Abstract: A variable vane includes a first vane portion and a second vane portion adjacent the first vane portion. The second vane portion includes a trunnion projecting outward from a radial end of the second vane portion. The second vane portion is configured to rotate about a trunnion axis of the trunnion from a first rotational position to a second rotational position.

Abstract: A variable vane includes a first vane portion and a second vane portion adjacent the first vane portion. The second vane portion includes a trunnion projecting outward from a radial end of the second vane portion. The second vane portion is configured to rotate about a trunnion axis of the trunnion from a first rotational position to a second rotational position.

Abstract: The invention relates to turbine engine module (1) including a case (9) rotating around a longitudinal axis (X) and carrying a propeller having a plurality of blades, a stationary case (15) comprising a cylindrical wall (16) extending between an inner wall (17) and an outer wall (18) of the rotating case (9), and a system (26) for changing the pitch of the blades (14) of the propeller. The wall (16) is connected downstream to a first frustoconical wall (42) and upstream to a second frustoconical wall (41), a first rolling bearing (19) being inserted respectively downstream directly between a radially outer face (21) of the inner wall (17) and a radially inner face (23) of the first frustoconical wall, and a second rolling bearing (19?) inserted downstream directly between the radially outer face (21) of the inner wall (17) and an inner face (43) of the second frustoconical wall (41).

Abstract: The present invention is a hair dryer holder system that can automatically control the movements of a hair dryer mounted thereon in a desired distance according to the movements of the hair brush/comb during the hair styling operation. The hair dryer holder system is a computer aided pivoting device having a tracking system to track the movements of the hair brush/comb and pivot means to provide rotation on orthogonal pivot axis (x, y, or z axis), and can be used to allow the hair dryer mounted thereon to rotate with three degrees of freedom. The hair dryer holder system is programmable to align with the movements of the hair brush/comb in a desired distance and angle to achieve an automatic and hands free hair dryer.

Abstract: An adjusting device for adjusting the rotation angle position of the rotor of a wind energy system should be improved by the invention, whereby a complicated processing of the brake disc previously used for engagement of the drive is no longer necessary, and whereby said brake disc can be flexibly arranged in an area with sufficient construction space. For this purpose, the adjusting device has at least one force transducer wheel and/or a force transducing disc which is mounted or can be mounted on a shaft (1) of the drive train which is switched downstream from the rotor, which is structured for engagement of a force transmitting means, and is designed as an independent component. The device also has a drive means for producing a drive force, and at least one force transmission means for transmitting the drive force to the force transducer wheel and/or the force transducing disc.

Abstract: An electric or battery powered fan has Omni-Directional adjustments which include a Single point keyhole Oscillation system that adapts a male end (key) flexible pipe coupled to a female keyhole detent system which is coupled to a spring push pin mechanism which allows for angle adjustments at a specific coefficient of friction, which are adjusted by torque from detent and stop mechanism. The flexible pipe allows for unlimited directional adjustments that withstand repositioning at any direction. Said flexible pipe rotates 360 degrees inside the clamp in both directions on a rotational axis. The clamp design which is a quick release mechanism based on the radius of clamp jaw and lag bolt which allows for a quick release mounting system. It is therefore possible to direct air-flow in infinite variations.

Abstract: The device (27) can be housed coaxially inside a sleeve (25) in which the supplies are situated, and comprises: a hollow cylindrical body (30) that fits inside the sleeve and accepts the mechanism (22) in the housing of the hollow body, with passages (33, 34, 36) for respectively connecting the supplies to said mechanism (22); and a cover (31) which is integrated or fixed, removably, on the front side of the cylindrical body and connects the hidden supplies to the respective passages of the body.

