Abstract: A blade-pitch change mechanism includes a motor comprising a rotating motor shaft and a housing, a solenoid coupled to a first end of the rotating motor shaft and to the housing, and a hub coupled with a second end of the rotating motor shaft. The hub includes a cylindrical puck having formed therein a gated castellated groove and connected to the second end of the rotating motor shaft and a cylindrical blade-pitch hub selectively couplable with the cylindrical puck via a plurality of drive pins and having formed therein a blade-pitch adjustment groove.

Abstract: Various mechanisms for adjusting pitches of propeller blades are described. For example, the pitch adjustment mechanism may include a propeller hub enclosing a geared mechanism that cooperates with a compound gearbox having first and second planetary stages to adjust pitches of propeller blades. Alternatively, the pitch adjustment mechanism may include a propeller hub enclosing a pitch adjustment assembly that utilizes tension cables and torsion springs, or rack-and-pinion structures, to adjust pitches of propeller blades. Using any of the various mechanisms, the pitches of propeller blades may be rotated at least 90 degrees, and up to and exceeding 360 degrees, in order to effect thrust reversals and/or adjust thrust profiles.

Abstract: A marine drive has an internal combustion engine that rotates a propulsor shaft that is operatively coupled to a propulsor to impart a propulsive thrust in water. The marine drive has a gearcase housing having an upper portion above a lower portion, the lower portion supporting the propulsor shaft. An exhaust passage in the gearcase housing is configured to convey exhaust gas from the internal combustion engine. An exhaust outlet on the upper portion of the gearcase housing is configured to discharge the exhaust gas from the exhaust passage to the water. The exhaust outlet faces the propulsor so that the exhaust gas is discharged into the water and towards the propulsor so as to aerate the water encountered by the propulsor.

Abstract: An exemplary turbomachine clutch assembly includes a clutch that moves from a first position to a second position in response to rotation of a turbomachine fan at a speed greater than a threshold speed. The clutch permits rotation of the turbomachine fan in a first direction whether the clutch is in the first position or the second position. The clutch limits rotation of the turbomachine fan in an opposite, second direction when the clutch is in the first position.

Abstract: A marine drive has an internal combustion engine that rotates a propulsor shaft that is operatively coupled to a propulsor to impart a propulsive thrust in water. The marine drive has a gearcase housing having an upper portion above a lower portion, the lower portion supporting the propulsor shaft. An exhaust passage in the gearcase housing is configured to convey exhaust gas from the internal combustion engine. An exhaust outlet on the upper portion of the gearcase housing is configured to discharge the exhaust gas from the exhaust passage to the water. The exhaust outlet faces the propulsor so that the exhaust gas is discharged into the water and towards the propulsor so as to aerate the water encountered by the propulsor.

Abstract: A bearing, such as a rolling bearing, is mounted on a support mobile in translation and includes a lubrication mechanism. The lubrication mechanism includes at least one pipe delivering a lubricant, linked to a lubricant supply source, and at least partially engaging in the support mobile in translation to deliver the lubricant from the mobile support along an internal channel to the bearing, passing through an inner ring of the bearing.

Abstract: The present application includes a blade-pitch control system for controlling a pitch angle of each of a plurality of blades on an aircraft rotor. A feedback lever associated with each blade is pivotally mounted to the rotating portion of a swashplate assembly. A pitch link connects an output arm of a lever to a pitch horn of a corresponding blade, and a feedback link connects the input arm of the lever to a yoke. Flapping motion of the yoke causes motion of the feedback link, and this motion causes corresponding rotation of the lever. Rotation of the lever causes motion of the pitch link, which changes the pitch angle of the attached blade. This provides for selected pitch-flap coupling between flapping motion of the yoke and pitch motion of the blades.

Abstract: A feathering device for the fan blades of a turboprop engine that includes at least one set of fan blades with adjustable orientation is provided. The assembly is attached in rotation to a rotating cowling connected to a turbine rotor. Each blade is coupled, for the adjustment of its orientation, to a control ring that is movable between two extreme positions, one of which corresponds to feathering of the blades. Mechanical parts are able to extend elastically as a result of a rise in their temperature, these mechanical parts being positioned facing the control ring so as to be able to exert a thrust force on the ring in order to put it in a position to feather the blades when they expand. A device to cause a rise in the temperature of the mechanical parts so as to expand them is also provided.

Abstract: A rotor blade is used in combination with a submersible electrical generator for generating electricity to be put into the grid, where the pitch of the rotor blade is controlled by a microprocessor. The microprocessor controls a radio frequency transmitter which emits signals to a receiver which controls a hydraulic value. The hydraulic valve controls a push-pull arrangement which through a right angle gear and pitch adjustment axial adjust the rotor pitch according to pre-programmed conditions stored in the microprocessor.

