Abstract: A device for controlling the pitch of the blades of a turbomachine rotor includes an electric motor having a stator which is stationary and a rotor, preferably of the permanent magnet or asynchronous kind, which is mounted on the turbomachine shaft and is rigidly secured to a toothed wheel meshing with pinion sectors rigidly secured to the roots of the blades, and a mechanism for locking the blade roots in position which includes an electromechanical actuator rigidly secured to the shaft and electrically powered by a rotary transformer.

Abstract: A direct current fan has a base, a stator assembly fixed to the base, a spindle extending from said the stator assembly, and a blade assembly rotatably mounted to the spindle. The stator assembly includes a central axle and a bobbin having electrically conductive winding formed over the central axle. Pole plates alternately extend from diametrically opposed upper and lower disks which are mounted to the respective upper and lower ends of the central axle. Each said pole plate has first and second circumferential sections located at different distances from the central axis. The blade assembly includes a cylindrical member having blades mounted thereto and a circular central recessed portion. A hub is formed in the center of the recessed portion for receiving a portion of the spindle. The hub has an aperture in its center and a plurality of tabs equally spaced around the aperture.

Abstract: An actuator for varying the pitch of a plurality of propeller blades mounted on a propeller blade hub comprising an electric motor driving a drive gear, a reduction gear set driven by the drive gear and driving an externally threaded drive spool, an internally threaded pitch ring including a tangential slot, a pin received within the tangential slot and disposed on a blade hub to which the propeller blade is secured. Rotary movement of the drive gear, the reduction gear set, and the drive spool results in translational movement of the pitch ring. Translational movement of the pitch ring causes movement of the pin within the tangential slot, resulting in rotation of the propeller blade.

Abstract: Pitch change for a variable pitch propeller or fan of the type utilized in a gas turbine engine is effectuated by the unique application of a bidirectional electrical induction AC motor and an electrical DC induction brake operatively connected to the pitch change actuator. The motor can be utilized in a slip speed range encompassing from a positive slip speed to zero slip speed and negative slip speeds which removes the limitations on the gear ratio.

Abstract: The pitch of either a fan or propeller driven by a gas turbine engine is changed by utilizing a pair of impulse turbines interfacing between the stationary and rotating portion of the fan or propeller and utilizing a servo control responding to a desired pitch input signal for actuating the normally inactive impulse turbines during fixed pitch to drive the impulse turbine which in turn is operatively connected through a pitch change actuator to change the pitch in accordance with the input signal.

Abstract: Blade pitch is changed by an actuator that is responsive to the relative rotation of two input members. Blade pitch is not changed when the members are rotated at the same speed. However, blade pitch is changed in one direction when a braking torque is applied to one member, and blade pitch is changed in an opposite direction when a braking torque is applied to the other member.

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: A propeller blade tip path plane-inclining device which is provided with a fuselage, a propeller including a center piece rotating unitary with a rotation shaft in association therewith and a plurality of blades extending substantially horizontally from the center piece and differing the variation in pitch during the rotation thereof from one another, a motor for driving the propeller for rotation, a position detector for detecting the position of the propeller in the propeller rotation plane, and a control device for controlling the motor in accordance with an output signal of the position detector.

Abstract: The present invention relates to a ram air turbine which is preferably used in conjunction with a refueling pod on an aircraft for purposes of operating a fuel pump and/or reeling mechanism for paying in and paying out a fuel line. The turbine generally comprises a rotatable housing having a main turbine output shaft disposed therein and rigidly connect thereto. A plurality of variable pitch turbine blades extend outwardly from and are cooperatively engaged to the housing such that rotation of the turbine blades causes simultaneous rotation of the housing and output shaft. Means are provided within the housing for establishing a preset reference rotational speed for the output shaft. Additionally, a control means cooperatively engaged between the turbine blades and the reference means is provided for adjusting the pitch of the turbine blades in response to a difference in the rotational speed of the output shaft and the preset reference rotational speed.

Abstract: A system for changing pitch in aircraft propfans is disclosed, in which a motor, located at a stationary position, changes pitch of the blades by of a gear train. Three features of the system are that a feather brake can override the motor and drive the blades toward feather; a unison brake can prevent pitch from undergoing excursions toward fine pitch when propeller speed exceeds a limit; and the motor is non-rotating in the absence of pitch change. A pair of such systems can be used in a counterrotating propfan system, in order to independently change pitch of the propfans.

