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Небесная энциклопедия

Космические корабли и станции, автоматические КА и методы их проектирования, бортовые комплексы управления, системы и средства жизнеобеспечения, особенности технологии производства ракетно-космических систем

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Мониторинг СМИ

Мониторинг СМИ и социальных сетей. Сканирование интернета, новостных сайтов, специализированных контентных площадок на базе мессенджеров. Гибкие настройки фильтров и первоначальных источников.

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Поддерживает ввод нескольких поисковых фраз (по одной на строку). При поиске обеспечивает поддержку морфологии русского и английского языка
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Применить Всего найдено 2192. Отображено 100.
31-05-2012 дата публикации

Fluid Turbine Having Optimized Blade Pitch Profiles

Номер: US20120134820A1
Автор: Jason Daniel Cormey, Robert Clifton Vance
Принадлежит: Broadstar Investment Co LLC, Broadstar Wind Systems Group LLC

A fluid turbine comprising a rotor, having an axis of rotation, comprising at least two rotor blades disposed at a radius from the axis of rotation, each rotor blade having a pitch axis and a variable pitch angle. The fluid turbine comprises a mechanism operable to control the pitch angle of at least one rotor blade about its pitch axis and to vary the pitch angle of the rotor blade between various pitch angles as the blade moves radially about the axis of rotation of the rotor.

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Номер записи: 1
11-04-2013 дата публикации

ADAPTIVE TWIST SYSTEM FOR A ROTOR BLADE

Номер: US20130089422A1
Автор: Brunken, JR. John E.
Принадлежит: Bell Helicopter Textron Inc.

The system of the present application includes an adaptive twist system for a rotor blade. The adaptive twist system includes a slider mechanism coupled to a spar and to a skin. The slider mechanism provides structural connectivity between the spar and the skin while also selectively translated the skin relative to the spar, thereby causing the rotor blade to twist. A control system is used to operate the slider mechanism so that the rotor blade is automatically twisted into the optional shape during changes in flight modes. 1. An adaptive twist system for a rotor blade , the adaptive twist system comprising:a slider mechanism coupled to a spar and to a skin, the slider mechanism configured to provide structural connectivity between the spar and the skin;an actuator configured to drive the slider mechanism;wherein the slider mechanism is configured to translate the skin relative to the spar, causing the rotor blade to twist.2. The adaptive twist system according to claim 1 , wherein the skin is a lower skin.3. The adaptive twist system according to claim 1 , the slider mechanism comprises:a screw drive shaft;a fixed collar coupled to the skin;a threaded collar coupled to the spar;wherein the threaded collar includes receiving threads such that rotation of the screw drive shaft causes the threaded collar to translate relative to the fixed collar.4. The adaptive twist system according to claim 4 , further comprising:a spar adapter located between the threaded collar and the spar.5. The adaptive twist system according to claim 4 , further comprising:a skin adapter located between the fixed collar and the skin.6. The adaptive twist system according to claim 1 , wherein the slider mechanism is configured to translate the skin relative to the spar in a spanwise direction.7. The adaptive twist system according to claim 4 , wherein the fixed collar includes a bearing to allow a first portion of the collar to rotate along with the screw drive claim 4 , while a second portion ...

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Номер записи: 2
25-04-2013 дата публикации

TURBOMACHINE BLADE INCIDENCE CONTROL SYSTEM AND TURBOMACHINE

Номер: US20130101419A1
Автор: Bocquet Denis Louis, Frantz Caroline, Le Gouellec Gilles, Marly Pascal
Принадлежит: SNECMA

Turbomachine blade incidence control system including a fluidic cylinder with a first and a second chamber and having a pressurized fluid network adapted to selectively supply pressurized fluid to the first and/or the second chamber, the fluid network having one fluid routing device having a first normal position and a second protection position. The fluidic cylinder includes a fluid inlet positioned to be in fluid communication with the first chamber when the fluidic cylinder is in the blocked position, the routing device being adapted to set up a fluid communication between the inlet and the second chamber when it is in the protection position and to inhibit the fluid supply to the inlet when it is in the normal position. 1. A turbomachine blade incidence control system , comprising:a fluidic cylinder adapted to modify the incidence of a turbomachine blade, comprising a first upstream chamber and a second downstream chamber with first and second fluid inlets respectively,a pressurised fluid network adapted to selectively supply pressurised fluid to the first and/or the second chamber of the fluidic cylinder through the first and/or the second inlet, the fluid network comprising at least one fluid routing device adapted to modify the fluid supply to at least the first chamber, the routing device having a first so-called normal position in which the fluid supply to the first chamber is said to be normal, and a second so-called protection position in which the fluid supply to the first chamber is adapted to inhibit operation of the fluidic cylinder in a predefined so-called inhibit position,wherein the fluidic cylinder comprises at least a third fluid inlet positioned to be in fluid communication with the first chamber when the fluidic cylinder is in the inhibit position, the routing device being adapted to set up a fluid communication between the third inlet and the second chamber through the fluid network when it is in the protection position, and to inhibit the ...

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Номер записи: 3
09-05-2013 дата публикации

Turbine

Номер: US20130115084A1
Автор: Capan Rahni Oguz
Принадлежит:

The turbine (T) of the invention comprises at least one rotor () which can rotate in connection with at least one base (); at least one blade () which rotates said rotor () by fluid flow (F). Said blade () has such a form that it can slide in at least one channel () within the rotor (). When the blade () reaches to backside (B) of the rotor (), it continues rotating the rotor () by the effect of flow (F) after it slides towards forepart (E) of the rotor (). In case many blades () and rotors () are used in the turbine (T) of the invention, some rotors () can be disconnected from other rotors () when desired. Therefore, that stable rotation speed is provided from the rotors () without need for using brake system in the turbine (T) and electric energy on stable level is produced by a generator connected to said rotors (). 1. A turbine (T) characterized in that it comprises{'b': 2', '3, 'at least one rotor () which can rotate in connection with at least one base ();'}{'b': 1', '2', '2', '5', '2', '2', '2, 'at least one blade () which rotates each rotor () by fluid flow (F), which reaches to forepart (E) of the rotor () by sliding through at least one channel () within a rotor () after it reaches to backside (B) of the rotor () by rotation of the rotor ().'}212. A turbine (T) according to characterized in that the blade () slides vertically (I-I) with respect to rotation axis (X) of the rotor ().38411. A turbine (T) according to characterized in that there are provided crimps () on two tips () of the blade () claim 1 , whose direction is in reverse rotation direction of the blade ().421. A turbine (T) according to characterized in that on the rotor () there is provided a mechanism which slides the blade () to forepart.5122. A turbine (T) according to characterized in that in case many blades () and rotors () are used claim 1 , there are detachable connections between the rotors ().61. A turbine (T) according to characterized in that the blades () are provided in angled ...

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Номер записи: 4
30-05-2013 дата публикации

BLADE-PITCH CONTROL SYSTEM WITH FEEDBACK SWASHPLATE

Номер: US20130136596A1
Автор: Stamps Frank B.
Принадлежит: Bell Helicopter Textron Inc.

A blade-pitch control system for controlling a pitch angle of blades on a rotor has an input swashplate assembly having non-rotating and rotating portions, the rotating portion being operably connected to blade grips. A feedback swashplate assembly has non-rotating and rotating portions, the rotating portion being connected to the yoke for movement with the yoke during flapping of the yoke. Linear actuators connect the non-rotating portion of the input swashplate assembly to the non-rotating portion of the feedback swashplate assembly. Motion of the yoke during flapping causes a corresponding motion of the feedback swashplate assembly and input swashplate assembly for providing selected pitch-flap coupling between flapping motion of the yoke and pitch motion of the grips. 1. A blade-pitch control system for controlling a pitch angle of each of a plurality of blades on a rotor , the blades being rotatably connected with blade grips to a yoke , the control system comprising:an input swashplate assembly having a non-rotating portion and a rotating portion, the rotating portion of the input swashplate assembly being operably connected to the blade grips;a feedback swashplate assembly having a non-rotating portion and a rotating portion, the rotating portion of the feedback swashplate assembly being coupled to the yoke and rotatably coupled to a mast, the feedback swashplate being configured to move in connection with the yoke during flapping of the yoke; andlinear actuators connecting the non-rotating portion of the input swashplate assembly to the non-rotating portion of the feedback swashplate assembly, so as to transfer movement between the input swashplate and the feedback swashplate;wherein the pitch angle of the plurality of blades on the rotor are adjusted in relation to movement of the input swashplate.2. The blade-pitch control system of claim 1 , further comprising:an idler connected between each linear actuator and the non-rotating portion of the feedback ...

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Номер записи: 5
06-06-2013 дата публикации

System and method for improving transition lift-fan performance

Номер: US20130140404A1
Автор: Robert Parks
Принадлежит: Aurora Flight Sciences Corp

A system and method enabled to increase efficiency during a VTOL aircraft's transition. A VTOL aircraft enabled to operate multiple lift fans arranged into separately controllable groups, wherein the VTOL aircraft initially has vertical flight but transitions to horizontal flight. A first group of lift fans may be kept at full throttle, a second group of lift fans may be throttled to balance thrust and/or weight, and a third group of lift fans may be shut off.

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Номер записи: 6
13-06-2013 дата публикации

Turbomachinery Having Self-Articulating Blades, Shutter Valve, Partial-Admission Shutters, and/or Variable-Pitch Inlet Nozzles

Номер: US20130145753A1
Автор: Becker Frederick E., DiBella Francis A., Fairman Kevin D., Gofer Alexander
Принадлежит: CONCEPTS ETI, INC.

An axial-flow turbine assembly that includes one or more features for enhancing the efficiency of the turbine's operation. In one embodiment, the turbine assembly includes a turbine rotor having blades that adjust their pitch angle in direct response to working fluid pressure on the blades themselves or other part(s) of the rotor. In other embodiments, the turbine assembly is deployable in an application, such as an oscillating water column system, in which the flow of working fluid varies over time, for example, as pressure driving the flow changes. In a first of these embodiments, the turbine assembly includes a valve that allows the pressure to build so that the flow is optimized for the turbine's operating parameters. In a second of these embodiments, one or more variable-admission nozzle and shutter assemblies are provided to control the flow through the turbine to optimize the flow relative to the turbine's operating parameters. 1. A turbomachine , comprising: a blade support designed and configured to rotate about said rotational axis; and', a blade having a leading edge and a pivot axis extending substantially parallel to said leading edge; and', 'an articulation mechanism engaged with said blade in a manner that controls pivoting of said blade about said pivot axis in response to changes in pressure of the working fluid., 'a plurality of self-articulating-blade assemblies engaged with said blade support and each including], 'a turbine comprising a rotor having a rotational axis and designed and configured to be driven by a working fluid, said turbine comprising a rotor that includes2. A turbomachine according to claim 1 , wherein said articulation mechanism is designed and configured to directly respond to pressure of the working fluid on said blade.3. A turbomachine according to claim 2 , wherein said articulation mechanism includes a rotation biaser designed and configured to:bias rotation of said blade about said pivot axis to a base position; andpermit ...

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Номер записи: 7
11-07-2013 дата публикации

ELECTRIC POWER SUPPLY FOR APPARATUSES SUPPORTED BY THE ROTOR OF AN AIRCRAFT ENGINE

Номер: US20130177421A1
Автор: De Wergifosse Eric, Duval Cedric
Принадлежит: HISPANO-SUIZA

An aircraft engine including: a stator; a main shaft; a first rotor; a second rotor; a transmission mechanism; a first electrical apparatus supported by the first rotor and a second electrical apparatus supported by the second rotor; at least one first field winding supported by the stator; a control unit configured to circulate direct electric current in the first field winding; at least one first armature winding supported by the first rotor and connected to the first electrical apparatus and at least one second armature winding supported by the second rotor and connected to the second electrical apparatus. 113-. (canceled)14: An aircraft engine comprising:a stator;a main shaft, a first rotor, and a second rotor;a transmission mechanism configured to convert rotation of the main shaft into rotation of the first rotor in a first direction and into rotation of the second rotor in a second direction opposite the first direction;at least one first electrical device carried by the first rotor and at least one second electrical device carried by the second rotor;at least one first field winding carried by the stator;a control unit configured to cause direct electric current to flow in the first field winding; andat least one first armature winding carried by the first rotor and connected to the first electrical device and at least one second armature winding carried by the second rotor and connected to the second electrical device;the first field winding being disposed between the first armature winding and the second armature winding, in one position of the main shaft.15: An engine according to claim 14 , in which the first field winding has an axis oriented parallel to the axis of rotation of the main shaft.16: An engine according to claim 14 , in which the control unit is fed by a permanent magnet generator.17: An engine according to claim 14 , in which the control unit is fed by an onboard network.18: An engine according to claim 14 , in which the control unit is ...

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Номер записи: 8
18-07-2013 дата публикации

Hydraulic device of a control device, such as a blade pitch-change device

Номер: US20130180397A1
Автор: Alain Francois Jean Lavie, Frederic Brettes
Принадлежит: SNECMA SAS

A hydraulic device includes a body, a piston rod configured to be actuated by a pressurised hydraulic fluid, and a first drainage channel for externally draining an internal leakage of hydraulic fluid in the device. The device includes a second drainage channel for externally draining the internal leakage of hydraulic fluid in the device, the first and second channels being oriented in two different directions and each of the channels communicating at one of the ends thereof inside the body of the device.

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Номер записи: 9
01-08-2013 дата публикации

Device and Method for Reducing Loads

Номер: US20130195654A1
Автор: Berger Guenter, Breidert Joachim, Buchtala Boris, Knoblauch Volker, Schmidt Sebastian, Schnurr Bernd, Zimmermann Stefan
Принадлежит: ROBERT BOSCH GMBH

A device for reducing loads in a drive train of a wind turbine includes a machine support. The wind turbine includes a sensor means, a controllable damper means, an actuating means. The sensor means is configured to detect at least one variable characterizing vibrations and/or misalignments in the drive train. The controllable damper means is configured to produce at least one adjusting torque which compensates at least one torque associated with the load in the drive train. The actuating means is configured to actuate the damping means based on the at least one variable detected by the sensor means. 1. A device for reducing loads in the drivetrain of a wind turbine generator system with a machine carrier , comprising:a sensor means configured to detect at least one variable characterizing vibrations and/or misalignments in the drivetrain;an activatable damping means configured to generate at least one adjusting torque, which compensates for at least one torque associated with the load in the drivetrain; andan activating means configured activate the damping means on the basis of the at least one variable detected by the sensor means.2. The device as claimed in claim 1 , wherein the damping means includes an actuator means claim 1 , by which an activatable movement of at least one element of the drivetrain in relation to the machine carrier can be brought about.3. The device as claimed in claim 1 , wherein the damping means includes a braking means claim 1 , by which an activatable braking of a movement of at least one element of the drivetrain in relation to the machine carrier can be brought about.4. The device as claimed in claim 2 , wherein the movement is a rotation of the at least one element about an axis of rotation of the drivetrain.5. The device as claimed in claim 2 , wherein the movement is a raising or lowering of at least one element in relation to the machine carrier.6. The device as claimed in claim 1 , wherein the sensor means includes speed claim 1 ...

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Номер записи: 10
08-08-2013 дата публикации

HYDRAULIC DEVICE FOR CHANGING THE PITCH OF A PROPELLER

Номер: US20130199167A1
Автор: Brettes Frédéric, Lavie Alain François Jean, Raulin Dominique
Принадлежит: SNECMA

A hydraulic device for changing the pitch of a propeller including a piston rod actuated by a hydraulic fluid, the piston rod including at its end a clevis mount able to provide a connection for transmitting the movements of the piston rod so as to change the pitch of at least one propeller, a thread nut held in position on the clevis of the piston rod by a fastener, the nut being able to collaborate with a threaded rod in order to provide a connection. 1. A hydraulic device for changing a pitch of a propeller comprising:a piston rod configured to be actuated by a hydraulic fluid, said piston rod comprising at its end a clevis configured to provide a connection for transmitting the movements of said piston rod so as to change the pitch of at least one propeller, anda threaded nut held in position on said clevis of said piston rod by a fastener, said nut being able to collaborate with a threaded rod in order to provide a connection.2. The hydraulic device for changing the pitch of a propeller according to claim 1 , wherein said threaded nut is a self-locking nut.3. The hydraulic device for changing the pitch of a propeller according to claim 1 , wherein said fastener is formed by the cooperation of a metallic plate integral with said threaded nut and an interface metal part integral with said clevis comprising an elastic device configured to receive and retain said metallic plate.4. The hydraulic device for changing the pitch of a propeller according to claim 3 , wherein said elastic device is formed by elastic lugs each comprising at least one slot.5. The hydraulic device for changing the pitch of a propeller according to claim 4 , wherein said metallic plate comprises protuberances configured to cooperate with said slots of said elastic lugs by clipping or by stapling.6. The hydraulic device for changing the pitch of a propeller according to claim 1 , comprising a blocking mechanism configured to block the rotation of said interface metal part with respect to said ...

