Abstract: Marine propellers for coupling to a propeller drive shaft may include a propeller hub. A plurality of propeller blades may extend from the propeller hub. A shearable drive assembly may include a drive core. The drive core may include a drive core wall configured to be drivingly engaged by the propeller drive shaft. At least one drive rib may extend from the drive core wall. At least one shear cavity may be provided in the at least one drive rib. A drive sleeve may be drivingly engaged for rotation by the drive core and configured to drivingly engage the propeller hub of the marine propeller for rotation. The drive sleeve may have at least one rib slot receiving the at least one drive rib of the drive core. Other marine propellers with shearable drive assemblies are also disclosed.

Abstract: A wind turbine rotor blade assembly which incorporates automatic-aerodynamic control of the blade pitch angle is disclosed. The airfoil of the rotor blade (110) is free to rotate about a strategically located longitudinal blade axis which forms the spar stub (115) and is connected to the hub (120) of a horizontal axis wind turbine. The location of this blade axis is precisely set with respect to the turbine blade's aerodynamic center and center of mass. By further incorporating a reflexed airfoil with positive pitching moment this arrangement aerodynamically induces an automatic and self-regulating alignment of the rotor blade pitch such that the airfoil is always operating at or near optimal angle of attack. Details are disclosed on these strategic relationships which enable the successful operation of the new blade design.

Abstract: A motor assembly having a rotational axis includes a motor housing comprising a plurality of cooling openings extending therethrough and defining a chamber. The motor assembly also includes a stator fixedly coupled to the motor housing and positioned within the chamber. A rotor is coupled to at least one of the motor housing and the stator, wherein the rotor is configured to rotate about the axis and is positioned within the chamber. The motor assembly includes a fan having a first inlet side on a first axial side of the fan and a second inlet side on a second, opposing, axial side of the fan. The fan is configured to draw cooling air in a first direction through the at least one cooling opening into the first inlet side, and the fan is also configured to draw cooling air in a second, opposite direction into the second inlet side.

Abstract: Aircraft capable of vertical takeoff and landing, hovering, and efficient forward flight are described. An aircraft includes two side mounted tiltable proprotors and a central rotor disposed above the proprotors. The proprotors are tiltable between at least a horizontal position for forward flight and a vertical position for vertical or hovering flight. The central rotor may be powered for vertical and transitional flight modes and may turn by free autorotation during forward flight. The proprotors may be differentially tilted during vertical or hovering flight to counter torque effects of the central rotor. The central rotor may be foldable and/or easily detachable from the aircraft to facilitate storage and transportation. Left and right proprotors may provide both forward thrust and attitude control. Control inputs to left and right proprotors may be connected directly to an autopilot creating closed loop actuation using motor RPM feedback.

Abstract: A vertical shaft wind turbine that is superior in a rotational startability, even at a low wind speed, and is suited to a wind power generator that has high rotational torque. Each blade is an upper-and-lower-ends fixed type vertically long blade which is suitable for use as a wind turbine or a water turbine. The string length and thickness of an upper-and-lower-ends fixed type vertically long blade (8) that is fixed upper and lower ends to a vertical main shaft (7) gradually decrease from a main part (8) thereof to tips of the upper and lower inwardly curved inclined parts (8B, 8B), and a cross section of the main part (8A) is a lift type. A thickness of the cross-sectional shape is continuously and gradually thins from the main part (8) to the tips of the inwardly curved inclined parts (8B, 8B).

Abstract: A fan wheel for a fan is equipped with at least two fan blades with a wavy design. A fan has at least one such fan wheel. A system has at least one fan with such a fan wheel.

Abstract: The invention relates to a vane (7) comprising: a structure made of composite material, a vane (7) root (16) attachment (9) comprising a base having a radial outer face (20) and in which a slot (24) configured to receive the vane (7) root (16) is formed and two platforms (26), extending on either side of the blade (18) opposite the radial outer face (20), and two stiffening parts (30), added and fixed on the radial outer face (20) on either side of the stilt (17) so as to tightly abut against the stilt (17).