Abstract: The invention concerns a system for controlling an aircraft propeller. A hydraulic motor controls pitch of the propeller blades. The propeller blades are characterized by the absence of feather-inducing counterweights. An overspeed governor senses when propeller speed exceeds a limit, and, in response, assumes control of the hydraulic motor and drives the blades toward a coarsened pitch position, which reduces the propeller speed. In another form of the invention, a mechanical brake can override the hydraulic motor and mechanically retard a rotating gear, which causes the propeller blades to move toward a coarsened pitch.

Abstract: A wind turbine assembly including a rotor body having mounted thereon a plurality of rotor blades. Each of the rotor blades may be joined at an inner extremity to a blade stem projection extending interiorly into the rotor body and secured to the rotor body by a torsional-spaced and axial-shock damping connection. The blade stem projection may also be secured within the rotor body in a manner allowing limited rotation of the blade stem projection relative to the rotor body, corresponding to a selective range of pitch of the associated rotor blade, with a system for rotating a blade stem projections of each of the rotor blades by corresponding degrees of rotation to provide a predetermined pitch of the rotor blades. Also disclosed are pitch-damping tower designs, and an integrated design wherein the tower is pitch- and yaw-damped.

Abstract: A gas turbine engine for aircraft propulsion includes a variable pitch fan, pitch change of which is effected by providing a small D.C. excitation current to a selected one of two non-rotating field coils dependent upon the direction of pitch change desired. The field coils each form the static part of respective polyphase A.C. alternators, and the rotating armatures of the alternators connect to respective separate stator windings of a compound polyphase A.C. reversible induction motor rotating with the fan. An armature of the motor is relatively rotatable and couples with the fan blades to pivotally vary their pitch angle. An A.C. current is available from the non-excited alternator field coil, and may be rectified and controlled for use as the D.C. excitation current. Thus, all energy requirements of the pitch change apparatus may be extracted from the rotor of the fan engine.

Abstract: A pitch change system (30) for varying the pitch of the blades (16) of a multi-bladed propulsor (10) comprises a pitch change actuation assembly (40) and a pitch change drive assembly (70) for selectively actuating the pitch change actuation assembly (70) whenever it is desired to change blade pitch. The pitch change actuation assembly (40) comprises a ballscrew (42), a ballscrew nut (44) threadably mounted to the ballscrew (42), and a pitch stop assembly (100) having a retractable feather stop (135) which in its normal position prevents the ballscrew (42) from driving the ballscrew nut (44) to move the blades (16) beyond the coarse pitch setting corresponding to blade feather, but in its retracted position permits the ballscrew (42) to drive the ballscrew nut (44) to move the blades (16) through feather to a desired reverse pitch setting.

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 concerns a pitch change mechanism for an aircraft propeller in which a common ring gear (51) changes pitch of all propeller blades on a given rotor simultaneously. Motion of the ring gear (51) is induced by a planet (40)-and-carrier (101) system driven by a pinion (110). Acceleration of the pinion causes a change toward flat pitch. Deceleration of the pinion causes change toward feathered pitch. If the motor driving the pinion fails, a large deceleration occurs, driving the blades to a safe, feathered position.

Abstract: A watercraft has a hull and a hollow support body secured below the hull. A propeller drive shaft is disposed rotatably in the body with one end extending out of the body and is adapted for connection to a driving engine. A main bearing for the drive shaft is disposed in the body, the shaft extending through the bearing. A variable pitch propeller has a hub and a plurality of variable pitch propeller blades. The hub is secured to the shaft. A plurality of adjusting elements are mounted in the hub parallel to the shaft, each element being secured to a corresponding blade for varying the pitch thereof. A coupling is slidably disposed along the shaft in the support body with a rotatable first section secured to the hub and a non-rotatable first section spaced from the shaft and having bearing means in which the first section is rotatably supported.

