Abstract: Today the low noise blades and especially the super low noise blades for large diameter axial fans which are employed in the big cooling machines and cooling plants are so costly and are requiring so many extra costs on the other related equipment, that the noise pollution abatement can increase the whole cooling apparatus cost by up to a 35%. This invention, provides a new technology to make low noise fans able to transform any common blade into a low noise or very low noise at very low cost, preserving the same high efficiency and tip speed, as opposite to all the other low noise blades at actual status of art. As the fans for the big cooling apparatus are generally their main noise source, this invention will offer the opportunity to dramatically reduce the noise pollution produced by big cooling machines and cooling plants.

Abstract: A blade pitch actuation mechanism comprising a rotating race member in which is formed a race configured to receive a trunnion pin attached to a blade, whereby the race defines a cam profile such that rotation of the race member causes the trunnion pin received in the race to rotate as it slides over the cam profile.

Abstract: Rotor hubs having pitch control systems and related methods are disclosed herein. An example apparatus includes a housing including a first housing arm to support a first blade grip and a first blade spindle and a second housing arm to support a second blade grip and a second blade spindle. The example apparatus includes a first pitch link and a second pitch link. The example apparatus includes a first pitch arm coupled to the first pitch link and one of the first blade grip or the first blade spindle and a second pitch arm coupled to the second pitch link and one of the second blade grip or the second blade spindle. The second pitch arm is to extend past the first housing arm to couple with the one of the second blade grip or the second blade spindle.

Abstract: A hybrid aircraft propulsion system. The system comprises a gas turbine engine comprising a compressor, a combustor, one or more turbines, a shaft coupled to one of the turbines, and a bypass fan mechanically driven by the shaft. The system further comprises an electrical generator mechanically coupled to the shaft, and an auxiliary propulsor mechanically coupled to an electric motor and electrically coupled to the electric generator. At maximum power, the gas turbine engine is configured to produce a turbine entry temperature at maximum power between 1800 Kelvin and 2000 Kelvin, the engine comprises a fan bypass ratio of between 4:1 and 13:1, and the generator is configured to absorb between 10% and 60% of the mechanical power generated by the turbine.

Abstract: A system for varying an angle of attack of blades of an aircraft turbine engine propeller, including an axial flow brushless motor including a stator including coils, and a rotor including permanent magnets. The rotor is mounted axially movable between a locked position in which it is secured in rotation with a rotary hub of the propeller, and an unlocked position in which its rotation relative to the hub along the axis of rotation of the propeller causes a variation of the angle of attack of the blades via a mechanical connecting mechanism.

Abstract: There is provided a free standing tidal power plant without a dam structure set to take up kinetic energy from a water flow. The tidal power plant includes a propeller-shaped water turbine in horizontal rotor configuration with rotor blades, the rotor blades having bidirectional profiles, wherein the rotor blades are fastened to a revolving unit, which defines a rotational plane, and an electric generator at least indirectly driven by the water turbine. Each rotor blade is associated with a first swivel axis and a second swivel axis, the first axis and the second swivel axis extending substantially along a longitudinal axes of a first coupling element and a second coupling element, respectively. The revolving unit includes a planar guide region having a sliding apparatus, a first guide groove and a second guide groove, the sliding apparatus connected to the rotor blade to transmit rotor blade forces.

Abstract: A method of deploying offshore wind turbine assemblies includes mounting a wind turbine assembly horizontally on a vessel and transporting the wind turbine assembly to an offshore site. The wind turbine assembly is raised to a vertical condition at the site and attached to anchor weights. Blades are attached to the turbine head after the wind turbine assembly is in the vertical condition. In one embodiment, the wind turbine assembly can include a tower including tapered lower and upper sections joined together at their respective wide ends, a turbine head connected to the upper section, and a platform connected to the lower section. The platform includes a buoy tank partially filled with ballast to provide mass and buoyancy. A wave piercing cowling is rotatively attached to the lower section. The turbine head can include an adjustable journal bearing, scabbard blade mounts, and a gearless induction generator with flux adjusting capabilities.