Abstract: A variable transmission is described having a transmission mechanism and a phase adjustment mechanism. The transmission mechanism has supports that are movable toward or away from one another to vary the effective size of an effective cog. The phase adjustment mechanism has a differential type gear arrangement that creates a phase change to adjust the transmission mechanism. Another configuration is described which includes a subassembly with a phase adjustment mechanism for adjusting the pitch of propellers. Counter-rotating elements to control relative gear phase or pitch are provided externally, internally, distally or proximally relative to the source of mechanical torque in various configurations.

Abstract: A turboprop provided with a blade-positioning device including a stationary nacelle, a rotary nacelle including a plurality of blade roots, a turbine, the stationary and rotary nacelles and the turbine being coaxial along a longitudinal axis, a blade positioning device including for each blade a device configured to transform movement suitable for transforming a translation movement into a rotation movement, each one of the device for transforming movement being secured to the rotary nacelle and being suitable for pivoting a blade. The positioning device is placed between the inner surface of the stationary nacelle and the outer surface of the turbine, the positioning device including a member including a body secured to the stationary nacelle and a rod for sliding along an axis substantially parallel to the longitudinal axis.

Abstract: Disclosed is a simultaneous twin pitch adjustment system that includes a flexible shafting cord operatively connected to first and second couplers. The couplers are supported by posts and are operatively connected to pitch communicators. A handle is supported by each post and is configured such that manipulation of the handle translates to adjustment of the pitch of an associated rotor blade assembly. When the simultaneous twin pitch adjustment system is engaged, manipulation of one handle further translates, via the flexible shafting cord, to adjustment of the pitch of another rotor blade assembly in an amount essentially equal to the amount the associated rotor blade assembly is adjusted.

Abstract: A wind turbine blade has one or more trailing edge flaps. An actuator mechanism for the flaps comprises a shaft extending along the blade length driven by a motor arrangement toward the blade root. The flap is connected to the shaft through a linkage so that rotation of the shaft pivots the flap about a hinge line. The linkage may be non-rigid and coupled to the shaft through a roller, or rigid and coupled to the shaft through a crank arm mounted on the shaft. An offset actuation mechanism is provided for imparting movement to the linkage in addition to movement due to rotation of the shaft.

Abstract: Wind turbine having a rotor, a nacelle frame (13) housing with electrical generation means coupled to the rotor hub (11), braking means and control means of the drive train rotational position, the nacelle frame (13) and the rotor hub (11) having an arrangement for preventing the rotor hub (11) rotation when certain maintenance or assembly activities should be carried out, the arrangement including at least one sliding pin (21) in the nacelle (13), first actuating means (31) for pushing/pulling it axially into/from at least one corresponding hole (23) in the rotor hub (11) and means for allowing vertical and lateral adjustment displacements of the sliding pin (21) so that it can remain concentrically aligned with the hole (23) when it is inserted into it.

Abstract: A swash plate assembly includes a rotationally stationary swash plate and rotational swash plate which rotates relative to the rotationally stationary swash plate through a bearing system. Each servo control rod is attached to the swash plate assembly to communicate control inputs thereto through a respective servo lug. Each servo lug defines a servo pivot point off an in-line plane inboard of the bearing system. As the servo lugs extend below the rotationally stationary swash plate, a relatively uncomplicated attachment arrangement is facilitated which provides for redundant locking features at a highly inspectable location which simplifies maintenance and increased safety. By locating the servo pivot point just inboard of the bearing system, an exceeding compact load path is defined thereby.

Abstract: The present invention provides a pitch drive apparatus of a wind generator and the wind generator constituted not to affect a main shaft or a gear box, and capable of preventing reliability from being deteriorated. The pitch drive apparatus includes a wind turbine blade (6) having a base portion (21) mounted so as to be turnable around an axis center L with respect to a rotor head (4), an electric drive member having an output shaft (19) mounted on the rotor head (4) so as to extend in a direction along the axis center (L), a lever (15) having one end fixed to the output shaft (19) and extending in a direction intersecting with the output shaft (19), and a connecting link (17) disposed so as to extend in a direction intersecting with the output shaft (19). One end of the connecting link (17) is rotatably mounted on a free end of the lever (15) and the other end of the connecting link (17) is rotatably mounted on a drive position P of the wind turbine blade (6).