Abstract: An assembly for changing the pitch of fan blades rotatably attached to a hub includes a main drive shaft configured to rotate the hub. The main drive shaft is rotated by a first motor. A secondary drive shaft is coupled to the main drive shaft via a gearing system located within the hub. The secondary drive shaft is also driven by a second motor. When driven by the second motor, the secondary drive shaft manipulates the gearing system to alter the pitch of the fan blades.

Abstract: A system adjusts the pitch of a variable pitch propeller having a non-rotating side and a rotating side. The rotating side of the propeller has a hub, a propeller blade mounted to the hub, a propeller shaft that rotates the hub and propeller blade, and an actuation system. The actuation system has a screw and a piston. A motor has a non-rotating component in communication with the non-rotating side of the propeller and a rotating component in communication with the actuation system. When the motor increases speed, the screw rotates and the piston moves laterally in a first axial direction to decrease the pitch of the propeller and, when the motor decreases speed, the screw rotates and the piston moves laterally in a second axial direction to increase the pitch of the propeller.

Abstract: A propeller system includes a propeller hub which supports a multiple of propeller blades. A tailshaft extends from a propeller hub portion of the propeller hub along an axis of rotation with a propeller pitch change yoke mounted within the propeller hub for movement along an axis of rotation to change a pitch of the multiple of propeller blades, the propeller pitch change yoke in sliding engagement with the tailshaft.

Abstract: A blade pitch actuation mechanism for a plurality of propeller blades supported in a blade hub comprises a plurality of bearing assemblies, a bearing support plate and a yoke. The plurality of bearing assemblies receives a plurality of actuation trunnion pins from the plurality of propeller blades. The bearing support plate is connected to the plurality of bearing assemblies and unifies the plurality of bearing assemblies in a ring-like configuration. The yoke is connected to the bearing support plate and translates within the hub to adjust the pitch of the plurality of propeller blades.

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 remotely controllable flying machine, such as a remote control ultralight helicopter, has at least one rotor blade (104), the pitch (?) of which may be adjusted. The adjustment of the pitch (?) of the at least one rotor blade is achieved by means of a force, such as a torsion force directly applied to the rotation axis of the rotor blade. The force is generated by a magnetic field, variable by the electrical control of at least one coil (196) which is not part of an electric motor.

Abstract: A propeller control generates a once per revolution (1P) blade thrust variation through cyclic pitch of rigidly mounted non-flapping propeller blades. The resultant shaft bending moment is used to provide aircraft attitude control. Axial translation of a pitch change assembly including a pitch change yoke along an axis of rotation drives a pitch link attached to each propeller blade to collectively change the propeller blade pitch angle. The pitch change yoke includes a translating pitch change yoke portion and an articulatable pitch change yoke portion. Deflection of the articulatable pitch change yoke portion changes the pitch change effect of each pitch link as a function of its angular position such that a sinusoidal pitch angle is superimposed on normal pitch angle. Cyclic pitch change actuators deflect the articulatable pitch change yoke portion in any angular direction while the linear deflection of the cyclic pitch change actuators generate the magnitude of the cyclic pitch.

Abstract: A variable-pitch propeller, especially for a sport board, has angularly displaceable blade support plates which can be rotated about respective radial axes. The plates are provided with radially inwardly directed claws which engage in circumferential grooves of bases of the blades. The latter can have radial projections reaching beneath the claws. The resulting bayonet connection simplifies mounting and dismounting of the propeller blades even under water.

Abstract: A variable pitch fan in which the pitch of the fan blades is varied under control of a controller according to the speed of the fan. The controller is programmed to respond to increased fan speed by decreasing pitch of the fan blades. The variable pitch fan has a piston extending axially from a main shaft, about which main shaft a fan blade hub rotates. A pitch shifter is mounted on a cylinder, which itself is mounted on the piston. The pitch shifter is actuated by hydraulic fluid supplied through the main shaft to the cylinder. The piston is preferably axially stationary in relation to the main shaft. The cylinder is secured against rotational movement by at least one guide pin passing into the main shaft. Grease for the pitch shifter is supplied through the guide pin. One guide pin may be used for grease supply, while another may be used for excess grease return.

Abstract: Each blade of the rotor has a rigid root oversleeve connected to a torsionable and flexible root strip by two laminated, spherical support half bearings, fixed by their outer frame with double rigid horns the lateral ends of which facing each other on each side of the strip and half bearings are clamped towards each other and against struts so as to allow a significant, calibrated pre-compression of the half bearings. The double horns and/or struts are fixed axially to the oversleeves by fixing elements distinct from the compression means of the double horns on the struts and perpendicular to these compression horns on the struts and perpendicular to these compression elements. One of the struts, possibly in a single piece with one double horn, is also in a single piece with a pitch lever.

