Abstract: A turbine engine and method of operating includes an engine core with a compressor, a combustor, and a turbine in axial flow arrangement. A flow path extends through the engine core from the compressor to the turbine to define a flow direction for a working airflow through the engine core.

Abstract: An exhaust device for a compressor bypass bleed system of a ducted fan engine includes a housing having an inlet end and an outlet end and defining a centerline axis from the inlet end to the outlet end, an inlet flow conditioner arranged at the inlet end, the inlet flow conditioner including a plurality of inlet openings for conducting a flow of compressed air therethrough into the housing, and an exit screen arranged at the outlet end of the housing. The exit screen includes a plurality of exit openings therethrough arranged at an acute angle with respect to the centerline axis so as to provide a flow of compressed air therethrough into a bypass flow passage at least partially in a same direction as a bypass airflow through the bypass flow passage.

Abstract: Various methods and systems are provided for stationary CT imaging. In one embodiment, a modular imaging system comprises a plurality of distributed x-ray units releasably coupled to a plurality of detector arrays, with the plurality of distributed x-ray units and the plurality of detector arrays forming a self-supporting structure including a central opening shaped to receive a subject to be imaged. The modular imaging system may image the subject without rotation of the distributed x-ray units or detector arrays around the subject.

Abstract: Systems and methods are provided for quantifying uncertainty of segmentation mask predictions made by machine learning models, where the uncertainty may be used to streamline an anatomical measurement workflow by automatically identifying less certain caliper placements. In one example, the current disclosure teaches receiving an image including a region of interest, determining a segmentation mask for the region of interest using a trained machine learning model, placing a caliper at a position within the image based on the segmentation mask, determining an uncertainty of the position of the caliper, and responding to the uncertainty of the position of the caliper being greater than a pre-determined threshold by displaying a visual indication of the position of the caliper via a display device and prompting a user to confirm or edit the position of the caliper.

Abstract: A Brayton cycle engine including a longitudinal wall extended along a lengthwise direction. The longitudinal wall defines a gas flowpath of the engine. An inner wall assembly is extended from the longitudinal wall into the gas flowpath. The inner wall assembly defines a detonation combustion region in the gas flowpath upstream of the inner wall assembly.

Abstract: A Brayton cycle engine and method for operation. The engine includes an inner wall assembly and an upstream wall assembly each extended from a longitudinal wall into a gas flowpath. An actuator adjusts a depth of the detonation combustion region into the gas flowpath between the inner wall assembly and the upstream wall assembly. The engine flows an oxidizer through the gas flowpath and the inner wall captures a portion of the oxidizer. The engine further adjusts the captured flow of oxidizer via the upstream wall and flows a first flow of fuel to the captured flow of oxidizer to produce rotating detonation gases. The engine flows the detonation gases downstream and to mix with the flow of oxidizer, and flows and burns a second flow of fuel to the detonation gases/oxidizer mixture to produce thrust.

Abstract: An acoustic core may include an array of resonant cells configured as a plurality of resonant cell groups. The resonant cell groups may include a plurality of resonant cells configured as a partitioned resonant cell that include a converging resonant cell and a diverging resonant cell. The converging resonant cell and the diverging resonant cell may be defined by a plurality of cell walls integrally formed with one another and a partition integrally formed with the plurality of cell walls. The partition may at least partially delimit the converging resonant cell from the diverging resonant cell. The converging resonant cell may define an upper resonant space delimited by the partition and a top face of the array of resonant cells. The diverging resonant cell may define a lower resonant space delimited by the partition and a bottom face of the array of resonant cells.

