Abstract: A rotor-hub flap-measurement system includes a rotor hub operable to flap relative to a main-rotor axis, a flap-linkage arm, a first end of the flap-linkage arm rotatably coupled to the rotor hub, the flap-linkage arm responsive to flapping of the rotor hub, and a magneto-resistive sensor system rotatably coupled to a second end of the flap-linkage arm and responsive to movement of the flap-linkage arm.

Abstract: The invention concerns a method for starting a hydroelectric turbine (10) in a pumping mode, said turbine being provided with a runner (6) mechanically coupled to a shaft line (8) and a variable speed electric motor connected to a grid, a distributor (4) comprising guide vanes to control a flow of water to said runner, the method comprising: a) a step of operating the variable speed motor at least partly at fixed speed, said guide vanes being only partially opened, and of defining or calculating: data of a plurality of hydraulic characteristics (C1, C2, Ci) of the turbine for an operation without cavitation; data of an operation range of the electric motor, giving the speed of the motor as a function of its power; b) then a step of operating the turbine in a power control mode.

Abstract: A propulsion device for a rotating blade aerodyne with vertical take-off and landing, comprising a hollow chassis and contra-rotating coaxial rotors with fixed-pitch blades. The means for driving the rotation of each rotor comprise motor means and, for each rotor, a rotating part capable of turning about a yaw axis, located in the central opening of the respective rotor and connected to the latter via a ball joint with finger, the centre of which is the intersection of the prospective rotor disc and the yaw axis and for which the prohibited rotation is that about the axis of rotation of the rotor. Means for controlling the inclination of the rotors about the roll and pitch axes. Aerodyne equipped with the propulsion device.

Abstract: A robust amphibious air vehicle incorporates a fuselage with buoyant stabilizers and wings extending from the fuselage. At least one lift fan is mounted in the fuselage. Movable propulsion units carried by the wings are rotatable through a range of angles adapted for vertical and horizontal flight operations.

Abstract: An airfoil, a turbine, and a gas turbine having enhanced cooling performance are provided. The airfoil including a leading edge and a trailing edge may include: a first cooling passage connected to the leading edge; a second cooling passage connected to the trailing edge; a third cooling passage formed between the first cooling passage and the second cooling passage; a plurality of partitions provided in the second cooling passage and configured to partition the second cooling passage into a plurality of portions in a height direction of the second cooling passage; and a perforated plate extending in the height direction of the second cooling passage, and coupled with the partitions to support the partitions.

Abstract: In response to a change in a state of at least some part of a vehicle, a control signal associated with countering the change in the state while the vehicle is in an occupant change state is generated. The control signal is sent to a rotor in the vehicle while the vehicle is in the occupant change state, wherein the control signal causes the rotor to move in a manner that is counter to the change in the state and the rotor rotates about a substantially vertical axis of rotation and enables the vehicle to perform vertical takeoffs and landings.

Abstract: Crossflow axes rotary mechanical devices with dynamic increased swept area including at least two rotors attached to a support structure having their axes of rotation parallel to each other, having at least one blade attached to each rotor via a joint where the swept areas created by the blades of each rotor intersect, having at least one rotor synchronizing component so the blades from each rotor do not collide during the rotation are described. The rotors with blades share the space, the support structure, the rotor synchronizing component, the electric machines, as well as the characteristics, parameters, and effects that the crossflow axes rotary mechanical devices with dynamic increased swept area have compare to the crossflow axes rotary mechanical devices without dynamic increased swept area.

Abstract: A rotor actuation system includes a swashplate assembly comprised of a stationary swashplate and a rotating swashplate operatively connected together for relative rotation about a rotor axis. A cyclic actuator is operatively connected to the stationary swashplate to tilt the swashplate assembly off axis from the rotor axis for cyclic control. A collective actuator is operatively connected to the swashplate assembly to move the swashplate axially along the rotor axis for collective control. The cyclic actuator and the collective actuator are operatively connected to the swashplate assembly to respectively actuate cyclic and collective control independent of one another.

Abstract: A device for controlling a collective pitch and a cyclic pitch of rotor blades of a rotoreraft of a direct turbine driven type and contra-rotating coaxial rotor type (DTDR) includes: a lower rotor and an upper rotor that are mounted concentrically on a shared rotor shaft; a first plate, that is not rotatable, fastened to a structure of the rotorcraft and connected to an actuator that communicates collective pitch and cyclic pitch controls to it, the first plate being mounted so as to be movable in translation along the shared rotor shaft and to oscillate relative to the shared rotor shaft, via a lower ball joint mechanism; and a second plate, that is rotatable, housed on the lower ball joint mechanism so as to be always parallel to the first plate, the second plate being driven in rotation by a member connecting it to the lower rotor.