Abstract: A blade-pitch control system has a swashplate configured for continuous rotation with an associated rotor and mast, and at least one link connects the swashplate to each blade of the rotor. The swashplate provides for collective control of the pitch angle of the blades through selective rotation of the swashplate about a swashplate axis while the swashplate is rotating with the rotor and mast. The system can be configured to provide for cyclic control of the pitch angle of the blades through planar translation of the swashplate or through tilting of the swashplate about axes generally perpendicular to the swashplate axis.

Abstract: A rotor system for a rotorcraft includes a rotor having a plurality of pitch control links and a pair of rotor blades mechanically coupled with each of the plurality of pitch control links. A rotorcraft includes a power train, a mast extending from the power train, a rotor having a plurality of pitch control links, the rotor mechanically coupled with the mast, and a pair of rotor blades mechanically coupled with each of the plurality of pitch control links.

Abstract: A back-up featherer for an engine arrangement having a main hydraulic actuator which angularly displaces propellers of a propeller assembly of the engine arrangement, and fluid supply lines for transferring hydraulic fluid between a hydraulic pressure power source located on a static structure of the engine arrangement and the main hydraulic actuator. The back-up featherer has a back-up actuator assembly for angular displacement of the propellers, the back-up actuator assembly rotating with the propeller assembly, a signal detector operatively connected to the back-up actuator assembly and rotates with the propeller assembly, and a back-up rotating coupling. A static side of the back-up rotating coupling is mounted to the static structure of the engine arrangement and communicates with a regulator located on a static structure of the engine arrangement. A rotating side of the back-up hydraulic rotating coupling rotates with the propeller assembly and communicates with the signal detector.

Abstract: An adjusting device for adjusting the rotation angle position of the rotor of a wind energy system should be improved by the invention, whereby a complicated processing of the brake disc previously used for engagement of the drive is no longer necessary, and whereby said brake disc can be flexibly arranged in an area with sufficient construction space. For this purpose, the adjusting device has at least one force transducer wheel and/or a force transducing disc which is mounted or can be mounted on a shaft (1) of the drive train which is switched downstream from the rotor, which is structured for engagement of a force transmitting means, and is designed as an independent component. The device also has a drive means for producing a drive force, and at least one force transmission means for transmitting the drive force to the force transducer wheel and/or the force transducing disc.

Abstract: A device for changing a pitch of a blade of an impeller/propeller is disclosed. It comprises at least one linear actuator. A first bearing is mounted to a non rotary mechanical element with the first portion, and a second bearing is mounted to the second portion, allowing a relative axial movement between the first bearing and second bearing. The first bearing is mounted between a supporting structure of the rotor shaft and the non rotary mechanical element, allowing a relative rotation between the supporting structure and the at least one linear actuator. The second bearing is mounted between the second portion and a lever means having a rotary point at the supporting structure.

Abstract: A variable control rotor hub is provided for harnessing kinetic energy of a water current flow. The hub comprises a hub body that is configured to rotate about a rotational axis, an energy storage reservoir entirely contained in the hub body, and a blade driver that is configured to effectuate rotor blade movement using energy received from the energy storage reservoir.

Abstract: A propeller includes a plurality of propeller blades. Each blade has an adjustable drag coefficient. A plurality of actuators adjusts the drag coefficients of the propeller blades. A controlling unit controls the plurality of actuators such that the drag coefficients of each propeller blade is adjusted according to a pattern that is dependent upon the rotational angle of the particular propeller blade so that the drag of each propeller blade is maximized at the same point through a course of revolution and minimized throughout the remainder of that revolution.