Abstract: Damping devices, turbomachines, and methods of damping vibration are provided. For example, a damping device for damping vibration of a shaft rotatable about an axis of rotation is provided. The damping device defines radial and axial directions. The damping device comprises a bearing, a housing, and a damper element. The housing and damper element define a cavity therebetween for receipt of a damping fluid. The cavity has a length along the axial direction that is curved away from the axis of rotation. As another example, a turbomachine comprising a shaft rotatable about an axis of rotation includes a damping device positioned annularly about the shaft. The damping device comprises a housing and a damper element defining a cavity therebetween for receipt of a damping fluid that has a curved shape. The cavity is curved in a plane extending along the radial and axial directions and including the axis of rotation.

Abstract: Systems and methods of aircraft thrust management are provided. For example, a propulsion system for an aircraft comprises a fuel cell assembly comprising a fuel cell, a turbomachine, and a controller comprising memory and one or more processors. The memory stores instructions that, when executed by the one or more processors, cause the propulsion system to perform operations including receiving data indicative of a propulsion system thrust discrepancy and modifying an output of the fuel cell in response to receiving data indicative of the propulsion system thrust discrepancy. Modifying the fuel cell output may include modifying output products, an electrical power output, or both of the fuel cell to balance the thrust provided by the propulsion system.

Abstract: A control system and methods for controlling the position of one or more engine-mounting links of an engine-mounting linkage system are provided. In one aspect, an engine-mounting linkage system includes one or more engine-mounting links that each have an adjustable inclination angle. An inclination angle of a link may be adjusted by an actuator of the control system. One or more controllers of the control system can control the actuator and thus the inclination angle of the link by determining a control command based at least in part on an output received from one or more sensors of the control system. The controllers can then cause the actuator to change the inclination angle of the link based at least in part on the determined control command.

Abstract: A system for manufacturing a tower structure of a wind turbine includes an additive printing device having a central frame structure with a platform and an arm member. The arm member is generally parallel to a longitudinal axis of the tower structure. The additive printing device also includes a plurality of robotic arms secured to the arm member of the central frame structure. Each of the robotic arms includes a printer head for additively printing one or more materials. The additive printing device further includes at least one nozzle configured for dispensing a cementitious material. Moreover, the system includes one or more molds additively printed via the additive printing device of a polymer material. As such, the mold(s) define inner and outer wall limits of the tower structure.

Abstract: A clearance control assembly for a gas turbine engine that defines an axial direction and a radial direction and includes a stage of rotor blades and a shroud hanger. The assembly includes a case configured to be positioned outward along the radial direction from the stage of rotor blades when installed in the gas turbine engine. The case is further configured to be engaged with the shroud hanger at a first location when installed in the gas turbine engine. The assembly also includes a baffle positioned outward along the radial direction from the case to define a chamber therebetween. The baffle has a forward end and an aft end. The forward end of the baffle is engaged with the case to form a first seal and the aft end of the baffle is engaged with the case to form a second seal. The baffle, the case, or both define an inlet to allow a fluid to enter the chamber and the case defines an outlet to allow the fluid to exit the chamber.

Abstract: Acoustic turbofan airfoil apparatus are disclosed. An example apparatus includes a platform of a turbofan engine, the platform including perforations to receive acoustic waves, acoustic chambers protruding from a first side of the platform, the acoustic chambers aligned with the perforations in a radial direction defined by the turbofan engine, the acoustic chambers to attenuate the acoustic waves, and an airfoil protruding from a second side of the platform opposite the first side of the platform.

Abstract: A system and method for controlling rotor dynamics at a rotor assembly. The system includes a magnetic actuator and a controller. The magnetic actuator is positioned in magnetic communication with the rotor assembly and is configured to obtain a measurement vector corresponding to the rotor assembly and a measurement vector indicative of a rotor dynamics parameter. The magnetic actuator is further configured to selectively output an electromagnetic force at the rotor assembly. The controller is configured to store and execute instructions.