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Номер записи: 11
08-08-2013 дата публикации

Oscillating Hydrofoil, Turbine, Propulsive System and Method for Transmitting Energy

Номер: US20130202407A1
Автор: Dumas Guy, Jean Yves, Kinsey Thomas, Lalande Guillaume, Lemay Jean, Plourde-Campagna Marc-Andre
Принадлежит: UNIVERSITE LAVAL

System and method for converting kinetic energy from a fluid flow into mechanical energy, the method comprising the steps of: a) providing a turbine including first and second hydrofoils, each of the hydrofoils being able to move lin-early in a heaving motion, and being able to oscillate about a spanwise axis in a pitching motion, said heaving and pitching motions being quasi-si-nusoidal, b) coupling the heaving motions of the first and second hydrofoils to the pitching motions of the second and first hydrofoils respectively, with the pitch-heave motion phase being substantially equal to the inter-hydrofoil phase, the heaving motion of one of the hydrofoils thereby driving the pitching motion of the other hydrofoil; and c) transforming the heaving motions of the hydrofoils into a rotational movement of a rotatable shaft, with linear-to-rotary transmission means. 1. A turbine for converting kinetic energy from a fluid flow into mechanical energy by driving a rotatable shaft , the turbine comprising:a support structure; for a given one of said hydrofoils, the heaving and pitching motions are out of phase by a pitch-heave motion phase, and', 'the respective heaving motions of the first and second hydrofoils are out of phase by an inter-hydrofoil phase; and, 'first and second hydrofoils extending from said support structure, each hydrofoil being slidably and rotatably connected to said structure, for allowing each of the hydrofoils to move linearly in a heaving motion, and to oscillate about a spanwise axis in a pitching motion; said heaving and pitching motions being quasi-sinusoidal, whereina heaving-to-pitching assembly, for coupling the heaving motions of the first and second hydrofoils to the pitching motions of the second and first hydrofoils respectively, the pitch-heave motion phase being substantially equal to the inter-hydrofoil phase, the heaving motion of one of the hydrofoils thereby driving the pitching motion of the other hydrofoil; anda linear-to-rotary ...

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Номер записи: 12
08-08-2013 дата публикации

FEATHERING PROPELLER WITH BLADE DAMPENING AT FORWARD AND BACKWARD MOTION AND BLADES PITCH CONTROL DURING BACKWARD MOTION

Номер: US20130202436A1
Автор: BIANCHI Massimiliano
Принадлежит: MAX PROP S.R.L.

Disclosed is a variable pitch propeller having a blade pivoted rotatably to a cylindrical propeller casing, a drive shaft, coupled to a propulsor and positioned coaxially inside the propeller casing, a kinematic mechanism coupled to the drive shaft, or to the propeller casing, and to the blade, for adjusting the rotary motion of the blade about its axis of pivoting to the propeller casing, and means for coupling in rotation the drive shaft to the propeller casing. The propeller provides a non-null angular range of relative rotation of the blade about its axis of pivoting, with respect to the propeller casing, or vice versa. The means for coupling in rotation the drive shaft to the cylindrical propeller casing include an elastic element interposed between the drive shaft and the cylindrical casing. 1. A variable pitch propeller of the type comprising at least one blade pivoted rotatably to a cylindrical propeller casing , a drive shaft , coupled to a propulsor and positioned coaxially inside said propeller casing , a kinematic mechanism coupled to said drive shaft , or to said propeller casing , and to said at least one blade , for adjusting the rotary motion of said at least one blade about its axis of pivoting to said propeller casing , and means for coupling in rotation said drive shaft to said propeller casing , said propeller being configured to provide at least one non-null angular range of relative rotation of said at least one blade about its axis of pivoting , with respect to said propeller casing , or vice versa , wherein said means for coupling in rotation said drive shaft to said propeller casing comprise at least one elastic element interposed between said drive shaft and said cylindrical casing and at least one intermediate element interposed between said drive shaft and said cylindrical propeller casing , said intermediate element being provided with a first and with a second contact surface with said drive shaft mutually spaced apart by an angular ...

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Номер записи: 13
15-08-2013 дата публикации

Pilot Control System with Compact Gimbal Mechanism

Номер: US20130209256A1
Автор: Linton Bradley D., Yates Travis L.
Принадлежит: Bell Helicopter Textron Inc.

According to one embodiment, a control assembly includes a first gimbal and a second gimbal. The first gimbal is rotatable about a first axis of rotation. The first gimbal comprises a first linkage attachment point offset from the first axis of rotation. The second gimbal is rotatably coupled to the first gimbal and rotatable relative to the first gimbal about a second axis of rotation. The second gimbal comprises a second linkage attachment point offset from the second axis of rotation and a control shaft attachment point. 1. A rotorcraft , comprising:a body;a power train coupled to the body and comprising a power source and a drive shaft coupled to the power source;a rotor system coupled to the power train and comprising a plurality of rotor blades; a post having a top, a bottom, and a body joining the top to the bottom;', 'a first gimbal coupled to inside the body, the first gimbal rotatable about a first axis of rotation, the first gimbal comprising a first linkage attachment point offset from the first axis of rotation;', 'a first linkage coupled to the first gimbal at the first linkage attachment point;', 'a second gimbal rotatably coupled to the first gimbal, the second gimbal rotatable relative to the first gimbal about a second axis of rotation, the second gimbal comprising a second linkage attachment point offset from the second axis of rotation;', 'a second linkage coupled to the second gimbal at the second linkage attachment point;', 'a grip; and', 'a shaft having a first end coupled to the second gimbal and a second end coupled to the grip; and, 'a control assembly, comprisinga rotorcraft control system operable to communicate commands to the rotor system based on movements of the first linkage and the second linkage.2. The rotorcraft of claim 1 , wherein at least part of the first linkage attachment point is coaxial with the second axis of rotation.3. The rotorcraft of claim 1 , wherein at least part of the second linkage attachment point is coaxial ...

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Номер записи: 14
22-08-2013 дата публикации

MECHANISM FOR SYNCHRONOUSLY VARYING PITCH OF A MULTI-BLADE ROTOR

Номер: US20130216380A1
Автор: Liu Jin Peng, Yuan Wei, Zhou Shao Jun
Принадлежит: SHANGHAI GHREPOWER GREEN ENERGY CO. LTD.

A mechanism for synchronously varying pitch of a multi-blade rotor, such as rotors used in wind or hydraulic generator and helicopter is provided in the present invention. Said sync-pitch-varying mechanism for the rotor mainly comprises a bearing a driver, a transmission, a linkage and a control unit, wherein said transmission includes a shaft coupling, a ballscrew, an intermediate cylinder, a driven shaft and a transition cylinder; said linkage includes a link hub, a guide support and multiple links; said control unit includes a speed sensor, a position sensor, a switch and a programmable controller; a rotatory driving force output by said driver through the shaft coupling is transmitted to the driven shaft through a screw-and-nut transmission between the ballscrew and the intermediate cylinder of said transmission so as to drive the driven shaft to move in a linear motion which is then transferred from the driven shaft to the link hub of the linkage through means of the transition cylinder; said controller is configured to enable the driven shaft to move reciprocally within a predefined range of length in order to move the link hub back and forth along the guide support in an axial direction thereof, and therefore multiple bearings for supporting the blades of the rotor are rotatably movable through the multiple links of the link hub Advantageously, the mechanism of the invention has a simple and compact structure, low cost and high reliability, and the operation is easy to be controlled precisely. 1. A mechanism for synchronously varying pitch of a multi-blade rotor having a rotor hub with multiple blades , 'each one of which includes a bearing having an outer ring and an inner ring being rotatably movable with respect to said outer ring,', 'wherein said multiple blades are equal-spaced mounted around said rotor hub through means of corresponding bearing seats,'} 'wherein said transmission includes a shaft coupling, a ballscrew, an intermediate cylinder, a driven ...

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Номер записи: 15
29-08-2013 дата публикации

DEVICE FOR SHIFTING A PROPELLER INTO REVERSE, COMPRISING AN ACTUATOR ACTING ON A CRANK PIN

Номер: US20130224021A1
Автор: Gallet Francois
Принадлежит: SNECMA

A device controlling shifting of a propeller turbine engine into reverse mode, by acting on a shaft for controlling pitch of propellers. The device includes: at least one centrifugal weight arranged to drive the propellers into a flag position thereof under action of the centrifugal force; and an actuator that can rotate the control shaft to shift the pitch of the propellers from a traction mode to a reverse mode, passing through a zero pitch position. The centrifugal weight is in an unstable equilibrium position in relation to action of the centrifugal force when the control shaft shifts the pitch of the propellers through the zero pitch position. Further, an actuation mechanism exerts a torque on the control shaft when the centrifugal weight is in the unstable equilibrium position, to prevent it from staying in this position. 114-. (canceled)15. A device for controlling a shift into reverse of a propeller-type turbomachine , through action on a pitch control spindle that controls a pitch of propellers , the device comprising:at least one bob weight mounted on and so as to project in cantilevered manner beyond the control spindle and configured to drive the propellers toward their feathered position under action of centrifugal force generated by rotation of the turbomachine;an actuator configured to cause the control spindle to turn to shift the pitch of the propellers from a traction mode to a reverse mode, passing via a zero-pitch position; andan actuating means that applies a torque to the control spindle when the control spindle turns to shift the pitch of the blades via a zero-pitch position, so as to prevent the control spindle from remaining in that position.16. The device as claimed in claim 15 , wherein the bob weight is in a position of unstable equilibrium with respect to the action of the centrifugal force when the control spindle causes the pitch of the propellers to pass via the zero-pitch position.17. The device as claimed in claim 15 , wherein the ...

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Номер записи: 16
19-09-2013 дата публикации

DEVICE FOR MONITORING THE FLAPPING AND/OR LAG BEHAVIOR OF A BLADE OF A ROTORCRAFT ROTOR

Номер: US20130243597A1
Автор: Chuc Charles, Imbert Nicolas, Perrin Christophe
Принадлежит: EUROCOPTER

The present invention relates to a rotorcraft rotor () having a plurality of blades () movably mounted on a hub () via blade roots () that are respectively associated therewith. The rotor () is fitted with an information capture appliance having at least one measurement assembly (E) comprising a flexible bar () interposed in engagement at its respective ends between the hub () and a blade root () that is allocated thereto. A strain gauge () formed of a SAW transducer is implanted on the bar () and generates information relative to the bending of the bar () following tilting orientations of the blade root () in flapping (B) and/or in lag (T). 11234. A rotorcraft rotor having a plurality of blades movably mounted on a hub by respective blade roots that are associated therewith , the blades being movable in pivoting about their own axes and about tilting orientations respectively in flapping (B) and in lag (T) , the said rotor being fitted with an information capture appliance having at least one strain gauge for generating information depending on the behavior of the blades in moving about at least any one of the orientations in flapping (B) and/or in lag (T) , wherein the information capture appliance includes at least one measurement assembly (E , E , E , E) having a flexible bar having at least one strain gauge mounted thereon to generate information about the bending of the bar in at least any one of said orientations in flapping (B) and/or in lag (T) , the bar being interposed in engagement at its respective ends between the hub and a blade root that is associated therewith.2. A rotor according to claim 1 , wherein the bar is firmly engaged at its proximal end to the hub and bears slidably against the blade root at its distal end.3. A rotor according to claim 2 , wherein the bar bears against the blade root relative to at least one of said tilting orientations (B claim 2 , T) claim 2 , the bar and the blade root being free to move relative to each other in the ...

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Номер записи: 17
19-09-2013 дата публикации

Rotor Blade Pitch Adjustment Device

Номер: US20130243624A1
Автор: Beckmann Bastian, Laube Martin, Schaefer Wolfgang
Принадлежит:

A rotor blade pitch adjustment device for a wind power installation includes a motor/pump unit whose rotation speed and direction are variable and which is connected for fluid-flow purposes to a hydraulic actuator via a hydraulic open-loop/closed-loop control system. The actuator is mechanically coupled to at least one rotor blade of the wind power installation in order to rotate the rotor blade about its longitudinal axis. An electrical control circuit, which comprises an emergency power supply device, is provided for operation of the motor. 1. A rotor blade pitch adjustment device for a wind power installation , comprising:a motor/pump unit which has a variable direction;a hydraulic actuator which is mechanically coupled to at least one rotor blade of the wind power installation in order to rotate said rotor blade about its longitudinal axis;a hydraulic open-loop/closed-loop controller configured to fluidically connect the motor/pump unit to the hydraulic actuator; andan electric control circuit, comprising an emergency power supply device, of the motor/pump unit.2. The rotor blade pitch adjustment device as claimed in claim 1 , wherein the emergency power supply device includes an accumulator or a plurality of capacitors which claim 1 , in the event of a predetermined drop in voltage in the electric control circuit claim 1 , are configured to be connected thereto.3. The rotor blade pitch adjustment device as claimed in claim 2 , wherein the emergency power supply device is configured to supply power to the electric control circuit and to the motor/pump unit.4. The rotor blade pitch adjustment device as claimed in claim 1 , further comprising:a hydraulic emergency operating device configured to supply the hydraulic actuator with hydraulic pressure energy in the event of a failure or of reduced power of the motor/pump unit.5. The rotor blade pitch adjustment device as claimed in claim 1 , wherein the hydraulic actuator is a hydraulic piston cylinder unit.6. The ...

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Номер записи: 18
03-10-2013 дата публикации

PITCH LOCK SYSTEM

Номер: US20130259688A1
Автор: SORENSEN Carsten Bendix
Принадлежит: ENVISION ENERGY (DENMARK) APS

A pitch lock system for a wind turbine with a rotor, at least one pitchable blade and a interface having a pitch bearing system with a first bearing ring, a second bearing ring and a pitch drive installed at a support plate at a structural part connected to the first bearing ring and interacting with teeth on a toothed element, where the toothed element is in fixed connection with the second bearing part. The pitch lock system has at least a base plate and an arrangement for fastening the base plate indirectly to the first bearing ring and a locking pawl that can be fasten to the base plate with an element on the locking pawl interacting with the toothed element. 1. A pitch lock system for a wind turbine with a rotor , the rotor comprising at least one pitchable blade , the at least one pitchable blade being connected to the rotor and comprising an outer blade part and an inner blade part , where the blade parts are interconnected at an interface , the interface comprising a pitch bearing system comprising a first bearing ring , a second bearing ring and a pitch drive , the pitch drive being installed at a support plate on a structural part that connected to the first bearing ring , the pitch drive comprising means for interacting with at least two of a number of teeth on a toothed element , where the toothed element is in fixed connection with the second bearing ring , the pitch bearing system being arranged for pitching at least a part of the blade in relation to the rotor about a first axis , where the pitch lock system comprises”at least a base plate andmeans for fastening the base plate indirectly to the first bearing ring,a locking pawl andmeans for fastening the locking pawl to the base plate,wherein the locking pawl comprises means for interacting with at least one of the teeth on the toothed element,wherein the base plate, when installed on a pitch bearing system, is rotatable about a second axis, the second axis being parallel to the first axis, and ...

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Номер записи: 19
17-10-2013 дата публикации

Method of Extending the Service Life of Used Turbocharger Compressor Wheels

Номер: US20130272889A1
Автор: Cornell Sean Olen, Fei Dong, McKimpson Marvin Grendel, Tian Yong
Принадлежит: CATERPILLAR INC.

A method is provided for extending the service life of a used metallic compressor wheel having a damaged surface. The method generally comprises the steps of inspecting the used compressor wheel for material discontinuities such as fatigue cracks and, if fatigue cracks exceeding a predetermined length are not present, renewing the used compressor wheel such as by peening. The inspection process comprises conducting a non-destructive examination of the used compressor wheel to detect cracks larger than those which would fall generally within the compressive stress zone that is generated by peening. 1. A method for extending the service life of a used metallic compressor wheel having a hub and blades radiating outward from the hub and affixed to the hub along blade roots , the hub having a curved front face to which the blades are attached and a curved back face , the method comprising the steps of:inspecting the used compressor wheel for material discontinuities; andif a material discontinuity exceeding a predetermined length is detected, discarding the used compressor wheel; butif such a material discontinuity is not detected, renewing regions of the used compressor wheel subject to the highest fatigue loadings.2. The method of wherein:the inspecting step comprises inspecting the back face using ultrasonic inspection.3. The method of wherein:the inspecting step comprises inspecting the blade roots using eddy current testing.4. The method of wherein:the inspecting step further comprises inspecting the blade roots using eddy current testing.5. The method of wherein the predetermined length is about 200 microns.6. The method of wherein the predetermined length is about 100 microns.7. The method of wherein the predetermined length is zero microns.8. The method of wherein claim 2 , after the inspecting step claim 2 , if a material discontinuity is detected claim 2 , then the compressor wheel is discarded.9. The method of wherein the regions of the used compressor wheel ...

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Номер записи: 20
31-10-2013 дата публикации

DYNAMIC TURBINE SYSTEM

Номер: US20130287572A1
Автор: Ehrnberg Daniel
Принадлежит:

Disclosed is a dynamic turbine, capable of altering the sweep area in a large interval by moving a first fixing structure, a second fixing structure and blades to and from an essential same plane along an axis of rotation of the turbine. 211161716171617. A dynamic turbine according to wherein said at least one blade () is attached at its first and second attachments to fixed points of said first and second fixing structures ( claim 1 , ) such that said top fixing structure () performs a rotational movement around said axle relative said second fixing structure () while the distance D between the first fixing structure () and second fixing structure () is changed.31111171617. A dynamic turbine according to wherein at least one of the attachments of said first and/or second attachments for a blade () comprises a rail such that said blade () performs a translational movement while rotating relative said first and/or second fixing structure () while the distance D between the first fixing structure () and second fixing structure () is changed.411111716171617. A dynamic turbine according to wherein at least one of the attachments of said first and/or second attachments for all blades ( ) comprises a rail such that said blade ( ) performs a translational movement while rotating relative said first and/or second fixing structure () while the distance D between the first fixing structure () and second fixing structure () is changed whereby the first and second fixing structures not rotate relative each other while the distance D between the first fixing structure () and second fixing structure () is changed.5. A dynamic turbine according to wherein said first and second turbine mode involves a change of the distance D between the first fixing structure and the second fixing structure corresponding to at least a factor 3 claim 1 , i.e. the distance D between the first and second fixing structures in the first turbine mode is three times longer than in the second turbine mode ...

