel delivery system includes a tube bank including an inner-tube where a first portion of the inner-tube extends through an inlet region of the tube bank, a second portion of the inner-tube extends through a mid-region of the tube bank, and a third portion of the inner-tube extends through an outlet region of the tube bank. A thermal buffer at least partially surrounds the inner-tube. A first portion of the thermal buffer extends along the first portion of the inner-tube, a second portion of the thermal buffer extends along the second portion of the inner-tube, and a third portion of the thermal buffer extends along the third portion of the inner-tube. A plurality of fins is disposed along the inner-tube and extends radially outwardly from an outer surface of the thermal buffer.

Abstract: To provide a technique with which an operator, when talking into a microphone, can recognize whether or not his/her voice is being output from a speaker in a scan room, a CT apparatus 1 has: an operator microphone 41 installed in an operation room R2 for receiving a voice of an operator 81; a patient microphone 2 installed in a scan room R1 for receiving a voice of a patient 80; a speaker 50 installed in the operation room R2 for outputting the voice of the patient 80 received by the patient microphone 2; a speaker 5 installed in the scan room R1 for outputting the voice of the operator 81 received by the operator microphone 41; and a light-emitting section 31 for informing, in the case that the patient microphone 2 has received the voice of the operator 81 output from the speaker 5, the operator 81 that his/her voice is being output from the speaker 5.

Abstract: An aircraft that includes a hybrid-electric propulsion system is provided. In one aspect, the hybrid-electric propulsion system includes at least one propulsor that includes a gas turbine engine and an electric machine mechanically coupled with a spool of the gas turbine engine. When idle operation is commanded, electrical power is provided to the electric machine to cause the electric machine to apply torque to the spool and fuel provided to the engine can be reduced. Thus, the electric machine is controlled to provide a power assist to maintain the engine at the commanded idle speed whilst reducing fuel consumption.

Abstract: A radiation detector head assembly includes a detector column. The detector column includes a detector having a first surface and a second surface opposite the first surface. The detector column also includes a first collimator disposed over the first surface of the detector configured for use during imaging scans involving radiation in a first energy range. The detector column further includes a second collimator disposed over the second surface of the detector configured for use during imaging scans involving radiation in a second energy range different from the first energy range.

Abstract: In some embodiments, apparatuses are provided herein useful to sealing a gap, such as a gap between a gas turbine engine nozzle flap and sidewall. An apparatus for sealing such a gap may be a plunger seal that includes a plunger, a retaining element, a guide pin, and a biasing element. The plunger includes a sealing edge and an actuating edge having at least one recess and an opening formed therein. The biasing element and a portion of the guide pin are nested in the recess. The retaining element anchor the plunger to the retaining element. The retaining element also anchors the plunger seal to the housing When installed in a gap, the housing engages the flap and the plunger engages the sidewall. The biasing element is under compression and urges the guide pin into the actuating edge to urge the plunger toward the sidewall and seal the gap.

Abstract: A method of additively manufacturing a three-dimensional object may be performed using an irradiation sequence that is based at least in part on a predicted location of one or more fume plumes emitted from the powder material when irradiated by a plurality of energy beams. An exemplary method may include determining, with a computing device, an irradiation sequence for selectively consolidating powder material using an energy beam system of an additive manufacturing machine, and providing control commands, from the computing device to the energy beam system, configured to cause the energy beam system to emit a plurality of energy beams to selectively consolidate the powder material.

Abstract: A device for fixing the position of adjustable vane rows of a turbomachine is disclosed. The device is intended for use with a turbomachine in which the guide vanes of a row of adjustable guide vanes are coupled together by a synchronizing ring. The device includes a support arm and at least one ring fixing set including a holding member and a fixing bolt. The fixing bolt is provided and dimensioned to engage an opening at the circumference of the synchronizing ring and to fix the position of the synchronizing ring and thus of the adjustable guide vanes coupled to the synchronizing ring.

Abstract: An invasive interventional device or probe for use in an interventional medical procedure includes a control handle operably connected to an imaging system and an insertion tube. The body having an exterior cross-sectional shape and defining an interior with an interior cross-sectional shape. The body is formed with a pair of opposed side panels, a pair of opposed end panels joining opposite ends of the pair of side panels, a top panel disposed over and joined to the pair of side panels and the pair of end panels and a bottom panel located opposite the top panel and joined to the pair of side panels and the pair of end panels with one or more control elements disposed on the body that control the operation of the interventional device. In addition, the exterior cross-sectional shape of the body conforms to a space defined within a hand in a relaxed grip position.

