Abstract: Various systems are provided for an X-ray system. In one example, an X-ray system comprises an X-ray source positioned opposite to and facing a first side of a table and an X-ray detector positioned directly opposite to and facing a second side of the table, wherein the second side is opposite the first side, wherein the X-ray source is a dual-energy X-ray source configured to scan in a raster pattern. In one example, an object is positioned on the first side of the table.

Abstract: A blade for a turbine engine with a wall separating a cooling fluid flow and a hot gas fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow. A plurality of cooling holes each having a passage extending between an inlet at the cooled surface and an outlet at the heated surface. The outlet extending between an upstream end and a downstream end with respect to the hot gas fluid flow to define a distance, the passage defining a centerline forming a first angle (?) with the heated surface.

Abstract: A system may include an insulation mount assembly configured to mount insulation within a component of an exhaust diffuser of a combustion system. The insulation mount assembly includes an insulation cover plate configured to cover the insulation over a wall of the component, and a plurality of mounting clips configured to extend partially over the insulation plate and couple to the wall of the component. Each clip of the plurality of mounting clips is configured to enable movement of the insulation cover plate in a first direction along a surface of the wall and block movement of the insulation cover plate in a second direction crosswise to the surface of the wall.

Abstract: A milling device for machining a slot into an inner surface of a casing for a gas turbine engine. The milling device includes a frame assembly including multiple structural guides configured to engage structural features on the inner surface of the casing to maintain an axial position of the milling device relative to a longitudinal axis of the casing. The milling device also includes a milling cutter coupled to the frame assembly. The milling device is configured to be displaced in a circumferential direction relative to the longitudinal axis to machine the slot, via the milling cutter, along the inner surface of the casing in the circumferential direction.

Abstract: An apparatus and method relating to a cooling hole of a component of a turbine engine. The cooling hole can extend from an inlet to an outlet to define a connecting passage. The cooling hole can contain a diffusing section. The diffusing section can be defined by an interior surface having variable geometries.

Abstract: Systems and methods for fusing and analyzing multiple sources of data from a plurality of aircraft-related data sources for fault determination and other integrated vehicle health management (IVHM) diagnostics are provided. More particularly, one or more portions of data from a plurality of aircraft-related data sources for one or more aircraft are accessed. One or more alerts indicative of a data anomaly within the one or more portions of aircraft-related data sources can be detected, wherein a type of alert and originating data source associated with each alert as well as optional related confidence scores can be identified. One or more aircraft faults can be determined based at least in part on a correlation of identified types and data sources for detected alerts. An output indicative of the determined one or more aircraft faults can be provided.

Abstract: A gas turbine engine is provided, having a turbomachine and a rotor assembly driven by the turbomachine and operable at a first blade passing frequency (f1) greater than or equal to 2,500 hertz and less than or equal to 5,000 hertz during a high power operating condition; a heat exchanger positioned within an annular duct and extending substantially continuously along the circumferential direction, wherein an effective transmission loss (ETL) for the heat exchanger positioned within the annular duct is between 5 decibels and 1 decibels for a high power operating condition, and wherein the heat exchanger comprises a heat transfer section defining an acoustic length (Li), and wherein an Operational Acoustic Reduction Ratio (OARR) is greater than or equal to 0.75 to achieve the ETL at the high power operating condition, the OARR equal to: sin ? ? ( 2 × ? × f 1 a 1 × L i ) 2 wherein a1 is equal to 13,200 inches per second during the high power operating condition.

Abstract: Systems and methods are disclosed for estimating or determining a rate or an amount of fuel coke formation in a fuel system, such as of a gas turbine engine. The system is operable to control a rate of fuel coke formation. The system may include a sensor that measures an operating parameter associated with fuel coke formation in the fuel system. A controller is in communication with the sensor to receive the signal therefrom for determining an amount or a rate of fuel coking in the fuel system. Based on this determination the controller may adjust the rate of fuel coke formation by adjusting the operation of the turbine engine, a thermal management system of the turbine engine, or the fuel system.

Abstract: The present disclosure generally relates to methods and apparatuses for chemical vapor deposition (CVD) during additive manufacturing (AM) processes. Such methods and apparatuses can be used to embed chemical signatures into manufactured objects, and such embedded chemical signatures may find use in anti-counterfeiting operations and in manufacture of objects with multiple materials.