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Номер записи: 21
02-01-2014 дата публикации

HUB FOR RADIAL HOUSING OF A HELICAL RING OF A TURBOMACHINE WITH VARIABLE-PITCH BLADES AND ASSEMBLY COMPRISING SUCH A HUB

Номер: US20140003945A1
Автор: JABLONSKI Laurent, JOLY Philippe Gérard Edmond, Perdrigeon Christophe
Принадлежит:

The present invention relates to a helical ring () comprising a polygonal body () and a plurality of cylindrical radial housings () arranged in said body, each housing () having a surface adapted to receive support means of a blade of a helix, characterised in that the surface of each housing () is arranged on a radially internal surface () of a corresponding hub (), each hub () being a separate piece attached to the body () of the ring, intended to be received in a radial housing () of the latter, and in that it also comprises two projecting pins () relative to its external surface to be fastened to the edges of a housing of the annular body, the two projecting pins forming a centring axis. 1. A hub for a radial housing of a helical ring of a turbomachine with variable-pitch blades , said ring comprising an annular rotor body and a plurality of radial housings distributed over said annular rotor body around a central axis , said hub comprising a piece separate from an annular body , configured to be received in a radial housing of the annular body , an internal surface of said piece being adapted to receive a cylindrical blade support crown , as well as centring and/or guiding means for rotation of the blade support crown , and further comprising two pins projecting relative to an external surface to fasten said external surface to the edges of a housing of the annular body , the two projecting pins forming a centering axis.2. The hub according to claim 1 , wherein said internal surface comprises a machined area adapted to receive bearing rings of the cylindrical blade support crown.3. The hub according to claim 2 , comprising two rims adapted to be supported on an edge of a housing when the centering pins are in place on the latter.4. An assembly for a helical ring of a turbomachine with variable-pitch blades comprising an annular rotor body and a plurality of radial housings distributed over said annular body around a central axis claim 1 , said assembly ...

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Номер записи: 22
09-01-2014 дата публикации

NOVEL TURBINE BLADE AND TURBINE ASSEMBLY

Номер: US20140010654A1
Автор: CIZMAS Paul G.A., FAJARDO Danny, GOLDBLATT Joel, WHITE Edward B.
Принадлежит:

A turbine assembly comprises an anchor plate, at least one turbine blade mounted to the anchor plate and having an elongated blade body having a longitudinal axis parallel to an axis of rotation, and the at least one turbine blade being operable to move between a first position relative to the axis of rotation and a second position relative to the axis of rotation. 1. A turbine assembly comprising:an anchor plate;at least one turbine blade mounted to the anchor plate and having an elongated blade body having a longitudinal axis parallel to an axis of rotation; andthe at least one turbine blade being operable to move between a first position relative to the axis of rotation and a second position relative to the axis of rotation.2. The turbine assembly of claim 1 , wherein the second position varies from the first position in the amount of inclination angle measured from the axis of rotation.3. The turbine assembly of claim 1 , wherein the second position varies from the first position in distance from the axis of rotation.4. The turbine assembly of claim 1 , wherein the second position varies from the first position in an amount of twist of the blade body.5. The turbine assembly of claim 1 , wherein the second position varies from the first position in an amount of helical twist of both blade bodies about the axis of rotation.6. The turbine assembly of claim 1 , further comprising a second anchor plate.7. The turbine assembly of claim 1 , wherein the blade body comprises a plurality of solar electricity-generating panels.8. The turbine assembly of claim 1 , wherein the turbine blades have semi-circular shape in cross-section.9. The turbine assembly of claim 1 , wherein a second end of the turbine blades comprises a scalloped edge.10. The turbine assembly of claim 1 , further comprising at least one second turbine blade mounted to the anchor plate at a predetermined configuration from the first turbine blade including a first off-set in a first axis and a second off- ...

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Номер записи: 23
16-01-2014 дата публикации

SYSTEM FOR CHANGING THE PITCH OF THE CONTRA-ROTATING PROPELLERS OF A TURBOSHAFT ENGINE

Номер: US20140017086A1
Автор: Balk Wouter, Charier Gilles Alain
Принадлежит: SNECMA

A system, including: a linear actuator axially arranged in a first propeller and rotatably secured thereto, a first linking mechanism connecting a rod of the linear actuator to a second propeller to change a setting of blades thereof, and including an intermediate bearing between the propellers, which is capable of transmitting translation of the rod of the linear actuator and disconnecting a rotatable link to the first propeller to make it possible to change the setting of the blades of the second propeller rotated in an opposite direction to the first propeller, and a second linking mechanism combined with blades of the first propeller to change a setting thereof. 110-. (canceled)11. A system for changing pitch of first and second coaxial and contra-rotating propellers of a turbo-engine including an unducted fan for aircraft , of type controlled by fluidic or analogous means via a linear actuator aligned axially in the first propeller , being secured in rotation with the first propeller , the system comprising:a first connecting mechanism connecting a rod of the linear actuator to a second propeller to change orientation of blades of the second propeller, and comprising an intermediate connecting bearing between the first and second propellers which is configured to transmit movement in translation of the rod of the actuator and break a connection in rotation with the first propeller such that the orientation of the blades of the second propeller, driven in rotation in an opposite direction to the first propeller, can be changed; anda second connecting mechanism associated with blades of the first propeller to change orientation of the blades of the first propeller; between the linear actuator connected to the first propeller and the intermediate bearing, a first connecting means articulated to a rod of a lower actuator and to one of races of the bearing, and', 'between the intermediate bearing and the blades of the second propeller, a second connecting means ...

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Номер записи: 24
06-03-2014 дата публикации

Control rod device

Номер: US20140064914A1
Автор: Jeurgen GOETTE, Matthias Müller, Uwe Arnold
Принадлежит: ZF FRIEDRICHSHAFEN AG

A control rod configuration for adjusting a position of a rotor blade of a helicopter. The control rod configuration includes a control rod which has a bearing eye, adjacent the swash plate, which is penetrated by an axle shaft which has a bearing supported by a bearing bracket. The control rod configuration, which can be simply constructed and is less susceptible to malfunction, has an eccentric with its pivotable bearing in the bearing bracket and which is provided between the bearing bracket and the bearing eye. In addition, a method in which a rotor blade of a helicopter has an assigned control rod which is supported by an axle shaft with a bearing in the bearing bracket which is mounted to the swash plate so as to enable adjustment of the control rod by pivoting the axle shaft during flight.

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Номер записи: 25
10-04-2014 дата публикации

TURBOMACHINE PROPELLER BLADE SETTING DEVICE

Номер: US20140099202A1
Автор: Dubois Adrien, Fernando Rasika, Gruber Mathieu, Jodet Norman
Принадлежит: SNECMA

The main subject matter of the invention is a device () for setting a turbomachine propeller blade (), characterised in that it comprises a first disc () and a second disc () respectively provided with first () and second () coupling means, the first () and second () discs being coaxial, means of tilting () at least one of the first () and second () discs with respect to the other, the device () being configured so that, during a tilting of at least one of the first () and second () discs with respect to the other, the coupling distance (D) of said at least one blade () on the first () and second () discs remains constant, bringing about the rotation of said at least one blade (). 1. A device for setting at least one blade of a turbomachine propeller , wherein:a first disc provided with first coupling means configured to cooperate with at least one first coupling point of said at least one blade for its fixation on the first disc,a second disc provided with second coupling means configured to cooperate with at least one second coupling point of said at least one blade for its fixation on the second disc, the first and second discs being coaxial,means of tilting at least one of the first and second discs with respect to the other,the device being configured so that, during a tilting of at least one of the first and second discs with respect to the other, the coupling distance of said at least one blade on the first and second discs, which corresponds to the distance between said at least one first and one second coupling points cooperating respectively with the first and second coupling means, remains constant, bringing about the rotation of said at least one blade,the first coupling means and the second coupling means being respectively configured to cooperate with said at least one first and one second coupling points by forming a slide type mechanical link,the means of tilting comprising actuators able to modify the orientation of at least one of the first and ...

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Номер записи: 26
07-01-2021 дата публикации

UNMANNED AERIAL VEHICLE

Номер: US20210001974A1
Автор: KUNII Shinya, MAKI Shinichi
Принадлежит: PRODRONE CO., LTD.

To provide an unmanned aerial vehicle that eliminates or minimizes the laboriousness involved in optimal pitch adjustment of propellers while eliminating or minimizing complexity and instability in airframe structure and/or flight programs. This object is solved by an unmanned aerial vehicle that is provided with a plurality of rotors and that includes: a center frame that is a central portion of an airframe of the unmanned aerial vehicle; and a plurality of arms extending radially from the center frame in plan view. A plurality of motors that are driving sources of the respective rotors are provided in the center frame. The plurality of rotors are supported by the respective arms. Each arm of the arms has a hollow cylindrical structure. A motive power transmission member configured to transmit a driving force of each motor of the motors to the each rotor is provided in the each arm. 1. An unmanned aerial vehicle provided with a plurality of rotors and comprising:a center frame that is a central portion of an airframe of the unmanned aerial vehicle;a plurality of arms extending from the center frame;a plurality of motors that are driving sources of the respective rotors; anda speed controller configured to control a rotational speed of each rotor of the rotors,wherein the plurality of motors are provided in the center frame,wherein the plurality of rotors are supported by the respective arms,each arm of the arms has a hollow cylindrical structure,wherein a motive power transmission member configured to transmit a driving force of each motor of the motors to the each rotor is provided in the each arm, andwherein the unmanned aerial vehicle is configured to make a mid-air movement by controlling the rotational speed of the each rotor.2. The unmanned aerial vehicle according to claim 1 ,wherein the plurality of motors, which are the driving sources of the respective rotors, are provided in the center frame such that an output shaft of the each motor is pointed toward ...

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Номер записи: 27
13-01-2022 дата публикации

HYBRID ELECTRIC POWERPLANT (HEP) CONTROL ARCHITECTURE

Номер: US20220009615A1
Автор: Guerchkovitch Leonid, MARK Michael
Принадлежит: PRATT & WHITNEY CANADA CORP.

A system includes a thermal engine operatively connected to drive a propeller. An electric motor is operatively connected to the thermal engine to drive the propeller together with the thermal engine. An external input system is configured to accept input and output a thrust command. A protection function module is configured to enforce limits on the thermal engine, electric motor, and propeller. A low select module is operatively connected to receive input from the external input system and form the protection function module and to output the lower of input from the protection function module and external input system to the thermal engine, the electric motor, and the propeller. 1. A system comprising:a thermal engine operatively connected to drive a propeller;an electric motor operatively connected to the thermal engine to drive the propeller together with the thermal engine;a external input system configured to accept input and output a thrust command;a protection function module configured to enforce limits on the thermal engine, electric motor, and propeller; anda low select module operatively connected to receive input from the external input system and form the protection function module and to output the lower of input from the protection function module and external input system to the thermal engine, the electric motor, and the propeller.2. The system as recited in claim 1 , further comprising a transmission connecting the thermal engine and the electric motor in parallel to drive the propeller.3. The system as recited in claim 1 , wherein the propeller is a variable pitch propeller claim 1 , wherein the low select module connects to the propeller through a propeller controller connected to control blade pitch of the propeller.4. The system as recited in claim 1 , wherein the low select module connects to the electric motor through a motor controller connected to control speed and/or torque of the electric motor by controlling electrical power supplied to ...

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Номер записи: 28
20-01-2022 дата публикации

BLADE PIVOT OF ADJUSTABLE ORIENTATION AND OF REDUCED BULK FOR A TURBOMACHINE FAN HUB

Номер: US20220018357A1
Автор: Belmonte Olivier, CHARIER Gilles Alain Marie, FRANTZ Caroline Marie, MILLIER Vincent François Georges
Принадлежит: SAFRAN AIRCRAFT ENGINES

A blade pivot of adjustable orientation for a turbomachine fan hub includes: a block having a retaining device configured to retain a fan blade root and a coupling device for the transmission of a torque; a ball type rolling bearing for taking up centrifugal forces having an inner ring; a clamping nut screwed onto an external thread of the block in order to clamp the inner ring of the ball type rolling bearing for taking up centrifugal forces to the block; a rolling bearing for taking up transverse forces; a pitch setting transmission ring positioned inside the inner radial end of the block and equipped with a coupling device cooperating with the coupling device of the block, and a device for locking the pitch setting transmission ring on the block. 1. A blade pivot of adjustable orientation for a turbomachine fan hub comprising:a block having retaining means at an outer radial end configured to retain a fan blade root and coupling means at an inner radial end, for the transmission of a torque;a ball type rolling bearing for taking up centrifugal forces having an inner ring mounted in transverse support against an outer radial portion of the block;a clamping nut screwed onto an external thread of the block in order clamp the inner ring of the ball type rolling bearing for taking up centrifugal forces on the block;a rolling bearing for taking up transverse forces having an inner ring mounted in transverse support against an inner radial portion of the block;a pitch setting transmission ring positioned inside the inner radial end of the block and equipped with coupling means cooperating with the coupling means of the block; andmeans for locking the pitch setting transmission ring on the block.2. The pivot according to claim 1 , wherein the rolling bearing for taking up the transverse forces comprises an outer ring configured to be mounted in transverse support inside a fan hub claim 1 , the inner and outer rings defining the rolling paths for a plurality of rolling ...

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Номер записи: 29
12-01-2017 дата публикации

PITCH CONTROL ASSEMBLY AND PROPELLER ASSEMBLY AND METHOD OF ADJUSTING PITCH

Номер: US20170008612A1
Автор: AGRAWAL Bajarang, G. Nagashiresha, GANIGER Ravindra Shankar, Kumar Sandeep, KURVINKOP Amit Arvind, PAWAR Rajendra Vishwanath, PERIASAMY Murugesan, YAMARTHI David Raju
Принадлежит:

Pitch control assembly and propeller blade assembly having a spider hub are disclosed. The spider hub includes a hub and a set of arms spaced circumferentially about the hub and projecting radially from the hub, wherein the set of arms are configured to receive a set of blades such that a blade root of a blade is rotationally mountable into an arm included in the set of arms, a crosshead located within the hub and axially moveable relative to the hub, a torque tube located in the arm and extending into the hub, wherein a pitch angle of the blade can be adjusted by axially moving the crosshead to rotate the torque tube to effect a corresponding rotation of the blade. 1. A propeller assembly comprising:a spider hub comprising a hub and a set of arms spaced circumferentially about the hub and projecting radially from the hub, wherein the set of arms are configured to receive a set of blades such that a blade root of a blade is rotationally mountable into an arm included in the set of arms;a crosshead located within the hub and axially moveable relative to the hub;a torque tube located in the arm and extending into the hub, and having opposing first and second ends, with the first end configured to mount to the blade root; anda motion converter coupling the crosshead to the torque tube and converting axial movement of the crosshead into rotational movement of the torque tube;wherein a pitch angle of the blade can be adjusted by axially moving the crosshead to rotate the torque tube to effect a corresponding rotation of the blade.2. The propeller assembly as claimed in claim 1 , wherein the motion converter includes a link fixedly mounted to the torque tube and a needle bearing pivotally coupling the link to the crosshead.3. The propeller assembly as claimed in claim 2 , wherein the motion converter further includes a crosshead flange coupling the needle bearing to the crosshead.4. The propeller assembly as claimed in claim 3 , wherein the crosshead flange includes a ...

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Номер записи: 30
14-01-2021 дата публикации

System and method for propeller response enhancement during transition from ground to flight configuration for a turbopropeller engine

Номер: US20210009252A1
Автор: Giuseppe Donini, Pierpaolo Forte, Stefano Ettorre
Принадлежит: GE Avio SRL

An electronic control system (35) for a turbopropeller engine (2) having a gas turbine (20) and a propeller assembly (3) coupled to the gas turbine (20), the control system (35) implementing a propeller control unit (PEC) to control propeller operation based on a pilot input request, via generation of a driving quantity (Ip) for an actuation assembly (29) designed to adjust a pitch angle (β) of propeller blades (10). The control unit engages a mechanical lock determining a minimum flight value for the pitch angle during a flight operating mode, and disengages the mechanical lock and controls the pitch angle below the minimum flight value, up to a minimum ground value lower than the minimum flight value, during a ground operating mode; the propeller control unit, during a transition from the ground operating mode to the flight operating mode, engages the mechanical lock, thereby causing an increase of the pitch angle towards the minimum flight value independently from the control action. In particular, the control unit anticipates the increase of the pitch angle in a time period (T) before the mechanical lock engagement due to transition from the ground operating mode to the flight operating mode.