Abstract: A pitch control device for a ducted tail rotor of a rotorcraft. The pitch control device comprises a control input member with a disc-shaped central component and at least two connecting arms that extend radially from the disc-shaped central component, wherein the disc-shaped central component is provided for being mounted to an associated pitch control shaft of the ducted tail rotor, and a control transfer member with a ring-shaped connector and at least two push rods that extend axially from the ring-shaped connector, wherein each one of the at least two push rods is provided for being coupled to an associated pitch lever of a rotor blade of the ducted tail rotor.

Abstract: A central-positioned pitch control device used in a coaxial helicopter includes an upper propeller hub; a lower propeller hub; a first blade mounted on the outside of the upper propeller hub; a second blade mounted on the outside of the lower propeller hub; and a central-positioned pitch control device placed between the upper propeller hub and the lower propeller hub.

Abstract: A rotor assembly for an aircraft operable to generate a variable thrust output at a constant rotational speed. The rotor assembly includes a mast rotatable at the constant speed about a mast axis. A rotor hub is coupled to and rotatable with the mast. The rotor hub includes a plurality of spindle grips extending generally radially outwardly. Each of the spindle grips is coupled to one of a plurality of rotor blades and is operable to rotate therewith about a pitch change axis. A collective pitch control mechanism is coupled to and rotatable with the rotor hub. The collective pitch control mechanism is operably associated with each spindle grip such that actuation of the collective pitch control mechanism rotates each spindle grip about the respective pitch change axis to collectively control the pitch of the rotor blades, thereby generating the variable thrust output.

Abstract: A coaxial twin-propeller twin-motor aerial vehicle comprises an upper propeller (1), a lower propeller (2) and an aerial vehicle body (3). A first motor (4) and a second motor (5) are disposed in the aerial vehicle body (3). The first motor (4) is connected to the lower propeller (2) through a first transmission shaft (42). The second motor (5) is disposed below the first motor (4) and is connected to the upper propeller (1) through a second transmission shaft (52). The second transmission shaft (52) passes through the first motor (4), the first transmission shaft (42), and the lower propeller (2) sequentially and then is connected to the upper propeller (1). The second transmission shaft (52) and the first transmission shaft (42) are coaxial. The upper propeller (1) and the lower propeller (2) rotate at the same speed and in opposite directions under the drive of their individual motors.

Abstract: A method of counteracting a rotor moment of one or more rotors of a concentric dual-rotor helicopter includes sensing angular velocity and angular acceleration of a helicopter during a flight maneuver. The angular velocity and angular acceleration are compared to a set of control parameters and one or more control servos change the cyclic pitch of the one or more rotors to counteract the rotor moment. A control system for counteracting a rotor moment of one or more rotors of a concentric dual-rotor helicopter includes one or more sensors configured to sense angular velocity and angular acceleration of a helicopter during a flight maneuver. A computer is operably connected to the one or more sensors and configured to compare sensor data to a set of control parameters. A plurality of control servos change the cyclic pitch of the one or more rotors to counteract the rotor moment.

Abstract: A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight.

Abstract: A rotorcraft provided with an anti-torque tail rotor having a drive axis of constant orientation and having a rotor disk that is arranged mainly to one side of the tail boom of the rotorcraft. A control mechanism for controlling the blades of the tail rotor includes a rotary control plate engaged with the blades and movable by a control rod extending along the drive axis of the tail rotor. The control plate is arranged in a constant mounting plane (PM) and serves to provide permanent cyclic variation in the pitch of the blades. Turning the control rod changes the way in which the cyclical variation of the pitch of the blades is operated between providing a contribution to lift and providing a contribution to propulsion in translation of the rotorcraft, depending on the angular orientation of the control plate in its mounting plane (PM).

Abstract: A control link disposed to transfer rotor shaft rotation from an elongate element rotatable with a shaft to a rotatable element is provided and includes a structure terminating at a first end thereof as a mating element, which is securable to the elongate element such that the elongate element is rotatable about an axis defined through the mating element and such that a moment reaction in opposition to structure rotation about the elongate element is generated and a rod coupled to the rotatable element being and configured to be coupled to a second end of the structure at variable distances relative to the rotatable element.