Abstract: A device for fixing the position of adjustable vane rows of a turbomachine is provided. The device includes a support arm and at least one clamping tool. The at least one clamping tool is attached to the support arm. The at least one clamping tool includes a clamping head and a retaining element. The retaining element connects the clamping head to the support arm.

Abstract: A trapped vortex reverse flow combustor for a gas turbine includes a first dome structure having a plurality of first-dome vortex driver airflow openings for providing a first vortex generating mid airflow therethrough to a trapped vortex cavity. A second dome structure is arranged downstream of the first dome structure and includes a plurality of second-dome vortex driver airflow openings providing a first vortex generating outer airflow therethrough to the trapped vortex cavity, and a plurality of primary driver airflow openings providing a primary driver airflow therethrough radially inward of the trapped vortex cavity.

Abstract: An air turbine starter that includes a housing with a divider structure dividing the housing into a wet chamber and an air chamber. The air turbine starter further including a bearing assembly, a turbine member, a first drive shaft, and a second drive shaft connecting the turbine member with a rotating assembly. A lubricant supply portion having at least one supply inlet fluidly coupled to the wet chamber and at least one supply outlet fluidly coupled to the bearing assembly whereby lubricant from the wet chamber can be supplied to the bearing assembly.

Abstract: A bipole power transmission scheme with two independent converts, two power feed and one return conduit. During operation of the bipole power transmission scheme under abnormal conditions, when a return conduit is faulty and unable to provide a return current path, each converter controller is programmed to monitor the first power feed in the first transmission conduit and the second power feed in the second transmission conduit and, if the first power feed in the first transmission conduit and the second power feed in the second transmission conduit differ from one another, at least one converter controller modifies the power infeed from its corresponding power source to reduce the difference between the first power feed and the second power feed.

Abstract: A bundled tube fuel nozzle is provided. The bundled tube fuel nozzle includes a first end wall, a second end wall, an outer band that extends between the first end wall and the second end wall, and an inner band that extends between the first end wall and the second end wall. The inner band is disposed within the outer band. A bellows wall is disposed between the inner band and the outer band. The bellows wall surrounds the inner band such that a first fuel plenum is defined annularly between the inner band and the bellows wall. The inner band defines a second fuel plenum that is in fluid communication with the first fuel plenum via one or more apertures defined in the inner band. A plurality of tubes extends in an axial direction between the first end wall and the second end wall within the second fuel plenum.

Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber; and an intermediate member disposed at least partially between the forward and aft liner segments and extending in the circumferential direction.

Abstract: The rotor with a non-through shaft for a rotary electric machine comprises a cylindrical magnetic body clamped between two half-shafts, each comprising an attachment flange connected to the magnetic body, axial housings being uniformly provided in the magnetic body on at least one diameter of the magnetic body in order to house conductive bars. At least one attachment flange comprises insertion holes, each arranged facing a housing for inserting the conductive bars into the housings and the exterior diameter of the attachment flange is substantially equal to the exterior diameter of the magnetic body, the attachment flange comprising as many insertion holes as housings.

Abstract: A method for operating a multi-level bridge power converter includes arranging a plurality of switching devices including at least four inner switching devices and at least two outer switching devices in an active neutral point clamped topology. The method also includes determining whether any of the switching devices is experiencing a failure condition by implementing a failure detection algorithm. The failure detection algorithm includes generating a blocking state logic signal by comparing a switching device voltage and a threshold reference voltage for each of the switching devices, determining an expected voltage blocking state for each of the switching devices based on gate drive signals of the switching devices and an output current direction, and detecting whether a failure condition is present in any of the switching devices based on the blocking state logic signals and the expected voltage blocking states of the switching devices.

Abstract: A turbine engine having a compressor section, a combustor section, a turbine section, and a rotatable drive shaft that couples a portion of the turbine section and a portion of the compressor section. A bypass conduit couples the compressor section to the turbine section while bypassing at least the combustion section. At least one particle separator is located in the turbine engine having a separator inlet that receives a bypass stream, a separator outlet that receives a reduced-particle stream flows, and a particle outlet that receives a concentrated-particle stream comprising separated particles. A conduit, fluidly coupled to the particle outlet, extends through an interior of at least one stationary vane.