Abstract: A controllable and variable pitch propeller assembly. This assembly includes a main drive shaft mounted for rotation, and a propeller hub connected to the drive shaft for rotation with the drive shaft. Power cylinders are formed integrally in a unitary cylinder member affixed to a watercraft, or to the drive housing thereof. These power cylinders have actuator rods movable with respect to the watercraft in a direction substantially parallel to the drive shaft. A plurality of propeller blades are mounted to the hub for rotation therewith. Each blade is rotatable about a respective hub radial, and each of the blades has at its inner end a respective thrust collar. A ring assembly is provided, connected between the actuator means and the respective thrust collars at one side of each of the propeller blades, the ring assembly causes the propeller blades to rotate about their respective hub radials, thereby changing the pitch of the propeller blades.

Abstract: A novel electro-hydraulic control system for use with a helicopter includes a plurality of electro-hydraulic modules which provide control signals to corresponding blade actuators. A controller receives helicopter parameter input signals as well as pilot command signals and generates the control signals in accordance with preestablished algorithms. The system is characterized by a hydraulic slip ring that transmits the hydraulic control signals from the fuselage to the rotating assembly. Consequently, the present system provides "fly by wire" operation with individually addressable helicopter blades.

Abstract: A watercraft has a rotatable propeller drive shaft connected to a driving engine. A coupling is slidably disposed along the shaft. The coupling has a rotatable first section secured to the shaft and a non-rotatable second section spaced from the shaft with a bearing arrangement in which the first section is rotatably disposed. A variable pitch propeller has a hub secured to the shaft. A plurality of propeller blades are rotatably disposed in bearing housings to the hub. Connecting rods are slidably disposed in the bearing housings. Each connecting rod has a position of protection at which it is disposed completely in the corresponding bearing housing wherein it cannot be attacked by foreign bodies. Devices for coupling one end of each rod to the base of the corresponding blade are provided.

Abstract: An inboard servo for a controllable pitch propeller of the force rod type comprises a feedback device having at least two feedback rods connected to the piston and extending through the cylinder end wall and an output ring connected to the rods. An emergency lock-up includes at least two threaded locking rods fastened to the cylinder and passing freely through holes in the feedback ring, each of which receives one or more nuts that can be threaded along the rod for engagement with the feedback ring to lock the piston in a desired position.

Abstract: A non-rotating actuating system for pitch control of a fan in a bypass turbine engine in which the actuating sleeve, that rotates with a fan and is moved axially to change to the pitch ofthe fan blade, is supported by a part of the fixed structure thereby to minimize loading of the disc supporting structure.

Abstract: Overspeed conditions in a ram air turbine are eliminated through a novel blade pitching mechanism. The mechanism includes a rotatable shaft with a hub mounted thereon for rotation therewith. The hub rotatably mounts at least one blade and a hollow blade pitch control shaft extends generally concentrically about the rotatable shaft and is mounted for reciprocating movement in a path toward and away from the hub. A reciprocating to rotary motion converting mechanism interconnects the control shaft and the blade so that the pitch of the blade can be controlled by controlling the position of the control shaft in the path. A first motor is provided for incrementally moving the control shaft within the path and a second motor is provided for rapidly moving the control shaft within the path to a position therein corresponding to a feathered position of the blades.

Abstract: Apparatus is for controlling load on an engine, particularly a marine engine powering a controllable pitch propeller which serves as an engine loading device. Apparatus cooperates with a circuit having a supply fluid at a constant supply pressure, and a control fluid at a variable control pressure reflecting engine load. The apparatus has a signal receiver to receive a load demand signal from an operator, and a positioner apparatus with a positioner output which cooperates with the loading device of the engine. The positioner apparatus receives the supply and control fluids and has a partition separating the fluids to permit interaction therebetween to control the positioner output. The apparatus has a hydraulic fluid valve to control flow of hydraulic fluid relative to the positioner apparatus, the fluid valve being connected to the positioner output and an output of the signal receiver so as to be responsive to relative positions of both outputs.

Abstract: Blade pitch varying means for use in a gas turbine engine are disclosed. The blade pitch varying means may be used on an engine with a single row or two counterrotating rows of variable pitch blades which are disposed outwardly from an annular gas flowpath and which are connected with a rotating airfoil within the flowpath. The blade pitch varying means comprise actuation means, bearing means, and gearing means. The actuation means are in a nonrotating reference frame disposed inwardly from the flowpath and deliver an axial force. The bearing means transmit the axial force from the nonrotating into a rotating reference frame which contains both the propulsor blade and the airfoil in the gas flowpath. The gearing means are located in the rotating reference frame and convert the axial force into a force for varying the blade pitch.

