Abstract: The present application relates to a propulsion device having a motor, a mast connected to the motor, an angle sensing device detecting the angle of the mast, a controller receiving the angle of the mast as an input and outputting a motor torque signal to the motor in response thereto, a hub attached to the mast via a single skewed hinge, and a propeller assembly with one or more blades connected to a hub.

Abstract: In general, the invention relates to wind turbines, the rotor blades of which can be adjusted in terms of their pitch angle. The invention relates in particular to an actuating drive for adjusting the pitch angle of a rotor blade of a wind turbine, comprising a large rolling bearing which comprises two bearing rings that can be rotated relative to each other, and an actuator for rotating the two bearing rings relative to each other. According to the invention, the actuating drive comprises a ring channel cylinder, which is formed in one of the bearing rings, and at least one piston, which is received in the ring channel cylinder in a movable manner and is drivingly connected to the other bearing ring of the two bearing rings.

Abstract: A main rotor blade 1, which is the main rotor blade 1 for a high-velocity helicopter, includes: a blade root part 10 having a length of 30% or more of a rotor radius R; and a blade main body 20 continuous with the blade root part 10. Preferably, a cross-sectional shape of the blade root part 10 satisfies (x/a)m+(y/b)m=1 and a>b, where m: arbitrary number, x: chord length direction, and y: blade thickness direction.

Abstract: The present invention is an improved wind turbine comprising: a wind turbine wheel having a hub, a rim and a cable extending between the hub and the rim; a set of airfoils rotatably carried by the cable and disposed between the hub and the rim; a cinch attached to the cable and disposed between adjacent airfoils; and, an upturned section included in at least one airfoil in the set of airfoils and disposed at a trailing edge of the airfoil wherein each airfoil has a different angle of attack relative to an adjacent airfoil.

Abstract: A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. Each blade is formed from a composite comprising ceramic matrix material. The blades each include a root that fits within dovetail slots of the rotor disk and cooperates with a blade retention assembly to couple the blades to the rotor disk.

Abstract: A roller bearing having a rotatable first ring and a non-rotatable second ring arranged concentrically, the first ring having a circumferential groove opening towards the non-rotatable second ring into which is arranged a protruding element, between which are arranged a single radial roller bearing and two axial roller bearings spaced apart in the axial direction respectively on opposite radial faces of the protruding element. The roller bearing includes a plurality of circumferentially spaced apart cam followers secured to the rotatable first ring.

Abstract: A propeller includes a blade free to rotate about a longitudinal axis of the blade. The propeller also includes a mechanical stop positioned to engage mechanically a first portion of the blade and/or a first structure coupled mechanically to the blade when the blade is in a first position. The propeller also includes a magnetic stop positioned to engage magnetically a second portion of the blade and/or a second structure coupled mechanically to the blade when the blade is in a second position. The blade rotates to the first position against the mechanical stop when the propeller is rotated at a first rotational speed and the blade rotates to the second position against the magnetic stop when the propeller is rotated at a second rotational speed in a same direction as when the blade is in the first position.

Abstract: Apparatus suitable for use in positioning ceiling or wall panels in predetermined locations. The apparatus includes one or more channel means shaped to receive at least part of a panel in use, said channel means at least partially defined by one or more substantially planar outer walls and at least one inner wall. At least part of the inner wall depends away from the outer wall thereby forming the opening into said channel means through which the ceiling or wall panel is inserted in use.

Abstract: The present disclosure is directed to a fastener retention assembly for a wind turbine rotor. The fastener retention assembly includes a rotor hub and a pitch bearing race coupled to the rotor hub. One of the pitch bearing race or the rotor hub defines an annular slot. The pitch bearing race and the rotor hub further defines a plurality of passages extending from the slot through the pitch bearing race and the rotor hub. The fastener retention assembly also includes a plurality of fasteners coupling the rotor hub and the pitch bearing race. Each of the plurality of fasteners is at least partially positioned within the slot and one of the plurality of passages. The fastener retention assembly further includes a retaining ring partially positioned within the slot to retain the plurality of fasteners within the plurality of passages.