Abstract: A seal assembly for a component of a turbomachine and method of assembly thereof is provided. The seal assembly includes at least one mating face positioned adjacent to the component and a seal coupled to the mating face. The seal includes an outer shell defining an interior space; an inner matrix filling the interior space comprising a plurality of unit cells comprising one or more metamaterials, wherein at least a portion of the plurality of unit cells are identical, and wherein the plurality of unit cells are repeated throughout the inner matrix; and one or more support struts extending throughout the inner matrix. The method of building the seal assembly may include selecting a first material for the outer shell and selecting the one or more metamaterials for the inner matrix based on the first material.

Abstract: Various systems and methods are provided for a biased cathode assembly of an X-ray tube with improved thermal management and a method of manufacturing same. In one example, a cathode assembly of an X-ray tube comprises an emitter assembly including an emitter coupled to an emitter support structure, and an electrode assembly including an electrode stack and a plurality of bias electrodes. The emitter assembly including a plurality of independent components that are coupled together. The electrode assembly including a plurality of independent components that are coupled together, and the emitter assembly being coupled to the electrode assembly.

Abstract: A seal assembly for a rotary machine, such as a turbine engine, may include a seal rotor comprising a rotor face, a seal slider comprising a slider face, a seal stator, wherein the seal slider is slidably coupled to the seal stator, and wherein the slider face and the rotor face define a primary seal. The seal slider may be configured to slidably engage and retract the slider face with respect to the rotor face. The seal assembly may further include a secondary seal disposed between the seal slider and the seal stator. The secondary seal may be configured to compress and rebound and/or to expand and rebound, over at least a portion of a range of motion of the seal slider.

Abstract: A method for generating an object 3D point cloud in a medical imaging system comprising a machine table and a scanning device comprises: extracting a valid 3D point cloud in a valid region where the machine table is located from a global 3D point cloud based on a current height of the machine table and boundary information of the machine table, wherein the global 3D point cloud comprises 3D point clouds of an object and a surrounding environment thereof, and the object 3D point cloud is comprised in the valid 3D point cloud; and removing an environment 3D point cloud of the surrounding environment from the valid 3D point cloud to obtain the object 3D point cloud, wherein the surrounding environment comprises at least part of the machine table. In some embodiments, a moving path of the machine table in the medical imaging system is planned using the object 3D point cloud. In some embodiments, collision prediction of the object is performed in the medical imaging system using the object 3D point cloud.

Abstract: An inlet filter housing includes a plurality of components that collectively form a complete filtering and conditioning system for filtering and conditioning a fluid along a housing flow path. Each component is fitted within an external structure of an International Organization of Standards (ISO) shipping container, which provides a rectangular cuboid enclosure. Each component includes operative structure of at least one of: a) only a portion of an axial extent of the filtering and conditioning system, and b) only a portion of a lateral cross-sectional area of the housing flow path.

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed for a structure of an engine component, including a first plurality of unit cells offset from a neutral plane in a first direction, a second plurality of unit cells offset from the neutral plane in a second direction, a plurality of nodes joining ones of the first plurality of unit cells and ones of the second plurality of unit cells, wherein the first plurality of unit cells and the second plurality of unit cells are arranged in pairs such that ones of the first plurality of unit cells are laterally adjacent to and interconnected with ones of the second plurality of unit cells, and wherein the structure is a stiffened structure.

Abstract: An apparatus and method for an engine component for a turbine engine. The engine component having an outer wall defining an interior and extending between a root and a tip to define a radial direction, a tip wall spanning the first side and second sides to close the interior at the tip. A tip rail extending from the tip wall and having an inner tip rail surface, an outer tip rail surface extending from at least one of the first or the second side, and radially terminating in an upper tip rail surface connecting the inner tip rail surface and the outer tip rail surface. A tip rim formed in at least one of the outer surface or the inner tip rail surface and spaced from the upper tip rail surface in the radial direction, and multiple cooling passages formed in the outer wall and fluidly coupling the at least one cooling conduit to the tip rim at corresponding passage outlets.

Abstract: An unducted thrust producing system, includes a rotating element, a stationary element. An inlet may be located forward or aft of the rotating element and the stationary element. An exhaust may be located forward, aft, or between the rotating element and the stationary element.

Abstract: Disclosed herein are embodiments for providing contingency automation to emergency response. One embodiment of a method includes determining a route for a vehicle to a primary destination, and determining a first upcoming area along the route that has been previously identified as an emergency response zone, where the emergency response zone may be used as a secondary destination in a contingency route for the vehicle in an emergency. In some embodiments, the method may include reserving airspace for the contingency route, determining that the emergency response zone is no longer useful, based on an updated position of the vehicle, and canceling the contingency route from reservation.

Abstract: An airfoil for a fan section of a turbine engine may include a fan blade or an outlet guide vane formed of a first material, and an edge guard disposed about an edge of the fan blade. The edge guard may include a matrix composite that has a toughness that is greater than a toughness of the first material. The airfoil may include a fan blade or an outlet guide vane. The first material of the airfoil may include a metal alloy and/or a matrix composite. A method of manufacturing an airfoil for a fan section of a turbine engine may include manufacturing an edge guard, attaching the edge guard to the airfoil.

