Abstract: Fan module with variable-pitch blades for a propulsion system that includes: a rotor supporting the blades, and including an internal shaft and an external shroud, defining between them a space; a pitch control device (22) of the blades that includes a load transfer bearing; a feathering device of the blades; said feathering device includes at least one lever that is articulated around a fixed axis (A) in relation to the rotor, where said lever features a first end located outside said space and a second end located inside said space, and where a flyweight is fastened to the first end and the second end is coupled to said bearing.

Abstract: The present invention relates to a hydraulic device of reversible type adapted to be used both as a water turbine and a hydraulic pump. Said device has characteristics of simplicity of construction and use. In the case of use as a water turbine it does not require distributors of a particular shape and does not require drops of great heights being adapted to take advantage of the pressure of the fluid and not only of the speed thereof.

Abstract: A proportional moving air power transmission and energy collection and control system includes a fixed vertical spindle, a vertical rotational hub and a plurality of wings being supported around the vertical hub in 360°. Each of the wings has a blunt leading end and a pointy trailing end and defining an outer surface and an inner surface. In a fully opened position, the trailing end of each wing is moved away from the vertical hub to a diameter of the wing assembly to drive the vertical hub to rotate. In a fully closed position, the wings are overlapped with each other end-to-end to form a hollow cylinder-like structure to furl, such that the diameter of the wing assembly is minimized for facing the wind at all direction.

Abstract: An apparatus comprising: a frame; a shaft mounted to the frame for rotation; plural vanes each mounted for rotation about a respective pitch adjustment axis on one or more respective arms extending from the shaft; a collar mounted to the frame coaxial with the shaft, the collar having a first outer circumferential surface defining a convex cam shape, and a second outer circumferential surface defining a non cam circular shape; and plural followers arranged to contact the first outer circumferential surface in a first configuration corresponding to a first speed of rotation of the shaft and the second outer circumferential surface in a second configuration corresponding to a second speed of rotation of the shaft, the second speed being higher than the first speed, the plural followers being each connected to adjust the pitch of a respective vane of the plural vanes.

Abstract: A pitch control assembly for a vertical axis wind turbine provides greater efficiency to the vertical axis wind turbine. The pitch control assembly comprises a pitch control assembly housing mechanically coupled to a first stop bar, a second stop bar and a cushion mass. The pitch control assembly housing is mechanically coupled to a pitch control assembly bottom plate where the pitch control assembly bottom plate is mechanically coupled to a dampening spring. The dampening spring is mechanically coupled to a blade control plate, where the blade control plate is mechanically coupled to a first blade control pusher bar, a second blade control pusher bar and a blade control plate stem. A heavier mass and a lighter mass rest upon the blade control plate; the blade control plate stem is mechanically coupled to a vertical axis, which is used in the vertical axis wind turbine.

Abstract: A Ram Air Turbine (RAT) is provided and includes a turbine hub having an end plate and a nose cone attached thereto at trailing and leading ends, respectively, a governor shaft, to which turbine blades are connected, which is coupled to the end plate and supported within the nose cone to be rotatable with the turbine blades about a central axis thereof and axially movable from a first position relative to the turbine hub to a second position relative to the turbine hub and a hub assembly operably coupled to the turbine hub, the governor shaft and the turbine blades whereby the hub assembly biases the governor shaft toward the first position at low rotational speeds such that the turbine blades assume a partial coarse pitch angle, and the second position at high rotational speeds such that the turbine blades assume a fine pitch angle.

Abstract: The invention provides a mechanism for attenuating torque pulsations between an engine (2) and a rotor (1) of a rotorcraft. Torsion means (5) are interposed between the driving and driven shafts and comprise a torsion shaft (6) axially engaged with the drive shaft (3) and the driven shaft (4) an inlet shaft (9) and an outlet shaft (10) respectively engaged with the drive and driven shafts (3, 4) a lever system (7) that extends radially relative to the torsion shaft (6) and that has the inlet and outlet shafts (9, 10) hinged thereto via points (11, 12) that are spaced apart; and a mass (8) carried by said lever arm (7) at its free end (13) radially farthest away from the axis along which the torsion shaft (6) extends.