Abstract: A trailing-edge segment of a wind-turbine rotor blade for increasing a profile depth of the rotor blade of a wind turbine. The trailing-edge segment of a wind-turbine rotor blade comprises at least one inner blade segment, having an inner blade shell, at least one middle blade segment, having a middle blade shell. In this case, the at least one middle blade segment and the at least one inner blade segment can be coupled to each other via a coupling means, and the coupling means has at least one shell element, having two inner sides that are parallel to each other and form a receiving space, designed to receive at least one of the inner blade shell or middle blade shell, and the two inner sides each being realized such that they can be connected to at least one of the inner blade shell or middle blade shell, in such a manner that a force acting upon the trailing-edge segment of a wind-turbine rotor blade is introduced centrically into the coupling means.

Abstract: Aerial vehicles may be equipped with propellers having pivotable blades that are configured to rotate or fold when the propellers are not rotating under power. A pivotable blade may rotate about an axis of a propeller with respect to a hub in the presence of wind flow until the pivotable blade is coaligned with a fixed blade, in a direction opposite to the wind flow. A pivotable blade may also fold over a hub of a propeller in the presence of wind flow, with the pivotable blade and a fixed blade being oriented in directions opposite to the wind flow. A center of mass of the pivotable blade may be caused to be on the same side of an axis as a center of mass of a fixed blade, even where the axis is not normal to the wind flow, thereby reducing an amount of drag generated by the propeller.

Abstract: The present invention discloses a rotor control system where rapid changes in rotor torque are transferred into moment forces acting about the blade pitch axis of a rotor blade in a thrust-generating rotor, to ultimately control the movements of a rotary wing aircraft. The moment forces acting on the rotor blade are transferred through a carefully adjusted damping member in order to allow rapid changes in rotor torque to create cyclic changes in blade pitch angle, while slow or permanent changes are cancelled out and affects the rotational speed and the thrust generated by the rotor, without permanently affecting the blade pitch angle of individual rotor blades.

Abstract: A blade for a wind turbine can include an elongated and curved sheet having a curved root, a curved tip, a leading edge, and a trailing edge. The root and the tip can be rotated relative to each other such that the blade is twisted along its length. The root can include an edge having curved projections, the curved projections being distributed along a curvature of the root. A wind turbine can include a mounting element and a plurality of turbine blades. Each turbine blade can be attached to the mounting element closer to the trailing edge than to the leading edge such that an intersection of the leading edge and the root projects upstream from the wind turbine. A wind turbine generator assembly for converting wind into electrical energy can include a wind turbine and a generator. In addition, a support structure can support the wind turbine and generator.

Abstract: Folding propeller system for safe packing and shipping, and easy deployment.

Abstract: A flexbeam unit for a multi-blade rotor of a rotary wing aircraft, the flexbeam unit comprising a plurality of flexbeam elements defining a predetermined number of torsion elements that are connectable with associated rotor blades of the multi-blade rotor, at least one of the predetermined number of torsion elements comprising at least one flexbeam element having an associated longitudinal direction, the at least one flexbeam element comprising at least one twisted area in which the at least one flexbeam element is twisted in the associated longitudinal direction.

Abstract: The invention relates to a device for converting kinetic energy of a flowing water into kinetic energy of a rotatable rotor shaft, wherein the device is adapted to be effective in a first flow direction and a second flow direction substantially opposite to the first, wherein the device comprises two rotor blades each connected to a blade shaft coupled to the rotor shaft for transfer of a torque relative to the rotor shaft, wherein the blades are each rigidly connected to their blade shaft, the blade shafts are mounted for rotation about their own axis relative to the rotor shaft, the blade shafts are coupled to each other for rotation in the same rotation direction and the rotor blades each have an asymmetrical cross-section. There is hereby always flow against the asymmetrical rotor blades from the same direction relative to the blade during the energy conversion process, so that the profile of the rotor blades can be optimized for this flow direction.

Abstract: A wing incorporating a wing tip with a curved leading edge and a curved trailing edge to minimize induced drag for a given wing form is disclosed. The curve of the leading and trailing edges of the wing tip may be described generally as parabolic, elliptic, or super elliptic. A finite tip segment may be included with a sweep angle between the end of the curved leading edge and the end of the curved trailing edge. The wing tip may also include a spanwise camber.