Abstract: Disclosed is a simultaneous twin pitch adjustment system that includes a flexible shafting cord operatively connected to first and second couplers. The couplers are supported by posts and are operatively connected to pitch communicators. A handle is supported by each post and is configured such that manipulation of the handle translates to adjustment of the pitch of an associated rotor blade assembly. When the simultaneous twin pitch adjustment system is engaged, manipulation of one handle further translates, via the flexible shafting cord, to adjustment of the pitch of another rotor blade assembly in an amount essentially equal to the amount the associated rotor blade assembly is adjusted.

Abstract: A turboprop including a rotary casing fitted with adjustable-pitch blades enabling thrust to be managed. Each blade is coupled, for the purpose of adjusting its pitch, to a control member of an annular actuator carried by the rotary casing.

Abstract: A pitch bearing and related method for wind electric turbines has an annularly-shaped first bearing ring connected with an associated wind turbine blade, and includes a first raceway groove. An annularly-shaped second bearing ring is connected with the rotor portion of the wind turbine, and includes a second raceway groove aligned with the first raceway groove. Rolling elements are positioned in the first and second raceway grooves to rotatably interconnect the two bearing rings. A gear segment is formed on one of the bearing rings, and is configured to engage a pitch drive portion of the wind turbine to pivot the blade axially between different pitch angles. The gear segment has an arcuate measure of less than 200 degrees to facilitate economical manufacture.

Abstract: The device for adjusting a rotor blade of a wind energy turbine is provided with a driving device (12) for driving an adjusting element (24) for selectably rotating the rotor blade (26) in both directions about its longitudinal axis (28), an energy storage unit (30) and a free-running means (32) adapted to be selectively activated, said free-running means (32), in its activated state, allowing rotation of the rotor blade (26) by means of energy stored in the energy storage unit (30) only in one of the two directions up to a desired rotational position.

Abstract: A rotor, especially for a rotary-wing aircraft, with a rotor mast and one or more adjustable rotor blades includes a rotor blade adjustment device without a swash plate and arranged on a carrier device that automatically rotates synchronously with the rotor blades, the rotor blade adjustment device rotating along with the carrier device in a manner that is free of relative movement with respect to the carrier device as well as with respect to the rotor mast and the rotor blades. The rotor blade adjustment device includes all of the blade actuators and kinematic elements required for a synchronized, cyclic and collective rotor blade adjustment as well as a control signal interface via which the control signals for the blade actuators can be transmitted from a stationary rotor section to the rotor blade adjustment device that is rotating along. Also, a rotary-wing aircraft, especially a helicopter, including at least one such rotor.

Abstract: An axial fan has a blade support wheel coupled to a drive shaft. A disk is positioned about the drive shaft adjacent the wheel. A torsion spring is coupled to the wheel and to the disk. When the torsion spring is in tension, the disk is poised for a relative rotation about the drive shaft. A lock couples the disk to the wheel when the torsion spring is in tension. Fan blades are supported by the wheel, and are coupled to the disk. Rotation of the drive shaft rotates the fan blades generating a specific flow direction. To reverse the flow direction, a release mechanism uncouples the lock from the disk and wheel causing the disk to experience rotation about the drive shaft as tension in the torsion spring is released. The disk's relative rotation re-positions the fan blades reversing the flow direction as the drive shaft continues to rotate.

Abstract: A fan motor assembly with integrated redundant availability is recited. The fan motor assembly can include a fan motor subassembly with a first fan motor and a second fan motor, and a fan motor selector mechanism coupled to the fan motor subassembly, so that the fan motor selector mechanism selectively couples the first fan motor or second fan motor to a fan. The fan motor assembly can also include a control unit coupled to the fan motor selector mechanism, wherein the control unit is configured to control the fan motor selector mechanism such that either of the first fan motor and second fan motor is selectively engaged to the fan.