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 method is provided for producing a blade, by casting, for a gas turbine. The blade includes an elongate airfoil which extends in a blade longitudinal direction, merges into a blade root at the lower end, has a shroud segment at the blade tip and is pervaded by a single cooling air channel running in the blade longitudinal direction from the blade root to the blade tip. The method includes, during the casting of the blade, the blade material being fed exclusively from the blade root into the mold provided therefor, and the cooling air channel is formed during the casting of the blade by using a single core body, which is provided, at the blade tip, with a local casting cross section increasing element.

Abstract: Apparatus for the ventilation of a rotor hub of a wind energy plant, with a cup-shaped ventilation cap, which has a circumferential side wall and a base portion, wherein the side wall has at least one bore for draining water and the base portion has at least one bore for ventilation, a pipe-shaped connection piece, which has an air entrance opening which runs out into an interior space of the rotor hub, wherein the ventilation cap is arranged before the air entrance opening and the at least one bore for ventilation is arranged in the ventilation cap outside of the air entrance opening of the pipe-shaped connection piece such that the air entrance opening is covered up by the ventilation cap.

Abstract: A tool capable of removing material is applied to a turbine wheel cooling slot. Material is removed from a selected portion of the cooling slot with the tool. And, stress concentrations are reduced within the slot through the removal of material.

Abstract: A helicopter includes a system to effect motion in a horizontal dimension thereby to direct the desired direction. The rotor blades are driven by a rotor shaft and which is hinge mounted on this rotor shaft, such that the angle between the plane of rotation of the main rotor and the rotor shaft may vary. A control for moving the angle of incidence of at least one blade of the rotor cyclically along at least part of a 360-degree rotation path around the rotor shaft. This causes a variation in a lift force of the blade along at least part of the rotations path. This causes the body to be urged in a relatively horizontal direction from a relative position of rest. The control includes an actuator for engaging with an assembly depending from the rotor, the inter-engagement of the actuator and assembly effecting a change in the angle of incidence of at least the one blade of the rotor. The system includes a rotor, preferably complemented with a stabilizer rotor.

Abstract: The present invention relates to a helicopter provided with a main rotor (1) having at least two blades (10, 20), each blade (10, 20) being provided with attachment means (11, 21) attaching it to a hub (2) of the rotor (1). The helicopter is provided with one lift element (12, 22) per blade (10, 20), said lift element being provided with a tiltable tab (19, 29), each lift element (12, 22) being mechanically connected to a single blade (10, 20) to vary the pitch of said single blade (10, 20).

Abstract: A gas turbine section of a gas turbine engine, including a first stage turbine disk, a forward outer seal carried on the turbine disk and a forward shaft cooperating with the first stage turbine disk for transmitting torque generated by the turbine section to a compressor section of the engine. The forward shaft intersects the first stage turbine disk at a non-perpendicular angle in the area of the disk hub for directing sufficient hot air against the disk hub to balance the thermal response rate of the disk hub to the thermal expansion rate of the forward outer seal.

Abstract: A turbine bucket comprising an airfoil portion and a shank portion with a substantially horizontal platform radially therebetween, the shank portion having a forward shank wall and an aft shank wall; at least the aft shank wall convexly curved from one side of the bucket to an opposite side of the bucket.

Abstract: An impingement insert sleeve is provided that is adapted to be disposed in a coolant cavity defined through a stator vane. The insert has a generally open inlet end and first and second diametrically opposed, perforated side walls. A metering plate having at least one opening defined therethrough for coolant flow is mounted to the side walls to generally transverse a longitudinal axis of the insert, and is disposed downstream from said inlet end. The metering plate improves flow distribution while reducing ballooning stresses within the insert and allowing for a more flexible insert attachment.

Abstract: The device for the individual control of the blades includes at least two sets of rotating swashplates centered on the rotor axis and non-rotating swashplates at least inclinable in all directions under the action of at least two actuators inserted between the first set and a non-rotating structure, and under the action of at least one other actuator inserted between this structure and the second set. Each non-rotating plate is held by a connecting piece to the non-rotating structure, and each rotating plate is rotated with the rotor and connected to at least one blade respectively of the rotor via a respective pitch rod. The device also includes at least as many actuators as the rotor has blades, and all the actuators are non-rotating.