Abstract: The invention relates to a rotor for a wind turbine of the type having a rotor hub (8) and a set of rotor blades (9). Each rotor blade (9) is rotatably mounted on the rotor hub (8) for rotation about a blade axis (11). A threaded spindle mechanism (13) interconnects the rotor blade (9) and the rotor hub (8). The threaded spindle mechanism (13) includes a spindle nut (32), a threaded spindle (31) and a drive (21) mounted on the rotor blade (9) adjacent a transition between the rotor hub (8) and the rotor blade (9). The drive (21) is rotatable together with the rotor blade (9) about the blade axis (11) relative to the rotor hub (8) by actuation of the threaded spindle mechanism (13).

Abstract: An impeller includes a hub, and a plurality of blades supported by the hub, the blades being arranged in at least two blade rows. The impeller has a deployed configuration in which the blades extend away from the hub, and a stored configuration in which at least one of the blades is radially compressed, for example by folding the blade towards the hub. The impeller may also have an operational configuration in which at least some of the blades are deformed from the deployed configuration upon rotation of the impeller when in the deployed configuration. The outer edge of one or more blades may have a winglet, and the base of the blades may have an associated indentation to facilitate folding of the blades.

Abstract: A pitch bearing assembly for a wind turbine including a stiffener is disclosed. The pitch bearing assembly includes an outer race and an inner race rotatable relative to the outer race. The inner race may define an inner circumference and may include a plurality of gear teeth around the inner circumference. Further, the pitch bearing assembly includes a stiffener having a body and at least one gear pinion configured with the body. The body extends at least partially around the inner circumference of the inner race and the at least one gear pinion engages a portion of the plurality of gear teeth. Further, the body remains fixed relative to the inner race while the gear pinions may freely rotate along with the inner race.

Abstract: A pitch bearing assembly for a wind turbine may include an outer race and an inner race rotatable relative to the outer race. The inner race may define an inner circumference and may include a plurality of gear teeth around the inner circumference. The inner race may also include a circumferential flange extending at least partially around the inner circumference. In addition, the pitch bearing assembly may include a stiffener coupled to the circumferential flange.

Abstract: A variable blade pitch wind turbine and method of passively varying the blade pitch is presented. Each blade of the turbine rotor can individually and passively rotate about a respective blade axis to continuously vary the pitch of the blades to adjust to the ever changing wind speed and direction without active controls or other mechanical or electrical induced inputs to force rotational movement of the blades. Sections of each blade can respectively rotate to change the blade twist. In one example, a second rotor is used to improve the efficiency of the wind turbine and increase output of the electric generating equipment.

Abstract: A spar for a rotor blade assembly is provided including a generally hollow tubular body. A spacer protrudes from at least one surface of the body along a length of the body. A hole extends through the body and the spacer. The hole is configured to align with a through hole in an adjacent flexbeam assembly. The spacer is configured to contact a surface of the adjacent flexbeam assembly to create a match fit between the body and the flexbeam assembly.

Abstract: A method and system for re-indexing a pitch bearing of a wind turbine includes: installing a plurality of first mounts to the fixed outer race of the pitch bearing; positioning the rotor blade to a downwardly-oriented; installing a hydraulic system; pressurizing the hydraulic system so as to support the weight of the rotor blade with the hydraulic system; detaching the rotor blade from the pitch bearing; lowering the rotor blade a predetermined vertical distance from the hub; installing a plurality of second mounts to the rotor blade; attaching a plurality of supports between the first mounts and the second mounts; transferring the weight of the rotor blade from the hydraulic system to the plurality of supports; disengaging the hydraulic system; and re-indexing the pitch bearing so as to engage a new set of pitch bearing teeth.

Abstract: A method for manufacturing a leading edge profile section of an aircraft lifting surface is provided. The method comprises the following steps: a) providing a set of laminated preforms of a composite material configured with a suitable shape for constituting the leading edge profile section; b) arranging said laminated preforms in a curing tooling and subjecting the assembly to an autoclave cycle to co-cure said laminated preforms; c) demoulding the curing tooling in a spanwise direction towards the aircraft symmetry plane. The invention also comprises a leading edge profile section manufactured by said method comprising in addition to the skin of the leading edge profile section, one or more of the following structural elements: an auxiliary spar, a longitudinal stiffener reinforcing an auxiliary spar, a longitudinal stringer reinforcing the skin of the leading edge profile.

