Abstract: A pitch actuation system for a turbomachine propeller, comprising an actuator with a movable portion configured to be connected to blades of the propeller in order to rotate them relative to the blade-pitch setting axes, wherein the actuator is an electromechanical actuator and comprises: blade-pitch control having a transmission screw rotated about an axis; a nut through which the transmission screw passes; and a member configured to engage with the blades in order to move the blades, wherein the nut is connected to the member via a decoupler configured such that a translational movement of the nut causes a translational movement of the member, but rotational movement of the member does not cause rotational movement of the nut.

Abstract: A pitch actuating system for a turbomachine propeller including an actuator having a movable portion configured to be connected to propeller blades for displacement thereof in rotation with respect to the pitch axes of the blades. A first pitch control system for the blades, includes a first transmission screw movable in rotation, a first nut traversed by the first transmission screw and configured to cooperate with the blades for their displacement, an auxiliary system for feathering the blades, which comprise a second fixed transmission screw, a second nut traversed by the second transmission screw and movable in translation on the second nut, and wherein the pitch actuation system is configured so that a translational movement of the second nut causes a translational movement of the first transmission screw.

Abstract: A pitch actuation system for a turbine engine propeller includes an actuator with movable part configured to rotate the blades of the propeller relative to the blade pitch axes. The actuator includes a transmission screw that is rotatable and movable in translation along a longitudinal axis, and a nut that engages the screw to move in translation along the longitudinal axis to adjust the pitch of the propeller blades. The actuator further includes non-rotatable decoupler for decoupling the rotation between the propeller and the nut. A blade feathering device has at least one electric drive motor and is configured to translate a member along the longitudinal axis. A blade pitch control device includes at least one electric motor configured to drive a rotor about the longitudinal axis, wherein that rotation rotates the screw and transmits translation of the member.

Abstract: A pitch change mechanism for a bladed rotor includes a driving sleeve, a drive shaft, a first pitch-changing element, a second pitch-changing element, and a plurality of blade drive gears. The driving sleeve has, in axial sequence, a first helical connection portion and a second helical connection portion. The driving sleeve is positioned concentrically with and surrounding the drive shaft. The first pitch-changing element has a first end drivingly engaged with the first helical connection portion, and a first ring gear portion at a second opposite end, while the second pitch-changing element has a first end drivingly engaged with the second helical connection portion, and a second ring gear portion at a second opposite end. The plurality of blade drive gears are arranged in a circumferential array around a longitudinal axis of the drive shaft.

Abstract: A gas turbine engine assembly includes, among other things, a clutch configured to move from a first position to a second position in response to rotation of a gas turbine engine fan at a speed greater than a threshold speed. Whether the clutch is in the first position or the second position, the clutch permits rotation of the gas turbine engine fan in a first direction. When the clutch is in the first position, the clutch limits rotation of the gas turbine engine fan only in an opposite, second direction. The clutch is disposed within a compartment that is accessible and removable via removal of an aft engine cover structure. The clutch is removable on-wing.

Abstract: Described herein is a system for increasing the robustness of a sealing surface and eliminating an expensive plating operation. The system includes an axially rotatable object comprising a first material that is subject to corrosion. The system also includes a radial shaft seal positioned radially outward from the axially rotatable object. The system also includes a sleeve coupled to the axially rotatable object, positioned between the axially rotatable object and the radial shaft seal and comprising a second material that is corrosion resistant.

Abstract: A control system includes a power actuator coaxial with the axis of rotation of the propeller, and a transmission device connecting the power actuator to pivots, of the blades to be controlled, arranged substantially radially with respect to the axis of rotation. The actuator is a rotary jack whose mobile part rotates about the axis of rotation and is connected to the transmission device by a mobile mechanical connection which transforms the rotation imparted by the mobile part of the jack about the axis of rotation into a rotation of the blades about the axes of the pivots which are perpendicular to the axis of rotation.

Abstract: The present invention is a device for controlling torque output of wind turbine blades, which can effectively keep the torque output of the blades of a wind turbine in constant and maintain the output stability of the wind turbine further. The present invention does not need any external power input and measurement signal generated from other devices and is a fully passive device which keeps the output of a wind turbine in constant. When the wind speed varies in the rated range, the present invention would adjust the pitch angle of the blades correspondingly and keep the output of a wind turbine in constant. When the wind speed is not in the rated range, the present invention would stop the rotation of the blades, so the output stability of the wind turbine can be kept, and the durability of the wind turbine can also be maintained.