Abstract: A system for controlling at least two variable geometry apparatuses of a gas turbine engine that includes at least a first body and a second body, the first apparatus including a stator blade stage with a variable setting angle of a compressor of the first body capable of switching between a closed position in an idle mode and an open position in a high-speed mode, and the second apparatus including at least one discharge valve of a compressor of the second body capable of switching between an open position in an idle mode and a closed position in a high-speed mode. The system further includes an actuator for actuating the two apparatuses.

Abstract: A system for controlling at least two sets of variable geometry equipment of a gas turbine engine including at least one first body and a second body, the first set of equipment being a stage of variable stator vanes of a compressor of the first body moving between a closed position during idling and an open position at high speed, and the second set of equipment being at least one bleed valve of a compressor of the second body moving between an open position during idling and a closed position at high speed. An actuator actuates the two sets of equipment.

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 propeller assembly is disclosed, comprising propeller blades pivotably mounted on a propeller hub. A cam follower is disposed on each propeller blade. A cam is movable between a first position, a second position and a third position. Recesses formed in the cam have a first segment, a second segment and a third segment, oriented at first, second and third angles. The first segment is oriented at a first angle relative to the central axis. The cam followers engage the first segment of the recesses when the cam moves between first and second positions to vary the pitch of the propeller blades between a first pitch and a second pitch. The cam followers engage the second segment of the recesses when the cam moves between second and third positions to vary the pitch of the propeller blades between the second pitch and a third pitch.

Abstract: A system for controlling at least two variable-geometry equipments of a gas turbine engine is disclosed. The engine includes at least a first core rotating at a first speed and a second core rotating at a second speed. The first equipment includes at least one variable-pitch stator blade of a compressor of the first core and the second equipment includes at least one air bleed valve of a compressor of the second engine core moving between an open position at idle speed and a closed position at high speed. The system includes an actuator which actuates both equipments.

Abstract: A system for adjusting the pitch of a variable pitch propeller has a hub assembly, a valve assembly, and a fluid supply assembly. The hub assembly comprises a hub rotatably driven by a propeller shaft, an actuator connected to the hub, and a plurality of propeller blades connected to the actuator with at least one mechanical connection. The valve assembly is in fluid communication with the valve assembly and the actuator. The fluid supply assembly comprises a valve control mechanism that is isolated from the valve assembly and the hub assembly. The valve control mechanism provides a variable hydraulic pressure control signal to the valve assembly, which transfers fluid to the actuator as a function of the variable hydraulic pressure control signal. Based on the fluid pressure in the actuator, the pitch of the propeller blades is adjusted.

Abstract: A compact variable pitch fan has a hydraulic pitch change mechanism. A pitch change piston is constrained to follow reciprocating motion under hydraulic control within a peripheral hub from which fan blades extend outward. An additional feature is the use of separated guiding and seal surfaces. A still further feature is the use of a pitch sensor, particularly on the hydraulic line leading to the variable pitch fan.

Abstract: A cooling fan is provided that does not place limitations on the installation conditions for the fan, is capable of cooling a backlight unit of a display panel with high efficiency, and produces less noise during operation. Also provided is an image display apparatus equipped with the cooling fan. The cooling fan includes a fan rotator composed of a rotational shaft that is rotationally driven by a driving motor and two vanes that have parallel revolution shafts that rotate together with the rotational shaft, are freely rotatable on the shafts, face one another, and revolve around the rotational shafts and a vane angle control unit that implements control so that each vane has a maximum rotation angle when a revolution angle of the vanes is in a vicinity of a first revolution angle and each vane has a rotation angle of 0° when a revolution angle of the vane is in a vicinity of a second revolution angle that is perpendicular to the first revolution angle.

Abstract: The expense of a bearing employed at the interface of a yoke (22) and a propeller blade pin (14) in a variable pitch propeller assembly is reduced in a bearing construction (16) wherein a bearing race (48) includes a crowned surface (50) adapted to engage a slot (20) in the yoke (22) and having a profile (Pi) wherein the diameter at one side (88, 90) of the race (48) is less than the diameter at the opposite side (90, 88) of the race (48).