Abstract: A bidirectional centrifugal fan having a self-adjusting vane. In one embodiment, the fan includes a driving disc having a pivot pin extending therefrom; a vane pivotably attached to the pivot pin, the vane including an aperture extending at least partially therethrough; and a trailing disc including a guide arm for receiving the aperture of the vane.

Abstract: Variable vane assemblies and methods for removing and assembling variable vane assemblies in turbine systems are provided. In one embodiment, a variable vane assembly includes a variable stator vane and an outer casing. A generally annular ring channel is defined in the outer casing. The variable vane assembly further includes a ring segment disposed in the ring channel, and a stem extending from a radially outer end of the variable stator vane at least partially through the ring segment. In another embodiment, a variable vane assembly includes a variable stator vane and a ring segment. The variable vane assembly further includes a stem extending from a radially outer end of the variable stator vane and configured to extend at least partially through the ring segment, and a stem extension configured to couple with the stem and protrude from the ring segment.

Abstract: An aerodynamic blade attachment (1) for a bearingless rotor, particularly a main rotor, of a helicopter, comprising: an airfoil blade (2) having a tip end and a root end and having a pitch axis from said tip end to said root end; a flexbeam (3); a control cuff (4, 22) enclosing and extending along said flexbeam (3) and a separable junction arrangement between said flexbeam (3), said control cuff (4) and said root end of said airfoil blade (2). Said junction arrangement is mechanical between said flexbeam (3), said control cuff (4) and said root end of said airfoil blade (2). Removable fasteners (5, 6) connect said root end of said airfoil blade (2) and said control cuff (4) with said flexbeam (3). Said junction arrangement comprises fairing means (10, 27, 28, 31, 32 and 39) encompass the removable fasteners (5, 6) and said flexbeam (3).

Abstract: An airfoil having active actuators and at least one morphing area allowing shape change of the airfoil and further allowing for optimization of the airfoil shape at more than one operating condition.

Abstract: The present invention relates to a rotorcraft rotor (1) having a plurality of blades (3) movably mounted on a hub (2) via blade roots (4) that are respectively associated therewith. The rotor (1) is fitted with an information capture appliance having at least one measurement assembly (E1) comprising a flexible bar (11) interposed in engagement at its respective ends between the hub (2) and a blade root (4) that is allocated thereto. A strain gauge (7, 8) formed of a SAW transducer is implanted on the bar (11) and generates information relative to the bending of the bar (11) following tilting orientations of the blade root (4) in flapping (B) and/or in lag (T).

Abstract: A device controlling shifting of a propeller turbine engine into reverse mode, by acting on a shaft for controlling pitch of propellers. The device includes: at least one centrifugal weight arranged to drive the propellers into a flag position thereof under action of the centrifugal force; and an actuator that can rotate the control shaft to shift the pitch of the propellers from a traction mode to a reverse mode, passing through a zero pitch position. The centrifugal weight is in an unstable equilibrium position in relation to action of the centrifugal force when the control shaft shifts the pitch of the propellers through the zero pitch position. Further, an actuation mechanism exerts a torque on the control shaft when the centrifugal weight is in the unstable equilibrium position, to prevent it from staying in this position.

Abstract: A rotary system including a yoke having an opening forming a bridge for receiving a spoke extending therethrough. A rotor blade couples to the spoke and a pitch horn positioned outside the opening pitches the rotor blade during flight. A bearing assembly attaches the spoke and the pitch horn to the bridge and control blade forces exerted against the hub assembly during flight.

Abstract: The invention relates to a rotor for a pump, having at least one blade, the rotor being able to be actuated to rotate about an axis of rotation in order to convey a fluid in the axial or radial direction, the rotor being able to be deformed reversibly elastically in the radial direction between a first, radially compressed state and a second, radially expanded state which the rotor adopts without the effect of external forces, and a third state of the rotor being provided in which, in pumping operation under fluid loading, the rotor is deformed from the first state to beyond the second state.