Abstract: A system and process that are configured to prepare incoming hydrocarbon feedstocks for storage. For incoming ethane gas, the embodiments can utilize a plurality of vessels to distill the incoming feedstock to vapor and liquid ethane that is suitable for storage. The embodiments can direct the vapor to a demethanizer column that is downstream of the vessels and other components. The process can include stages for distilling an incoming feedstock at a plurality of vessels to form a vapor and a liquid for storage; directing the vapor to a demethanizer column; and circulating liquid from the demethanizer column back to the plurality of vessels.

Abstract: An additive manufacturing machine includes an energy beam system situated in a fixed position relative to a reference plane coinciding with an expected location of a build plane, an energy beam system with an irradiation device configured to generate an energy beam and to direct the energy beam upon the build plane, and a position measurement system configured to determine a position of the build plane. A position measurement assembly includes one or more position sensors, and one or more mounting brackets configured to attach the one or more position sensors to an energy beam system of an additive manufacturing machine. The position measurement assembly is configured to determine a position of a build plane with the energy beam system situated in a fixed position relative to a reference plane coinciding with an expected location of the build plane.

Abstract: The present invention relates to a system and a method for calibration between coordinate systems of a 3D camera and a medical imaging apparatus. The calibration system includes a calibration tool having markers and a reference point that is aligned with a center of the medical imaging apparatus to serve as an origin of the coordinate system. Positions of the markers in the coordinate system of the medical imaging apparatus are calculated according to relative positions of the markers with respect to the reference point. A 3D camera captures images to determine positions of the markers in the coordinate system of the 3D camera. A calculation device calibrates the coordinate system of the 3D camera and the coordinate system of the medical imaging apparatus using the positions of the markers in the coordinate system of the 3D camera and the p in the coordinate system of the medical imaging apparatus.

Abstract: Various methods and systems are provided for cable management for portable electronic medical devices. In one embodiment, a system comprises: a frame for a portable electronic medical device, the frame including a first wall and an opposing, second wall forming inner surfaces of a channel; and a cable coupler adapted to seat within the channel, including: counterpart outer surfaces shaped to engage the inner surfaces; and a passage shaped to enclose a portion of a cable.

Abstract: Systems, methods, and apparatus to generate and utilize predictive workflow analytics and inferencing are disclosed and described. An example predictive workflow analytics apparatus includes a data store to receive healthcare workflow data including at least one of a schedule or a worklist including a patient and an activity in the at least one of the schedule or the worklist involving the patient. The example apparatus includes a data access layer to combine the healthcare workflow data with non-healthcare data to enrich the healthcare workflow data for analysis with respect to the patient. The example apparatus includes an inferencing engine to generate a prediction including a probability of patient no-show to the activity by processing the combined, enriched healthcare workflow data using a model and triggering a corrective action proportional to the probability of patient no-show.

Abstract: A system for analyzing noise in one or more electrophysiology studies is provided. The system includes at least one processor and at least one memory device. The memory device stores an application that adapts the at least one processor to: identify, based at least in part on a machine learning model, one or more noise fingerprints within data derived at least in part from one or more study signals acquired from one or more patients during the one or more electrophysiology studies.

Abstract: A system and method for enhancing color flow Doppler and pulsed wave Doppler ultrasound images acquired based on clinically-specific profiles of imaging parameters is provided. The method includes presenting selectable clinical objects at a display. Each of the selectable clinical objects may be associated with color flow Doppler and pulsed wave Doppler profiles. Each of the profiles may comprise imaging parameters for the associated clinical object. The method includes receiving a selection of one of the selectable clinical objects and retrieving the color flow Doppler and pulsed wave Doppler profiles associated with the selected clinical object. The method includes acquiring and presenting color flow Doppler ultrasound data based on the imaging parameters of the retrieved color flow Doppler profile. The method includes initiating a pulsed wave Doppler imaging mode, and acquiring and presenting pulsed wave Doppler ultrasound data based on the imaging parameters of the retrieved pulsed wave Doppler profile.

Abstract: Systems and methods of maternal and fetal monitoring include acquiring ultrasound physiological data with an ultrasound transducer. A plurality of electrodes acquire biopotential physiological data from the skin of a patient. A controller receives the ultrasound and biopotential physiological data and calculates fetal heart rate (fHR) values, maternal heart rate (mHR) values, and uterine activity (UA) values from the ultrasound and biopotential physiological data.

Abstract: An airfoil for a turbine engine having a spar assembly. The spar assembly including a composite spar, a metallic hub, and a composite body. The metallic hub can receive a portion of the composite spar at an interior surface to define an overlapping region. The composite body is located at the overlapping region.