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Номер записи: 31
14-01-2021 дата публикации

HYDRAULIC ACTUATION SYSTEM

Номер: US20210009253A1
Автор: LASSALLE Julien, MARGER Thibaut
Принадлежит:

There is provided an hydraulic actuation system for an aircraft, the hydraulic actuation system includes an actuator (A), a primary actuation arrangement to provide hydraulic fluid to control the actuator (A), wherein the hydraulic actuation system is configured to detect a fault in the actuator (A). The hydraulic actuation system also includes a secondary actuation arrangement to provide hydraulic fluid to control the actuator (A) in response to a detection of a fault in the actuator (A). 1. An hydraulic actuation system for an aircraft , the hydraulic actuation system comprising:an actuator (A);a primary actuation arrangement to provide hydraulic fluid to control the actuator (A), wherein the hydraulic actuation system is configured to detect a fault in the actuator (A);a secondary actuation arrangement to provide hydraulic fluid to control the actuator (A) in response to a detection of a fault in the actuator (A).2. The hydraulic actuation system of any claim 1 , wherein the actuator (A) further comprises:a first chamber and a second chamber, and wherein the primary actuation arrangement controls the hydraulic fluid in the first chamber and the second chamber; anda third chamber, wherein the secondary actuation arrangement controls the hydraulic fluid provided in the third chamber.3. The hydraulic system of claim 2 , wherein the first chamber is configured to decrease pitch of a propeller blade of the aircraft;wherein the second chamber is configured to increase pitch of the propeller blade of the aircraft; andwherein the third chamber is configured to increase pitch of the propeller blade of the aircraft.4. The hydraulic actuation system of claim 1 , wherein the primary actuation arrangement includes at least one pressure sensor to detect a fault in the actuator (A).5. The hydraulic actuation system of claim 1 , wherein the primary actuation arrangement includes an electric pump claim 1 , a main pump claim 1 , a by-pass valve and a primary electro-hydraulic ...

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Номер записи: 32
14-01-2021 дата публикации

SYSTEM AND METHOD FOR COMBINED PROPELLER SPEED AND PROPELLER PITCH CONTROL FOR A TURBOPROPELLER ENGINE

Номер: US20210009278A1
Автор: Donini Giuseppe, Ettorre Stefano, Forte Pierpaolo
Принадлежит:

An electronic control system () for a turbopropeller engine () having a gas turbine () and a propeller assembly () coupled to the gas turbine (), controls propeller operation based on a pilot input request, via generation of a driving quantity (Ip) for an actuation assembly () designed to adjust a pitch angle (β) of propeller blades () of the propeller assembly (). The control system () envisages: a propeller speed regulator (), receiving at its input a propeller speed error (ep), indicative of a difference between a propeller speed measure (Nr) and a propeller speed demand (Nrref), and generating at its output, based on the propeller speed error (ep), a first control quantity (Outi); a propeller pitch regulator (), receiving at its input a propeller pitch error (ep), indicative of a difference between a propeller pitch demand ( ) and a pitch position measure (β), and generating at its output, based on the propeller pitch error (ep), a first control quantity (Out); and a priority selection stage (), configured to implement a priority selection between the first and the second control quantities, for providing at the output the driving quantity (IP), based on the priority selection between the first and the second control quantities. 116-. (canceled)17. An electronic control system for a turbopropeller engine having a gas turbine and a propeller assembly coupled to the gas turbine , the control system being configured to control propeller operation based on a pilot input request , via generation of a driving quantity for an actuation assembly designed to adjust a pitch angle of propeller blades of the propeller assembly , the electronic control system comprising:a propeller speed regulator configured to receive at its input a propeller speed error indicative of a difference between a propeller speed measure and a propeller speed demand, and to generate at its output, based on the propeller speed error, a first control quantity;a propeller pitch regulator configured ...

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Номер записи: 33
10-01-2019 дата публикации

DEVICE FOR LOCKING THE PITCH AND FOR FEATHERING ADJUSTABLE-PITCH FAN BLADES OF A TURBINE ENGINE PROPELLER

Номер: US20190009886A1
Автор: Patsouris Emmanuel Pierre Dimitri, Tajan Sébastien Emile Philippe
Принадлежит: SAFRAN AIRCRFT ENGINES

A device for locking the pitch and for feathering adjustable-pitch fan blades of a turbine engine propeller, the device including an actuator having at least one movable portion designed to be coupled to pivots of the fan blades of the propeller in order to modify their pitch angle when it slides, a movable part having first mechanical device suitable for co-operating with the actuator when in a fan blade pitch-unlocking position in order to enable the actuator movable portion to slide over an extended actuator stroke; and second mechanical device suitable for co-operating with the actuator when in a fan blade pitch-locking position in order to enable the actuator movable portion to slide over an actuator stroke that is shorter than the extended actuator stroke, and an actuator. 1. A device for locking the pitch and for feathering adjustable-pitch fan blades of a turbine engine propeller , the device comprising:an actuator having at least one movable portion extending parallel to an axis of rotation of the propeller and designed to be coupled to pivots of the fan blades of the propeller in order to modify their pitch angle when it slides;a movable part that is movable relative to the actuator having first mechanical means suitable for co-operating with the actuator when in a fan blade pitch-unlocking position in order to enable the actuator movable portion to slide over an extended actuator stroke; and second mechanical means distinct from the first mechanical means and suitable for co-operating with the actuator when in a fan blade pitch-locking position in order to enable the actuator movable portion to slide over an actuator stroke that is shorter than the extended actuator stroke; anddrive means for moving the movable part between the unlocking position of the actuator and the locking position of the actuator.2. The device according to claim 1 , wherein the actuator movable portion comprises a flat and the first mechanical means of the movable part include a ...

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Номер записи: 34
10-01-2019 дата публикации

A SYSTEM FOR CONTROLLING THE PITCH OF FAN BLADES OF A TURBINE ENGINE, THE SYSTEM HAVING A FEATHERING-LOCKING PEG

Номер: US20190009887A1
Автор: MOUTON Clementine Charlotte Marie, Patsouris Emmanuel Pierre Dimitri, YVON Didier Jean-Louis
Принадлежит: SAFRAN AIRCRAFT ENGINES

A system for controlling the pitch of fan blades of a turbine engine propeller, the system including an actuator secured to a casing of the turbine engine, having a movable portion that is movable in translation relative to the casing, the movable portion being mechanically coupled to a load transfer bearing having an outer ring that is coupled to fan blade pivots so that a movement in translation of the movable portion of the actuator leads to a change in the pitch angle of the fan blades, and at least one locking peg secured to the casing of the turbine engine and suitable, in the event of the actuator malfunctioning, for mechanically locking the load transfer bearing in a position wherein the fan blades are feathered. 1. A system for controlling the pitch of fan blades of a turbine engine propeller , the system comprising:an actuator secured to a casing of the turbine engine, having a movable portion that is movable in translation relative to said casing, the movable portion being mechanically coupled to a load transfer bearing having an outer ring that is coupled to fan blade pivots so that a movement in translation of the movable portion of the actuator leads to a change in the pitch angle of said fan blades; andat least one locking peg secured to the casing of the turbine engine and suitable, in the event of the actuator malfunctioning, for mechanically locking the load transfer bearing in a position in which the fan blades are feathered.2. The system according to claim 1 , wherein the locking peg is suitable for occupying two different positions: an extended position in which the locking peg bears radially against an inside surface of an inner ring of the load transfer bearing claim 1 , and a retracted position in which the locking peg does not bear against said inner ring of the load transfer bearing.3. The system according to claim 2 , wherein claim 2 , in the extended position claim 2 , the locking peg is suitable for bearing radially against various ...

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Номер записи: 35
10-01-2019 дата публикации

VARIABLE PITCH BLADE PIVOT FOR A TURBINE ENGINE FAN HUB

Номер: US20190010957A1
Автор: Belmonte Olivier, Jacquemard Christophe Paul, MOUTON Clementine Charlotte Marie, Patsouris Emmanuel Pierre Dimitri
Принадлежит: SAFRAN AIRCRAFT ENGINES

A pivot for an adjustable-pitch blade for a turbine engine fan hub, the pivot including a stud having coupling device for transmitting a twisting torque and an outside thread, a force-decoupling part positioned around the stud, provided with an outside thread, pressing transversely against the stud at its radially outer end, an outer rolling bearing having an inside ring mounted to press transversely against the force-decoupling part, an inner rolling bearing assembled around the force-decoupling part and held thereby, a pitch transmission ring provided with a coupling device co-operating, with the coupling device of the stud, a first clamping nut screwed onto the outside thread of the force-decoupling part in order to clamp the outer and inner rolling bearings around the fan hub, and a second clamping nut screwed onto the outside thread of the stud in order to provide clamping between the stud, the force-decoupling part, and the pitch transmission ring. 1. A pivot for an adjustable pitch blade for a turbine engine fan hub , the pivot comprising:a stud having, at a radially inner end, coupling means for transmitting a twisting torque and an outside thread;an annular force-decoupling part positioned around the stud and provided at a radially outer end with an outside thread, said force-decoupling part pressing transversely against the stud at its radially outer end and having no contact with said stud at a radially inner end;an outer rolling bearing having an inside ring mounted to press transversely against the radially outer end of the force-decoupling part;an inner rolling bearing assembled around the radially inner end of the force-decoupling part and held thereby;a pitch transmission ring positioned around the radially inner end of the stud and provided with coupling means co-operating with the coupling means of the stud;a first clamping nut screwed onto the outside thread of the force-decoupling part in order to clamp the outer and inner rolling bearings around ...

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Номер записи: 36
19-01-2017 дата публикации

HUB ASSEMBLY AND PROPELLER ASSEMBLIES

Номер: US20170015404A1
Автор: AGRAWAL Bajarang, G Nagashiresha, GANIGER Ravindra Shankar, Kumar Sandeep, KURVINKOP Amit Arvind, PAWAR Rajendra Vishwanath, PERIASAMY Murugesan, YAMARTHI David Raju
Принадлежит:

Hub assembly and propeller blade assemblies incorporating partial hub assembly having a backing plate with a set of partial root seats and a set of clamps selectively operably couplable to the backing plate with each clamp defining a second partial root seat and wherein when a clamp is coupled to the backing plate a root seat is formed, propeller blades having roots are received within the root seats. 1. A propeller assembly , comprising: a backing plate with a set of partial root seats; and', 'a set of clamps selectively operably couplable to the backing plate with each clamp defining a second partial root seat and wherein when a clamp is coupled to the backing plate a root seat is formed; and, 'a partial hub, comprisinga propeller blade having a root received within the root seat.2. The propeller assembly of wherein the backing plate of the partial hub is at a rear side of the propeller assembly and provides a mounting surface to an engine.3. The propeller assembly of wherein the backing plate includes a contoured plate having the set of partial root seats spaced about its periphery.4. The propeller assembly of wherein the clamps are fastened to the backing plate.5. The propeller assembly of claim 1 , further comprising a cover operably coupled over the set of clamps.6. The propeller assembly of wherein the cover includes at least one opening configured to accommodate a portion of the propeller assembly.7. The propeller assembly of claim 1 , further comprising a retainer selectively operably coupled to the partial hub and configured to retain the root of the propeller blade within the partial hub when the retainer is coupled to the partial hub.8. The propeller assembly of claim 7 , further comprising a bearing assembly provided between the root and the partial hub and where the bearing assembly allows the propeller blade to rotate within the partial hub.9. The propeller assembly of wherein the bearing assembly includes a parallel roller bearing assembly claim 8 , ...

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Номер записи: 37
17-01-2019 дата публикации

HYDRAULIC ACTUATOR

Номер: US20190016442A1
Автор: LABASCOULE Jean-Christophe, MARGER Thibaut, POULY François
Принадлежит:

An actuator is disclosed comprising: a moveable member; a first hydraulic chamber in contact with a first surface of the moveable member; a second hydraulic chamber in contact with a second, opposing surface of the moveable member; a movable locking mechanism coupled to a moveable wall of the second hydraulic chamber; and a resilient biasing member acting on the moveable wall of the second hydraulic chamber so as to bias the moveable wall and locking mechanism. The actuator is configured to selectively vary the pressure in the second hydraulic chamber so that the resilient biasing member is able to bias the moveable wall to move, thereby moving the locking mechanism to engage the moveable member so as to prevent the movement of the moveable member towards at least one of the first and second hydraulic chambers. 1. An actuator comprising:a moveable member;a first hydraulic chamber in contact with a first surface of the moveable member;a second hydraulic chamber in contact with a second, opposing surface of the moveable member;a movable locking mechanism coupled to a moveable wall of the second hydraulic chamber; anda resilient biasing member acting on the moveable wall of the second hydraulic chamber so as to bias the moveable wall and locking mechanism;wherein the actuator is configured to selectively vary the pressure in the second hydraulic chamber so that the resilient biasing member is able to bias the moveable wall to move, thereby moving the locking mechanism such that it engages the movable member so as to prevent the movement of the moveable member towards at least one of the first and second hydraulic chambers.2. The actuator of claim 1 , wherein the movable wall is on the opposing side of the second hydraulic chamber to the second claim 1 , opposing surface of the moveable member.3. The actuator of claim 2 , wherein the first hydraulic chamber is arranged to contact the movable wall claim 2 , such that the movable wall separates the first and second ...

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Номер записи: 38
21-01-2016 дата публикации

VARIABLE-PITCH VANE

Номер: US20160017728A1
Автор: FABRE Adrien, Laurenceau Adrien
Принадлежит:

A variable-pitch vane comprising: a plurality of propeller blades (), each being of variable pitch according to a blade rotational axis (A) and each having a root (), a plurality of rotor connecting shafts (), each shaft having a foot () and a head (). the root () of each blade being mounted on the head () of a rotor connecting shaft via a pivot () in such a way as to allow each blade () to rotate according to the blade rotational axis (A), in which each blade () has a blade pitch, such that the blade rotational axis (A-i) of same is inclined relative to a radial axis (A) passing through the foot () of the corresponding shaft.

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Номер записи: 39
16-01-2020 дата публикации

SYSTEM AND METHOD FOR FEATHERING AN AIRCRAFT PROPELLER

Номер: US20200017196A1
Автор: Chahal Jasraj, Lisio Carmine, McGrath Darragh, Zingaro Giancarlo
Принадлежит:

A system and method for feathering an aircraft propeller are provided. The aircraft propeller is coupled to an actuator for setting a blade pitch of the propeller. The blade pitch is controlled by modulating a supply of hydraulic fluid to the actuator. At least one feather solenoid is provided that comprises a first solenoid coil, a second solenoid coil, and a solenoid valve coupled to the actuator and to the first and the second solenoid coil. At least one controller is configured to selectively energize and de-energize the first and the second solenoid coil. The solenoid valve is configured to be activated when the first solenoid coil and the second solenoid coil are de-energized and to, when activated, modulate the supply of hydraulic fluid to the actuator for adjusting the blade pitch of the propeller towards a feather position. 1. A system for feathering an aircraft propeller having coupled thereto an actuator for setting a blade pitch of the propeller , the blade pitch controlled by modulating a supply of hydraulic fluid to the actuator , the system comprising:at least one feather solenoid comprising a first solenoid coil, a second solenoid coil, and a solenoid valve coupled to the actuator and to the first and the second solenoid coil; andat least one controller configured to selectively energize and de-energize the first and the second solenoid coil,the solenoid valve configured to be activated when the first solenoid coil and the second solenoid coil are de-energized and to, when activated, modulate the supply of hydraulic fluid to the actuator for adjusting the blade pitch of the propeller towards a feather position.2. The system of claim 1 , wherein the at least one controller comprises a first solenoid driver configured to selectively energize and de-energize the first solenoid coil and a second solenoid driver configured to selectively energize and de-energize the second solenoid coil claim 1 , the at least one controller comprising a first channel for ...

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Номер записи: 40
16-01-2020 дата публикации

SYSTEM AND METHOD FOR FEATHERING AN AIRCRAFT PROPELLER

Номер: US20200017197A1
Автор: Chahal Jasraj, Jarvo Jim R., Lisio Carmine, McGrath Darragh, Zingaro Giancarlo
Принадлежит:

A system and method for feathering an aircraft propeller are provided. A first feather solenoid and a second feather solenoid each comprising at least one solenoid coil and a solenoid valve coupled to the actuator and to the at least one solenoid coil are provided. At least one controller is configured to selectively energize and de-energize the at least one solenoid coil. The solenoid valve of the first feather solenoid is configured to be activated when the at least one solenoid coil of the first feather solenoid is energized and the solenoid valve of the second feather solenoid is configured to be activated when the at least one solenoid coil of the second feather solenoid is de-energized. The solenoid valve is configured to, when activated, modulate the supply of hydraulic fluid to an actuator for adjusting a blade pitch of the propeller towards a feather position. 1. A system for feathering an aircraft propeller having coupled thereto an actuator for setting a blade pitch of the propeller , the blade pitch controlled by modulating a supply of hydraulic fluid to the actuator , the system comprising:a first feather solenoid and a second feather solenoid each comprising at least one solenoid coil and a solenoid valve coupled to the actuator and to the at least one solenoid coil; andat least one controller configured to selectively energize and de-energize the at least one solenoid coil,the solenoid valve of the first feather solenoid configured to be activated when the at least one solenoid coil of the first feather solenoid is energized and the solenoid valve of the second feather solenoid configured to be activated when the at least one solenoid coil of the second feather solenoid is de-energized,the solenoid valve configured to, when activated, modulate the supply of hydraulic fluid to the actuator for adjusting the blade pitch of the propeller towards a feather position.2. The system of claim 1 , wherein the at least one solenoid coil comprises a first ...