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 controllable-pitch propeller for a sport-type watercraft has a push rod eccentrically connected to each blade displaceable in a bore of the propeller hub. The push rod is sealed with respect to the end of that bore by a multifold bellows whose radial flange is clamped by a cap of an axial flange of the housing in which the bore is provided.

Abstract: An air driven turbine having variable pitched blades is provided that includes a pitch change mechanism for adjusting the pitch of the blades during either rotating or non-rotating operational modes of the air driven turbine. The pitch control mechanism includes a resettable overspeed protection device which is directly actuated by an overspeed condition of the turbine and operates independently from the pitch change mechanism to move the blades to a failsafe, feathered, or coarse pitch, low speed position. The pitch control mechanism utilizes a linear actuator in the form of an acme screw drive. The air driven turbine includes a ball ramp thrust bearing for attaching the blades to a hub of the turbine in such a manner that during rotation of the turbine actuation loads on the pitch change mechanism are reduced.

Abstract: A variable pitch boat prop includes a hub fixed to the prop shaft, a sleeve surrounding the hub and having bearings which receive stub shafts from a plurality of blades. The stub shafts pivot in the bearings, so that the blade pitch can change. Pinion teeth formed on the stub shafts mate with respective toothed racks fixed to the hub and disposed at an acute angle to the hub axis. The center of pressure of each blade is offset downstream from the stub shaft axis, so that dynamic pressure on the blades tends to decrease blade pitch, while the rack and pinion tend to increase blade pitch. These opposing moments are at equilibrium at different blade pitches, according to the speed of the boat and the prop shaft torque. Blade pitch increases automatically as speed increases, and decreases at load increases.

Abstract: A tail rotor for a rotary wing aircraft is located in a laterally directed duct located at the end of a tail cone extending rearward from the aircraft cabin and at the base of an empennage extending upward from the duct. The rotor includes a rotor shaft driveably connected to a power source, a rotor hub connected to the rotor shaft, a rotating control shaft, a stationary control shaft, and an actuator connected to the stationary control shaft for moving the rotating control shaft axially. The rotor hub includes rotor arms each supporting a pitch shaft for pivotable movement about a pitch axis. Each pitch shaft is adapted to support a rotor blade so that its angle of attack changes with movement of the pitch shafts. A pitch beam, located adjacent the rotor hub, supports flexure members, each connected to a pitch shaft eccentric of its pitch axis.

Abstract: A rotor for a rotary wing aircraft includes a rotor shaft driveably connected to a power source, a rotor hub connected to the rotor shaft, rotor arms inclined with respect to a plane perpendicular to the rotor axis and pitch shafts supported on each rotor arm. The rotor arms each support a pitch shaft for pivotable movement about a pitch axis. A pitch beam carries flexures, each connected to a pitch arm at a location offset laterally from the associated pitch axis. The flexures driveably connect the pitch arms to the pitch beam and transmit pitch control motion to the blades as the pitch beam moves along the rotor axis. Each flexure is intentionally displaced by bending radially during installation in a direction that reduces forces among components of the flexure bearings developed during operation.

Abstract: An integral marine propulsion unit utilizes both collective and cyclic propeller blade pitch angle variations to generate a thrust vector in any of three degrees of motion for use with both the submersible and surface marine vessels. The present marine propulsion unit eliminates the need for extraneous drag generating control surfaces and rudders for motion control of a marine vessel by incorporating a flat plate mechanism which includes an Oldham coupler coupled to a pair of plates and a slotted plate coupled with one of the plates. The slotted plate and the one plate coupled to the slotted plate are relatively rotatable about a fixed axis. The flat plate mechanism permits relative angular displacement between the slotted plate and the one plate to collectively pivot all of the propeller blades and permits radial movement of the slotted plate along with propeller blades.

Abstract: An inboard servo for a controllable pitch propeller of the force rod type comprises a feedback device comprising a feedback ring located externally of the propeller drive shaft, affixed to the force rod for rotation and axial translation therewith and having a planar surface perpendicular to the propeller drive shaft axis, and a distance-measuring device for substantially continuously detecting the position of the ring, and therefore the position of the force rod. The distance-measuring device directs a high frequency pulsed signal onto the ring surface from a fixed position spaced apart therefrom, detects the signal as it is reflected by the ring surface from a fixed position spaced apart therefrom, and processes the directed and reflected signals to produce a signal indicative of the position of the ring surface based on the time difference between the pulses directed onto the ring surface and the pulses reflected from the ring surface.

Abstract: A rotor blade control mechanism includes a transmission driving a hollow rotating drive shaft, extending through the transmission. A rotor head is attached to a top end of the drive shaft and includes rotor blade shafts of variable pitch and having control arm and lengths for cyclic and collective variation of the rotor blade shafts. A control regulates the rotor head control and lengths and includes at least a pair of rods extending through the hollow drive shaft with upper ends operably connected to the rotor head control arm and links and lower ends terminating substantially at a drive shaft bottom end. The control includes a fork with spaced fingers at the drive shaft bottom end and a yoke with spaced arms positioned in opposed relation to the fork. The yoke has a mounting block extending between the arms with the control rod lower ends swingably connected to the mounting block. A swing pin extends perpendicular to the yoke, through the mounting block, and is retained in the fork by the spaced fingers.