Abstract: An exhaust nozzle for a gas turbine engine. The exhaust nozzle comprises a nozzle body having an upstream end axially spaced from a downstream end with respect to an axial centerline of the nozzle body, and a plurality of chevrons circumferentially spaced apart and extending downstream from the downstream end. Each chevron includes an inner wall radially spaced from an outer wall, a root and a tip axially spaced from the root. At least one chevron of the plurality of chevrons includes a first segment extending axially downstream from the root, a second segment extending axially downstream from the first segment, and a third segment extending axially downstream from the second segment to the tip. The inner wall extends along the first segment, the second segment, and third the segment. The first segment is distinguishable from the second segment and the second segment is distinguishable from the third segment.

Abstract: A mammography system includes a biopsy guidance system that employs a simplified robot arm support, to enable previously unusable locations for the mounting of the biopsy device directly to the mammography system, such as on a compression paddle, combined with a vision guidance and control system. The vision system operates to determine the position of the biopsy device and the biopsy needle tip, as well as to control the movement/operation of the biopsy guidance system, such as movement to the final end-pose or pre-firing position of the biopsy device to perform the biopsy procedure. The vision system utilizes one or more cameras to visually determine the position the biopsy device relative to a region of interest being biopsied within the required tolerances for the biopsy procedure without the need for precise positional information to be provided by the biopsy guidance system to the mammography system.

Abstract: A gear assembly for use with a turbomachine comprises a sun gear, a plurality of planet gear layshafts that each support a first stage planet gear and a second stage planet gear, and a ring gear. The sun gear is configured to rotate about a longitudinal centerline of the gear assembly, and the plurality of planet gear layshafts comprise an interior passage that receives one or more lubrication supply lines.

Abstract: Various methods and systems are provided for stationary computed tomography (CT) imaging. In one embodiment, a stationary CT system includes one or more detector arrays extending around at least a portion of an imaging volume, a stationary distributed x-ray source unit comprising a plurality of emitters including a first set of emitters configured to operate at a first voltage and a second set of emitters configured to operate at a second voltage, different than the first voltage, and a source controller for triggering the first set of emitters for acquiring first projection data by the one or more detector arrays and triggering the second set of emitters for acquiring second projection data by the one or more detector arrays, the first projection data and the second projection data usable to reconstruct one or more basis material composition images or monochromatic images of an object within the imaging volume.

Abstract: An ultrasound probe hanger includes a stem, shoulders, arms, and a probe holder. The shoulders are arranged generally perpendicular to the stem and are connected to a proximal end of the stem. The arms are arranged generally parallel to each other and to the stem. The arms are connected at upper ends to outer shoulder ends of the shoulders. The probe holder includes outer side portions, a rear portion, a partially open front portion, and four protrusions. The outer side portions are each connected to lower ends of the arms. The rear portion extends between the outer side portions. The partially-open front portion includes outer front portions each extending from the outer side portions and defining a central front open portion. The four protrusions are arranged in a rectangle on an inside surface of the probe holder and are configured to suspend a wireless ultrasound probe within the probe holder.

Abstract: The present application presents novel systems and methods for tracking reinforcement member placement in an additively manufactured structure that are simple, accurate, non-labor-intensive, and cost-effective. The present application also presents a novel method of manufacturing a tower structure comprising: depositing, via an additive printing system, a first printed layer of a wall with a printhead assembly, the wall at least partially circumscribing a vertical axis of the tower structure; positioning a first reinforcement member on the first printed layer; depositing, via the additive printing system, a second printed layer of the wall with the printhead assembly on the first reinforcement member, the second printed layer configured to hold a second reinforcement member thereon; and determining, via an optical sensor of the additive printing system, a position for placing the second reinforcement member based on the first reinforcement member positioning.

Abstract: A passive flow modulation device for a machine defining an axial direction and a radial direction, the passive flow modulation device including: a first ring with a first coefficient of thermal expansion; a second ring disposed coaxially with the first ring and positioned at least partially inward of the first ring along the radial direction, spaced from the first ring along the axial direction, or both, the first ring, the second ring, or both defining at least in part one or more passages, the second ring with a second coefficient of thermal expansion that is less than the first coefficient of thermal expansion to passively modulate a size of the one or more passages during operation.