Abstract: Systems and method for an electrical system on an aircraft are provided. In example embodiments, the electrical system can be for an aircraft having a turbine engine. The turbine engine having a high pressure (HP) spool and a low pressure (LP) spool. The HP spool can be configured to drive a first generator to provide a first electrical output. The LP spool can be configured to drive a second generator to provide a second electrical output. The first generator and the second generator can be coupled to an electrical power distribution bus that provides electrical power to a load. A hybrid electric propulsion system and a secondary aircraft systems bus can both be coupled to the electrical power distribution bus. The electrical system can further include a control system configured to allocate power among the first generator, the second generator, and the hybrid electric propulsion system, and the secondary aircraft systems bus.

Abstract: A gas turbine engine including: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order; a fan defining a fan axis and comprising a plurality of fan blades rotatable about the fan axis; and a pitch change mechanism operable with the plurality of fan blades, the pitch change mechanism including a plurality of linkages, the plurality of linkages including a first linkage coupled to a first fan blade of the plurality of fan blades and a second linkage coupled to a second fan blade of the plurality of fan blades; and a non-uniform blade actuator system operable with one or more of the plurality of linkages to control a pitch of the first fan blade relative to a pitch of the second fan blade.

Abstract: A thrust mount assembly includes a thrust link-lever that has a first end region, a second end region, and a fulcrum region disposed between the first end region and the second end region. A thrust link-lever may be coupled or couplable to a fulcrum body of an aft engine-mount at a fulcrum position of the thrust link-lever. When coupled to a turbomachine, the fulcrum position of the thrust link-lever may be laterally offset and/or laterally adjustable relative to an axis of rotation of the turbomachine. A load translated from an engine frame of a turbomachine to an engine-mounting linkage system may be determined and a fulcrum position for the thrust mount assembly may be adjusted laterally relative to an axis of rotation of the turbomachine.

Abstract: An additive printing device and a method for using the same to manufacture a tower structure of a wind turbine is provided. The additive printing device includes a vertical support structure, a support ring suspended from the vertical support structure, and a printer head movably coupled to the support ring for selectively depositing cementitious material. A drive mechanism, such as a rack and pinion, moves the printer head around the support ring while selectively depositing cementitious material. The vertical support structure may be raised and/or the relative position between the vertical support structure and the printer head may be adjusted to raise the printer head to print subsequent layers. This process may be repeated to print the tower structure layer-by-layer from the ground up.

Abstract: A method for manufacturing a tower structure of a wind turbine includes printing, via an additive printing device, the tower structure of the wind turbine of a cementitious material. The method also includes printing, via the additive printing device, one or more additional airflow modifying features on an outer surface the tower structure of the wind turbine so as to reduce and/or prevent vortex shedding, excitation, and/or drag of the tower structure. Further, the method includes curing the cementitious material so as to form the tower structure.

Abstract: A system includes a gas turbine having a turbine shaft disposed along a rotational axis, a turbine casing disposed circumferentially about the turbine shaft, a combustion gas path disposed between the turbine shaft and the turbine casing, and a turbine stage disposed in the combustion gas path. The turbine stage includes a plurality of turbine vanes disposed upstream from a plurality of turbine blades. The gas turbine includes an isothermal expansion system coupled to the turbine stage, wherein the isothermal expansion system includes a plurality of flame stabilizers configured to vary axial positions of combustion within a turbine stage expansion of the turbine stage to reduce temperature variations over the turbine stage expansion. The flame stabilizers are disposed in different axial positions over an axial length between leading and trailing edges of the turbine blades, wherein at least one flame stabilizer is coupled to each of the turbine blades.

Abstract: A method of manufacturing a blade component of rotor blade of a wind turbine includes providing a plurality of pultrusions constructed of one or more fibers or fiber bundles cured together via a resin material. The method also includes placing a protective cap over at least one end of one or more of the plurality of pultrusions. Further, the method includes heat treating a surface of the plurality of pultrusions while the protective cap remains over the at least one end. Moreover, the method includes removing the protective cap from the at least one end. The method further includes arranging the plurality of pultrusions in a mold of the blade component. In addition, the method includes infusing the plurality of pultrusions together so as to form the rotor blade component.