Abstract: A blade of a turbomachine includes a blade body of composite material having a fiber reinforcement having a three-dimensional weave and densified by a matrix, the reinforcement having a first part extended by a second, end, part including two segments separated from each other; and an insert having a pi-shaped section, the insert having a platform part and two longitudinal flanges separated from each other, the platform part including a housing delimited by a bottom wall and a rim, the bottom wall including an opening communicating with the space between the two flanges, the first part of the fiber reinforcement being clamped between the two flanges of the insert, the segments of the second part of the fiber reinforcement being folded against the bottom wall of the housing.

Abstract: A variable pitch blade holder for use with a gas turbine engine. The variable pitch blade holder is configured to retain a blade and to rotate about a center axis with the blade during operation of the gas turbine engine. The blade holder is adapted to rotate about a pitch change axis to vary a pitch of the blade.

Abstract: A rotor assembly includes a yoke operably associated with a rotor blade. The yoke includes a first device and a second device that attach the rotor blade to the yoke. The first device is configured to allow transverse movement of the rotor blade about a chord axis and rotational movement about a pitch-change axis. The second device is configured to allow rotational movement of the rotor blade solely about the pitch-change axis. The method includes rotating rotor assembly about a first plane of rotation, while retaining a relatively stiff out-of-plane rotation and a relatively soft in-plane rotation during flight.

Abstract: A damper pin for damping adjacent turbine blades coupled to a rotor shaft includes a first end portion that is axially aligned with and axially spaced from a second end portion and a retention pin that is coaxially aligned with and disposed between the first end portion and the second end portion. The retention pin couples the first end portion to the second end portion. The damper pin further includes a plurality of rings coaxially aligned with and disposed along the retention pin between the first end portion and the second end portion. The first end portion, the second end portion and the plurality of rings define a generally arcuate outer surface of the damper pin that is configured to contact with a groove defined between the adjacent turbine blades.

Abstract: A wind-driven power generating system with a hybrid wind turbine mounted on a floating platform that heels relative to horizontal in the presence of a prevailing wind. The hybrid turbine has a turbine rotor with at least two rotor blades, each mounted to a turbine shaft by at least one strut, and the system is configured so that the shaft forms a predetermined non-zero operating heel angle relative to vertical in the presence of a prevailing wind at a predetermined velocity. The blades and struts are airfoils with predetermined aerodynamic characteristics that generate lift forces with components in the direction of rotation around the shaft of the blades and struts at the operating heel angle to drive an electrical generator carried by the platform. The system can be designed to generate maximum power at the predetermined heel angle or essentially constant power over a range of heel angles.

Abstract: An aerial vehicle may be equipped with propellers having reconfigurable geometries. Such propellers may have blade tips or other features that may be adjusted or reconfigured while the aerial vehicle is operating, on any basis. Propellers having reconfigurable blade tips joined to blade roots may cause the blade tips to be aligned with the blade roots, or substantially perpendicular to the blade roots, e.g., in order to counter adverse effects of tip vortices, or at any intervening angle. The propellers may be reconfigured at predetermined times during operation of an aerial vehicle, or upon sensing one or more operational characteristics or environmental conditions, as may be desired or required.

Abstract: A composite blade assembly and a method of assembling a composite blade are provided. The composite blade assembly includes a composite blade having a radially inner root. A composite blade assembly includes a first platform and a circumferentially adjacent second platform abutting the first platform at a platform joint. Each of the first platform and the second platform includes a radially outer surface and a radially inwardly extending attachment member. The platform joint includes a slot extending through adjacent edges of the first platform and the second platform. The slot is configured to receive the radially inner root and the radially inner root is configured to be sandwiched between the attachment members. The blade assembly includes an adhesive system configured to join the radially inner root of the composite blade and the attachment members into a unitary structure, and a retaining clip configured to bias the attachment members towards each other.

Abstract: A gas turbine engine, a fan section for a gas turbine engine, and a method for assembling a fan section of a gas turbine engine are disclosed. The fan section may include a fan hub having a slot, a spinner having a castellated spinner seal, a fan blade including an airfoil extending from a root to a tip, wherein the airfoil has a leading edge and the root is received in the slot, and a platform secured to the fan hub and arranged between adjacent fan blades. The fan section may further include a flap seal having a base secured to a side of the platform, and a flap integral with and extending from the base portion and canted toward the root and engaging the blade, the seal trimmed back from the leading edge of the airfoil.