Abstract: Control schemes for controlling a gas turbine engine in response to disturbances associated with a load mechanically coupled with the gas turbine engine are provided. In one aspect, a gas turbine engine mechanically coupled with a load has a controller that includes executable control logic. The control logic includes a feedforward module, an aggressive control module, and a power turbine governor module. By executing the modules, the controller seeks to maintain a constant power turbine speed stably and subtly in response to small disturbances associated with the load and aggressively in response to large disturbances associated with the load, as well as smooth transitions between the responses.

Abstract: An airfoil for a turbine engine, the airfoil having an outer wall defining an interior and a camber line extending through the airfoil, and at least one cell located within the interior. The at least one cell can include a forward portion and an aft portion with respect to the camber line. The forward portion and the aft portions can be connected by side portions. A braided fabric can be provided on at least one of the forward or aft portions, while a braided fiber can be provided on at least one of the side portions.

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed. An example apparatus includes a compressor comprising a rotor defining a radial direction and a circumferential direction, the rotor including a slot; a first blade and a second blade disposed in the slot, the first blade including a first platform and a first dovetail, the second blade including a second platform and a second dovetail; and a hollow block disposed circumferentially between the first blade and the second blade in the slot, the hollow block including: a platform interface portion to interface with the first platform and the second platform, the platform interface portion including a central opening defined by a circumferential face of the platform interface portion; and a hollow dovetail interface portion to couple the first dovetail and the second dovetail.

Abstract: Systems and methods to fuse aviation-related data systems for comprehensive aircraft system health monitoring are provided. One example method includes obtaining, by one or more computing devices, fault data indicative of a plurality of fault indications provided by a first plurality of components of an aircraft. The method includes obtaining, by the one or more computing devices, condition indicators describing the respective operational conditions of a second plurality of components of the aircraft. The method includes fusing, by the one or more computing devices, the fault data with the condition indicators to form a comprehensive data set. The method includes identifying, by the one or more computing devices, one or more causes of the plurality of fault conditions based at least in part on the comprehensive data set. One example system includes a data fuser, a cause identifier, and an alert generator.

Abstract: Based upon a measured first resistance, a first delta curve is selected. Based upon a measured second resistance, a second delta curve is selected. A first fuel valve position (FVP) is received from a first position sensor, and the first FVP is applied to the first delta curve to obtain a first offset. A second FVP is received from a second position sensor, and the second FVP is applied to the second delta curve to obtain a second offset. The first offset is applied to the first measured FVP to obtain the first compensated FVP and the second offset is applied to the second measured FVP to obtain the second compensated FVP. The first compensated FVP and the second compensated FVP are correlated to obtain a final compensated FVP, which is applied to a desired fuel valve position to obtain a final fuel valve position.

Abstract: Methods for processing an iron cobalt alloy, along with components formed therefrom, are provided. The method may include: pre-annealing a sheet of an iron cobalt alloy at a pre-anneal temperature (e.g., about 770° C. to about 805° C.); thereafter, cutting a component from the sheet; thereafter, heat-treat annealing the component at a treatment temperature (e.g., about 845° C. to about 870° C.) for a treatment period (e.g., about 1 minute to about 10 minutes); and thereafter, exposing the component to oxygen at an oxidizing temperature to form an insulation layer on a surface of the component.

Abstract: A light detection and ranging (LiDAR) system includes light sources configured to generate separate beams of light, a lens array configured to receive the separate beams of light from the light sources and to collimate the separate beams of light into collimated outgoing light that is directed toward an examined area of interest, a light sensitive detector configured to sense reflection of at least part of the collimated outgoing light, and one or more processors configured to determine a distance to one or more objects off which the at least part of the collimated outgoing light was reflected toward the light sensitive detector. The one or more processors are configured to determine the distance based on the reflection of the at least part of the collimated outgoing light.

Abstract: A combustor assembly for a gas turbine engine includes an outer liner that at least partially defines a combustion chamber. The outer liner extends between an aft end and a forward end generally along an axial direction within an outer casing of the gas turbine engine. The outer liner includes an inner surface facing the combustion chamber and an outer surface facing away from the combustion chamber. The combustor assembly includes a radial damper assembly disposed against the outer liner at a plurality of circumferential points.

