Abstract: A vane assembly includes vanes, an actuator assembly, and a controller. The vanes are configured to rotate about their pitch axes. The actuator assembly includes an annular ring arranged radially outward of the vanes and coupled to the vanes, a magnet arranged on the annular ring, and a stator arranged adjacent the magnet. The ring is configured to rotate the vanes about the pitch axes in response to rotation of the ring about the central axis and the stator is configured to selectively rotate the magnet and annular ring about the central axis. The controller controls movement of the ring via the stator and magnets in response to at least one of (i) at least one operating condition of the gas turbine engine, or (ii) at least one operating parameter of the at least one first vane.

Abstract: The present invention discloses an axial flux magnet motor stator assembly, an assembling method, and a ceiling fan, wherein a coil winding assembly can be prefabricated, then assembled on a stator winding column without the need to reserve a large avoidance space between two adjacent stator winding columns, accordingly the gap between them can be minimized, for which each of them can have a maximum number of turns of the coil winding assembly to enhance the magnetic flux, further improve the output power and torque, provide an assembly efficiency and reduce the manufacturing cost. The terminals of each coil winding assembly are located in the bottom cover filling slot and fixed by an adhesive to ensure that the electrical connection is reliable and stable. Thus, a ceiling fan of the present invention using the above assembly has the characteristics of large output power and torque under the same size.

Abstract: An optimized blade with an anchor element to be used in a streaming engine and method of manufacturing such blade. The blade contains a lower part, an upper part and an anchor element, wherein the anchor element is located inside of the blade, and wherein the anchor element connects the lower part and the upper part.

Abstract: A method for manufacturing a blade of a fan for an aircraft turbomachine extending around a longitudinal axis, the blade including an aerofoil made of a composite material having a leading edge and a trailing edge connected by a pressure side and a suction side, the aerofoil extending between a base and a free end, the method including each of the following steps: —pairing and bonding a metal shield to the leading edge, —obtaining a first measurement of a radial moment weight of the blade before or after the metal shield has been bonded to the leading edge and determining a machining kerf, —machining the free end and/or the trailing edge along the machining kerf so as to adjust the mass and radial moment weight of the blade, —obtaining a second measurement of the radial moment weight of the blade.

Abstract: A turbo fan, formed by ultrasonic welding, a first component including: a flat portion; and plate-shaped blade portions standing from the flat portion, and a second component having recessed groove portions in each of which an end portion of the respective blade portion fits. The groove portions have a groove width greater than a thickness of the end portions of the blade portions. The turbo fan includes a group of positioning ribs partially burying two clearances created on two sides of the end portion in a thickness direction thereof, respectively, in a pre-welding state. The group of positioning ribs protrude in the thickness direction from the end portion of at least one of the blade portions, or from side surfaces of at least one of the groove portions, and are in contact with side surfaces of the groove portion, or in contact with the end portion of the blade portion.

Abstract: A fan is provided for a lighting device of a motor vehicle, and includes an impeller, a frame, and a housing. The impeller is rotatably mounted on the frame. The housing is mountable on the lighting device, and the frame is form-lockingly fastened to the housing. The housing includes compliance elements, which are in preloaded contact with the frame, and which are designed for damping of vibrations of the frame along three spatial axes (X, Y, Z).

Abstract: The present application provides a control method and a control device (710) for a wind turbine (720). The control method includes: acquiring incoming wind information of the wind turbine (720); determining whether there is a sector with a complex wind condition around the wind turbine (720) based on the acquired incoming wind information; in response to determining that there is a sector with a complex wind condition around the wind turbine (720), performing feed-forward load reduction control on the wind turbine (720) based on the complex wind condition.

Abstract: A fibrous preform of a turbomachine vane or blade includes two fibrous portions formed by three-dimensional weaving and forming an aerodynamic profile of the vane or blade and defining therebetween an interior volume, wherein each fibrous portion has at least one fibrous vibration damping stiffener including one or several unidirectional layers of yarns and present in the interior volume, and wherein the at least one fibrous stiffener is present on a non-interlinked area on which the unidirectional layer(s) of yarns are separated from the corresponding fibrous portion, and wherein the yarns of this or these unidirectional layers are woven with the corresponding fibrous portion outside the non-interlinked area, or wherein the at least one fibrous stiffener is added onto each fibrous portion.

Abstract: The invention relates to a compressor for an engine, wherein the compressor has compressor stages arranged in succession in a flow direction of the compressor and each compressor stage has a rotating blade cascade and a guide vane cascade arranged downstream of the rotating blade cascade and the rotating blade cascade and the guide vane cascade each have an aspect ratio.

Abstract: A charger may include: a casing including an air inlet and an air outlet; an inner wall extending from an inner surface of the casing and defining an accommodating space between the inner surface of the casing and the inner wall; and a centrifugal fan including an air feed port and disposed in the accommodating space. The air outlet may be disposed to face the air feed port. The air inlet may be disposed closer to the centrifugal fan than the inner wall is. In a direction of a rotation axis of the centrifugal fan, a width between the inner wall and the centrifugal fan may be less than or equal to 150% of a width of the centrifugal fan.

Abstract: The invention employs blades featuring multiple holes. The metal decoration for coupling conceals perforated sections, which ease the mounting and alignment for screws installation. The blade holder incorporates two or more slots for screws to slide through the decoration cover, securing the blade assembly onto the fan motor for assembly and operation. The decoration cover has a minimum of two holes for alignment screw installation and one hole for preassembling and fastening it onto the blade. Alignment screws serve a dual purpose by sliding into the blade holder's slots and installing the blade assembly. This not only aligns the blade holder but also temporarily holds the assembly, freeing the installer's hands for subsequent installation steps. This simplifies the process, minimizes installer fatigue and allowing the use of both hands to handle screws, making it a time-efficient and straightforward task. The installation difficulty then reduces from 9 to 1.