Abstract: The present application includes a main rotor assembly for an aircraft. The rotor assembly has a main rotor mast configured for rotation about a mast axis and two yokes pivotally connected to the mast for rotation therewith about the mast axis. Each yoke is independently pivotable relative to the mast about at least one flap axis that is generally perpendicular to the mast axis. In at least one embodiment, a torque splitter connects the yokes and allows for limited rotation of the yokes relative to each other about the mast axis. Each yoke is configured for the attachment of rotor blades extending generally radially relative to the mast axis.

Abstract: A rotor hub has a yoke with radial arms allowing flapping of connected blades about a flap axis. A grip is rigidly attached to each blade, and a lead-lag bearing connects each grip to one of the arms, the bearing defining a lead-lag axis outboard of the flap axis. Each arm has a pair of straps located on opposite sides of the rotor plane for transferring centrifugal force from the blades to the central portion of the yoke. A pair of lead-lag dampers is provided for each grip, the dampers of each pair being located on opposite sides of the rotor plane and connecting an inboard end portion of the grip to the adjacent strap. In-plane motion of a blade causes rotation of the attached grip about the lead-lag axis, causing opposite motion of an inboard end portion of the grip. The dampers act to oppose rotation of the grip.

Abstract: The catheter device comprises a drive shaft connected to a motor, and a rotor mounted on the drive shaft at the distal end section. The rotor has a frame structure which is formed by a screw-like boundary frame and rotor struts extending radially inwards from the boundary frame. The rotor struts are fastened to the drive shaft by their ends opposite the boundary frame. Between the boundary frame and the drive shaft extends an elastic covering. The frame structure is made of an elastic material such that, after forced compression, the rotor unfolds automatically.

Abstract: A rotor assembly for a wind turbine including at least one blade adapted to automatically adjust its shape as a function of rotational speed to create an efficient fluid dynamic profile over a wide range of wind conditions and rotational speeds. The rotor assembly includes at least one blade configured to respond to rotation induced forces to automatically bend in a manner to optimize its wind profile.

Abstract: The present invention concerns an apparatus for generating a variable or rotating air disturbance with the use of a plurality of filaments controlled by actuators. The filaments are configured to create a movable air disruption that does not require extensive infrastructure to operate and is sufficiently small as to be portable by an individual. The present invention incorporates computer controlled actuators and nozzles to generate programmable air disturbance patterns.

Abstract: A wind turbine blade is configured such that the lift force from the blade airfoil is always normal, or nearly normal, to the shaft torque. This condition maximizes energy conversion. This objective may be achieved by a) having the airfoil chord always aligned to the actual wind direction (subject only to small angle of attack variations), and b) slowing the turbine rotation rate so that no blade twist is needed. As a result, blade tip speed due to shaft rotation is less than the wind speed, and preferably much less. This low tip speed eliminates any hazard to birds. The lift force from the blade airfoil directly drives the torque on the shaft, so the control problem simplifies to adjusting the blade angle of attack to keep the lift constant across varying wind speeds.

Abstract: An airfoil arranged for use in a fluid flow of varying direction relative to the airfoil, has arranged thereon a plural axis hinge for automatic adjustment of the angle of pitch of the airfoil. The airfoil can be applied to a rotary crossflow device for use in a fluid flow of varying apparent flow direction, an oscillating device for use in a fluid flow, a force generation device for use in a fluid flow of varying direction, or a flow control device for use in a fluid flow of alternating direction.

Abstract: A pitch bearing for a wind turbine rotor comprises a rotor hub and at least one rotor blade, the pitch bearing comprising a cylindrical inner bearing ring connectable to a rotor blade of the wind turbine rotor, a cylindrical outer bearing ring connectable to the rotor hub of the wind turbine rotor and an annular reinforcement section for reinforcing the outer bearing ring. The annular reinforcement section adjoins the cylindrical outer bearing ring at its radial outer surface.

Abstract: A series of rings in varying diameters, divided by sets of formed fins arranged in an offset pattern. The offset pattern was inspired by a non-wind apparatus namely a conventional hand cheese grater. Such a pattern has proven to create superior lift, torque, and thus rotation when applied to the Windjet® Turbine Ring. The WindJet® Turbine Ring experiences high revolutions which power hydraulic motors that transfer power into an electrical generation system found at the base of the tower.