Abstract: An imaging system and method acquires non-contrast images of a region of interest in a body and determines an entrance criterion based on the non-contrast images. The entrance criterion dictates conditions in which to begin acquiring contrast imaging exposures of the region of interest. An amount of a contrast agent is measured in one or more locations in the imaged body subsequent to acquiring the non-contrast images. The system and method determine that the one or more conditions of the entrance criterion are met based on the amount of the contrast agent that is measured in the imaged body, and acquire one or more contrast images of the region of interest in the imaged body responsive to determining that the one or more conditions of the entrance criterion are met.

Abstract: A system for readying sub-critical and super-critical steam generator, a servicing method of the sub-critical and the super-critical steam generator and a method of operation of sub-critical and super-critical steam generator is provided. The steam generator includes a first auxiliary heating device disposed on at least one water-steam separator for heating the at least one water-steam separator, and/or a second auxiliary heating device disposed at least on a part of furnace top-end piping for heating the furnace top-end piping. The auxiliary heating devices are heating steam producing components of the steam generator and thus allowing to keep them above the temperature in which materials creating the steam producing components are brittle. The method includes recirculation of the water through the steam generator.

Abstract: A method for removing or controlling or quantifying the presence of aldehydes, in particular acetaldehyde, is described. Such a method is useful in prolonging the shelf life of a pharmaceutical product.

Abstract: A control system for an engine operatively coupled with a propeller and methods for controlling an engine operatively coupled with a propeller are provided. In one example aspect, the control system includes a controller and an electric propeller governor. The electric propeller governor includes a motor operatively coupled with a flyweight governor spring. The motor is communicatively coupled with the controller. The controller is operable to receive data indicative of the speed of the propeller, determine if the measured speed exceeds a propeller speed threshold, and if the threshold is exceeded, the controller is configured to change a propeller speed set point. Particularly, the controller can cause the motor to change the preload on the flyweight governor spring, which in turn causes adjustment of the propeller speed set point. In this way, propeller speed overshoot is prevented during fast acceleration of the engine.

Abstract: An airfoil is provided defining a spanwise direction, a chordwise direction, a root end, a tip end, a leading edge end, and a trailing edge end. The airfoil includes: a leading edge extending from the leading edge end; a body extending along the spanwise direction between the root end and the tip end, the body including a plurality of cavity walls defining a plurality of cavities, each of the plurality of cavities having an inlet located at the leading edge; and a porous face sheet positioned on at least one inlet of the plurality of cavities.

Abstract: In the present invention, a right leg drive RLD monitoring system is employed on a medical computing system/computer, such as an ECG, HEMO and/or EP monitoring, mapping and/or recording system, that includes a number of RLD circuits to be utilized for different procedures or monitoring states to be performed using the system. The RLD monitoring system operates to actively monitor and/or record the feedback voltage to the RLD isolated from the patient. Using the measured feedback voltage data, the RLD monitoring system can identify and determine if the RLD circuit in use is approaching saturation, has reached saturation and the duration the RLD circuit was in saturation. The RLD monitoring system can concurrently and/or subsequently select and/or provide selection information regarding an optimal RLD circuit to be utilized to most effectively perform the desired function of the RLD in the procedure being performed using the monitoring, mapping and/or recording system.

Abstract: A propulsion system is provided including: a gas turbine engine including a combustion section having a combustor; and a modular fuel cell assembly. The modular fuel cell assembly includes: a first fuel cell string comprising a first processing unit and a first fuel cell stack, the first fuel cell stack comprising a first fuel cell defining an outlet configured to provide output products from the first fuel cell to the combustor; and a second fuel cell string comprising a second processing unit and a second fuel cell stack, the second fuel cell stack comprising a second fuel cell defining an outlet configured to provide output products from the second fuel cell to the combustor.