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Номер записи: 41
16-01-2020 дата публикации

PROPELLER BLADE ANGLE FEEDBACK ARRANGEMENT AND METHOD

Номер: US20200017234A1
Автор: Basse Olivier, Dobson Martin, FARRELL Ian, Lavoie Marc, MARONE Joseph Ernesto, YAKOBOV Ella
Принадлежит:

A blade angle feedback ring assembly for an aircraft propeller rotatable about a longitudinal axis and having an adjustable blade angle is provided. A feedback ring is coupled to the propeller to rotate therewith and to move along a longitudinal axis with adjustment of the blade angle. A plurality of rods are coupled to the feedback ring and extending along a direction substantially parallel to the longitudinal axis, the rods configured to support the feedback ring for longitudinal sliding movement along the longitudinal axis with adjustment of the blade angle. At least one shielding element is provided between the feedback ring and the propeller for shielding the feedback ring from electromagnetism. 1. A blade angle feedback ring assembly for an aircraft propeller , the propeller rotatable about a longitudinal axis and having an adjustable blade angle , the assembly comprising:a feedback ring coupled to the propeller to rotate with the propeller and to move along the longitudinal axis with adjustment of the blade angle;a plurality of rods coupled to the feedback ring and extending along a direction substantially parallel to the longitudinal axis, the plurality of rods configured to support the feedback ring for longitudinal sliding movement along the longitudinal axis with adjustment of the blade angle; andat least one shielding element provided between the feedback ring and the propeller, the at least one shielding element configured to shield the feedback ring from electromagnetism.2. The feedback ring assembly of claim 1 , wherein the at least one shielding element comprises the plurality of rods being made from a non-conductive material.3. The feedback ring assembly of claim 1 , wherein the feedback ring comprises a plurality of threaded inserts spaced around a circumference of the feedback ring and each configured to receive therein a given one of the plurality of rods claim 1 , the at least one shielding element comprising the plurality of threaded inserts ...

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Номер записи: 42
10-02-2022 дата публикации

DUAL-CONCENTRIC CONTROL VALVE WITH DIRECT DRIVE CONTROL AND FAILED MOTOR PROTECTION

Номер: US20220041266A1
Автор: ATKINS Brady Garrett, Covington Charles Eric, Fenny Carlos Alexander, Reynolds Robert Paul
Принадлежит: Textron Innovations Inc.

Systems and methods include providing an aircraft with a direct drive dual-concentric valve (D3V) having a body, an outer secondary spool coaxially located within a bore of the body and linearly displaceable relative to the body, an inner primary spool coaxially located within a bore of the secondary spool and linearly displaceable relative to the secondary spool and the body. A plurality of piezo stacks is coupled to a first end of the primary spool, and applying a voltage to at least one of the piezo stacks causes an output stroke of the plurality of the piezo strokes for displacing the primary spool. The secondary spool is displaced together with the primary spool relative to the body if displacement of the primary spool relative to the secondary spool cannot occur. 1. A spool valve , comprising:a body;a secondary spool carried within a bore of the body and linearly displaceable relative to the body;a primary spool carried within a bore of the secondary spool and linearly displaceable relative to the secondary spool and to the body;a plurality of piezo stacks coupled to a first end of the primary spool and configured to cause selective displacement of the primary spool; anda spring coupled to a second end of the primary spool and configured for biasing the primary spool toward the piezo stacks;wherein applying a voltage to at least one of the piezo stacks causes an output stroke of the plurality of the piezo strokes for displacing the primary spool; andwherein the secondary spool is displaced together with the primary spool relative to the body if displacement of the primary spool relative to the secondary spool cannot occur.2. The valve of claim 1 , further comprising:a primary plunger coupling the plurality of piezo stacks to the primary spool.3. The valve of claim 1 , further comprising:a secondary plunger coupling the spring to the primary spool.4. The valve of claim 1 , further comprising:an output lever configured to amplify the output stroke.5. The valve ...

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Номер записи: 43
25-01-2018 дата публикации

Single Input Engine Controller and System

Номер: US20180023489A1
Автор: Cranmer William J., Doers Douglas A., Webb Dennis R.
Принадлежит:

A single input engine controller and system are provided for translating a single input indicative of the amount of fuel to be supplied to an engine from a fuel control interface into separate signals for controlling the amount of fuel supplied to the engine and the RPM of a propeller powered by that engine. The single input controller translating the single input into the separate signal for the RPM of the propeller according to a fuel efficiency relationship between the fuel amount and the propeller RPM. 1. A single input aircraft engine and propeller control system comprising:a fuel control interface to produce a first mechanical signal corresponding to a specific amount of fuel to be fed to an engine to produce a specific amount of horsepower, the specific amount of horsepower having a corresponding RPM setting for a propeller coupled to the engine, the RPM setting corresponding to a maximum fuel efficiency;a single input engine controller coupled to the fuel control interface to receive the first mechanical signal, translate the first mechanical signal into a second mechanical signal indicative of the RPM setting corresponding to the specific amount of horsepower, and output a third mechanical signal indicative of the specific amount of fuel, the third mechanical signal being induced by the first mechanical signal;a fuel distribution system coupled to the single input engine controller to receive the third mechanical signal, the third mechanical signal triggering the fuel distribution system to feed the specific amount of fuel to the engine; anda propeller RPM controller coupled to the single input engine controller to receive the second mechanical signal, the second mechanical signal triggering the RPM controller to set the RPM of the propeller to the corresponding RPM setting.2. A single input aircraft engine and propeller control system comprising:a fuel control interface to produce a first mechanical signal corresponding to a specific amount of fuel to be ...

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Номер записи: 44
23-01-2020 дата публикации

SHORT INLET WITH LOW SOLIDITY FAN EXIT GUIDE VANE ARRANGEMENTS

Номер: US20200024980A1
Автор: Rose Becky, Schwarz Frederick
Принадлежит: UNITED TECHNOLOGIES CORPORATION

A propulsor for a gas turbine engine may comprise a case including a duct disposed along an axis to define a flow path, a rotor including a row of propulsor blades extending in a generally radial direction outwardly from a hub, the hub rotatable about the axis such that the propulsor blades deliver airflow into the flow path, and a row of guide vanes situated in the flow path. A first guide vane may comprise a radially inner length (LI), a radially outer length (LO), and a midspan length (LM). The first guide vane may have a first dimensional relationship defined as LO/LM. The first guide vane may have a second dimensional relationship defined as LI/LM. The first dimensional relationship and/or the second dimensional relationship may be greater than 1.05. 1. A propulsor for a gas turbine engine comprising:a case including a duct disposed along an axis to define a flow path;a rotor including a row of propulsor blades extending in a generally radial direction outwardly from a hub, the hub rotatable about the axis such that the propulsor blades deliver airflow into the flow path;a row of guide vanes situated in the flow path, the row of guide vanes comprises a first guide vane and a second guide vane;wherein the first guide vane extends in the generally radial direction between inner and outer surfaces of the duct, extends in a chordwise direction between a first leading edge and a first trailing edge to define a vane chord dimension (VCD) at a first span position of the first guide vane, and defines a vane circumferential pitch (VCP) at the first span position of the first guide vane and the second guide vane;wherein the first guide vane comprises a radially inner length (LI) and a radially outer length (LO) and a midspan length (LM); andwherein the first guide vane has a first dimensional relationship defined as LO/LM, the first dimensional relationship being greater than 1.05, and the first guide vane has a second dimensional relationship defined as LI/LM, the ...

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Номер записи: 45
23-01-2020 дата публикации

VARIABLE PITCH FAN ACTUATOR

Номер: US20200024981A1
Автор: Miller Brandon Wayne, Niergarth Daniel Alan, Zatorski Darek Tomasz
Принадлежит:

A gas turbine engine including a core having in serial flow order a compressor, a combustor, and a turbine—the compressor, combustor, and turbine together defining a core air flowpath. The gas turbine engine additionally includes a fan section mechanically coupled to the core, the fan section including a plurality of fan blades, and each of the plurality fan blades defining a pitch axis. An actuation device is operable with the plurality fan blades for rotating the plurality fan blades about their respective pitch axes, the actuation device including an actuator located outward of the core air flowpath to, e.g., simplify the gas turbine engine. 1. An actuation device for a gas turbine engine comprising a core defining a core air flowpath and a fan section mechanically coupled to the core , the fan section comprising a plurality of fan blades each rotatable about a pitch axis , the actuation device comprising:an actuator configured to be located outward of the core air flowpath of the core when the actuation device is installed in the gas turbine engine; anda connection assembly extending from the actuator for operably connecting said actuator to the plurality of fan blades through the core air flowpath when the actuation device is installed in the gas turbine engine, said connection assembly comprising a rotating to static transfer device.2. The actuation device of claim 1 , wherein said rotating to static transfer device of said connection assembly is configured to be positioned in the fan section of the gas turbine engine when said actuation device is installed within the gas turbine engine.3. The actuation device of claim 1 , wherein said rotating to static transfer device comprises an inner race claim 1 , an outer race claim 1 , and a plurality of bearings located between said inner race and said outer race.4. The actuation device of claim 1 , wherein said connection assembly further comprises a non-rotating mechanical coupling extending between said rotating to ...

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Номер записи: 46
04-02-2016 дата публикации

Control system for controlling collective and cyclic pitch of rotor blades of a multi-blade rotor in a rotary-wing aircraft

Номер: US20160031557A1
Автор: Benedikt Bammer
Принадлежит: AIRBUS HELICOPTERS DEUTSCHLAND GMBH

The invention is related to a control system for controlling collective and cyclic pitch of rotor blades of a multi-blade rotor 1 a in a rotary-wing aircraft, the control system comprising a swash plate assembly with at least one non-rotating plate and at least one rotating plate that is mounted rotatably to the at least one non-rotating plate, the at least one rotating plate and the at least one non-rotating plate being mounted to a non-rotating sliding sleeve, wherein a spherical bearing is provided on the non-rotating sliding sleeve, wherein at least one non-rotating stop arm is provided for non-rotatably connecting the at least one non-rotating plate to the non-rotating sliding sleeve.

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Номер записи: 47
01-02-2018 дата публикации

BISTABLE PITCH PROPELLER SYSTEM WITH UNIDIRECTIONAL PROPELLER ROTATION

Номер: US20180029694A1
Автор: Reichert Todd, Vander Lind Damon
Принадлежит:

A propeller includes a blade free to rotate about a longitudinal axis of the blade. The propeller also includes a mechanical stop positioned to engage mechanically a first portion of the blade and/or a first structure coupled mechanically to the blade when the blade is in a first position. The propeller also includes a magnetic stop positioned to engage magnetically a second portion of the blade and/or a second structure coupled mechanically to the blade when the blade is in a second position. The blade rotates to the first position against the mechanical stop when the propeller is rotated at a first rotational speed and the blade rotates to the second position against the magnetic stop when the propeller is rotated at a second rotational speed in a same direction as when the blade is in the first position. 1. A propeller , comprising:a blade free to rotate about a longitudinal axis of the blade within at least a defined range of motion;a mechanical stop positioned to engage mechanically one or both of a first portion of the blade and a first structure coupled mechanically to the blade when the blade is in a first position at a first end of said defined rotational range of motion; anda magnetic stop positioned to engage magnetically one or both of a second portion of the blade and a second structure coupled mechanically to the blade when the blade is in a second position at a second end of said defined rotational range of motion;wherein the blade rotates to the first position against the mechanical stop when the propeller is rotated at a first rotational speed and the blade rotates to the second position against the magnetic stop when the propeller is rotated at a second rotational speed in a same direction as when the blade is in the first position.2. The propeller of claim 1 , wherein the first rotational speed is faster than the second rotational speed.3. The propeller of claim 1 , wherein the first structure is the same as the second structure.4. The propeller ...

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Номер записи: 48
31-01-2019 дата публикации

Propeller Arrangement For An Aircraft

Номер: US20190031318A1
Автор: Bichler Bartholomäus, Judas Michael
Принадлежит: Airbus Defence and Space GmbH

A propeller arrangement for an aircraft, and an aircraft having a propeller arrangement of said type, are specified. The propeller arrangement has a first propeller blade and a second propeller blade, and a propeller mount on which both the first propeller blade and the second propeller blade are mounted. The propeller arrangement furthermore has a drive shaft with a holding unit, and a first connecting unit. The first propeller blade is rotatable about a first axis of rotation and the second propeller blade is rotatable about a second axis of rotation. The propeller mount is pivotable about a pivot axis. The first connecting unit is coupled to the first propeller blade and to the holding unit, such that, in the event of a pivoting of the propeller mount about the pivot axis, the first propeller blade is set in rotational motion about the first axis of rotation. 1. A propeller arrangement for an aircraft , comprising:a first propeller blade and a second propeller blade;a propeller mount on which both the first propeller blade and the second propeller blade are mounted;a drive shaft with a holding unit; anda first connecting unit;wherein the first propeller blade is rotatable about a first axis of rotation and the second propeller blade is rotatable about a second axis of rotation;wherein the propeller mount is pivotable about a pivot axis;wherein the drive shaft is arranged so as to set the propeller mount in rotation;wherein the holding unit couples the propeller mount to the drive shaft; andwherein the first connecting unit is coupled to the first propeller blade and to the holding unit, such that, in the event of a pivoting of the propeller mount about the pivot axis, the first propeller blade is set in rotational motion about the first axis of rotation.2. The propeller arrangement according to claim 1 , wherein the first connecting unit is coupled to the first propeller blade such that the connecting unit subjects the first propeller blade to a rotational force ...

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Номер записи: 49
31-01-2019 дата публикации

PROPELLER CONTROL SYSTEM FOR AN AIRCRAFT

Номер: US20190031319A1
Автор: CALKINS Steven Clark, CARRINGTON Christopher Roy, Castellani Simone, Fletcher, Jr. Albion Richardson, Kenney Thomas Bradley
Принадлежит:

Propeller control systems and methods for controlling the pitch of a plurality of propeller blades of a variable pitch propeller assembly operatively coupled with an engine is provided. In one exemplary aspect, the propeller control system includes features for combining overspeed and feathering protective functions in a protective control valve communicatively coupled with a controller. In such an event the controller controls the protective control valve to selectively allow a controlled amount of hydraulic fluid to flow to or from a pitch actuation assembly such that the pitch of the propeller blades can be adjusted based at least in part on the condition of the engine. 1. An engine defining an axial direction , a radial direction , and a circumferential direction , the engine comprising a variable pitch propeller assembly driven by the engine , the engine comprising:a plurality of propeller blades rotatable about the axial direction and spaced apart along the circumferential direction, each propeller blade rotatable through a plurality of blade angles about their respective pitch axes each extending in the radial direction; a pitch actuation assembly for adjusting the plurality of propeller blades through the plurality of blade angles;', a primary control valve configured to selectively allow a flow of hydraulic fluid to or from the pitch actuation assembly;', 'a protective control valve configured to selectively allow a flow of hydraulic fluid to or from the pitch actuation assembly;, 'a pitch control unit, comprising;'}, determine a condition of the engine; and', 'control the protective control valve to selectively allow a controlled amount of hydraulic fluid to flow to or from the pitch actuation assembly based at least in part on the condition of the engine., 'a controller communicatively coupled with the primary control valve and the protective control valve, wherein the controller is configured to], 'a propeller control system, comprising2. The engine of ...

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Номер записи: 50
06-02-2020 дата публикации

BISTABLE PITCH PROPELLER SYSTEM WITH UNIDIRECTIONAL PROPELLER ROTATION

Номер: US20200039634A1
Автор: Reichert Todd, Vander Lind Damon
Принадлежит:

A propeller includes a blade free to rotate about a longitudinal axis of the blade. The propeller also includes a mechanical stop positioned to engage mechanically a first portion of the blade and/or a first structure coupled mechanically to the blade when the blade is in a first position. The propeller also includes a magnetic stop positioned to engage magnetically a second portion of the blade and/or a second structure coupled mechanically to the blade when the blade is in a second position. The blade rotates to the first position against the mechanical stop when the propeller is rotated at a first rotational speed and the blade rotates to the second position against the magnetic stop when the propeller is rotated at a second rotational speed in a same direction as when the blade is in the first position. 1. A method , comprising: a blade free to rotate about a longitudinal axis of the blade within at least a defined range of motion;', 'a mechanical stop positioned to engage mechanically one or both of a first portion of the blade and a first structure coupled mechanically to the blade when the blade is in a first position at a first end of said defined rotational range of motion; and', 'a magnetic stop positioned to engage magnetically one or both of a second portion of the blade and a second structure coupled mechanically to the blade when the blade is in a second position at a second end of said defined rotational range of motion;', 'wherein the blade rotates to the first position against the mechanical stop when the propeller is rotated at a first rotational speed and the blade rotates to the second position against the magnetic stop when the propeller is rotated at a second rotational speed in a same direction as when the blade is in the first position;, 'measuring an amount of vibration associated with the propeller, wherein the propeller includesdetermining if the measured amount of vibration exceeds a threshold; and determining a desired blade position;', ...

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Номер записи: 51
06-02-2020 дата публикации

Variable pitch propeller control system

Номер: US20200039635A1
Автор: Benoit Lachance, Ignazio Broccolini
Принадлежит: Pratt and Whitney Canada Corp

The variable pitch propeller control system can have a source of adjustable, actuation hydraulic pressure, a feather valve openable to provide an actuation path of the actuation hydraulic pressure between the source and the actuator, and closeable to connect the actuator to a drain below the actuation hydraulic pressure and close the actuator path, and a bypass path parallel to the actuator path, the bypass path having a restricted flow area relative to a flow area of the actuator path.