Abstract: A fan is provided. The fan may comprise a fan blade and a blade platform coupled to the fan blade. The blade platform may be a thermoplastic. A fan blade platform is also provided. The fan blade platform may comprise a first platform half comprising a slot at a first end of the first platform half and a first receiving member at a second end of the first platform half opposite the first end of the first platform half. A second platform half may comprise a hook. The second platform half may also include a second receiving member at a second end of the second platform half opposite the first end of the second platform half with the hook configured to interface with the slot. A pin may be configured to pass through the first receiving member and the second receiving member.

Abstract: A turbine arrangement is provided, particularly a gas turbine arrangement, having at least one rotor blade and a turbine disc, the rotor blade having a root portion, the turbine disc having at least one slot in which the root portion of the rotor blade is secured. The slot has a plurality of opposite pairs of slot lobes and a plurality of opposite pairs of slot fillets, and a slot bottom of the slot. The slot bottom is arranged to have a first convex surface section. Furthermore the root portion of the rotor blade has a root bottom with a first concave surface section corresponding to the first convex surface section of the slot bottom. Additionally, the first convex surface section is pierced by an outlet of a cooling duct through the turbine disc.

Abstract: An apparatus comprising a soft in plane rotor yoke comprising two longitudinal side portions connected together via two outboard portions, wherein the outboard portions comprise a plurality of first layers formed of a first composite fabric material having a plurality of first fibers oriented in a first direction, and a plurality of second layers formed of a second composite fabric material having a plurality of second fibers oriented in a second direction. Included is an apparatus comprising a soft in plane rotor comprising two longitudinal side portions connected together via two outboard portions, wherein the outboard portions comprise a plurality of first layers formed of a first composite fabric material, and a plurality of second layers formed of a second composite fabric material, wherein the soft in plane rotor yoke does not comprise any narrow steered slit tape or filament windings.

Abstract: A helicopter main rotor control system includes a trunnion head mountable to a rotatable helicopter mast wherein the trunnion head has a control bar pivot supported by the trunnion head and pivotal about an axis substantially at a right angle to the helicopter mast. A control bar extends through the control bar pivot at a right angle thereto, and a pair of opposing leaf hinges are pivotal about the control bar and centered about said trunnion head. Each leaf hinge has a hinge plate extending from the control bar and defines a rotor blade mount hole therethrough.

Abstract: A composite flexure that secures a rotor blade to a gimbaled yoke in a tiltrotor rotor system. The composite flexure includes a composite flexure member, a first end, and a second end. The first end of the composite flexure couples the composite flexure to the gimbaled yoke, and the second end of the composite flexure couples the composite flexure to the rotor blade. The composite flexure is twisted when the composite flexure is not subject to torsional loads in order to accommodate various forces imparted on the rotor system.

Abstract: A method of making a platform of a blade includes the steps of creating two platform sections by solidifying a material with a fabric in a mold and positioning a band of fabric around the two platform sections to retain an airfoil and define a blade. The method further includes the step of bonding the two platform sections together by solidifying the material to define a platform of a solid material. The platform is not bonded to the airfoil.

Abstract: A windmill is disclosed having over speed protection. In a preferred embodiment, the vanes are symmetric, curved metal sheets, with each vane's shape having a circular arc corresponding to its portion of the cylindrical support structure. Each vane is mounted with a large leading portion exposed to the wind. The imbalance of surface area causes the wind to push the vane open when moving downwind and push the vane closed when moving upwind. During periods of high rotational speed, the off-axis centers of mass cause each vane to rotate towards a closed position under centrifugal force. Once the critical speed is reached, the vanes fully close as they pass through the upwind side.

Abstract: A pitch bearing assembly for a wind turbine having a stiffener is disclosed. The pitch bearing assembly may include an outer race and an inner race rotatable relative to the outer race. The inner race may define a mounting surface and an inner circumference. The mounting surface may extend generally perpendicular to the inner circumference. In addition, the stiffener may include a body and a mounting flange. The body may extend axially within a volume defined by the inner circumference of the inner race. Further, the mounting flange of the stiffener may be coupled to the mounting surface of the inner race.