Abstract: A method for providing overspeed protection for a gas turbine engine having an engine shaft includes monitoring, via an overspeed protection system, a torque of the engine shaft. The method also includes determining, via the overspeed protection system, at least one additional condition of the engine shaft. Further, the method includes determining, via the overspeed protection system, an overspeed condition of the gas turbine engine when the torque of the engine shaft drops below a torque threshold and the at least one additional condition of the engine shaft is indicative of the gas turbine engine being in an operational state. Thus, the overspeed condition is indicative of an above normal rotational speed of the engine shaft. In addition, the method includes initiating a shutdown procedure for the gas turbine engine in response to the determined overspeed condition to reduce the rotational speed of the engine shaft.

Abstract: A rotor lock assembly for locking a rotor of a wind turbine. The rotor lock assembly has at least one relocatable rotor lock. The relocatable rotor lock has a housing, a bushing element, a pin shaft position within the bushing element, and a locking mechanism. The housing includes a mounting portion adapted for mounting to a bearing housing adjacent to a rotor lock plate of the rotor.

Abstract: A system and process for restarting a turbomachine includes a shutdown cooldown protection process implemented by a plant level control system or direct control system of the turbomachine. The system and process for restarting ensure rotating components are cooled as expected prior to a unit restart. This system and process for restarting will lockout an ability to restart if an improper cooldown of rotating components is detected. If this lockout is enabled, delaying restart for the rotating components to cool naturally is needed, or the operator could decide to force cool the components.

Abstract: A heat exchanger is provided. The heat exchanger includes a first wall manifold. The heat exchanger further includes a second wall manifold spaced apart from the first wall manifold. The heat exchanger further includes a plurality of vanes that extend generally circumferentially between the first wall manifold and the second wall manifold. The heat exchanger further includes a plurality of fluid circuits defined within the heat exchanger. Each fluid circuit in the plurality of fluid circuits includes an inlet channel portion and an outlet channel portion defined within the first wall manifold. A return channel portion defined within the second wall manifold. At least one passage portion of a plurality of passage portions defined within each vane of the plurality of vanes. The at least one passage portion extends between the return channel portion and one of the inlet channel portion and the outlet channel portion.

Abstract: Methods and systems are provided for adaptive scan control. In one embodiment, a method for an imaging system includes performing, with the imaging system, a first contrast scan of a subject including injection of a contrast agent to the subject; processing projection data of the subject acquired during the first contrast scan to measure a contrast signal of the subject at a monitoring area; estimating a target acquisition timing for a first acquisition of a second contrast scan of the subject based on the contrast signal; and performing, with the imaging system, the second contrast scan of the subject, with the first acquisition performed at the target acquisition timing and without performing any monitoring scans between the first contrast scan and the second contrast scan.

Abstract: A method for determining a lesion location in a patient for biopsy along X, Y, and Z axes. The method includes positioning the patient in an examination device to collect examination images showing the lesion. The method includes positioning the patient in a biopsy device configured for holding the patient during the biopsy and collecting a biopsy image of the patient using the biopsy device. The method includes analyzing the biopsy image to determine a measured x-coordinate and a measured y-coordinate of the lesion along the X and Y axes, respectively, analyzing the examination images to determine a calculated z-coordinate along the Z axis of the lesion, and determining the location of the lesion based on the measured x-coordinate and the measured y-coordinate from the biopsy image and the calculated z-coordinate determined from the one or more examination images.

Abstract: A turbomachine component has a wall outer surface and an internal coolant source. A film-cooling hole is in the wall and extends from the internal coolant source to the wall outer surface. The film-cooling hole includes a metering section in fluid communication with the internal coolant source, and a diffuser section in fluid communication with the metering section and including a first internal surface spaced from a second internal surface. A coating collector receives part of a coating and is part of the diffuser section. The film-cooling hole also includes a hood section including a member extending outwardly from the wall outer surface. The member may include a hood internal surface contiguous with the first internal surface of the diffuser section and a hood outer surface parallel to the wall outer surface. The hood section reduces, and possibly prevents, the coating from filling the film-cooling hole during application thereof.