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Номер записи: 52
15-02-2018 дата публикации

Automated Variable Pitch Propeller Blade

Номер: US20180043988A1
Автор: Baldwin Leo, Campell Scott Patrick, Fong Gary
Принадлежит:

A variable pitch propeller is designed to adjust the pitch of the propeller blade during flight to maximize the propeller efficiency. The propeller blade may comprise airfoil cross-sections. Each cross-section may be composed of different materials at the leading edge and trailing edge. In various embodiments, these materials are selected and oriented to achieve the necessary elastic moduli of the leading and trailing edge for the airfoil cross-section. During liftoff, the airfoil at the blade tip possesses a high blade pitch (e.g. 20 degrees), thereby increasing the generated lift on the propeller blades. During flight or hover conditions when maximal lift is no longer required, the trailing edge of the airfoil displaces upward and reduces the blade pitch to minimize the drag forces on the blade tip. 1. A propeller blade comprising: 'a plurality of sections, one or more sections of the plurality of sections composed of a first material having an elastic modulus above a threshold number and one or more sections of the plurality of sections composed of a second material having an elastic modulus below the threshold number.', 'a plurality of airfoil cross-sections, the plurality of airfoil cross-sections further comprising2. The propeller blade of claim 1 , wherein the one or more sections composed of a first material having an elastic modulus above a threshold number further comprises a leading edge of the airfoil cross-section.3. The propeller blade of wherein one or more sections composed of a second material having an elastic modulus below the threshold number further comprises a trailing edge of the airfoil cross-section.4. The propeller blade of wherein the one or more sections of a first material and the one or more sections of a second material form a laminar structure.5. The propeller blade of wherein the one or more sections composed of a first material are interspersed as fibers throughout the one or more sections composed of a second material.6. The ...

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Номер записи: 53
15-02-2018 дата публикации

PITCH-CHANGE SYSTEM EQUIPPED WITH MEANS FOR ADJUSTING BLADE PITCH AND CORRESPONDING TURBINE ENGINE

Номер: US20180043989A1
Автор: Mayhew Dominique Gerhadt, Miqueu Xavier Bertrand, SERVANT RÉGIS EUGÈNE HENRI, Souryavongsa Eddy Keomorakott, Tajan Sébastien Emile Philippe
Принадлежит: SAFRAN AIRCRAFT ENGINES

A system changes the pitch of blades of at least one turbine engine propeller provided with a plurality of blades. The system includes a link mechanism connected to the propeller blades at a first interface, and a control means acting on the link mechanism and having a body movable in translation along a longitudinal axis. A load transfer module is arranged between the link mechanism and the control means. The load transfer module is connected to the link mechanism at a second interface. The system further includes means for adjusting the setting of the blades, the adjustment means having first adjustment elements configured to adjust an axial position of the second interface along the axis. The adjustment means also includes second adjustment elements configured so as to adjust an axial distance along the axis between the first interface and the second interface. 1. A system for changing the pitch of blades of at least one turbine engine propeller provided with a plurality of blades , the system comprising:a link mechanism connected to the blades at a first interface;a control means acting on the link mechanism and having a movable body translatable along a longitudinal axis relative to a fixed body;a load transfer module arranged between the link mechanism and the control means, the load transfer module being connected to the link mechanism at a second interface; and removable first adjustment elements arranged between the load transfer module and the movable body and configured to adjust an axial position of the second interface along the longitudinal axis, and', 'second adjustment elements configured to adjust an axial distance along the longitudinal axis between the first interface and the second interface., 'means for adjusting the setting of the blades, comprising2. The system according to claim 1 , wherein the first adjustment elements comprise an annular shim of a predetermined length along the longitudinal axis dependent on an expected displacement of the ...

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Номер записи: 54
15-02-2018 дата публикации

PITCH CHANGE MODULE FOR TURBINE ENGINE AND CORRESPONDING TURBINE ENGINE

Номер: US20180043990A1
Автор: CHARIER Gilles Alain Marie, COTTET Clement, FABRE Adrien Jacques Philippe, Perdrigeon Christophe Marcel Lucien, Tajan Sébastien Emile Philippe
Принадлежит:

The invention relates to turbine engine module () including a case () rotating around a longitudinal axis (X) and carrying a propeller having a plurality of blades, a stationary case () comprising a cylindrical wall () extending between an inner wall () and an outer wall () of the rotating case (), and a system () for changing the pitch of the blades () of the propeller. The wall () is connected downstream to a first substantially frustoconical wall () and upstream to a second substantially frustoconical wall (), a first rolling bearing () being inserted respectively downstream directly between a radially outer face () of the inner wall () and a radially inner face () of the first frustoconical wall, and a second rolling bearing (′) inserted downstream directly between the radially outer face () of the inner wall () and an inner face () of the second frustoconical wall (). 1. A turbine engine module with longitudinal axis , the module including:a case rotating around the longitudinal axis and carrying a propeller provided with a plurality of blades;a stationary case comprising a cylindrical wall extending between an inner wall and an outer wall of the rotating case; anda system for changing the pitch of the blades of the propeller comprising a connecting mechanism connected to the blades of the propeller and a control means acting on the connecting mechanism,the cylindrical wall of the stationary case being connected downstream to a first substantially frustoconical wall and upstream to a second substantially frustoconical wall, a first rolling bearing being inserted respectively downstream directly between a radially outer face of the inner wall of the rotating case and a radially inner face of the first frustoconical wall, and a second rolling bearing being inserted upstream directly between the radially outer face of the inner wall of the rotating case and an inner face of the second frustoconical wall.2. The module according to claim 1 , wherein the first and ...

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Номер записи: 55
15-02-2018 дата публикации

PITCH CHANGE SYSTEM EQUIPPED WITH MEANS FOR SUPPLYING FLUID TO A CONTROL MEANS AND CORRESPONDING TURBINE ENGINE

Номер: US20180043991A1
Автор: FABRE Adrien Jacques Philippe, FORESTO Paul Antoine, Ibarzo Stéphane, SERVANT RÉGIS EUGÈNE HENRI, Tajan Sébastien Emile Philippe
Принадлежит: SAFRAN AIRCRAFT ENGINES

A system is configured to change the pitch of blades of at least one turbine engine propeller provided with multiple blades. The system includes a control means acting on a connecting mechanism connected to the blades of the propeller. The control means includes a stationary body and a movable body translatable along a longitudinal axis (X) relative to the stationary body and defining two chambers. A fluid supply means is configured to be connected to a fluid supply source and to supply the chambers. The fluid supply means includes at least one channel. The channel is arranged and extends along an axis (Q) parallel to the longitudinal axis in an overthickness of a wall of the stationary body, the overthickness extending radially inside relative to the longitudinal axis. 1. A system for changing the pitch of blades of at least one turbine engine propeller provided with multiple blades , the system comprising a control means acting on a connecting mechanism connected to the blades of the propeller , said control means including a stationary body and a movable body translatable along a longitudinal axis relative to said stationary body and defining two chambers , and fluid supply means configured to be connected to a fluid supply source and to supply said chambers , the supply means comprising at least one channel , wherein the channel is arranged and extends along an axis parallel to the longitudinal axis in an overthickness of a wall of the stationary body , the overthickness extending radially inside the stationary body and at least partially along an outer cylindrical surface of the wall of the stationary body relative to the longitudinal axis , the system further comprising a connecting ring secured upstream from the stationary body and provided with hydraulic , mechanical and/or electrical connecting interfaces of the control means , the channel being connected to a first hydraulic connection interface of the connecting ring connected to the fluid supply source , ...

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Номер записи: 56
19-02-2015 дата публикации

PROPELLER PITCHLOCK SYSTEM WITH A ROTATING INTERFACE

Номер: US20150050149A1
Автор: Perkinson Robert H.
Принадлежит: HAMILTON SUNDSTRAND CORPORATION

A pitchlock system includes a ballscrew screw mounted along an axis of rotation of an actuator, the ballscrew screw has an internal ballscrew bore; a pitchlock nut mounted about the ballscrew screw, the pitchlock nut including an internal pitchlock nut thread; a ballscrew ballnut mounted about the ballscrew screw and axially adjacent the pitchlock nut; a pitchlock actuation rod mounted axially within the internal ballscrew bore, the pitchlock actuation rod having an internal pitchlock actuation bore and a ball bearing aperture for receiving multiple ball bearings; a pitchlock retainer pin mounted axially within the internal pitchlock actuation bore; and a belleville spring which biases the ballscrew screw towards an axially fixed surface of the actuator in a pitchlock position, the ballscrew screw being movable between an operational position and the pitchlock position. 1. A pitchlock system comprising:a ballscrew screw mounted along an axis of rotation of an actuator, the ballscrew screw having an internal ballscrew bore;a pitchlock nut mounted about the ballscrew screw, the pitchlock nut including an internal pitchlock nut thread;a ballscrew ballnut mounted about the ballscrew screw and axially adjacent the pitchlock nut;a pitchlock actuation rod mounted axially within the internal ballscrew bore, the pitchlock actuation rod having an internal pitchlock actuation bore and a ball bearing aperture for receiving multiple ball bearings;a pitchlock retainer pin mounted axially within the internal pitchlock actuation bore; anda belleville spring which biases the ballscrew screw towards an axially fixed surface of the actuator in a pitchlock position, the ballscrew screw being movable between an operational position and the pitchlock position.2. The pitchlock system of claim 1 , further comprising:a pitchlock piston axially coupled to the pitchlock retainer pin.3. The pitchlock system of claim 2 , wherein the pitchlock piston is coupled to a pitchlock transfer tube ...

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Номер записи: 57
03-03-2022 дата публикации

Blade Dovetail and Retention Apparatus

Номер: US20220065118A1
Автор: Kray Nicholas Joseph, Prentice Ian F.
Принадлежит:

Methods, apparatus, systems, and articles of manufacture are disclosed to adjust a pitch axis of a blade of an engine. An example blade apparatus includes: a hub to facilitate movement of blades in an engine, the engine having a radial center line; and a trunnion connected to the hub. The example trunnion includes a slot to accommodate a first blade, and at least one of the trunnion or the first blade is positioned with at least one of a tilt or a lean with respect to the radial center line to form a pitch axis offset from the radial center line such that the pitch axis is not parallel to or co-linear with the radial center line. The example hub is to rotate the first blade about the pitch axis.

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Номер записи: 58
25-02-2016 дата публикации

Actuator lock

Номер: US20160053620A1
Автор: Marco Gianfranceschi
Принадлежит: Microtecnica SRL

A locking device for use in a rotor blade, said locking device comprising: a locking member that is arranged to be movable from an unlocked position to a locking position upon experiencing sufficiently fast rotation; and a selectively engagable retaining device arranged when engaged to retain the locking member in the unlocked position. The locking device will typically default to an unlocked position during normal rotation and will only be locked so as to prevent movement when the retaining device is de-activated. A method of locking an actuator is also disclosed. The locking device has applications in helicopter rotor blades and wind turbine blades amongst others.

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Номер записи: 59
22-02-2018 дата публикации

APPARATUS AND METHODS FOR AIRCRAFT PROPELLER CONTROL

Номер: US20180050816A1
Автор: JARVO James Robert, YAKOBOV Ella
Принадлежит:

An aircraft propeller control system for an aircraft propeller with adjustable blade angle has a blade angle feedback ring and a sensor, one of which is mounted for rotation with the propeller. The blade angle feedback ring moves longitudinally along with adjustment of the blade angle and has position markers circumferentially spaced apart at distances that vary along a longitudinal axis. The sensor is positioned adjacent the feedback ring for producing signals indicative of passage of the position markers. Intervals between signals are indicative of circumferential distances between position markers. A controller measures longitudinal position of the feedback ring based on the intervals and is configured to produce a warning signal if the longitudinal position is outside a first threshold range. 1. A propeller control system for an aircraft propeller rotatable about a longitudinal axis and having an adjustable blade angle , the control system comprising:a blade angle feedback ring coupled to the propeller to rotate with the propeller and to move along the longitudinal axis along with adjustment of the blade angle, said blade angle feedback ring comprising a plurality of position markers spaced around its circumference such that a circumferential distance between at least some adjacent ones of said position markers varies along said longitudinal axis;a sensor positioned adjacent said blade angle feedback ring for producing signals indicative of passage of said position markers, such that an interval between ones of said signals is indicative of a circumferential distance between adjacent ones of said position markers; anda controller in communication with said sensor to measure a longitudinal position of said feedback ring based on an interval between consecutive ones of said signal, said controller configured to produce a warning signal if said longitudinal position is outside a first threshold range.2. The propeller control system of claim 1 , wherein said warning ...

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Номер записи: 60
13-02-2020 дата публикации

Automated propeller feather testing

Номер: US20200049027A1
Автор: Brant Duke, Kenneth Matheson
Принадлежит: Pratt and Whitney Canada Corp

There is described herein methods and systems for testing a propeller feathering function. The method comprises monitoring a rotational speed over time of propeller blades of an aircraft, commanding an angle change of the propeller blades, comparing a post-angle change rotational speed of the propeller blades to an expected rotational speed without the commanded angle change and obtaining, by the processor, a rotational speed difference, and issuing a test passed signal when the rotational speed difference exceeds a threshold and a test failed signal when the rotational speed difference does not exceed the threshold.

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Номер записи: 61
01-03-2018 дата публикации

PROPELLER PITCH CONTROL ACTUATION SYSTEM

Номер: US20180057146A1
Автор: Dutka Martin, Futa, JR. Paul W., McRoberts Brad, Shelby Dugan
Принадлежит: HONEYWELL INTERNATIONAL INC.

A propeller pitch control actuation system includes a relatively lightweight, relatively inexpensive means for selectively preventing the propeller pitch control actuator from commanding reverse pitch positions. 1. A propeller pitch control actuation system , comprising:an actuator body including a first head-end fluid port, a second head-end fluid port, and a rod-end fluid port;a propeller pitch control actuator movably disposed within the actuator body and movable, in response to differential fluid pressure between the rod-end fluid port and one or both of the first and second head-end fluid ports, to an actuator position;a reverse lockout valve body having a first fluid control port and a second fluid control port, the first fluid control port in fluid communication with the first head-end fluid port, the second fluid control port in fluid communication with the second head-end fluid port;a reverse lockout valve disposed within the reverse lockout valve body and selectively moveable between (i) a closed position, in which the valve prevents fluid flow to and from the first head-end fluid port via the reverse lockout valve body, and (ii) an open position, in which the valve allows fluid flow to and from the first head-end fluid port via the reverse lockout valve body;a check valve body having a fluid inlet port and a fluid outlet port, the fluid inlet port in fluid communication with the second head-end fluid port and the second fluid control port, the fluid outlet port in fluid communication with the first head-end fluid port and the first fluid control port; anda check valve disposed within the check valve body and movable between (i) a closed position, in which fluid is prevented from flowing through the check valve body and into the first head-end fluid port, and (ii) an open position, in which fluid may flow through the check valve body and into the first head-end fluid port.2. The system of claim 1 , further comprising:a reverse lockout valve actuator ...

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Номер записи: 62
01-03-2018 дата публикации

TURBINE ENGINE WITH AN OIL GUIDING DEVICE AND METHOD FOR DISASSEMBLING THE TURBINE ENGINE

Номер: US20180058260A1
Автор: COTTET Clement, Cretin Fabrice Michel François René, Jacquemard Christophe Paul, Perdrigeon Christophe Marcel Lucien, Toribio Leny
Принадлежит: SAFRAN AIRCRAFT ENGINES

A turbine engine is provided with a longitudinal rotation axis having at least one shaft with a radial axis, in particular a pitch change system for the blades of a propeller, said shaft traversing a radial passage of a substantially cylindrical case around the longitudinal axis. The turbine engine includes an annular oil guiding device around the radial shaft. The device has first and second annular parts nested in one another and secured to one another by hooping. The first part is secured by hooping to the radial shaft, and the second part is configured so as to be separated from the first part under the action of a force oriented along the radial axis and exerted on the second part by a member of the turbine engine forming a stop during a radial movement of the radial shaft. 1. A turbine engine provided with a longitudinal rotation axis comprising at least one shaft with a radial axis , in particular a pitch change system for the blades of a propeller , said shaft traversing a radial passage of a substantially cylindrical case around the longitudinal axis , andwherein the turbine engine comprises an annular oil guiding device that extends around the radial shaft, said oil guiding device comprising a first annular part and a second annular part nested in one another and secured to one another by hooping, the first part being secured by hooping to the radial shaft and the second part being configured to be separated from the first part by the action of a force oriented along the radial axis and exerted on the second part by a member of the turbine engine forming a stop during a radial movement of the radial shaft.2. The turbine engine according to claim 1 , wherein the first part passes through the member claim 1 , the inner diameter of the member of the turbine engine being substantially larger than the outer diameter of the first part.3. The turbine engine according to claim 1 , wherein the first part comprises a cylindrical support step extending in a plane ...