Abstract: The rotating and non-rotating swash-plates are guided in axial translation and in tilting on the rotor axis by two non-rotating pillars and slides provided with runners with a cylindrical external face permanently tangentially engaged and sliding against the internal faces of the pillars, the slides bearing two diametrically opposite trunnions allowing the pivoting of the non-rotating plate around a diametrical axis, whereas the sliding and pivoting of the runners on the pillars guide the pivoting of the non-rotating plate around a second diametrical axis, which is the axis of the cylindrical face of the runners.

Abstract: In a helicopter having three or more rotor blades, and with mechanical actuation of the rotor blades by a swash plate and a superimposed electrohydraulic active control system, in addition to three regulating units (18) is an actuator (4) between a rotatable part (9) of the swash plate and a rotorblade mount (2) of each rotor blade. This arrangement allows for the safe actuation of individual blades in helicopter noise reduction, and increased efficiency at a modest constructional effort.

Abstract: The non-rotating plate of the device is stopped from rotating around the rotor axis by a stop arm with at least one rigid stop track extending substantially axially and secured to the structure of the rotor aircraft. The track works together with a stop pin, integral with the non-rotating plate to stop the latter from rotating. The track has two flanges between which the pin is engaged so as to follow on this track a straight trajectory, parallel to the rotor axis and a circular arc trajectory centered on this axis, in the case of variation in the collective and cyclic pitch respectively. The stop pin includes a pad sliding between the two flanges of a slide constituting the said track and hinged around its fastening axis on the non-rotating plate.

Abstract: A split fan for providing lift for an aircraft is described. In one embodiment, a main engine shaft extends to the split fan, and a portion of the split fan is located at an elevation above the main engine shaft and a portion of the split fan is located at an elevation below the main engine shaft. In the one embodiment, the split fan includes an outer casing configured to be mounted to a fuselage of the aircraft, a first stage rotor including a shaft, a gear secured to the shaft, and a plurality of rotor blades radially extending from the shaft. The split fan also includes a second stage rotor including a shaft, a gear secured to the shaft, and a plurality of blades radially extending from the shaft. A drive shaft having a first end and a second end is coupled at the drive shaft first end to the main engine shaft.

Abstract: One embodiment of a coaxial transmission/center hub subassembly for a rotor assembly having ducted, coaxial counter-rotating rotors includes a single stage transmission, a transmission housing, and a center hub support structure that are structurally and functionally interactive. The transmission housing includes upper and lower standpipe housings secured in combination with a middle housing. The single stage transmission includes an input pinion gear rotatably mounted in combination with the middle housing, and upper and lower spiral bevel gears rotatably coupled in combination with the input pinion gear to provide counter-rotation thereof. The spiral bevel gears include integral rotor shafts, respectively, rotatably mounted in the standpipe housings.

Abstract: A vertical lift aircraft comprising an aircraft body and a lifting assembly is presented. The lifting assembly comprises a frame wherein at least one airfoil assembly which includes a plurality of airfoils attached to a drive ring is secured. As the drive ring rotates, the airfoils move through the air and create lift. The pitch of the airfoils or blades can be fixed or variable. The drive ring is rotated by a band which is in frictional contact with the inner surface of the drive ring. The band is rotated by at least one pair of rollers which are in frictional contact with the band. Aircraft stability is controlled by regulating airfoil pitch which is responsive to pivoting of a control ring. Alternatively, aircraft stability is provided by regulating the flow of air or gas from a plurality of nozzles disposed about the aircraft. The body, a portion of which may be located inside the lifting assembly, includes a passenger and load carrying compartment and an engine assembly.

Abstract: An individual pitch control device for the blades (7) of a rotor of a rotor craft employing respective rotating linear jacks (29) for controlling the pitch of the rotor blades. The linear jacks are implanted in a rotating support (25) which is driven in rotation with the rotor. The jacks (29) include rods (31) which are connected via additional rods (33) to drive pitch control levers (24) for each respective blade. The jacks (29) are linear, electrohydraulic, dual-action jacks having at least one body, and are supplied by control servovalves (36) which are also mounted in a rotating reference system. The servovalves (36) are supplied from a hydraulic circuit in a fixed reference system positioned on the rotor craft, having at least one hydraulic collector (27) which is at least partially rotating.