Abstract: An operating rod is connected at its one end to a runner vane rotary shaft through a link and lever mechanism. The operating rod is supported by a rotational propelling force bearing. The rotational propelling force bearing is reciprocatingly moved through a link and lever mechanism by a servomotor disposed outside of a stay ring. With such a construction, the rotational operation of the runner vanes may be smoothly attained.

Abstract: A controllable pitch propeller assembly has an inner housing attached to a main drive shaft, the housing having rails on the outer surface thereof. Modules carrying the propeller blades are positively mounted on the rails, each module having a housing receiving a hub cylinder and bushings axially aligned at opposite sides thereof. Each pair of bushings receives an adjusting piston having an adjusting pin which engages a groove forming a control path in a propeller hub. Each blade is adjusted by a control lever which adjusts each adjusting piston through a mechanical linkage including an adjusting sleeve and a thurst bearing and flange.

Abstract: A ceiling fan includes auxiliary vanes pivotally connected to the opposite ends of its main vanes, wherein each auxiliary vane is pivotally connected to a common bracket unit through a pull rod at its opposite end to the main vanes. The bracket unit is capable of moving up and down in accordance with the rotating direction of an electric motor along a shaft supporting the body of the fan on a ceiling. By operating a solenoid the bracket unit is connected to or disconnected from the motor. Thus the auxiliary vanes are rotated in a clockwise direction or a counter-clockwise direction, thereby changing the angle of attachment thereof to the main vanes as desired while the main vanes are in rotation.

Abstract: A device for controlling the cyclic and collective pitch of a helicopter rotor in which a fixed ring of an oscillating plate is maintained regularly fixed and is guided in its oscillations with respect to a drive shaft by a plurality of variable configuration supports uniformly distributed about the said drive shaft and connected to the said fixed ring by means of cylindrical pivots at least one of which is eccentric with respect to an axis rotation of an associated supported fork, which is perpendicular thereto.

Abstract: A horizontal shaft wind turbine with few blades, is provided with device for turning or twisting the blades about their longitudinal axes, comprising a power source situated outside the turbine shaft and adapted to impart axial motion to a first axially displaceable clutch mounted on the shaft, the clutch having two main parts in mutual coaction such that one part is rotationally stationary on the shaft, whereas the other part may rotate with the shaft, the part rotating with the shaft being coupled to the blades.

Abstract: Means are provided for coupling at will a driven shaft (2), intended more particularly for adjusting the orientation of the blades of a boat propellor, either to the output shaft (1) of a motor or to a hand operable member (3). To this end there are provided three coaxial inwardly splined ring-wheels juxtaposed axially and integral respectively, the first two (13,14) with the two shafts and the third one (16) with said member, an outwardly splined hub (15), a tangent wheel (22) integral with said member and coacting with an endless screw (23) operable by means of a crank and screw means actuated by the rotation of a crank mounted on a head (28) and arranged so as to control the axial sliding of the hub by means of thrust bearings (32) and springs (33).

Abstract: There is disclosed a hydraulically-controllable variable pitch propeller device capable of being removably mounted on a propeller shaft. The device includes a rotatable mounting flange and a stationary hydraulic mechanism located between the mounting flange and the propeller hub. The hydraulic mechanism includes a cylinder and a piston. The device also includes means for varying the pitch of the propeller blades in response to movement of the piston within the cylinder. The varying means includes a thrust face cooperating with a face of the piston, both the thrust face and piston face having mating races in which ball bearings are mounted.The device also includes a novel control mechanism for regulating the amount of hydraulic fluid in the hydraulic cylinder for controlling the location of the piston and thus the pitch of the propeller blades.

Abstract: A movable blade pump including an actuating mechanism for imparting rotational movement to blades which mechanism is contained in an impeller boss sealed against the outside and filled with hydraulic fluid and is driven by a hydraulic cylinder device secured to a suction casing below the impeller boss. Feed and discharge of hydraulic fluid into and from the hydraulic piston device are effected through fluid passages formed in the suction casing and a fixed mounting for the hydraulic fluid device, and the blades are set at any angular positions within the range of the stroke of the piston.