Abstract: A wind-driven electric generator of the downwind type has a wind turbine rotor with oppositely disposed flexible blades attached to the hub of a drive shaft by a flexible spar extending from the hub into hollow portions of the blades. The ends of the spar are attached to intermediate regions of the blades by respective ball joints. Each blade has a root-rib with a stub shaft that is slidably supported in a ball joint mounted on the hub. The blades are pitched to a stall position by a collective pitch mechanism in the absence of proper operating conditions. A nacelle cover of the wind turbine defines an airflow path through the head, and an airflow responsive device inside the nacelle cover controls the collective pitch mechanism to place the blades in a stall position or run position depending upon predetermined airflow conditions. A reverse-cone prevention device limits the ability of the blades to cone reversely.

Abstract: A boat propeller has a housing adapted to be fixed to a boat, a hub rotatable about a main axis on the housing, a plurality of generally radially projecting vanes pivotable on the hub, and an operating core shaft coaxially received in the hub, rotatable about the main axis but axially nondisplaceable relative thereto, and having a rear end projecting axially from the hub and a front end. A yoke is fixed to the rear core-shaft end and respective rods fixed to the yoke are connected to the vanes for pivoting the vanes on angular movement of the core shaft about the main axis. A cylinder axially fixed in the housing at the front core-shaft end holds an axially displaceable piston. A nut element having a nonbinding internal screwthread is threaded on a screw element. One of the elements is axially coupled to the piston and the other of the elements is axially coupled to the core-shaft front end.

Abstract: A cycloidal propeller including a so-called slider-crank mechanism. The couplers of the slider-crank mechanism are attached to a control ring which is attached to a ball socket located at the lower end of a control rod. The required torsional retention relative to the rotor housing is accomplished by a dual parallel guide, which is mounted by revolute joint connections to the control ring on one side and by revolute joint connections to the rotor housing on the other side.

Abstract: A propulsion blade retraction and pitch control apparatus includes a hollow primary drive shaft, a pitch control gear assembly mounted, within a propeller hub, to the primary drive shaft, a radially spaced array of pitch control stub shafts mounted to, in co-operation with, the pitch control gear assembly, so as to be selectively rotatable about corresponding pitch control shaft longitudinal axes upon selective actuation of the pitch control gear assembly, propulsion blades pivotally mounted to the pitch control stub shafts at ends of the pitch control stub shafts radially distal from the pitch control gear assembly, one or two coaxial nested pitch control drive shafts, rotatably co-axially journalled so as to be nested within, and co-axial to, the hollow primary drive shaft, said pitch control drive shaft or shafts selectively rotatable to actuate the pitch control gear assembly.

Abstract: A variable-pitch marine propeller system has a propeller unit for mounting on a drive shaft, and a power unit including a stationary annular hydraulic cylinder for operating the propeller unit, a hydraulic remote control unit being fluid-coupled to the power unit. An annular piston of the hydraulic cylinder is coupled to a ring-shaped actuator yoke by a roller thrust bearing, the actuator yoke axially displacing a mating yoke of the propeller unit with which the actuator yoke is allowed to rotate. The piston operates in a sealed environment for the exclusion of water from the separately sealed surfaces of the cylinder itself. In one configuration, the propeller unit is replaceable without disturbing the sealed environment of the annular piston. The control unit includes a hydraulic control cylinder that is operated by a rotatably mounted barrel that engages a threaded piston rod. Alternatively, the control cylinder is actuated by a lever having biasing springs and an adjustable brake.

Abstract: Blade pitch of variable pitch blades is changed by an actuator having first and second ac machines. The first ac machine is excited with ac power to apply a motoring torque to a control shaft of the actuator, thereby causing blade pitch to change in one direction. The second ac machine is excited with appropriate power to apply a braking torque to the control shaft, thereby causing blade pitch to change in an opposite direction. When the second ac machine is an induction machine, dc excitation will brake the control shaft. When the second ac machine is a synchronous machine, an ac excitation causing a retarding magnetic field will brake the control shaft.