Abstract: The expense of a bearing employed at the interface of a yoke (22) and a propeller blade pin (14) in a variable pitch propeller assembly is reduced in a bearing construction (16) wherein a bearing race (48) includes a crowned surface (50) adapted to engage a slot (20) in the yoke (22) and having a profile (P1) wherein the diameter at one side (88, 90) of the race (48) is less than the diameter at the opposite side (90, 88) of the race (48).

Abstract: A variable-pitch boat propeller has a hub rotatable about a hub axis, a plurality of vanes rotatable on the hub and extending generally radially of the hub axis, and an adjustment element rotatable on the hub about the hub axis and connected to the vanes for pivoting the vanes on the hub. An adjustment knob is pivotal on the hub about the hub axis and interengaging formations on the knob and hub limit angular displacement of the knob on the hub between a pair of end positions so that a limited range of adjustment of the vanes is possible with the knob. The interengaging formations include an axially open groove having a pair of ends constituting abutments and an axially projecting screw head and rotationally fixed relative to the hub and received in the groove. The groove is formed in the knob and the screw head is carried on a yoke rotationally coupled to the hub. The groove is arcuate, centered on the hub axis, and has an arc length of substantially less than 360°.

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 fan assembly (10) includes first and second housing sections (70, 72) which, when mated by a first set of fasteners, define a plurality of circumferentially spaced openings (162) that lead to an internal housing chamber (82). The fan assembly (10) also includes a plurality of blade units (140), each of which includes an integral support stem (142) having a journal portion (148) rotatably mounted within a respective one of the openings (162), an enlarged flange portion (144) and a radial post portion (138) rotatably supported by a hub member (106) within the internal chamber (82). Each blade unit (140) preferably has a thrust bearing (156), bushing sleeve (158) and fan blade (152) integrated with the support stem (142), with the fan blade (152) being preferably molded to the support stem (142) following positioning of the thrust bearing (156) and bushing sleeve (158) to form an integral component.

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: An actuation system which includes apparatus for transferring control signals for varying the blade pitch from a non-rotating member to a rotating member of a gas turbine engine is described. In one embodiment, the engine includes a main disk containing a row of blades, and the disk is coupled to a main shaft which rotates about the engine axis. An actuating disk, or cone, rotates with the main disk, and the torque required to rotate the actuating cone is transmitted through ball splines attached to the main shaft. The ball splines allow transmission of torque between the disk and the cone and at the same time enable the disk and the cone to move axially relative to each other without binding. The actuating cone is supported at one end by the ball splines and at its other end by ball thrust bearings. The ball thrust bearings are pre-loaded to enable the bearings to withstand axial loads in opposite directions.

Abstract: An impeller has a plurality of rotating passageways which can be defined between adjacent blades, the blades having a curved root portion and able to pivot across a part spherical hub to maintain a fine line contact. The passageways have a convergence to improve the efficiency of the impeller. The hub can be split into two relatively rotating portions, with the blades attached to each portion to provide an efficient means to vary the pitch of the blades.

Abstract: A Kaplan turbine or similar hydraulic machine has a hub body (1) fixed to the turbine shaft with radial blades attached to the hub body. The blades are fitted with oil lubricated bearings in the hub body. A sealing arrangement for the oil system has first (60) and second (61) circumferential sealing members with a circumferential space (65) between the first and second sealing members (60, 61). High pressure water from a water source is directed into the circumferential space (65) via a connecting channel (64) to block the lubricating oil from leaking into the working fluid.

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: 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: A propeller is controlled to change pitch at at least two different rates. In one embodiment, an electric motor is provided with a high or low voltage for driving a pitch change mechanism at a high or low change rate. Preferably the rate is selected automatically. Preferably, the high rate is not used unless the current pitch is below a threshold.

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: A variable-pitch propeller or fan comprises a hollow boss, a number of propeller blades fitted rotatably on the boss, and also an adjusting element which is axially slidable in the boss and has a number of grooves running essentially at right angles to the direction of sliding, each propeller or fan blade having a control pin which is placed eccentrically relative to its rotary shaft and is slidingly accommodated in a groove of the adjusting element. In order to increase the range of adjustment each groove comprises an essentially straight part and also a second part connecting to the straight part and forming an angle with the essentially straight part.