Abstract: A method of additively manufacturing three-dimensional objects, and/or a method of controlling one or more irradiation parameters of the energy beam system, may include determining an irradiation setting using an irradiation control model and outputting an irradiation control command to an energy beam system based at least in part on the irradiation setting. The irradiation control model may be configured to determine the irradiation setting based at least in part on a power density factor and/or an irradiation vector factor. The irradiation control command may be configured to change one or more irradiation parameters for additively manufacturing a three-dimensional object. An additive manufacturing system may include an energy beam system and a control system that includes an irradiation controller. The irradiation controller may include a control module configured to perform such a method.

Abstract: Embodiments of the present application provide a magnetic resonance system and a shimming method and an imaging method thereof. The shimming method comprises: performing a scout scan on a subject to be examined, and obtaining phase data of a plurality of slice positions; determining three-dimensional space static magnetic field information according to the phase data of the plurality of slice positions; and determining a shimming value of a slice in a region of interest according to the three-dimensional space static magnetic field information.

Abstract: A control system an unmanned vehicle includes a first processing unit configured to execute a primary autopilot process for controlling the unmanned vehicle. The control system further includes a programmable logic array in operative communication with the first processing unit. The control system also includes a state machine configured in the programmable logic array. The state machine is configured to enable control of the unmanned vehicle according to a backup autopilot process in response to an invalid output of the first processing unit.

Abstract: A combustor for a gas turbine engine has a combustor liner that has a cold surface side and a hot surface side, the liner defining an upstream end and a downstream end, and a dilution opening through the combustor liner. The dilution opening includes a main dilution hole portion having an upstream edge and a downstream edge, a notched portion disposed at the upstream edge and extending upstream from the upstream edge, the notched portion being in fluid communication with the main dilution hole portion, and a slotted portion disposed at the downstream edge and extending downstream of the downstream edge, the slotted portion being in fluid communication with the main dilution hole portion.

Abstract: The usual coding order according to which the reference view is coded prior to the dependent view, and within each view, a depth map is coded subsequent to the respective picture, may be maintained and does lead to a sacrifice of efficiency in performing inter-view redundancy removal by, for example, predicting motion data of the current picture of the dependent view from motion data of the current picture of the reference view. Rather, a depth map estimate of the current picture of the dependent view is obtained by warping the depth map of the current picture of the reference view into the dependent view, thereby enabling various methods of inter-view redundancy reduction more efficiently by bridging the gap between the views.

Abstract: An idea used herein is to use the same function for the dependency of the context and the dependency of the symbolization parameter on previously coded/decoded transform coefficients. Using the same function—with varying function parameter—may even be used with respect to different transform block sizes and/or frequency portions of the transform blocks in case of the transform coefficients being spatially arranged in transform blocks. A further variant of this idea is to use the same function for the dependency of a symbolization parameter on previously coded/decoded transform coefficients for different sizes of the current transform coefficient's transform block, different information component types of the current transform coefficient's transform block and/or different frequency portions the current transform coefficient is located within the transform block.

Abstract: A method for controlling an inverter-based resource having a power converter connected to an electrical grid includes receiving, via a regulator of a controller of the inverter-based resource, a plurality of power signals. The method also includes determining, via the regulator, a power error signal as a function of the plurality of power signals. Further, the method includes receiving, via the regulator, a dynamic multiplier factor from a supervisory controller. Moreover, the method includes applying, via the regulator, the dynamic multiplier factor to one or more gains of the regulator to determine one or more modified gains. In addition, the method includes applying the one or more modified gains to the power error signal to obtain an intermediate power signal. Thus, the method includes generating, via the regulator, one or more control commands for the power converter as a function of the intermediate power signal.