Abstract: A flight control system is provided for a helicopter furnishing safety feres, and providing back up control in the event of failure of controls of the rotary head swashplate of a helicopter. The swashplate is regulated by a series of actuators which are angularly positioned at particular settings around the swashplate. In the event of a control system failure, a supplemental system controls the selected settings for the swashplate, rotary head, and spar root and blade assemblies of the helicopter.

Abstract: A helicopter having a mast 50 which drives a rotor and which is driven from a transmission 16 has a swashplate 10 individually linked to pitch horns on each rotor blade. At least four control channels 11-15 are coupled to the swashplate. Three channels may control the attitude and position of the swashplate. The control channels 11-15 are actuated in response to pilot commands transmitted by means including mechanical, optical or electrical systems. A separate power unit 21-25, 31-35 supplies each control channel. Each power unit is directly driven by the transmission 16. Means 11c-15c applies control of the swashplate 10 from among the control channels 11-15.

Abstract: A helicopter mast is driven by a transmission with a swashplate individually linked to pitch horns on each rotor blade. At least four actuators are coupled to the swashplate, three of which normally control the attitude and position of the swashplate. A separate power unit is provided for each actuator, each power unit being independently driven from the transmission. Means are then provided to shift control of the swashplate from one of the three actuators to a fourth actuator upon any one becoming disabled.

Abstract: A relative motion between a solid propeller shaft and a sleeve surrounding the propeller shaft is utilized to control a pitch of a marine propeller; the front end of the sleeve being supported by a pair of taper roller bearings and the rear end of the sleeve being connected to the hub of the propeller. A bearing housing supporting the taper roller bearings is formed as a piston of a servomotor and a casing receiving the bearing housing is formed as a cylinder of the servomotor. The casing is formed as a common oil reservoir for feeding lubricating oil to a stern tube bearing and bearings in the hub of the propeller.

Abstract: A pitch-change apparatus for a ducted thrust fan having a plurality of variable pitch blades employs a camming ring mounted coaxially of the hub at an axially fixed station along the hub axis for rotation about the hub axis both with the blades and relative to the blades. The ring has a generally spherical outer periphery and a plurality of helical camming grooves extend in a generally spherical plane on the periphery. Each of the variable pitch blades is connected to a pitch-change horn having a cam follower mounted on its outer end, and the camming ring and the horns are so arranged about the hub axis that the plurality of followers on the horns engage respectively the plurality of helical camming grooves. Rotary drive means receives pitch-change commands from an appropriate controller and rotates the camming ring relative to the blades to cause blade pitch to be changed through the cooperative operation of the camming grooves on the ring and the cam followers on the pitch-change horns.

Abstract: An axial flow fan wherein the cylindrical housings for the shanks of blades are mounted on a flat plate-like circular base of the hub which is rotated by an electric motor through the medium of a belt transmission and a hollow shaft. The motor, transmission and shaft are mounted at one side and the housings are mounted at the other side of the base.

Abstract: An improved actuating mechanism is provided for a gas turbine engine incorporating fan blades of the variable pitch variety, the actuator adapted to rotate the individual fan blades within apertures in an associated fan disc. The actuator includes means such as a pair of synchronizing ring gears, one on each side of the blade shanks, and adapted to engage pinions disposed thereon. Means are provided to impart rotation to the ring gears in opposite directions to effect rotation of the blade shanks in response to a predetermined input signal. In the event of system failure, a run-away actuator is prevented by an improved braking device which arrests the mechanism.

Abstract: A fan assembly particularly adaptable for use with an induced draft heat exchanger having a fan with a plurality of variable pitch blades, a drive mechanism and a pitch control mechanism, wherein the drive mechanism and the pitch control mechanism are designed to be located upstream of the heating element on the cool-air side of the heat exchanger. The pitch control mechanism is coupled directly to the rotating fan shaft, separate from the frame member for the heat exchanger to prevent problems in the alignment of the bearings for supporting the fan assembly. A fail safe mechanism is also provided in the rotating assembly of the fan to insure maximum pitch of the fan blades if the pitch control mechanism fails.