Abstract: A self-actuating variable pitch marine propeller which incorporates two or more blades which are rotatably connected to a central hub; the blades rotate relative to the hub center about the shank axis. In operation, the blades are biassed towards the lower pitch, both by mechanical means, such as a spring, and optionally also by hydrodynamic load means. As the propeller rotational speed increases, centrifugal forces act to move the blades towards the higher pitch position. In one alternative mode the hydrodynamic load also acts towards the higher pitch position. There is further provided a holding mechanism to retain or hold the blades at least preferably in the lower pitch position, the holding mechanism being so designed that at a sharply defined combination of parameters, including rotational speed and optimally hydrodynamic load acting on the blades, the holding mechanism is caused to be released and the blades permitted to move to a second higher pitch position.

Abstract: A multiple vane, variable pitch, fluid active or reactive device to move or be moved by a fluid including first and second wheels each rotatable about its axis and the axes disposed in selected parallel offset relation. Aperatures provided in the first wheel receive rotatable vane shafts. A vane is provided on each shaft and a distal end of each shaft extends through the aperture. Follower members are connected to the distal ends of the shaft and extend generally parallel to the chord line of the vanes to control the pitch angle of the vanes. The second wheel is inset a selected distance from the first wheel and provides cams that extend outwardly from the second wheel to engage the follower members of the first wheel. A drive member is provided so that a rotational force applied to either wheel is transferred by a gear drive to the other wheel.

Abstract: A variable-pitch mechanism, for use in an airplane, a ship, or the like, for adjusting the pitch of a plurality of blades of a propeller in which attachment shafts of a plurality of radial blades of a propeller are rotatably mounted on a tubular hub which can be driven by a drive shaft, and eccentric pins projecting from ends of the attachment shafts are held in an annular groove defined in the outer periphery of an adjusting ring which is disposed concentrically in the hub and axially movable. The attachment shafts can be turned about their own axes through the eccentric pins in response to axial displacement of the adjusting ring for adjusting the pitch of the propeller blades.

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: 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 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 fan assembly has variable pitch blades adjustable from outside the assembly while the fan is operating so as to alter the volume and direction of the induced airflow. The fan blades have an airfoil configuration such that air is moved by the fan in either direction with equal inefficiency. The airfoil configuration of the blades is neutral and the blades are straight. The fan assembly is lubricated by a pick-up non-rotatably mounted in a reservoir formed by the pulley hub and blade hub. The pick-up feeds lubrication directly to the bearing assemblies on which the spider and pulley hub are mounted.The neutral airfoil shape of the blade extends along the blade, and the blade has a blunt leading edge and a tapered trailing edge.

Abstract: A fan assembly has variable pitch blades adjustable from outside the assembly while the fan is operating so as to alter the volume and direction of the induced airflow. The fan blades have an airfoil configuration such that air is moved by a fan in either direction with equal efficiency. The fan assembly includes a non-rotating secondary shaft axially moveable in a main shaft. The secondary shaft has a spider interconnected with the crank arms of the blade arms by a snugly fitted universal joint assembly. The airfoil configuration of the blades is neutral and the blades are straight. The fan assembly is lubricated by a pick-up non-rotatably mounted in a reservoir formed by the pulley hub and blade hub. The pick-up feeds lubrication directly to the bearing assemblies on which the spider and pulley hub are mounted.

Abstract: An automatic variable pitch propeller including a central hub defining an axis of propeller rotation and a plurality of blades connected to and extending from the central hub substantially normal to the axis of rotation, each blade being mounted for rotation about a pitch axis, a cam mechanism to translate centrifugal forces imposed on that blade into a force tending to rotate that blade toward a course pitch, that force being opposed by water pressure tending to decrease blade pitch. The cam mechanism including a cam groove formed in an insert, of a material harder than the blades, in each blade shaft and the propeller being provided with variable minimum and maximum blade pitch stops, resilient bias toward minimum blade pitch and manual a pitch-up shift mechanism.