Abstract: A fuel cell unit that includes a support structure having a plurality of flow channels and an active layer membrane coupled with the support structure, the active layer membrane comprising at least one electrode layer. Each flow channel of the plurality of flow channels is configured to direct one of air and fuel across at least one electrode layer of an active layer membrane to create electric current. Each flow channel of the plurality of flow channels includes at least one enhancement feature that is configured to disrupt a formation of a boundary layer near a surface of the active layer membrane where reactions occur. The plurality of flow channels can be positioned in a zig-zag configuration to allow for an increase in power density of the fuel cell unit.

Abstract: A combustion section defines an axial direction, a radial direction, and a circumferential direction. The combustion section includes a casing that defines a diffusion chamber. A combustion liner is disposed within the diffusion chamber and defines a combustion chamber. The combustion liner is spaced apart from the casing such that a passageway is defined between the combustion liner and the casing. A fuel cell assembly is disposed in the passageway. The fuel cell assembly includes a fuel cell stack having a plurality of fuel cells each extending between an inlet end and an outlet end. Each fuel cell of the plurality of fuel cells includes an air channel and a fuel channel each fluidly coupled to the combustion chamber.

Abstract: A power system includes a turbine assembly including a turbine and a turbine shaft, a generator assembly including a generator and a generator shaft, an inertia assembly including a flywheel coupled to the generator shaft, and a clutch assembly for coupling the turbine shaft to the generator shaft. The clutch assembly is transitionable between a closed state, in which the turbine shaft is coupled to the generator shaft, and an open state, in which the turbine shaft is decoupled from the generator shaft. The power system is operable in a power generation mode when the clutch assembly is in the closed state and a synchronous condenser mode when the clutch assembly is in the open state.

Abstract: A method for magnetizing a section of one or more permanent magnets arranged substantially in a V-shape, comprising: applying a first magnetic field such that magnetic flux lines are substantially perpendicular to a first leg of the V-shape, and removing the first magnetic field. Then the method comprises applying a second magnetic field such that magnetic flux lines are substantially perpendicular to a second leg of the V-shape, and removing the second magnetic field. Systems and methods for magnetizing sections of permanent magnet modules are also provided.

Abstract: A combustor liner for a combustor of a gas turbine includes an outer liner having a plurality of outer liner segments, and an inner liner having a plurality of inner liner segments. Each segment of the inner liner and the outer liner includes at least one slotted dilution opening therethrough extending in a circumferential direction, and each slotted dilution opening includes a deflector wall extending radially from the respective liner into a dilution zone of a combustion chamber between the outer liner and the inner liner. The at least one slotted dilution opening may be a curved slot (either concave or convex) dilution opening, and the curved slot dilution openings for each segment of the outer liner and the inner liner may be connected so as to provide a wavy slotted dilution opening extending annularly through the outer liner and the inner liner.

Abstract: Methods and systems are provided for medical imaging systems. In one embodiment, a method for a medical imaging system comprises acquiring emission data during a positron emission tomography (PET) scan of a patient, reconstructing a series of live PET images while acquiring the emission data, tracking motion of the patient during the acquiring by determining a per-voxel variation for selected voxels in a current live PET image of the series of live PET images, and outputting an indication of patient motion based on the per-voxel variation for the selected voxels in each live PET image. In this way, patient motion during the scan may be identified and compensated for via scan acquisition and/or data processing adjustments, thereby producing a diagnostic PET image with reduced motion artifacts and increased diagnostic quality.

Abstract: Various embodiments provide a method of additively manufacturing a part including depositing a layer of a powder on a working surface, depositing a binder solution on the layer of the powder at first locations, and depositing a sintering aid solution on the layer of the powder at second locations. The sintering aid solution comprises a sintering aid in a solvent. In various embodiments, the sintering aid enables an increased brown strength as compared to parts containing unbound powder. The method enables binders that provide high green strength to be used at the edges of the part, while also balancing a shortened debind time with an increased brown strength. Embodiments in which binder solution is deposited according to a predetermined pattern at second locations are also described.

Abstract: An aircraft includes a gas turbine engine, an electric motor, and a propulsion device. The gas turbine engine and the electric motor are configured to provide a target cumulative output to the propulsion device. An electronic control unit is configured to set the gas turbine engine to a first engine mode to provide a first engine output to the propulsion device, set the electric motor to a first motor mode to provide a first motor output to the propulsion device, a sum of the first engine output and the first motor output being within a predetermined range of the target cumulative output, and in response to a speed of the aircraft reaching a target speed and the first engine output increasing to a second engine output, set the electric motor to a second motor mode.