Abstract: A rotor assembly for a wind turbine includes a hub adapted to be carried by a shaft of the wind turbine, a plurality of prop arms extending from the hub, a plurality of blades carried by the plurality of prop arms, and a rotor speed regulating mechanism adapted to alter a pitch of the plurality of blades responsive to varying wind speeds, thereby regulating the speed of the plurality of blades.

Abstract: A hub assembly for a tilt rotor includes a yoke having a plurality of yoke arms located substantially orthogonal to a central axis of the hub assembly. An inboard pitch change bearing assembly substantially surrounds a yoke arm of the plurality of yoke arms. An outboard pitch change bearing assembly is located at the yoke arm. The inboard pitch change bearing assembly and the outboard pitch change bearing assembly are operably connectable with a rotor blade to allow pitch change of the rotor blade relative to the yoke about a pitch change axis.

Abstract: A system for damping vibrations in a turbine includes a first rotating blade having a first ceramic airfoil, a first ceramic platform connected to the first ceramic airfoil, and a first root connected to the first ceramic platform. A second rotating blade adjacent to the first rotating blade includes a second ceramic airfoil, a second ceramic platform connected to the second ceramic airfoil, and a second root connected to the second ceramic platform. A non-metallic platform damper has a first position in simultaneous contact with the first and second ceramic platforms.

Abstract: A pumping apparatus comprises a rotatable shaft coupled to a motor. At least one control structure is mounted on the shaft, and at least one impeller is carried by the shaft. The impeller is adapted to rotate independently of the shaft so as to pump a fluid. The apparatus also comprises a magnetic coupling between the control structure and the impeller. Further, the impeller is adapted to translate axially along the shaft in response to a change in downstream pressure to alter the strength of the magnetic coupling.

Abstract: According to one embodiment, a rotor system comprises a yoke, a grip, an elastomeric bearing, and a bearing restraint. The grip is positioned around a portion of the yoke and has both a closed end and an open end. The elastomeric bearing is coupled to the closed end of the grip and located between the closed end and the yoke. The bearing restraint is coupled to the grip between the yoke and the open end at a distance from the closed end such that the yoke contacts the bearing restraint when the rotor system is subject to a first centrifugal force but does not contact the bearing restraint when the rotor system is subject to a second centrifugal force greater than the first centrifugal force.

Abstract: An electrical submersible pump can include a housing with a head and a base; a shaft arranged for rotation within the housing; an impeller stack that includes ceramic impellers mounted along the shaft; a diffuser stack that includes diffusers disposed within the housing; and a spring sleeve that includes axially spaced and overlapping tangential slots, the spring sleeve mounted along the shaft to apply a compressive force between the shaft and the impeller stack. Various other devices, systems, methods, etc., are also disclosed.

Abstract: A present invention's object is to maintain a discharge performance by making a discharge flow rate constant in a low rotation region of an engine rotation speed and to reduce the discharge flow rate in a high rotation region. The present invention consists of a housing case, an impeller base provided with plural holes and plural elliptical elongated holes, a vane body provided with a rotary shaft on an inner peripheral side and a rocking shaft on an outer peripheral side, a plate cam in which an elongated groove is formed on an outer peripheral side of a disc portion and a single torsion spring. The spring and the plate cam are housed in the housing case and the impeller base. The rotary shaft is inserted rotatably into the holes, and the rocking shaft is movably inserted into the elliptical elongated holes and the elongated groove.

Abstract: A damper unit includes a first damper arranged to transmit a torque around a rotation axis transmitted from an input member side to an output member side, an intermediate member arranged to transmit a torque around the rotation axis transmitted from the first damper to the output member side, and a second damper arranged to transmit a torque around the rotation axis transmitted from the intermediate member to the output member side, wherein at least a portion of the second damper is disposed on a straight line that passes through the first damper and is parallel or substantially parallel to the rotation axis.

Abstract: A resilient hub assembly comprises a top plate, bottom plate, central hub, and outer spars. The central hub is coupled between the top plate and the bottom plate. The outer spars are coupled between the top plate and the bottom plate, and the outer spars are positioned in a circular arrangement about a common longitudinal axis of the top plate and the bottom plate. The resilient hub assembly is configured to be flexible. The top plate and/or the bottom plate may comprise cutouts, and/or the outer spars may be positioned as to allow a gap between the central hub and the outer spars to promote flexibility.