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: 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: An automatic variable pitch propeller comprising a central hub defining an axis of propeller rotation and a plurality of blades connected to and extending from said central hub substantially normal to the axis of rotation, each blade being mounted for rotation about a pitch axis, means to translate outward movement of that blade resulting from centrifugal forces imposed on that blade by rotation of the propeller into a force tending to rotate that blade about its pitch axis toward a feathered pitch condition, the force being opposed by a feathering force acting at a center pressure of the blade offset from the pitch axis, caused by resistance to rotation of said propeller and tending to decrease blade pitch toward a feathered condition.

Abstract: A variable pitch mechanism for a propeller comprises a crank pin on each rotatable blade of a propeller, or fan impeller, rotatable about a longitudinal axis thereof, a translational member having a crank pin engagement element for each crank pin, an actuating device connected to the translational member for causing the translational member to be moved in a desired direction resulting in movement of each crank pin means to cause each blade to rotate on its longitudinal axis in unison with and in the same sense as the other blade or blades of the propeller or fan impeller to cause variation in pitch of the blades. The propeller blade root assembly may have a housing, a blade root mounting rotatable about the longitudinal axis of the blade in the housing, an end cap fixed to the blade root mounting and having a thrust bearing engaging the housing to resist centrifugal force acting on the blade.

Abstract: A rotary joint having a non rotary housing surrounding a rotating shaft and being sealed by a mechanical seal. Monitoring impulses are transmitted by hydraulic fluid which is transported between the housing and the shaft by means of a distribution socket. The socket is arranged so that a number of column seals are formed between the shaft and the socket. The apparatus is supported by two prestressed, reversed roller bearings.

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 collective pitch change system for gyroplane rotary wing aircraft is provided. The system is particularly adapted for teter-bar rotors and is simple and direct. The system can change the blade pitch while the rotor is rotating to permit jump take-offs.

Abstract: The basic characteristics of an airplane and of a helicopter are combined into one flying craft: a HELIPLANE. This aircraft can fly forward like an airplane and hover like a helicopter. In the hovering mode, the craft lifting force is generated by gyrating blades and the craft control forces and moments are provided by a tail end propeller. In the forward flying mode, the craft lifting forces are generated by two wings and the gyrating blades. The propeller alone provides the forward propulsive thrust. The operations of the gyrating blades, of the craft control surfaces and of the power plant are all integrated, monitored and controlled to coordinate such operations during hovering, forward flight and any transition phase between hovering and forward flight. The gyrating blades never generate any forward propulsive thrust. The cyclic pitch motion of the gyrating blades needed to accommodate the craft forward flight velocity is induced by this forward velocity.

Abstract: A pitch control mechanism for propellers uses an elongated flat strip twisted into a helicoidal. The helicoidal is longitudinally slidable within a hollow propeller shaft. A cup-shaped cylindrical control ring coaxially mounted with respect to the front transverse surface of the propeller shaft is supported by an inner bearing ring permitting both longitudinal and rotational movement of the control ring relative to the propeller shaft. The control ring has a rectangular slot in its disc-shaped front face which fits conformally over the transverse cross section of the helicoidal. Longitudinal motion of the helicoidal therefore causes rotation of the control ring. Propeller blades are fastened to support rods terminating in downward extending, bifurcated fork-like support structures. The front tine of each fork is rotatably supported in a radial hole in the control ring, while the rear tine is rotatably supported by an axial hole in the propeller shaft.

Abstract: In an axial blower, a plurality of blades are disposed around a hub and each blade is supported on a respective strut which is rotatable in a pair of radially separated bearings. An axially displaceable disk in the hub is connected with the blades for rotating them. The drive shaft for the rotor is hollow and delivers oil to the disk which in turn delivers it to the rotation levers of the struts. The oil moves successively to the bearings radially outward of the disk and accumulated oil is collected by a scoop at the radially outer bearing. The collected oil is delivered to a collection chamber and is recirculated by a pump back to the hollow shaft. An additional cooling circuit may be provided.