Abstract: Variable-pitch propeller (1) of the type comprising at least one blade (6a, 6b, 6c) rotatably pivoted (20a, 20b, 20c) to a cylindrical casing of the propeller (3a, 3b, 4), a shaft coupled to an engine and coaxial to that propeller casing, a kinematic system (7, 8a, 8b, 8c, 10a, 10b, 10c, 11), coupled to the shaft, or to the propeller casing, and to above mentioned at least one blade, for regulating the rotary motion of said at least one blade around its own pivot axis to the propeller casing, as well as means (2, 14, 15) for transmitting the rotary motion of the shaft to the propeller casing, the propeller being shaped to provide at least one not null angular range for the free relative rotation of the above mentioned at least one blade (6a, 6b, 6c) around its pivot axis, relatively to the propeller casing (3a, 3b, 4). The propeller also comprises at least one elastic element (18, 18?) countering the relative rotation of said at least one blade relatively to the propeller casing (3a, 3b, 4), or vice versa.

Abstract: A self setting and self powered system for adjusting the blade angles of a wind turbine such that they have a high angle of attack when parked to promote early start up, move to their ideal setting angle for normal running, can respond to gusts and lulls with appropriate changes, and feathers the blades to limit the rpm and reduce loads in storm conditions. The system balances the thrust loads on the turbine against centripetal forces generated by masses reacting to the rpm, increasing the blade pitch with gusts to increase torque and hence rotational acceleration and reducing blade pitch in lulls to conserve rotational momentum, and uses springs to establish the starting position and the rpm limit appropriate for the generator mechanism.

Abstract: An improved ram air turbine for generating emergency aeronautical supplemental power with a plurality of concentric or nested linear bearings for supporting a speed governor yoke plate on a speed governor shaft comprising a movable sleeve that supports the yoke plate and rides on the governor shaft.

Abstract: A backup governing system for a variable pitch propeller, carried by the propeller hub which is hydraulically interposed between a main control for the propeller and a propeller blade moving, double acting piston, the backup governing system comprising a spool valve including a spool movable between a plurality of metering positions along with first and second opposing springs applying oppositely directed biasing forces to the valve member. A flyweight assembly is connected to the spool and applies a speed dependent valve positioning force to the spool in opposition to a first of the springs and in addition to the second of the springs. A piston valve is operatively associated with the second spring and operable to change the bias applied by the second spring to the spool.

Abstract: A centrifugally activated variable damper assembly for a stopped-rotor aircraft is disclosed for adjusting dampening level of teetering motions produced by the rotors during the in-flight conversion process from rotary-wing to fixed-wing flight, or vise versa. The assembly includes a damper valve responsive to centrifugal forces produced by rotational speed of the aircraft rotor. The assembly also includes dampers within the rotor system that operate at variable damping levels in response to centrifugal forces acting upon the damper valve.

Abstract: A system for controlling propeller blade pitch is disclosed. The system comprises a transfer tube, wherein the transfer tube defines an element of the rotatable portion and wherein the transfer tube is non-translating relative the rotatable and non-rotatable portions. A transfer bearing for providing hydraulic fluid to and interfacing with the transfer tube is also used, wherein the transfer bearing is located on the non-rotatable portion. The system further includes a pitch change actuator and a mechanism form for actuating the pitch change actuator, wherein the mechanism is fluidically connected to and translatable relative to the transfer tube. A device for measuring blade angle of the propeller blade is also provided, wherein the device is separate and distinct from the transfer tube.

Abstract: In a helicopter having a device for stabilizing yaw motion through the use of a tail rotor with a plurality of rotor blades extending radially from a hollow rotor shaft which is mounted for rotation about a transverse rotor axis. The tail rotor is provided with a device for varying the thrust by a pilot input to the blades of the tail rotor and through the use of a gyro rotor for automatic control of the tail rotor. The invention further comprises a three point mixing linkage that permits the control of the tail rotor through both the pilot inputs and the gyro rotor inputs.