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Номер записи: 63
01-03-2018 дата публикации

MEANS FOR CONTROLLING A PITCH CHANGE SYSTEM COMPRISING AN ANTI-ROTATION DEVICE, A PITCH CHANGE SYSTEM EQUIPPED WITH SAID CONTROL MEANS, AND A CORRESPONDING TURBINE ENGINE

Номер: US20180058324A1
Автор: FABRE Adrien Jacques Philippe, Ibarzo Stéphane, SERVANT RÉGIS EUGÈNE HENRI, Souryavongsa Eddy Keomorakott, Tajan Sébastien Emile Philippe
Принадлежит:

The invention relates to a means () for controlling a system for changing the pitch of blades of a turbine engine propeller, the control means () comprising a fixed member () and a member () which is movable in translation along a longitudinal axis (X) relative to the fixed member (), and an anti-rotation device () configured so as to prevent the rotation of the movable member () relative to the fixed member () about the axis (X). 1. Controlling means of a pitch change system for changing the pitch of blades of at least one turbine engine propeller , the control means comprising a fixed member and a member which is movable in translation along a longitudinal axis relative to said fixed member and an anti-rotation device which is configured so as to prevent the rotation of the movable member relative to the fixed member about the longitudinal axis , wherein the anti-rotation device comprises a longitudinal structural crossmember which is mounted by means of a first and a second end on the fixed member and support and guide means integrally in translation the movable member along the longitudinal axis , the crossmember extending radially outside the movable member and the fixed member relative to a radial axis which is perpendicular to the longitudinal axis and being guided through the support and guide means.2. Control means according to claim 1 , wherein the crossmember is passed through claim 1 , along an axis which is substantially in parallel with the longitudinal axis claim 1 , by a line for supplying lubricant which is connected to a source for supplying lubricant and supplying a component of the turbine engine.3. Control means according to claim 2 , wherein the line is mounted in a sliding manner in the crossmember.4. Control means according to claim 2 , wherein the crossmember comprises damping means between an internal wall of the crossmember and an external wall of the line.5. Control means according to claim 1 , wherein the support and guide means comprise ...

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Номер записи: 64
20-02-2020 дата публикации

Pitch control system

Номер: US20200055587A1
Автор: Chunmei Chen, Ryan M. Randall
Принадлежит: Qingdao Randall Aerodynamic Engineering LLC

A pitch control system characterized by a hub with at least two blade housings on the hub that are disposed around the hub axis. The blade housings have corresponding blades that engage with them. The blades spiral along housing longitudinal axes toward and away from the hub axis about a segment of helical path to effect a change in the pitch of each blade. One or more elastic members draw the blades toward the hub axis, either directly or indirectly. There are pitch mechanisms effective to facilitate blades to spiral around housing-longitudinal axes. A blade will spiral away from the hub axis when the centrifugal force exerted on the blade exceeds the opposing elastic force in the housing-longitudinal direction (neglecting other forces). Conversely, blades spiral toward the hub axis when said centrifugal force is less than said elastic force. There is an imaginary plane orthogonal to the hub axis. Housing-longitudinal axes have angles with respect to the imaginary plane of not more than 30 degrees.

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Номер записи: 65
02-03-2017 дата публикации

VARIABLE PITCH FAN PITCH RANGE LIMITER

Номер: US20170058683A1
Автор: Miller Brandon Wayne, Niergarth Daniel Alan
Принадлежит:

A variable pitch fan for gas turbine engine is provided. The variable pitch fan includes a plurality of fan blades rotatably coupled to a disk and an actuation assembly for changing a pitch of each of the plurality of fan blades. The actuation assembly generally includes an actuation member operably connected to at least one of the plurality of fan blades and a pin. The pin is movable between a first position in which the pin is positioned at least partially in a channel defined in the actuation member, and a second position. The pin blocks movement of the actuation member relative to the pin past a range defined by the channel when in the first position. The actuation assembly further includes a retraction system for selectively engaging the pin in moving the pin from the first position to the second position. 1. A variable pitch fan for a gas turbine engine , the variable pitch fan comprising:a plurality of fan blades rotatably coupled to a disk, each of the plurality of fan blades defining a pitch; and an actuation member operably connected to at least one of the plurality of fan blades and defining a channel; and', 'a pin moveable between a first position in which the pin is positioned at least partially in the channel defined in the actuation member and a second position, the pin blocking movement of the actuation member relative to the pin past a range defined by the channel when in the first position; and', 'a retraction system for selectively engaging the pin and moving the pin from the first position to the second position., 'an actuation assembly for changing a pitch of each of the plurality of fan blades, the actuation assembly including'}2. The variable pitch fan of claim 1 , wherein the actuation member is a scheduling ring rotatable relative to the disk.3. The variable pitch fan of claim 2 , wherein the scheduling ring defines a plurality of slots claim 2 , wherein the actuation assembly further includes a plurality of linkage arms claim 2 , wherein ...

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Номер записи: 66
05-03-2015 дата публикации

RAM AIR TURBINE STARTUP

Номер: US20150064006A1
Автор: Russ David Everett
Принадлежит:

A ram air turbine (RAT) in which a cam follower is operably coupled to turbine blades such that a cam follower position determines turbine blade pitch. 1. A ram air turbine (RAT) in which a cam follower is operably coupled to turbine blades such that a cam follower position determines turbine blade pitch , the RAT comprising:an axially movable governor shaft having an end nested within a nut;a post having threading that engages with the nut and a screw driving feature;a handle having an end that is engageable with the screw driving feature when the handle occupies an engagement position and disengageable from the nut when the handle occupies a disengagement position; anda system operably coupled to the governor shaft and the post whereby, at start up, the handle selectively occupies the engagement position and is manually rotatable in a first direction to move the governor shaft in a first axial direction such that the cam follower is positioned at a first position, and, as RPMs increase from zero due to airstream flow, the post is automatically rotatable in a second direction to move the governor shaft in a second axial direction such that the cam follower is positioned at second positions favorable for start up.2. A startup assistance apparatus for a ram air turbine (RAT) , the apparatus comprising:a shaft having threading over a partial length thereof;a nut disposed on the shaft to travel back and forth between a beginning of the partial length, an end of the partial length and a remote position remote from the partial length;an elastic element to bias the nut towards the remote position;a lever operably coupled to the nut to selectively move the nut from the remote position to the end of the partial length against the elastic element bias; anda system by which the nut provides the RAT with first direction blade rotation assistance while traveling from the beginning to the end of the partial length and second direction blade rotation of the RAT selectively moves ...

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Номер записи: 67
22-05-2014 дата публикации

POWER GENERATION APPARATUS

Номер: US20140140846A1
Автор: Birkestrand Orville J.
Принадлежит:

A power generation apparatus comprises a rotor rotatably mounted to a support and a plurality of vanes extending radially out from the rotor and positioned to be engaged by a moving fluid stream. Each vane includes a wing-shaped main blade having leading and trailing edges, and a co-extensive conditioner blade having leading and trailing edges. The conditioner blade is spaced parallel to the main blade so as to define therebetween a slot having an entrance and an exit. A lift-varying device boarders the slot to vary the lift produced by that vane inversely to the speed of the moving fluid stream so that the rotor turns at a relatively constant rate. The rotor, driven by wind or water, may be coupled to the armature of an induction motor/generator to produce electric power. 1. Power generation apparatus comprising a rotor rotatably mounted to a support , a plurality of vanes extending radially out from the rotor and positioned to be engaged by a moving fluid stream , each vane including a wing-shaped main blade having opposite surfaces , a leading edge and a trailing edge , a co-extensive conditioner blade having opposite surfaces , a leading edge and a trailing edge and being spaced parallel to the main blade so as to define therebetween a slot having an entrance and an exit , and a lift varying device bordering the slot in each vane to vary the lift produced by that vane inversely to the speed of the moving fluid stream.2. The apparatus defined in wherein the entrance of each slot is larger than the exit thereof so that each slot has a funnel-shaped cross-section.3. The apparatus defined in wherein the lift varying device comprises a flap pivotally mounted to the corresponding main blade so as to form said trailing edge thereof claim 1 , each said flap being movable between a home position wherein it is angled toward the corresponding conditioner blade and a fully open position wherein it is not angled toward the corresponding conditioner blade claim 1 , and a ...

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Номер записи: 68
28-02-2019 дата публикации

AIRCRAFT PROPELLER COMPRISING COLLAPSIBLE VARIABLE PITCH BLADES

Номер: US20190061914A1
Автор: HERANGER Christophe, Prampolini Marco
Принадлежит:

Propeller for an aircraft engine comprising: a blade mounting associated with each blade, mounted so as to pivot on the hub according to an incident pitch axis; a pivoting link between each blade mounting and the root, allowing the blade to pivot relative to the blade mounting thereof according to a blade collapsing axis; associated with at least one of the blades, a member for controlling the collapsing/extension of the blade configured to pivot the root relative to the blade mounting according to the collapsing axis; and a passive device for synchronising the collapsing/extension of the blades, including a central synchronisation element mounted so as to rotate relative to the hub according to the propeller rotation axis, as well as a coupling element associated with each blade, including a first end mounted on the blade root and a second end mounted on the central synchronisation element. 121486. A propeller () for an aircraft engine () for being rotated about a propeller axis of rotation () , the propeller comprising a hub () as well as a plurality of blades () circumferentially distributed about the hub , characterized in that it further comprises:{'b': 10', '8', '14, 'a blade support () associated with each blade, said blade support being pivotably mounted on said hub () about an incidence pitch axis ();'}{'b': 16', '10', '8', '14, 'incidence control means () for the blades configured to pivot said blade support () relative to the hub (), about said incidence pitch axis ();'}{'b': 20', '10', '6', '6', '10', '22, 'i': 'a', 'a pivoting connection () between each blade support () and the root () of its associated blade, the pivot connection enabling the blade () to be pivoted relative to its blade support () about a blade folding axis ();'}{'b': 6', '24', '6', '10', '22', '24', '28', '30', '28', '8', '32', '30', '36', '32', '6, 'i': a', 'a', 'b', 'a, 'associated with at least one of the blades (), a blade folding/unfolding control member () configured to pivot ...

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Номер записи: 69
28-02-2019 дата публикации

Dual valve systems for actuator control

Номер: US20190061916A1
Автор: Timothy Maver
Принадлежит: Hamilton Sundstrand Corp

A system for controlling propeller pitch in the event of electro-hydraulic servo valve (EHSV) failure can include an actuator and a selection valve in fluid communication with the actuator. The selection valve can be fluid communication with a first EHSV having a first null state bias configured to bias the actuator to an increased-pitch position, and a second EHSV having a second null state bias configured to bias the actuator to a decreased-pitch position. The selection valve can be configured to selectively allow fluid communication between one of the first EHSV and actuator and/or the second EHSV and the actuator.

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Номер записи: 70
08-03-2018 дата публикации

ADAPTABLE ARTICULATING AXIAL-FLOW COMPRESSOR/TURBINE ROTOR BLADE

Номер: US20180066671A1
Автор: Bravo Luis, Ghoshal Anindya, Murugan Muthuvel
Принадлежит:

Conventional gas turbine engines are generally optimized to operate at nearly a fixed speed with fixed blade geometries for the design operating condition. When the operating condition of the engine changes, the flow incidence angles may not be optimum with the blade geometries resulting in reduced off-design performance. By contrast, according to embodiments of the present invention, articulating the pitch angle of turbine blades in coordination with adjustable nozzle vanes improves performance by maintaining flow incidence angles within the optimum range at all operating conditions of a gas turbine engine. Maintaining flow incidence angles within the optimum range can prevent the likelihood of flow separation in the blade passage and also reduce the thermal stresses developed due to aerothermal loads for variable speed gas turbine applications. 1. An articulating blade assembly comprising:a hub;a plurality of articulating blades arranged around the hub;one or more actuators positioned in the hub; and an articulating pin attached to the base of the blade; and', 'a set of gears operatively connecting the articulation pin to an actuator positioned in the hub and the one or more actuators; and, 'an actuator assembly operatively connected to each blade and comprisingone or more sensors configured to monitor the position of the blades; anda controller, connected to the one or more sensors, which controls that the actuators such that the articulating blades are rotated to have an optimum incidence angle for their operation.2. The articulating blade assembly of claim 1 , wherein the set of gears comprise: a first gear attached to the articulating pin; and a second gear operatively connected to the actuator engaging the first gear.3. The articulating blade assembly of claim 1 , wherein one actuator is provided for each blade.4. The articulating blade assembly of claim 1 , wherein there are fewer actuators than blades claim 1 , with at least one actuator controlling a ...

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Номер записи: 71
09-03-2017 дата публикации

PITCH CHANGE MECHANISM FOR A BLADED ROTOR

Номер: US20170066522A1
Автор: CURNOCK Philip A., DI MARTINO Mario
Принадлежит: ROLLS-ROYCE PLC

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. 1. A pitch change mechanism for a bladed rotor comprising:a driving sleeve having, in axial sequence, a first helical connection portion and a second helical connection portion;a drive shaft, the driving sleeve being positioned concentric with and surrounding the drive shaft;a first pitch-changing element having a first end drivingly engaged with the first helical connection portion, and a first ring gear portion at a second opposite end;a second pitch-changing element having a first end drivingly engaged with the second helical connection portion, and a second ring gear portion at a second opposite end; anda plurality of blade drive gears arranged in a circumferential array around a longitudinal axis of the drive shaft,the first pitch-changing element being positioned axially adjacent to the second pitch-changing element with the first ring gear portion facing the second ring gear portion,wherein the first and second pitch-changing elements are positioned concentrically over the driving sleeve, such that axial movement of the driving sleeve causes the first helical connection portion to rotate the first pitch-changing ...

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Номер записи: 72
09-03-2017 дата публикации

SYSTEM AND METHOD FOR CONTROLLING PROPELLER PITCH

Номер: US20170066523A1
Автор: MISZKIEWICZ Krzysztof
Принадлежит:

Systems and methods are disclosed for controlling the pitch angle of a propeller and rotor assembly that selectively limit the pitch angle according to a selected mode of operation. The system comprises an actuator having forward and aft chambers, an oil transfer bearing (OTB), and a fine stop collar. The fine stop collar including a first passage in fluid communication with the OTB and forward chamber during a ground-based mode of operation, and a second fluid passage being in fluid communication with the OTB and forward chamber during a flight-based mode of operation. 1. A pitch control system , comprising:a linear actuator engaged with a propeller blade crankshaft to vary propeller blade pitch, the actuator including:a cylinder including a fluidly-sealed cylinder wall,a piston translatably attached to the propeller blade crankshaft, the piston including a flange disposed within the cylinder to define a forward chamber and an aft chamber thereof, a projection extending from the flange through the cylinder aft chamber, and a coarse rotatable pipe attached to the piston and disposed through the cylinder forward chamber;an oil transfer bearing (OTB) positioned along a central axis, the OTB being joined to the cylinder wall in fluid communication with the forward chamber; anda fine stop collar annularly positioned above the OTB, the fine stop collar defining discrete first and second fluid passages, the first fluid passage being in fluid communication with the OTB and forward chamber during a ground-based mode of operation, the second fluid passage being in fluid communication with the OTB and forward chamber during a flight-based mode of operation.2. The pitch control system of claim 1 , wherein the OTB comprises a rotatable rotor and a rotationally-fixed stator positioned about the rotor claim 1 , the rotor being joined to the cylinder wall in parallel with the coarse rotatable pipe.3. The pitch control system of claim 2 , wherein the OTB rotor defines at least one ...

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Номер записи: 73
11-03-2021 дата публикации

DUAL ACTUATOR HYDRAULIC PITCH-LOCK PROPELLER SYSTEM

Номер: US20210070425A1
Автор: Maver Timothy
Принадлежит:

A system is provided. The system includes a dual piston actuator and valves. The dual piston actuator includes a primary actuator and a protection actuator. The primary and protection actuators move to increase and decrease a pitch of propellers of an aircraft with respect to a supply of first and second mediums. The valves include a first check valve, a second check valve, and a third valve. The third valve operates between a first mode and a protection mode. The second medium is directed to the primary and protection actuators through the first and second check valves by the third valve when the third valve is operating in a protection mode. 1. A system comprising:a dual piston actuator comprising a primary actuator and a protection actuator,wherein the primary and protection actuators move to increase and decrease a pitch of propellers of an aircraft with respect to a supply of first and second mediums; anda plurality of valves comprising a first check valve, a second check valve, and a third valve,wherein the third valve operates between a first mode and a protection mode,wherein the second medium is directed to the primary and protection actuators through the first and second check valves by the third valve when the third valve is operating in a protection mode.2. The system of claim 1 , wherein the protection mode comprises a hydraulic pitch-lock condition with a capability to increase the pitch of the propellers.3. The system of claim 1 , wherein the first medium comprises a hydraulic force used to decrease the pitch of the propellers.4. The system of claim 1 , wherein the second medium comprises a hydraulic force used to increase the pitch of the propellers.5. The system of claim 1 , wherein a connection of the protection actuator receives atmospheric pressure or the first medium.6. The system of claim 1 , wherein the third valve comprises a solenoid operated valve that generates a controlled magnetic field that provides a force acting on the third valve.7. ...