Abstract: Pitch adjustment in a feathering propeller employing a planet gear engagement between a pinion hub keyed on the drive shaft and planet pinions at the base of the blades of the propeller which are rotatably mounted through holes of the wall of a hub's casing may be easily performed manually by registering the relative angular position of a second portion of casing in respect to a first portion of the casing housing the planet gear. The registration of the pitch takes place by parting the second portion of casing from the first portion against the resistance of a push-back spring for a distance sufficient to disengage a coupling between the second portion and first portion of the casing or the pinion hub, rotating the second portion so disengaged in respect to the first portion of the casing before releasing the pull causing again the engagement of the two portions in a modified relative angular position.

Abstract: A helicopter blade pitch control system allows blade pitch to be controlled with regard to the degree of rotational position of the blade with respect to the direction of travel and also the degree of pitch. The invention provides an improved arrangement wherein speed paddles attach to rotor blades can change in pitch around the circle of rotation of the blade and also the amount of pitch change can be adjustably changed by the pilot. The apparatus includes a cylindrical member surrounding the rotor of the helicopter and being static with respect thereto so that variable pitch speed paddles connected to and forming a part of the blade assembly and which carry rotating foot members track the upper surface of the cylindrical member changing the pitch of the blade as it moves through a 360 degree rotation.

Abstract: A variable pitch marine propeller comprising two removable symmetrical propeller blades with cylindrical bases each having a drive lug attached proximate the driving edge of the point of attachment of each blade. A coupling are associated with the drive lugs of the bases and structured to hold the blades by the bases to align and simultaneously rotate the pitch of the blades in equal and opposite directions in response to movement of the coupling. A hub sub-assembly encases the coupling and bases of the blades to allow the blades to pivot and assume a forward or rearward pitch. The hub sub-assembly has a front end, and a rear end capable of mounting onto a drive shaft. A spring is associated with the coupling to initially position said coupling in a position which holds the blades in a rear pitch configuration.

Abstract: A filament wound fiber reinforced resin matrix composite structure. The structure is particularly adapted for use as a torque drive diaphragm in a rotary wing aircraft hub. The structure comprises a substantially flat diaphragm and a rim. The diaphragm has a central hole therethrough for receiving a shaft and the rim has an inward turning flange for attachment. The diaphragm has an attachment means surrounding the central hole. An alternative embodiment of the structure is a hollow disc having first and second substantially flat diaphragm sides with a rim. The sides have concentric central holes therethrough and attachment means surrounding the holes. The structure comprises a resin matrix, fibers wound substantially tangentially to the central hole with sufficient tension in a multiple circuit pattern to form the structure, and fibers wound with sufficient tension in an essentially circumferential manner to reinforce the rim of the structure.

Abstract: A mechanical linkage for adjusting propeller blades includes a two-armed lever arranged on the downstream side of the hub of a variable pitch propeller driven by a driving engine by means of a drive shaft. The push rod of a linear motor connected to an energy source moves one arm of said adjusting lever. The other arm of the adjusting lever is articulated to a non-rotatable adjusting sleeve which is coupled via a thrust bearing to a rotary intermediate adjusting member. Adjusting rods are fixed to the intermediate adjusting member and are guided in the hub and accomplish the adjustment of the propeller blades.

Abstract: A filament wound fiber reinforced resin matrix composite structure. The structure is particularly adapted for use as a torque drive diaphragm in a rotary wing aircraft hub. The structure comprises a substantially flat diaphragm, a rim, rim reinforcement fibers and at least one fiber reinforcement ring. The diaphragm has a central attachment means for receiving a shaft and the rim has an attachment means. An alternative embodiment of the structure is a hollow disc having first and second substantially flat diaphragm sides with a connecting rim, rim reinforcement fibers and at least one fiber reinforcing ring for each diaphragm side. The sides have centrally located attachment means.