Abstract: A wind turbine system includes turbine blades (16) that turn a low speed shaft (18). A shrink disc coupling (24) radially connects the low speed shaft to a low speed gear box input shaft (22). A brake (26) for the gear box input shaft is operatively connected with the coupling. At least one circuit including a processor controls the brake to keep torsional force on the gear box input shaft below a threshold. The at least one circuit is associated with sensors that can sense conditions away from the gear box input shaft. The at least one circuit can determine when a current condition exists which can cause the threshold to soon be exceeded if preventive braking is not timely applied to the gear box input shaft. The current condition can include a sensed weather condition that is approaching the wind turbine system.

Abstract: An actuator device for actuating a swivel-mounted member carried by a rotor of a propulsion engine including: at least one electricity source; an electric actuator for swiveling the swivel-mounted member; a power supply circuit connecting the electricity source to the actuator; and an inertial device connected to the power supply circuit, the inertial device configured to convert electrical energy coming from the power supply circuit into mechanical energy, to store the mechanical energy, and to convert the mechanical energy into electrical energy for the power supply circuit.

Abstract: The invention relates to a mobile rotor locking device for locking a rotor of a wind turbine, the rotor locking device being designed to lock a rotor in such a way that it is prevented from rotating about a horizontal axis, and that a longitudinal axis of a rotor blade is fixed in a vertical plane. The invention also relates to a kit and a locking member for a mobile rotor locking device and to a method for locking a rotor of a wind turbine. According to the invention, the rotor locking device is characterized in that the rotor locking device is designed to fix a main shaft, on which a rotor is disposed torsionally stiffly, so that it is prevented from rotating about its longitudinal axis.

Abstract: A brake system for a ram air turbine (RAT) causes the RAT to slow or lock if the RAT achieves an over-speed condition with a centrifugal force operated trigger system that actuates a compression type brake pack to slow or lock the turbine hub.

Abstract: A helicopter rotor brake assembly for arresting rotational movement of a main rotor drive shaft, wherein the helicopter rotor brake assembly is mechanically interconnected with the main rotor drive shaft through a main transmission. The helicopter rotor brake assembly includes a brake disc rotatably mounted about an axis, wherein the brake disc is mechanically interconnected with the main transmission, and wherein the brake disc defines a plane substantially perpendicular to the axis. A bracket is provided for disposal in combination with the brake disc, and comprises a beam member defining a first end and a second end, a first arcuate member connected to the first end of the beam member and disposed substantially co-planar with the plane defined by the brake disc, and a second arcuate member connected to the second end of the beam member and disposed substantially co-planar with the plane defined by the brake disc.

Abstract: A control mechanism is provided which feathers the propeller blade pitch during stopping and stores restart energy in the blade pitch governor mechanism. Deceleration to the feathered mode is aided by the airstream. During restart, excess stored energy is used to increase reliability, but is then dissipated mechanically, as by a flywheel mechanism, to maintain low internal impact stresses. More specifically, where single governor spring is used for controlling the pitch of all propeller blades, a braked ball screw device is used to compress that spring during stoppage. Upon restart, the governor spring expands and causes blade pitch change. The ball screw arrangement then dissipates a large portion of the excess energy through torque transmission to mechanical components.

Abstract: A lightweight and compact apparatus is provided for altering and controlling the pitch of a plurality of rotating blades during rotation using a mechanical clutch and gear arrangement driven by a rotational speed differential between the blade drive shaft and the blades. A first set of clutches and gears controls the direction of rotational power to the pitch change mechanism and is disengaged from rotation when desired blade pitch is established. A second set of clutches and gears controls the speed of rotational power applied to the pitch change mechanism. This pitch change mechanism includes a failsafe capability against pitch change through disengagement of the directional clutches except when needed, and an inherent rotational lock resulting from the rate change clutches' bias to simultaneous engagement. Variation of that speed of rotational power permits coarse and fine pitch adjustments at variable rates.

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

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

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

Abstract: Fault-tolerant apparatus for controlling first and second input members of a mechanical actuator includes first and second electrical machines and at least two controllers. The first and second electrical machines, which apply braking forces to the first and second input members, respectively, are provided with stators having pluralities of isolated phase windings. Each controller is coupled to a phase winding of the first electrical machine, and also to a phase winding of the second electrical machine. Any one controller can excite the first electrical machine to apply the braking force to the first input member or the second electrical machine to apply the braking force to the second input member.