Abstract: A rotor blade assembly for a turbine engine, including an airfoil blade including an inner diameter end and an outer diameter end, a lower blade carrier coupled to the inner diameter end of the airfoil blade and rigidly coupled to a disk via a pin, an upper blade carrier coupled to the outer diameter end of the airfoil blade, and an outer drum coupled to the upper blade carrier via a radial joint. The radial joint supports radial motion of the upper blade carrier relative to an axis extending through a center of the rotor blade assembly.

Abstract: The rotor for rotary electric machine has a magnetic mass clamped between two compaction elements, and tie rods passing through the magnetic mass and connecting the two compaction elements, at least a first compaction element has as many through holes as tie rods, each through hole of the first compaction element has a counterbore on one side opposite to the side in contact with the magnetic mass, each tie rod passing through a different through hole of the first compaction element and being fixed in the said through hole by a fixing element of the first compaction element logged in the counterbore, characterized in that each fixing element and the associated counterbore cooperate so that each fixing element is in contact with the counterbore in a radial direction of the rotor.

Abstract: The application concerns a compression sealing gasket including an annular main body made of an elastomer material and having a main axis A, the main body including an annular radially outer face and an annular radially inner face parallel and coaxial to each other, wherein the gasket includes an insert mounted on the inner face. The application also concerns a sealing system having the sealing gasket.

Abstract: According to some embodiments, a system, method, and non-transitory computer readable medium are provided comprising a plurality of real-time monitoring nodes to receive streams of monitoring node signal values over time that represent a current operation of the cyber physical system; and a threat detection computer platform, coupled to the plurality of real-time monitoring nodes, to: receive the monitoring node signal values; compute an anomaly score; compare the anomaly score with an adaptive threshold; and detect that one of a particular monitoring node and a system is outside a decision boundary based on the comparison, and classify that particular monitoring node or system as anomalous. Numerous other aspects are provided.

Abstract: A control system for a power production facility is provided. The control system includes a plurality of power generating assets configured to supply power to a power grid. The control system further includes a controller coupled in communication with the plurality of power generating assets. The controller is configured to receive at least one feedback value corresponding to a feedback parameter. The at least one feedback value represents a measured value associated with the power grid. The control system is further configured to determine, based on the received at least one feedback value, to operate in one of a closed-loop mode or an open-loop mode of control.

Abstract: A method and circuit for determining and extinguishing electrical faults includes a power supply, and electrical load, a controller module, and electrical sensors, and when the controller module does not extinguish the electrical fault, another switch blows a fuse.

Abstract: Hybrid video decoder supporting intermediate view synthesis of an intermediate view video from a first- and a second-view video which are predictively coded into a multi-view data signal with frames of the second-view video being spatially subdivided into sub-regions and the multi-view data signal having a prediction mode is provided, having: an extractor configured to respectively extract, from the multi-view data signal, for sub-regions of the frames of the second-view video, a disparity vector and a prediction residual; a predictive reconstructor configured to reconstruct the sub-regions of the frames of the second-view video, by generating a prediction from a reconstructed version of a portion of frames of the first-view video using the disparity vectors and a prediction residual for the respective sub-regions; and an intermediate view synthesizer configured to reconstruct first portions of the intermediate view video.

Abstract: Embodiments of the present disclosure relate to techniques for facilitating personalized neuromodulation treatment protocols. In one embodiment, a predetermined treatment position of an energy application device is used to guide future treatments for the patient. In one embodiment, a position of the energy application device relative to the predetermined treatment position is determined. In one embodiment, a total dose of ultrasound energy applied to the region of interest is determined.

Abstract: A method of fabricating a component is provided. The method includes depositing particles onto a build platform. The method also includes distributing the particles to form a build layer. The method further includes operating a consolidation device to consolidate a first plurality of particles along a scan path to form a component. The component includes a top surface spaced apart from the build platform and an outer surface. The outer surface extends between the build platform and the top surface, and at least a portion of the outer surface faces a substantially particle-free region of the build platform.