Abstract: The invention relates to a bearing unit for a long rotor blade, especially a wind power installation, said bearing unit comprising two annular elements that can be rotated in relation to each other and are directly or indirectly connected to the rotor blade hub and to the rotor blade, and at least two running tracks that can be axially staggered in relation to each other and comprise peripheral rolling bodies with an approximately cylindrical shape, i.e. each comprising a lateral surface that is rotationally symmetrical to a rotational axis in a very precise manner. The aim of the invention is to be able to fully absorb the tipping moment caused by the wind pressure on the rotor blade and on the bearing unit, and optionally to absorb other forces and other moments.

Abstract: A rotor blade assembly includes a rotor blade including one or more pockets and a housing located on the rotor blade within one or more pockets. The housing is secured to the rotor blade via one or more dovetail joints. A drive mechanism for a control surface of a rotor blade includes an actuator and a rocker operably connected to the actuator. At least one hinge rod is operably connected to the rocker and operably connected to a control surface at a control surface pivot. The drive mechanism translates substantially linear motion of the actuator into rotational motion of the control surface about the control surface pivot.

Abstract: A rotor coupling (10) including a first member (12) rotatable about a first axis of rotation (14) and a second member (16), engageable with the first member, and rotatable about a second axis of rotation (18). The rotor coupling (10) further includes at least one torque pin (24) for transmitting torque between the first and second members such that the first and second axes of rotation are allowed to respectively angularly vary during rotation of the rotor coupling.

Abstract: A wind turbine having a plurality of airfoils disposed on the end of spokes which extend from a hub connected to a drive shaft. The airfoils are preferably disposed on an angle of about 40 to about 50 degrees with respect to the plane of rotation of the hub.

Abstract: A method is provided for adjusting a position of a blade ring relative to a rotor in a gas turbine engine. An outer casing surrounds the blade ring and the blade ring surrounds the rotor. The method comprises: determining an amount of vertical movement needed to reposition the blade ring relative to the rotor so that the blade ring is at a desired position relative to the rotor; providing at least one torque pin assembly comprising a torque pin and a variable thickness defining structure; determining a change in the thickness of the variable thickness defining structure so as to effect the necessary vertical movement of the blade ring; changing the thickness of the variable thickness defining structure; and coupling the at least one torque pin assembly to the outer casing such that at least one torque pin engages the blade ring.

Abstract: An apparatus for storing and using wind energy has a hub, blades extending radially outwardly from the hub, a shaft interconnected to the hub, a generator connected to the shaft, a first coupler for coupling and decoupling the shaft from the hub, a first tank having an inlet and an outlet, a second tank having an inlet and an outlet, a line connecting the first tank and the second tank, a second coupler for coupling and decoupling the shaft from the line, an elevated reservoir having a first discharge port and a second discharge port, a base reservoir having a first receiver port and a second receiver port, a pump for pumping a fluid from the base reservoir to the elevated reservoir, a transmission interconnected to the shaft between the line and the generator, and a sheave positioned on a side of the transmission opposite the shaft.

Abstract: A rotor blade for a driven horizontal rotor of a rotary-wing aircraft comprises an elongated main body which includes a leading edge, a trailing edge, and an upper surface extending between the leading edge and the trailing edge. The rotor blade further comprises at least one flap having a front end and a rear end and mounted to the main body at its front end swiveling about a swiveling axis running in parallel to the radial or spanwise axis of the rotor blade. The flap has a basic position in which it lies flat against the upper surface of the main body. Further, the flap is passively swiveled by aerodynamic forces and inertial forces about its swivel axis to raise above the upper surface of the main body, and a reset force acts upon the flap to reset it into its basic position on the surface of the main body.

Abstract: A fixed horizontal axis-mounted wind turbine blade impelled by an independently rotating, pressure cambered fin includes a wind turbine blade comprised of a solid, rigid leading edge and trailing edges. The blade is triangular in shape, the base of the triangular blade is attached to a center, longitudinally fixed, horizontal, primary rotating axis and the point opposite the base is most distant from the horizontal rotating axis. The wind turbine blade base and length are aligned mutually perpendicular to the primary horizontal axis of rotation. A triangular fin is attached to the trailing edge of the blade end most distant from the base. The base of the attached fin is coincident to a secondary axis of rotation. The secondary axis of rotation allows the fin to rotate past either side of the plane of primary blade revolution in response to wind pressure.