Abstract: A pitch controller (10) for controlling the pitch of a plurality of blades (11) of a fan powered by a turbine propulsion engine, with a pitch adjusting device (16) having an input (18) for controlling the pitch of the blades. An input drive shaft (15) provides rotary power from the free turbine to the first input of a transmission (14). The transmission also has a second input (25) controlling the input to the pitch adjusting device, a first output (18) which is the input to the pitch adjusting device and a second output (21) which is applied to a rotary power device (20). Input power from the free turbine is provided to the rotary power device by the transmission which in response to a pitch control signal (28) causes the second input to rotate at a speed different from the first input thereby changing the pitch of the blades in proportion to the pitch control signal.

Abstract: An adjusting device for adjustable rotor vanes of a machine rotor including a first gear wheel (34) on a machine shaft (2) and a second gear wheel (44) on an adjusting shaft (4), whereby a relative rotation between the machine shaft and the adjusting shaft can be initiated through a transmission (38) by either of two braking devices (12, 22). The adjusting device of the invention makes it possible to adjust the rotor vanes with a simple construction and with a good degree of efficiency while simultaneously providing good accessibility for assembly and service. A further brake (40, 41) is provided between the transmission (38) and the machine shaft (2) or the adjusting shaft (4) to maintain synchronous rotation of the adjusting shaft (4) with the machine shaft (2) during normal operation, i.e., so long as no adjustment of the rotor vanes (64) is to take place.

Abstract: A drag operated collective pitch control system is provided for gyroplane rotary wing aircraft. The system employs drag surfaces which are selectively engaged while the hub is rotating to actuate the system. Each blade mount is provided with a feathering pivot. Pinion gears control the pitch of each blade, and the pinions, mounted on the hub, are engaged by a pair of ring gears, also carried on the hub. To operate the system, either one or the other of the ring gears, to which the drag surfaces are coupled, is engaged by suitable drag means. The pitch of all the blades is thereby adjusted simultaneously.

Abstract: Complexity, and thus reliability difficulties, are avoided in a ram air turbine including a stationary shaft 14 defining an axis of rotation 16. A hub 24 is journalled on the shaft 14 and in turn movably mounts at least one blade 38 for positioning between a feathered position and a plurality of positions of different pitch. A selectively operable brake 96, 100, 116 is mounted on the shaft 14 and a screw 112 is journalled on the shaft for rotation about the axis 16. The screw has a head 114 engageable by the brake 96, 100, 116 and exterior, widely spaced threads 120. A governor plate 50 is disposed about the shaft 14 and includes a sleeve 124 with widely spaced internal threads 126 surrounding the screw 112. The governor plate is connected to the blades 38 to position the same in response to movement of the governor plate 50. A torsional spring 130 is connected to the screw 112 to effect rotation of the same when the brake 90, 100, 116 is disengaged.

Abstract: Apparatus and methods for adjusting the pitch of a fluid reactive blade member carried upon a rotor in response to a speed difference between the rotor and a reference speed shaft.

Abstract: An apparatus for controlling pitch variations of the blades of a propeller. A first planetary gearset includes a sun gear, a ring gear and at least one planetary gear meshed with the sun and ring gears, the sun gear being statically grounded. A second planetary gearset is stacked in concentric juxtaposition with the first planetary gearset and includes a sun gear, a ring gear and at least one planetary gear meshed with the sun and ring gears. The planetary gears of the respective gear sets are coupled for conjoint orbiting about their respective sun gears. A main rotor drive input is coupled to the ring gear of the second planetary gearset. A blade actuator output is coupled to the ring gear of the first planetary gearset to be rotated thereby.

Abstract: A windpower system includes a support and a turbine having a shaft rotatively mounted to the support. The turbine has variable pitch blades whose pitch is controlled by the differential motion of a rotary control shaft coaxial with the turbine shaft and the turbine shaft itself so that the blade pitch can be varied by a stationary motor without requiring any slip rings or other such wear-prone couplings. In the event of a power failure, rotary motion of the control shaft is prevented so that the turbine blades are feathered solely due to the force developed by the rotating turbine. Also, if the turbine is used to generate electrical power, an induction generator coupled to the turbine shaft is employed whose shaft speed is indicative of generator output power.

Abstract: In a variable pitch fan assembly having a plurality of fan blades mounted in a rotor for rotation about their longitudinal axes and a drive shaft for rotatively driving the rotor, the pitch varying mechanism has a planetary gear train connected to each fan blade to rotate the latter to change the pitch or angle of attack of the blades, actuator means for effecting bi-directional rotation of the planetary gear train and a no-back, bi-directional brake interposed between the actuator means and the planetary gear train to transmit pitch-changing rotation from the actuator means to the planetary gear train and lock the planetary gear train to the rotor and prevent transmission of blade torque loads to the actuator means during steady state operation when no blade pitch-change is being effected.