Abstract: An omnidirectional variable thrust propeller for a vehicle includes a hub, plurality of blades, and a plurality of shafts. Each shaft is coaxially rotatably connected to a respective blade and extends through the hub at an acute angle to a hub longitudinal axis. Each shaft has a lever arm and an inner end portion which terminates inside the hub. A reciprocably moveable device engages the inner end portions of the blade shafts to uniformly rotate the blades in one direction when the device moves longitudinally in one direction and uniformly rotate the blades in an opposite direction when the device moves in an opposite direction to enable a change of thrust. Another device pivotally supports the reciprocably movable device at a variable acute angle to the longitudinal axis. Another device selectively move the reciprocably movable device about the pivot point to nonuniformly change the rotation or pitch of the blade that alters the propeller's thrust direction.

Abstract: A helicopter tail rotor (10, 130) includes a drive mast (12) having an axis of rotation (14). A first blade pair (20) is mounted for rotation about the drive mast (12). The first blade pair (20) includes a pitch change axis (54) perpendicularly disposed to the drive mast axis of rotation (14). A second blade pair (34) is mounted for rotation about the drive mast (12) and is spaced apart from and parallel disposed to the first blade pair (20). The second blade pair (34) includes a pitch change axis (60) parallel to the pitch change axis (54) of the first blade pair (20).

Abstract: In a helicopter having a power shaft with a main axis and bearings for supporting an even number of blades for pivoting about their longitudinal axes, arms mounted on the respective blades for pivoting them in the same and opposite directions for cyclic and total pitch control, respectively, a featured control lever mounted intermediate its ends on a first pivot which lies in a first plane in which the main axis lies, with the control lever having movability of first and second kinds bodily with its pivot axis in the first plane and rockable about its pivot axis, respectively, links connecting the ends of the control lever with the free ends of the arms for pivoting the blades in first and second directions on movements of the control lever of the first and second kinds, respectively, an axially immovable control shaft turning with the power shaft, a swashplate mounted on the control shaft for universal movement on the latter, a first operating connection between the swashplate and first pivot, and including

Abstract: A vertical axis windmill having a rotating structure is provided with a series of articulated vertical blades whose positions are controlled to maintain a constant RPM for the rotating structure, when wind speed is sufficient. A microprocessor controller is used to process information on wind speed, wind direction and RPM of the rotating structure to develop an electrical signal for establishing blade position. The preferred embodiment of the invention, when connected to a utility grid, is designed to generate 40 kilowatts of power when exposed to a 20 mile per hour wind. The control system for the windmill includes electrical blade actuators that modulate the blades of the rotating structure. Blade modulation controls the blade angle of attack, which in turn controls the RPM of the rotor. In the preferred embodiment, the microprocessor controller provides the operation logic and control functions.

Abstract: A directional and yaw control mechanism for coaxial helicopters, comprising a three coaxial ring system interconnected through a cam and link assembly for transmitting control signals from a steering station to change the rotor blade pitch either collectively to provide lift or independently in opposing directions to control yaw. Cyclic pitch control is also similarly provided.

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: Pitch control linkage for the upper rotor of coaxial counterrotating rotors utilizes conventional swashplate, control rod and servomotor elements for changing blade pitch but without the conventional rotating and non-rotating scissors for reacting swashplate torque. This is accomplished by the use of rotating and non-rotating walking beams and combination torque reacting control rods between the walking beams and the rotatable and non-rotatable swashplate elements. Means are also disclosed for shimming the rotatable walking beams to achieve pre-track adjustment of the pitch of individual blades.

Abstract: An analog mixer for a helicopter rotor control system mounted for tilting motion about a variable tilt axis and connected to the rotor control swashplate to cause synchronous tilting and including means to impart tilt generating control inputs to the analog mixer, and means to vary the position of the analog mixer tilt axis as a function of helicopter speed to thereby vary the phase angle of the helicopter rotor without imparting control inputs to the rotor control swashplate.

Abstract: A jet aircraft is equipped with powered helicopter type rotor blades and control mechanisms whereby it can take off and land vertically, yet in horizontal flight can operate at speeds and altitudes typical of jet aircraft. The rotor blades are foldably retractable to a compact locked, trailing position for horizontal travel and are readily unfoldable by a manually operated control mechanism within the aircraft. While the rotors are rotating, the blade pitch can be selectively controlled and, on power failure, will be automatically controlled to provide for same direction autogyro rotation. In one form, the wings and stabilizers are tiltable between substantially horizontal positions for normal horizontal flight and substantially vertical positions for vertical flight. The craft is ground supported by flexible legs.