Abstract: A rotor hub and method to dampen a force exerted on a rotor hub by a rotor blade during flight. The rotor hub including a central member rotatably coupled to a rotor mast, a blade grip rigidly attached to a blade and movably coupled to the central member, and an adjustable damper operably associated with the blade grip. The method includes damping the force exerted on the rotor hub with the adjustable damper and selectively adjusting the adjustable damper between a first spring rate and a second spring rate.

Abstract: A sculpted throat spool of a tension-torsion strap assembly is disclosed. Using the sculpted throat spool minimizes the stress riser typically present at the edge of the spool when a tension-torsion strap is articulated.

Abstract: A prestressing device extending about an axis between a first plane and a second plane, the first plane being located at a predetermined distance from the second plane, each plane being perpendicular to the axis. The device includes at least three deformation areas. The deformation areas extend in the first plane. The device further includes, between each deformation area, a planar contact surface extending in the second plane.

Abstract: This invention uses a novel shape of airfoil to achieve an improved lift to drag ratio and to improve performance at higher angles of attack. The airfoil has a three dimensional wave pattern that modifies the shape of a traditional airfoil to coordinate the airflow through channels on both the top and bottom sides. The uniquely shaped airfoil of this invention could have many uses including a wind turbine blade. This invention not only provides for a more efficient device by improving the effective angle of attack and lift/drag ratio, but also provides for a quiet airflow thus greatly reducing nuisance noise over conventional devices.

Abstract: A method for connecting a tension-torsion strap. The method includes sliding a sleeve into an arm of a hub; aligning holes in the sleeve with holes in the hub; installing a bushing in each aligned hole in the sleeve; sliding a first end of the tension-torsion strap through the sleeve; and placing a pin through the bushings and the tension-torsion strap.

Abstract: A fan includes an impeller and a fan frame. The impeller is accommodated within the fan frame. The impeller has a hub and a plurality of blades disposed around the hub. The hub has a top portion and a side wall connected with the top portion. The hub further has a plurality of flexible portions disposed and located on the side wall. The blades are connected with the flexible portions, respectively, so that the blades are connected to the hub.

Abstract: The present invention relates to a damper (10) provided with an inner end strength member (20) and an outer end strength member (30) that are tubular and coaxial, a return member (40) being arranged between the inner end strength member (20) and the outer end strength member (30). The return member (40) includes an intermediate strength member (43) coaxial with the inner and outer end strength members (20, 30), said return member (40) having first and second return means (41, 42), said first return means (41) being arranged between the outer end strength member (30) and said intermediate strength member (43), said second return means (42) being arranged between the inner end strength member (20) and said intermediate strength member (43).

Abstract: A wind turbine for use in a wide range of wind conditions is disclosed. The wind turbine uses blade pitch change and/or blade folding to accommodate wind conditions and maintain a substantially constant speed. The blades are configured to fold in unison for balanced wind turbine operation.

Abstract: A wind turbine includes a plurality of rotor blades, with each blade having a root portion connected to a rotor hub and an airfoil portion extending radially outward from the rotor hub. The airfoil portion further includes a main foil section and a winglet pivotally connected to the main foil section so as to pivot from an in-line position wherein the rotor blade has a first sweep length to an articulated position wherein the rotor blade has a second sweep length. In the articulated position, the winglet may pivot to not more than 90 degrees relative to a longitudinal axis of the main foil section. A deployable sleeve may be connected to the winglet so as to extend between the winglet and the main foil section in the articulated position of the winglet. The sleeve is stowable within either or both of the main foil section or the winglet in the in-line position of the winglet.

Abstract: The present teachings relate to a fluid mechanical converter having at least one energy-accumulator mass system that can be powered by a power drive. To provide a fluid mechanical converter, which improves overall efficiency using the simplest components, it is proposed according to the present teachings that the displacement of the driven energy accumulator-mass system is overlaid with a displacement that is caused by at least one inertial force.

