Abstract: A hydrokinetic energy interface device includes a hydrokinetic wheel and a moveable support structure with an angled frame. The angled frame mounted upon the moveable support structure connects between a hydrokinetic wheel and a counterbalance. A bearing is mounted at a vertex between a first end and a second end of the angled frame. The angled frame pivots to move the hydrokinetic wheel and the counterbalance in opposite vertical direction. The hydrokinetic wheel maintains vertical alignment as the angled frame pivots. The hydrokinetic wheel can be formed with interconnectable rim sections. The hydrokinetic wheel may be cantilevered out away from a riverbank by the counterbalance. The hydrokinetic wheel may be raised or lowered by actuation. The movable support structure supporting the hydrokinetic wheel may be rolled away from a free-flowing river for maintenance, repairs, or modification.

Abstract: A dual rotor propulsion system for a tiltrotor aircraft having VTOL and forward flight modes. The dual rotor propulsion system includes an engine operable to provide an input torque to a transmission that, responsive thereto, generates an output torque. A first output shaft is coupled to the transmission and is operable to receive a first portion of the output torque. A first rotor assembly is coupled to and rotatable with the first output shaft. A second output shaft is coupled to the transmission and is operable to receive a second portion of the output torque. A second rotor assembly is coupled to and rotatable with the second output shaft. In operation, the first and second rotor assemblies rotate coaxially, the first rotor assembly is a different diameter than the second rotor assembly and the first rotor assembly is stoppable and foldable in the forward flight mode.

Abstract: A quad tiltrotor aircraft has a longitudinally extending fuselage with forward and aft stations. A forward wing having first and second outboard ends extends laterally from the forward station. An aft wing having first and second outboard ends extends laterally from the aft station. First and second forward rotors are respectively coupled proximate the first and second outboard ends of the forward wing and are tiltable relative to the forward wing between vertical lift and forward thrust orientations. First and second aft rotors are respectively coupled proximate the first and second outboard ends of the aft wing and are tiltable relative to the aft wing between vertical lift and forward thrust orientations. The forward rotors are higher disk-loading rotors than the aft rotors. The aft rotors are foldable in the forward flight mode to provide extended range for the quad tiltrotor aircraft.

Abstract: The present invention relates to a wind turbine with blade pitch system with an angle between the longitudinal direction of the blade and axis of rotation of the bearing of the blade pitch system, disposing the driving plate of the blade pitch system between the blade and the bearing of the blade pitch system.

Abstract: A system for controlling propeller blade pitch in a turboshaft engine, including: a first track connected to a propeller blade, of which the rotation provides for the setting of the incidence of this blade; a second track; a member actuating the first track, arranged between the first and second tracks, and having a recessed angular portion; and at least one locking member provided between the first and second tracks, housed in the recessed angular portion and in the notch. The locking member can occupy a normal over-center position rendering the first and second tracks integral in rotation, and a release position authorizing the displacement in rotation of a unit including the first track, the locking member, and the actuating member.

Abstract: A system for controlling pitch of a propeller blade of a turboshank engine, including two automatic locking members making it possible, depending on their controlled position, to lock rotation of a blade root in both directions of rotation, or to allow the rotation of the blade root support in either of the two directions.

Abstract: A blade pitch control mechanism for a propeller assembly (10) includes an actuation shaft (24) having a spherical member (28) located at a propeller axis (22). A yoke (40) is located around the spherical member (28) and is rotatable thereon about a yoke tilt axis (62) substantially perpendicular to the propeller axis (22). The yoke (40) includes a plurality of propeller blade attachments (44), each receptive of a propeller blade (14). The plurality of blade attachments (44) are configured such that rotation of the yoke (40) about the yoke tilt axis (62) results in rotation of each propeller blade (14) about a blade pitch change axis (48).

Abstract: A system (10) having a control plate (15) for controlling the pitch of the blades (5) of a propeller, a power block (20), and a directional control valve (30) for feeding said power block (20) with fluid. The power block (20) is sealed and includes at least a body in which at least one piston (22) that is secured to a piston rod (25) projecting from said body (21) is movable in translation, a repeater rod (50) connecting said piston rod (25) to said control plate (15). The control valve (30) is sealed and comprises a stationary manifold (35) and a movable manifold (40) that is movable in rotation, said stationary manifold (35) being controlled by a control lever (31) connected by repeater means (32) to said repeater rod (50). A respective pipe (60) connects each chamber (23, 24) of said power block (20) to said movable manifold (40).

Abstract: A dual direction axial fan is provided and includes a body having a retention assembly and being rotatable in first or second directions, a blade being retained by the retention assembly such that the airfoil section extends from the body with the blade assuming first, second or third orientations and a switching mechanism coupled to the retention assembly to urge the blade to assume the second or the third orientation when the body rotates in the first or the second direction, respectively.

Abstract: An anti-torque mechanism which permits a full range of swashplate assembly motion. The anti-torque mechanism generally includes an anti-torque shaft and a compound bearing mounted thereto to provide five-degrees-of-freedom (spherical-linear-elastomeric) so as to permit a swashplate attachment point to move axially in response to pitch input; pivot in response to swashplate tilt; and move in/out in the radial direction.