Abstract: A ram air turbine is provided for use in driving electric and/or hydraulic power systems in an aircraft, wherein the ram air turbine includes primary and secondary speed control governors. The primary governor includes centrifugal flyweights for cam-actuated adjustment of the pitch angle of a turbine blade or blades, within a selected adjustment range, to achieve substantially constant turbine speed in response to varying air speed and/or load. The secondary governor preloads the turbine blade or blades to a selected midrange pitch angle in the at-rest condition, wherein the midrange pitch angle is chosen for faster turbine acceleration on deployment to the desired full-speed rotation. The secondary governor controls blade pitch angle until the turbine reaches a selected rotational speed, after which the primary governor regulates and adjusts blade pitch angle within the selected adjustment range.

Abstract: In a helicopter having a tail rotor with a plurality of rotor blades extending radially from a hollow rotor shaft which is mounted for rotation about a transverse rotor axis, and having a push-pull rod extending through the hollow shaft and operably connected to the blades to manually vary the collective pitch of the blades, a device for automatically stabilizing the yaw motion of the helicopter includes a gyroscopic assembly having a gyro rotor mounted to rotate with the tail rotor, to pivot about a substantially longitudinal pivot axis by and at the outboard end of the push-pull rod and to automatically vary the collective pitch of the blades in response to yaw motion.

Abstract: There is provided a self-actuating variable pitch marine propeller which incorporates two or more blades, each independently rotatable, relative to the propeller hub, between a first lower and a second higher pitch. The blades are preferably mechanically linked by coordinating means and are caused to move preferably by a combination of centrifugal force effect resulting from inertial mass means and the hydrodynamic forces acting upon the blade hydrodynamic surface. The rotation of the blades relative to the propeller hub is limited primarily as to speed of rotation by restricted viscous fluid flow damping means operably connected to the blades. In one preferred embodiment, the viscous flow means further acts as an initial restraint against all motion by closing off the viscous flow orifice until a certain minimum propeller rotational speed is achieved.

Abstract: A self-actuating variable pitch marine propeller which incorporates two or more blades having cylindrical shafts which are rotatably connected to a central hub via cylindrical joints; the blades rotate about and translate radially, relative to the hub center, along the blade shaft, or shank, axis. In operation, the blades move radially outwardly from the hub center as they rotate from lower to higher pitch. The blades are biased towards the lower pitch. As the propeller rotational speed increases, centrifugal forces act on the blade mass creating a radially directed outward force. This radially outward force, upon reaching a sufficient magnitude, causes the blades to move radially outward. A blade positioning mechanism connected between each blade and the hub directs the blades to rotate to a higher pitch angle as the blades move radially outward.

Abstract: A windmill construction embodying an improved arrangement for driving a load through a centrifugal clutch and for adjusting the pitch angle of the blades. The adjusting mechanism is responsive to speed so as to increase the pitch angle as the speed increases and further incorporates a latch mechanism for latching the blades in a maximum feathering pitch angle and for introducing a hysteresis effect into the mechanism.

Abstract: The present invention relates to an improved blade pitch control mechanism for an air driven turbine blade mounted for rotation in a hub assembly. The control mechanism includes a drive member mounted for reciprocation along a central axis of the hub assembly. The drive member has a control member secured to one end and a seat member at the other end. The blade has operatively coupled thereto, a centrifugally responsive means which includes a pin in mating engagement with the control member. A spring is positioned between the hub assembly and the control member to thereby cause the blade to assume a coarse or high pitch position when the blade and hub assembly are in storage. A slide member is mounted on a portion of the hub assembly for reciprocation along the central axis. A spring is positioned between the seat member and the slide member. A flyweight is supported on the hub assembly and engages the slide member.