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: A controllable pitch marine propeller includes a hub body having a forward section provided with holes for bolts and locating and torque pins and a frontal surface that mates with a hub flange and an internal flange that defines an annular cavity and receives a cup-shaped cross-head. A hub flange and propeller shaft assembly comprises separate hub flange and shaft members joined by at least one weldment formed in a tapered weld cavity and protected by a liner shrink-fitted on the perimeter of the hub flange and a removable plate sealed to the hub liner and the shaft liner.

Abstract: A device of retractable stops for the blades of articulated rotors for giroplanes, which includes a stationary stop 20 with a finger 22 radially converging towards the exterior and externally radially protruding on the external spar 9 of the articulation means 7 of each blade on the hub 3, as well as a movable stop 21 with a receptacle 36 resiliently returned by a return device 45 in a position fit around the finger, but disengaged from the finger by centrifugal force when the rotation speed of the blades is higher than a set value. The invention therefore provides absolute stops in flapping and drag in the "ground" position and sharp stops in the flight position. One advantageous application is for helicopter rotors.

Abstract: An improved integral marine propulsion unit is disclosed that can generate a thrust vector in any of three degrees of motion. The unit utilizes both collective and cyclic propeller blade pitch angle variation to generate these thrust. This unit obviates the need for control surfaces and rudders for motion control of a marine vessel. Additionally, this unit provides flexibility in external propulsor arrangements on a marine hull. The unit integrates the swash plate mechanism and actuators within the central bore of a ring type prime mover.

Abstract: A variable pitch propeller assembly includes a hollow casing which, at its inner surface, fits securely around the propeller shaft. The outer surface of the casing forms the general shape of a cylinder which is coaxially located with respect to the propeller shaft's axis of rotation. A hollow collar is disposed around the outer surface of at least a portion of the casing and is further configured for movement with respect to the casing along the casing's longitudinal axis. A plurality of propeller blades are arranged around the outer circumference of the casing, and are connected to the casing so that the pitch of each blade with respect to the axis of rotation of the propeller shaft is varied by rotation of the blade about an axis which extends generally perpendicularly from the outer surface of the casing.

Abstract: The present invention provides for a propulsion apparatus for fluid medium comprising an open-ended sleeve having an inlet and outlet for flow through of fluid and a series of cooperating blades positioned along the sleeve. Each of the blades has a leading and trailing edge and the blades are fixed to rotate with the sleeve and cause a progressive acceleration of fluid from the inlet to the outlet with rotation of the sleeve thereby providing thrust for propulsion. The blades cooperate to define a fluid path to accelerate a fluid from the inlet to the outlet to thereby provide thrust for propulsion as the sleeve is rotated. The apparatus of the present invention provides forward and reverse speed of propulsion independent of the speed and rotation of the driving mechanism whereby adjustment of the blades at a fixed speed accelerates or decelerates the propulsion effort.

Abstract: A controllable pitch marine propeller comprises a hub body carrying a plurality of propeller blades for rotation about pivot axes disposed radially of the hub axis, a force rod extending into the hub body from the propeller shaft, and a cross-head affixed to the force rod and coupled to each propeller blade by a pin and slideway such that the propeller pitch is controlled by fore and aft movements of the force rod. The hub body has a tubular mount spigot that receives the aft end of the shaft with the shaft and mount spigot terminating aftward of the pivot axes of the blades. The cross-head is generally cup-shaped, having a base portion affixed to the force rod aftward of the pivot axes of the blades and a tubular portion extending forewardly from the base portion and surrounding aftward portions of the spigot in telescoping relation. The cross-head in supported in plain bearing relation by the hub body for fore and aft movements.

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 thrust bearing and flange. The hub is provided with open spaces formed between the inner and outer housings to create hub through exhaust ducts.

Abstract: A blade support hub of hollow circular ring structure for an axial fan, constituted essentially of two opposing parts rigidly fixed together by bolts, the hollow circular ring structure being provided with circular cavities for inserting the fan blade shank, the bolts for joining together the two parts of the hub also serving for fixing all the blade shanks.

Abstract: A system of rotatably and pivotally mounted radially extended bent supports for radially extending windmill rotor vanes in combination with axially movable radially extended control struts connected to the vanes with semi-automatic and automatic torque and other sensing and servo units provide automatic adjustment of the windmill vanes relative to their axes of rotation to produce mechanical output at constant torque or at constant speed or electrical quantities dependent thereon.

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.