Abstract: An approach for facilitating mechanical and electrical connection of electric machines and electrical components in an electrical system using connectors with quick connect/disconnect electrical connectors is disclosed. Each quick connect/disconnect electrical connector can be placed on the end of an electrical power distribution cable that connects with an electric machine or electrical component. The electric machines and electrical components and the electrical power distribution cables can have hollow coolant passages formed therein to receive cooling fluid from a cooling device for direct cooling of the electric machines, electrical components and the electrical power distribution cables.

Abstract: A system for dynamic rating of a power grid may include a plurality of terminal units, and a controller. The terminal units may detect a voltage phasor and a current phasor at nodes of the power grid. The controller may, based on the voltage phasors and the current phasors of the plurality of nodes, determine a dynamic thermal stability power rating for each line, a dynamic angular stability power rating for each node, and a dynamic voltage stability power rating for each node. The controller may, based on the dynamic thermal stability power rating, the dynamic angular stability power rating, and the dynamic voltage stability power rating, determine a dynamic system rating for the power grid. The controller may control the power grid in response to the dynamic system rating.

Abstract: Systems and methods of controlling a length of an air gap in an electric machine using an air gap controller may include: determining an air gap length value for an electric machine at least in part using an air gap controller, comparing the determined air gap length value to an air gap target value using the air gap controller, and outputting a control command from the air gap controller to a controllable device associated with an air gap control system when the determined air gap length value differs from the air gap target value by a predefined threshold. A control command may be configured to impart a change to an operating parameter associated with the air gap control system to adjust a length of an air gap between an outer surface of a rotor core and an inner surface of a stator core of the electric machine.

Abstract: A fuel supply system for a turbine engine that provides a modulated thrust control malfunction accommodation (TCMA) is disclosed. An example fuel supply system includes a fuel supply line to supply fuel to a combustion engine, a fuel metering valve coupled to the fuel supply line, the fuel metering valve to control a flow of fuel through the fuel supply line to the combustion engine, a throttle valve coupled to the fuel supply line downstream of the fuel metering valve, the throttle valve to bleed off fuel supplied to the combustion engine based on a pressure difference across the fuel metering valve, and a controllable servo coupled to the throttle valve, the controllable servo to control the throttle valve based on a sensor output indicative of the pressure difference.

Abstract: A rotor blade system. The rotor blade system includes a rotor and a plurality of blades coupled to the rotor. The plurality of blades are arranged in an airfoil distribution pattern. The airfoil distribution pattern includes one or more baseline blades and one or more intentionally mistuned blades including an intentional mistuning feature.

Abstract: A method of manufacturing a lead assembly of a cryogenic system is provided. The method includes developing a three-dimensional (3D) model of a heat exchanger. The heat exchanger includes a plurality of channels extending longitudinally through the heat exchanger from the first end to the second end, the plurality of channels forming a plurality of thermal surfaces within the heat exchanger, the heat exchanger having a transverse cross section. The method further includes modifying the 3D model by at least one of reducing an area of the cross section and increasing the plurality of thermal surfaces. The method also includes additively manufacturing the heat exchanger using an electrically-conductive and thermally-conductive material according to the modified 3D model. Further, the method includes providing a high temperature superconductor (HTS) assembly that includes an HTS strip, and connecting the HTS assembly to the heat exchanger at the second end of the heat exchanger.

Abstract: A vibration mitigating device for engagement with a wind turbine blade includes an air flow modifying element that is configurable between a retracted configuration and an extended configuration. A frame is attachable to and has a fixed length in a span-wise direction of the wind turbine blade. The air flow modifying element is movable along the frame between the retracted configuration and the extended configuration. In the retracted configuration, the modifying element extends between the blade tip and the blade root with a first spanwise length, and in the extended configuration the modifying element extends between the blade tip and the blade root with a second, greater spanwise length.