Abstract: Disclosed is a handheld fan, including a main body, a housing cover and a fan blade. The main body includes a handheld area and a fan blade area longitudinally arranged, the main body is internally provided with a driving device, the driving device drives the fan blade to rotate, a sliding connecting structure is arranged between the main body and the housing cover, the housing cover leans against the sliding connecting structure and slides relative to the main body, and the housing cover has two working positions, one for covering the fan blade area and the other for exposing the fan blade area.

Abstract: A propeller assembly for an aircraft includes a main shaft rotatable about a propeller axis, a rotor hub mounted to the main shaft, and a plurality of blades coupled to the rotor hub. Each blade is rotatably coupled to the rotor hub for rotation about a blade rotation axis. A control system rotates each blade about the corresponding blade rotation axis and includes a ball screw coupled to the main shaft for rotation about the propeller axis and configured to translate along the propeller axis, an actuator beam mounted on the ball screw, and a ball nut coupled to the ball screw. When the ball nut rotates relative to the ball screw, the ball screw translates relative to the main shaft along the propeller axis. A differential transmission is configured to rotate the ball nut relative to the ball screw such that the ball screw is translated.

Abstract: The present invention relates to a vane (7) of a turbine engine, comprising: —a structure which has an aerodynamic profile (20); —a spar (21) comprising a vane root portion (24), a blade portion (25) arranged inside the structure which has an aerodynamic profile (20), and a stilt portion (26), the blade portion (25) comprising a body (27) connected to the vane root portion (24) and two arms extending radially from the body (27); and —a structural reinforcement (31) extending from the vane root portion (24) to the body (27) of the blade portion (25), the structural reinforcement (31) being rigidly connected to the vane root portion (24) and configured to form a force path separate from the stilt portion (26) in the event of failure of the spar (21) within the stilt portion (26).

Abstract: Embodiments of a compressor stage, in particular for a turbocharging system and/or a turbocompound, and a process for operating a compressor stage are provided herein. The compressor stage comprises an impeller, and a vaned diffuser arranged downstream of the impeller. The vaned diffuser is in fluid connection with an outlet of the impeller and comprises an injection device configured to inject a secondary fluid into the vaned diffuser. The injection device comprises a displaceable port at least partially arranged between an adjacent pair of vanes of the diffuser.

Abstract: A method for controlling a wind turbine includes receiving operational data of at least one component of the wind turbine. The operational data includes a time-series of one or more high speed signals both before, during, and after an anomaly. Further, the high speed signal(s) may be digital or analog signals. The method also includes storing the operational data. Moreover, the method includes analyzing the stored operational data to identify a specific type and location of the anomaly using at least one of pattern recognition, machine learning, or rules-based conditions. In addition, the method includes determining an appropriate response action for the specific type and location of the anomaly. Further, the method includes adjusting a control parameter of the wind turbine. Thus, the method includes implementing the appropriate response action for the specific type and location of the anomaly.

Abstract: Provided is a blade capable of optimizing an outflow angle in substantially the entire hub region and tip region, particularly in a blade-end-side hub region and a blade-end-side tip region. The blade includes: a base blade part; a suction-side elevated portion provided on a suction surface near a trailing edge in at least one of the blade-end-side tip region and the blade-end-side hub region of the base blade part; and a pressure-side elevated portion provided on a pressure surface near the trailing edge in at least one of a midspan-side tip region and a midspan-side hub region of the base blade part. An airfoil at each spanwise position where the elevated portion is provided is such that a trailing-edge curve of a base airfoil is changed to a modified trailing-edge curve.

Abstract: An airfoil includes an airfoil wall that circumscribes a main cavity and defines radially inner and outer ends, leading and trailing edges, and pressure and suction sides. The airfoil wall includes a lay-up of ceramic matrix composite (CMC) plies that span the radially inner and outer ends and have an inner-most CMC ply bounding at least a portion of the main cavity, an exterior skin CMC ply, and intermediate CMC plies between the inner-most CMC ply and the exterior skin CMC ply. At least one of the intermediate CMC plies has cutout voids that define cooling channels in the airfoil wall. The cooling channels are bound on lateral sides by the at least one of the intermediate CMC plies, bound on an inner side by a first adjacent one of the CMC plies, and bound on an outer side by a second, different adjacent one of the CMC plies.

Abstract: Fibrous preform for a composite blade and also a composite blade formed by means of such a preform, a rotor and a rotating machine comprising such a blade, the preform comprising a first longitudinal section, configured to form a blade root, and a second longitudinal section, extending from the first longitudinal section, configured to form a portion of an airfoil, wherein the first longitudinal section has a first thickness at its upper end and wherein the second longitudinal section comprises at least one set-back zone having a thickness at least three times less than the first thickness, said set-back zone occupying at least 50% of the second longitudinal section.

Abstract: A vibration damping system includes a vibration damping element for a turbine nozzle or blade. A body opening extends through the turbine nozzle or blade between the tip end and the base end thereof, e.g., through the airfoil among potentially other parts of the nozzle or blade. A vibration damping element includes a plurality of stacked plate members within the body opening. Each plate member is in surface contact with at least one adjacent plate member to cause friction that dampens vibration of the nozzle or blade. The body opening has an inner dimension, and each plate member has an outer dimension sized to frictionally engage the inner dimension of the body opening to damp vibration. Plate members may each include a central opening therein, and a fixed elongated body or cable may extend through the central openings. The damping element may alternatively include a helical metal ribbon spring.