Abstract: There is described a rotor for a helicopter, having a hub rotating about a first axis; a number of blades projecting from the hub in respective longitudinal directions lying in a plane crosswise to the first axis, and each connected to the hub so as to be movable at least about a second axis crosswise to the first axis and to the relative longitudinal direction; and a number of damping devices for damping vibration of the helicopter, each interposed between a respective blade and the hub; each damping device has a plate member fixed, on one side, to the hub, elastically connected, on the opposite side, to the relative blade, and flexible, during movement of the blade, about a third axis coaxial with the second axis.

Abstract: A helicopter rotor include a blade, a rotor hub which supports the blade, and a lead-lag angle mechanism configured to change a lead-lag angle of the blade, in synchronization with a rotation of the rotor hub. The lead-lag angle mechanism changes the lead-lag angle of the blade such that a circumferential speed of a blade tip of the blade (3) is slow on a forward side and fast on a backward side. Accordingly, a helicopter, a helicopter rotor, and a control method of helicopter that enable high speed flight are provided.

Abstract: An assembly for providing flexure to a blade of a rotary blade system includes an upper support plate having an upper curved surface, a lower support plate having a lower curved surface, and a yoke positioned therebetween. At least one of the upper and lower yoke surfaces has a layer of cushioning material positioned thereon and secured thereto. An alternate embodiment includes an assembly for providing flexure to a blade of a rotary blade system, including, an upper support plate having an upper curved surface, a lower support plate having a lower curved surface, and a yoke positioned therebetween and directly contacting the support plates wherein one of the curved surfaces is a non-circular arc that does not form part of the circumference of a circle. Another alternate embodiment includes a similar assembly having a twist-shank type of yoke for providing rotation of attached blades about their respective pitch axes.

Abstract: An airborne centrifugally stiffened and cyclically controlled system which uses airfoils which rotate around a central hub, similar to the mechanics of an autogyro. The airfoils may achieve speeds significantly above the wind speed feeding the system. The airfoils may be linked to the central hub by flexible radial tethers which stiffen considerably as the speed of the airfoil increases, or may be linked to the central hub by rigid radial links. The central hub may be linked to the ground with an extendible main tether. Power generation turbines may reside on the airfoils and utilize the high apparent wind speed for power generation. The generated power may travel down the radial tethers and across a rotating power conduit to the main tether and to the ground. The system may use autorotation, similar to the mechanics of an autogyro.

Abstract: A rotor for a helicopter, having a drive shaft rotating about a first axis; a hub angularly integral with the drive shaft about the first axis; and at least two blades projecting from the hub on opposite sides of the first axis and elongated along respective second axes crosswise to the first axis; each blade is movable with respect to the hub and to the other blade about a respective third axis crosswise to the respective second axis; the rotor has at least two dampers for damping oscillation of respective blades about the respective third axes, and which have respective first portions movable integrally with the respective blades about the respective third axes; and the dampers have respective second portions connected elastically to the respective first portions and functionally to each other.

Abstract: Rotor apparatus and methods for vertical lift aircraft are disclosed. In one embodiment, a bearing assembly adapted for rotatably coupling a rotor blade to a support member includes an inner housing annularly disposed about a portion of the support member, an outer housing annularly disposed about at least part of the inner housing and is rotatably coupled to the inner housing by an annular bearing device, and a flexible member adapted to be coupled to the support member and including an engagement portion adapted to engage the outer housing and to at least partially relax a side force exerted on the annular bearing device by a bending of at least one of the rotor blade and the support member.

Abstract: Described herein is a rigid rotor assembly configured to allow rotation of helicopter rotor blades attached to the rigid rotor assembly from a deployed position to a stowed position. The rigid rotor assembly includes a base including a shaft extending therethrough, a first spindle configured to engage the shaft, and a second spindle configured for placement onto the shaft. The second spindle is operable to maintain a first position with respect to the first spindle via an attachment mechanism therebetween, the second spindle further operable to maintain a second position with respect to the first spindle via the attachment mechanism.

Abstract: An apparatus may comprise a housing, a first member, and a second member. The housing may have a first end, a second end, a first side, a second side, an opening located in the first end, and a passage extending from the opening. The first member may extend from the first side. The first member may have a first channel in communication with the passage and the channel has a first center axis. The second member may extend from the first side. The second member may have a second channel in communication with the passage and the second channel has a second center axis substantially aligned with the center axis of the channel in the first member.