Abstract: A ram air turbine with a strut that is pivotable through a pivot plane about a pivot point on the strut from a generally horizontal rearward rest position to a generally vertical central operating position comprises at least one movable brace that extends between a stationary brace mounting point and a brace support point on the strut below the pivot point.

Abstract: A frame for supporting equipment arranged in a hub of a wind turbine is fixed to the hub at one end and flexibly connected to the hub at another end. The variation of the relative position between the hub and the frame caused by the deformation of the hub associated with a rotation of the wind turbine or the like is absorbed by the flexible connection. A wind turbine whose frame in the hub has high durability against the rotation can be provided.

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: A wind turbine comprising a tower and a nacelle which is rotatably mounted on the tower and whose alignment is adjustable by means of a yaw system, wherein the yaw system has at least one adjusting drive, a rotatable yaw bearing, at least one brake disk and at least two brake units which can exert a braking torque on the brake disk, wherein the at least one of the brake units has a first brake pad with a first coefficient of friction, and at least one of the brake units has a second brake pad with a second coefficient of friction, wherein the first and the second coefficient of friction are different from each other.

Abstract: It discloses a wind turbine blade bearing that makes it possible to avoid the collision of the blade with the wind turbine tower by providing a separation thereof via the disposal of the blades at an angle with respect to the wind turbine hub; where said angle is given by the bearing of the blade pitch change system.

Abstract: A propulsive thrust device for an engine includes a rotor blade and a hub assembly on which the rotor blade is mounted. The rotor blade comprises an airfoil and at least two support members. A propeller thrust device includes a rotor blade, a central hub at which the rotor blade centrifugal load is supported, and an outer hub supporting a control mechanism mechanically connected to the rotor blade and controllable to vary the pitch of the rotor blade on the central hub. A rotor blade for an aircraft engine or in a separate ducted fan housing driven by a powered shaft or gearbox output shaft includes an airfoil and first and second support members attached to the airfoil. An extended arm or portion of the structure at the root of the airfoil of each blade is attached to a controllable mechanism that can vary the pitch of all blades simultaneously.

Abstract: The present invention relates to an adjustment device for adjusting the pitch angle of the propeller blades (4) of a propeller pump (1) and a propeller pump incorporating such a device.

Abstract: A self-guiding wind turbine made of two reinforced parallel girders whose side center of thrust is displaced from the column axis where it is supported and turns. Its dihedral-shaped two-bladed rotor is self-stabilizing since its center of thrust is behind its center of gravity and the guiding axis of the turbine, thus improving self-guiding whilst in motion. The axial thrust is controlled, whilst the head and rotor are tilting, hydraulically by counter-pressure, ensuring they do not surpass the power collected and the moments on the structure, shoe and ground. The self-guiding structure can tilt hydraulically lowering its head and rotor and facilitating its assembly and maintenance, and can remain “asleep” when not in use, thus reducing the visual impact on the environment. This turbine makes use of the force of the wind to control itself, simplifying the manufacture of large turbines connected to the network or in isolated applications.

Abstract: A portable electric fan includes a rechargeable battery disposed in the bottom portion of a housing for storing and for supplying electric power. An opening is formed in the front portion of the housing for receiving a fan device, the fan device includes two shafts rotatably secured to the housing and each having a number of notches formed in the outer peripheral portion. Two resilient devices are engaged with the notches of the shafts so as to retain the fan device in suitable positions.

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: The invention relates to a propeller assembly, particularly suitable for use with axial flow pumps. The propeller assembly is provided with a cam-operated rotatable propeller blade compression shaft which rotates in response to a detected increase load on the propeller blade. An elongated rod connected to a power source transmits movement to a spring which, in turn, transmits the movement to the cam. To accommodate tilting of the propeller blade during changing of the pitch, a hub outer surface is formed convex and the inner surface of the enclosing shroud is formed concave. The radii of curvature of the hub and the shroud are generally complementary to the radius of curvature of the inner and outer surfaces of the propeller blade, respectively.

Abstract: The invention relates to a boat propeller having rotatably journalled blades in its hub to enable shifting between forward and reverse without reversing the direction of rotation. The hub is rotatably journalled on the propeller shaft and contains a transmission between the shaft and the blades. The transmission can be coupled between positions for forward, reverse and neutral. The invention uses the torque of the motor and the reaction moment of the water against the blades to achieve a relative rotation between the shaft and the hub, whereby the transmission turns the blades to one of two stops, which define the positions for forward or reverse.

Abstract: An aircraft forwardly propelled by a power plant including a pair of jet engines, is operated in a VTOL mode by powered rotation of a rotary wing mechanically rotoring the engines. When unloaded during fixed wing flight, the power plant is operated in an accelerating rocket mode preceding high speed ram jet operation. Radially extensible blades of the rotary wing vary the mechanical loading on the engines while adjustable chokes at the intake of each engine and in the outlet of a common after-burner for the engines, condition the power plant for its different operational modes.