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Номер записи: 74
15-03-2018 дата публикации

PROPELLOR BLADE ANGLE CONTROL SYSTEM

Номер: US20180072402A1
Автор: WADDLETON David
Принадлежит:

A control circuit for changing the angle of propeller blades includes a propeller pitch change mechanism, and a fixed-displacement pump providing the supply of oil from an engine oil return system. A valve has an outlet port to direct oil from a cavity of the valve, and a pitch port in fluid communication with the pitch change mechanism. A spool of the valve is operable between a first position and a second position to respectively open and close the outlet port, and direct oil flow away from or to the pitch change mechanism. 1. An oil system of a turboprop gas turbine engine having a propeller of an aircraft , the propeller having a plurality of variable pitch propeller blades , the oil system comprising:an engine oil return system having a supply of oil; and a propeller pitch change mechanism;', 'a fixed-displacement pump communicating between the propeller pitch change mechanism and the supply of oil; and', 'a valve disposed downstream of the pump, the valve having a valve body with a cavity therein, the valve body including an outlet port, an inlet port, and a pitch port, the inlet port fluidly communicating with the pump, the outlet port fluidly communicating with the engine oil return system via an oil cooling line, and the pitch port fluidly communicating with the propeller pitch change mechanism, the valve including a spool within the cavity displaceable between a first position and a second position within the valve body;, 'a propeller blade angle control circuit communicating with the engine oil return system, includingwherein in the first position, the spool permits communication through the outlet port to the oil cooling line, and in the second position the spool substantially blocks the outlet port to permit oil to flow through the pitch port to the propeller pitch change mechanism.2. The oil system as defined in claim 1 , wherein the spool is in the second position during transient operation of the propeller pitch change mechanism.3. The oil system as ...

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Номер записи: 75
15-03-2018 дата публикации

ADJUSTMENT OF TRACK AND BALANCE OF A MULTI-BLADE ROTOR

Номер: US20180072412A1
Автор: BUESING Moritz
Принадлежит: AIRBUS HELICOPTERS DEUTSCHLAND GMBH

A multi-blade rotor of a rotary wing aircraft, the multi-blade rotor comprising at least one rotor blade that defines a pitch axis and that is provided with an associated pitch-control lever that is operatively coupled to a pitch link rod, the pitch link rod defining a longitudinal axis, wherein the associated pitch-control lever comprises an accommodation that is located on the longitudinal axis of the pitch link rod at a predetermined distance from the pitch axis of the at least one rotor blade, the pitch link rod being operatively coupled to the associated pitch-control lever at the accommodation of the associated pitch-control lever, wherein the predetermined distance is adjustable in order to enable adjustment of track and balance of the multi-blade rotor. 1. A multi-blade rotor of a rotary wing aircraft , the multi-blade rotor comprising at least one rotor blade that defines a pitch axis , the at least one rotor blade being provided with an associated pitch-control lever that is operatively coupled to a pitch link rod , the pitch link rod defining a longitudinal axis , wherein the associated pitch-control lever comprises an accommodation that is located on the longitudinal axis of the pitch link rod at a predetermined distance from the pitch axis of the at least one rotor blade , the pitch link rod being operatively coupled to the associated pitch-control lever at the accommodation of the associated pitch-control lever ,wherein the associated pitch-control lever comprises a bushing accommodation, the bushing accommodation being provided with an exchangeable bushing that provides the accommodation of the associated pitch-control lever so that the predetermined distance is adjustable in order to enable adjustment of track and balance of the multi-blade rotor.2. The multi-blade rotor of claim 1 ,wherein the exchangeable bushing is arranged in a supplementary bushing that defines the bushing accommodation, the supplementary bushing being arranged in an associated ...

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Номер записи: 76
24-03-2022 дата публикации

Pitch control assembly for an aircraft-bladed rotor

Номер: US20220089273A1
Автор: Dana TOMESCU
Принадлежит: Pratt and Whitney Canada Corp

There is provided a pitch control assembly for a rotor of an aircraft, the rotor rotatable about a longitudinal axis and having blades each rotatable about a span-wise axis to adjust a blade pitch angle thereof, the assembly comprising a plurality of position markers spaced circumferentially around the longitudinal axis and having lengths along the longitudinal axis which vary monotonically and incrementally, at least one sensor configured for producing at least one sensor signal in response to detecting a relative movement between the plurality of position markers and the at least one sensor, and a control unit communicatively coupled to the at least one sensor and configured to generate a feedback signal indicative of the blade pitch angle in response to the at least one sensor signal received from the at least one sensor.

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Номер записи: 77
15-03-2018 дата публикации

ROTARY MACHINE

Номер: US20180073375A1
Автор: Iwakiri Kenichiro
Принадлежит: MITSUBISHI HEAVY INDUSTRIES, LTD.

A rotary machine comprises a hub including: a blade-facing hub portion including a first blade-facing surface which faces a spherical hub-side end surface of a variable blade and which has a first spherical region having a spherical shape; an upstream hub portion disposed upstream of the blade-facing hub portion in an axial direction of the hub and having a first outer-peripheral surface being adjacent to the first blade-facing surface in the axial direction; and a downstream hub portion disposed downstream of the blade-facing hub portion in the axial direction and having a second outer peripheral surface being adjacent to the first blade-facing surface in the axial direction. At least one of following condition (a) or (b) is satisfied: (a) a downstream end of the first outer peripheral surface is disposed on an outer side of an upstream end of the first blade-facing surface in the radial direction of the hub; (b) an upstream end of the second outer peripheral surface is disposed on an outer side of a downstream end of the first blade-facing surface in the radial direction of the hub. 1. A rotary machine comprising:a hub configured to be rotatable about a rotational center axis;a casing configured to cover the hub and forming a fluid flow passage between the casing and the hub; anda variable blade disposed in the fluid flow passage and configured to be revolvable about a pivot axis along a radial direction of the hub,wherein the variable blade includes a hub-side end surface having a spherical shape and recessed outward in the radial direction of the hub, a blade-facing hub portion including a first blade-facing surface which faces the hub-side end surface of the variable blade and which has a first spherical region having a spherical shape and protruding outward in the radial direction of the hub;', 'an upstream hub portion disposed upstream of the blade-facing hub portion in an axial direction of the hub and having a first outer-peripheral surface being adjacent ...

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Номер записи: 78
15-03-2018 дата публикации

ROTARY MACHINE

Номер: US20180073376A1
Автор: Iwakiri Kenichiro
Принадлежит: MITSUBISHI HEAVY INDUSTRIES, LTD.

A rotary machine satisfies at least one of Dr1Dc2. Dr1, Dh1, Dr2, Dc1, Dt1, and Dc2 are distances from a rotational center axis of a hub to an upstream end of a first blade-facing surface facing a hub-side end surface of a variable blade, an upstream end of the hub-side end surface when the blade angle is maximum, a downstream end of a first outer peripheral surface adjacent to an upstream side of the blade-facing surface, an upstream end of a second blade-facing surface facing a tip-side end surface of the variable blade, an upstream end of the tip-side end surface when the blade angle is minimum, and a downstream end of a first inner peripheral surface adjacent to an upstream side of the second blade-facing surface, respectively. 1. A rotary machine comprising:a hub configured to be rotatable about a rotational center axis;a casing configured to cover the hub and forming a fluid flow passage between the casing and the hub; anda variable blade disposed in the fluid flow passage and configured to be revolvable about a pivot axis along a radial direction of the hub, a blade-facing hub portion including a first blade-facing surface facing a hub-side end surface of the variable blade; and', 'an upstream hub portion disposed upstream of the blade-facing hub portion in an axial direction of the hub and having a first outer peripheral surface being adjacent to the first blade-facing surface in the axial direction,, 'wherein the hub includes a blade-facing casing portion including a second blade-facing surface which faces a tip-side end surface of the variable blade; and', 'an upstream casing portion disposed upstream of the blade-facing casing portion in the axial direction and having a first inner peripheral surface being adjacent to the second blade-facing surface in the axial direction, and, 'wherein the casing includes [{'br': None, 'Dr1Dc2\u2003\u2003(b)'}], 'wherein at least one of following ...

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Номер записи: 79
19-03-2015 дата публикации

TIGHTENING AND OIL DISCHARGING NUT, AND A TURBINE ENGINE

Номер: US20150078899A1
Автор: Belmonte Olivier, Patsouris Emmanuel Pierre Dimitri
Принадлежит: SNECMA

The invention relates to a device () for controlling the pitch of the blades of a rotor, comprising: 1. A device for controlling the pitch of the blades of a rotor , comprising:a radial shaft, wherein rotation of said radial shaft controls the a pitch of the blades,a guiding bearing, for guiding the radial shaft,wherein: a circumferential rib extending as a protrusion towards an outside of the nut, for guiding a lubrication oil of the guiding bearing towards the outside of the nut,', 'a circumferential groove capped by the circumferential rib, said circumferential groove comprising one or more oil discharge holes, for discharging oil out of the nut., 'a nut configured to tighten the guiding bearing along a radial axis, and comprising2. The device according to claim 1 , wherein the circumferential rib extends as a protrusion towards the inside of the nut.3. The device according to claim 2 , comprising a circumferential cavity capped by a portion of the rib protruding towards the inside of the nut.4. The device according to claim 3 , wherein:the circumferential rib extends as a protrusion towards an inside of the nut so as to cap the cavity,the nut comprises one or more oil discharge holes facing the cavity,so as to ensure guiding of the oil from the cavity towards the outside of the nut.5. The device according to claim 1 , wherein:the nut surrounds the radial shaft, anda portion of the rib protruding towards the inside of the nut caps a junction area between the radial shaft and the nut.6. The device according to claim 1 , wherein:the nut comprises a circumferential joint in contact with a ferrule supporting the guiding bearing, anda portion of the rib protruding towards the outside of the nut caps a contact area between the ferrule and the circumferential joint.7. . A turbine engine claim 1 , comprising:a rotor, comprising blades with variable pitch;{'claim-ref': {'@idref': 'CLM-00001', 'claim 1'}, 'a device for controlling the pitch of these blades, according to ...

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Номер записи: 80
05-06-2014 дата публикации

Apparatus, System, and Method for Pitching and Twisting a Blade of a Rotorcraft

Номер: US20140154074A1
Автор: Friedrich K. Straub, Terrence S. Birchette, Thomas A. Zientek
Принадлежит: Boeing Co

A method and apparatus for moving a blade of a rotorcraft. The method comprises operating the rotorcraft and applying a torque to an elongate member connected to a tip portion of the blade during operation of the rotorcraft using a tip actuation mechanism that is external to the blade and associated with the elongate member such that the tip portion of the blade rotates about an axis through the blade.

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Номер записи: 81
05-06-2014 дата публикации

DEVICE FOR SUPPLYING AND DISTRIBUTING FLUID

Номер: US20140154076A1
Автор: Belmonte Olivier, Curlier Augustin, Perrier Mathieu
Принадлежит: SNECMA

The device () is intended to supply a rotating linear displacement actuator capable of controlling the pitch of the blades of a propeller, according to separate operating states, from a rotary power assembly, the device being arranged so as to be located between the power assembly and the actuator, along a longitudinal axis (A), and being connected in rotation therewith. According to the invention, the device comprises means () for supplying fluid interacting with said power assembly and defining as many supplies as there are operating states of the actuator, and a fluid distributor () to which said supplies are connected and having separate channels for transporting the fluid in the direction of the actuator according to the operating states, by means of tubular equipment () connected to the distributor. 1. Device for supplying and distributing fluid for a rotating linear displacement actuator capable of controlling the pitch of the blades of a propeller , according to separate operating states , by means of a rotary power assembly , said device being arranged so as to be located between the power assembly and the actuator , along a longitudinal axis , and being connected in rotation therewith , characterised in that it comprises:means for supplying fluid comprising radial arms having internal passages capable of interacting with said power assembly and defining as many supplies as there are operating states of the actuator,a fluid distributor to which the internal passages of the arms of said supplies are connected, and having channels capable of separately transporting the fluid in the direction of the actuator according to the operating states, andtubular equipment connected coaxially to the distributor and forming at least two independent chambers connected to separate lateral channels of the distributor, and one or the other of which are capable of being in communication with said actuator for two operating states thereof, said distributor comprising another ...

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Номер записи: 82
18-03-2021 дата публикации

PROPELLER ASSEMBLY AND PITCH CONTROL UNIT

Номер: US20210079855A1
Автор: Bellocchio Giuseppe, Castellani Simone, Cervelli Giuseppe, Jirasek Vojtech, Manzoni Miriam
Принадлежит:

A variable pitch propeller assembly operatively coupled with an engine and methods for controlling the pitch of a plurality of propeller blades thereof is provided. In one example aspect, the variable pitch propeller assembly includes features for combining overspeed, feathering, and reverse functionality in a single secondary control valve. The secondary control valve is operable to selectively allow a controlled amount of hydraulic fluid to flow to or from a pitch actuation assembly such that the pitch of the propeller blades can be adjusted to operate the variable pitch propeller assembly in one of a constant speed mode, a feather mode, and a reverse mode. 1. A variable pitch propeller assembly for an engine defining an axial direction , a radial direction , and a circumferential direction , the variable pitch propeller assembly comprising:a plurality of propeller blades rotatable about the axial direction and spaced apart along the circumferential direction, each propeller blade of the plurality of propeller blades rotatable through a plurality of blade angles about respective pitch axes each extending in the radial direction;a pitch actuation assembly for adjusting the plurality of propeller blades through the plurality of blade angles and including a propeller dome defining a chamber; and at least one electrohydraulic servovalve operable to selectively allow a flow of hydraulic fluid to or from the propeller dome of the pitch actuation assembly and when hydraulic fluid is not located at an inlet port of the at least one electrohydraulic servovalve an oil starvation condition is defined; and', 'at least one valve selectively fluidly coupling the propeller dome to the inlet port of the at least one electrohydraulic servovalve., 'a pitch control unit, comprising2. The variable pitch propeller assembly of wherein the at least one valve is a one-way valve having an inlet fluidly coupled to the propeller dome and an outlet fluidly coupled to the inlet port of the at ...

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Номер записи: 83
23-03-2017 дата публикации

SINGLE LEVER TURBOPROP CONTROL SYSTEMS AND METHODS UTILIZING TORQUE-BASED AND POWER-BASED SCHEDULING

Номер: US20170081038A1
Автор: Coffey Scot, Looper Dave, Xiong Yufei
Принадлежит: HONEYWELL INTERNATIONAL INC.

Embodiments of a single lever turboprop control method and system are provided, which utilize torque-based and/or power-based scheduling to achieve a desired (e.g., substantially proportional) relationship between control lever position and the power output of a turboprop engine. In one embodiment, the method includes the step or process of monitoring, at an Engine Control Unit (ECU), for receipt of a Power Lever Angle (PLA) signal from a single lever control device. When a PLA control signal received at the ECU, a target torque or power output is established as a function of at least the PLA control signal. A first engine setpoint, such as a blade angle setpoint or an engine rotational speed setpoint, is determined utilizing the target torque output. An operational parameter of the turboprop engine is then adjusted in accordance with the first engine setpoint. 1. A method for operating a turboprop engine utilizing a single lever control system including a single lever control device operably coupled to an Engine Control Unit (ECU) , the method comprising:at the ECU, monitoring for receipt of a Power Lever Angle (PLA) control signal from the single lever control device;when a PLA control signal received at the ECU, establishing a target torque output for the turboprop engine as a function of at least the PLA control signal;determining a first engine setpoint utilizing the target torque output; andadjusting an operational parameter of the turboprop engine in accordance with the first engine setpoint.2. The method of further comprising:measuring the current torque output of the turbopropeller engine after adjusting the operational parameter of the turboprop engine; andfurther adjusting the operational parameter of the turboprop engine to reduce any discrepancy between the current torque output and the target torque output.3. The method of wherein the first engine setpoint comprises an engine rotational speed setpoint claim 1 , and wherein adjusting comprises adjusting ...

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Номер записи: 84
02-04-2015 дата публикации

SYSTEM AND METHOD OF MONITORING WEAR IN A BEARING

Номер: US20150093059A1
Автор: Davis Hunter J.
Принадлежит: Bell Helicopter Textron Inc.

A bearing can include a ball member, a race, and a liner located on an interior surface of the race, the liner having a first surface bonded to an interior surface of the race, the liner having a second surface that is adjacent to the ball member. The bearing also includes a wafer having a wear surface that is aligned with the second surface of the liner, the wafer being an electrically conductive member. Operational wear of the liner can be calculated by comparing a measured resistance of the wafer to an original known resistance of the wafer. 1. A bearing , comprising:a ball member;a race;a liner located on an interior surface of the race, the liner having a first surface bonded to an interior surface of the race, the liner having a second surface that is adjacent to the ball member; anda wafer having a wear surface that is aligned with the second surface of the liner, the wafer being an electrically conductive member.2. The bearing according to claim 1 , wherein the ball member has a hole located therethrough.3. The bearing according to claim 1 , further comprising:a first lead and second lead electrically coupled to the wafer.4. The bearing according to claim 3 , further comprising:a terminal coupled to the first lead and the second lead.5. The bearing according to claim 4 , wherein the terminal is located on an exposed surface of the bearing.6. The bearing according to claim 4 , wherein the terminal is located on an exposed surface of the race.7. The bearing according to claim 1 , wherein the liner includes a polytetrafluoroethylene material.8. The bearing according to claim 1 , wherein the wafer is a ring shaped member that is concentric with a centerline axis of the race.9. The bearing according to claim 1 , wherein the wafer is an arc shaped member that extends from a first face of the race to a second face of the race.10. The bearing according to claim 1 , wherein the wafer is an arc shaped member that intersects an axial load path axis of the bearing.11. ...

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Номер записи: 85
02-04-2015 дата публикации

ELECTRICALLY DRIVEN AIRCRAFT

Номер: US20150093272A1
Автор: Kömer Olaf, LANGE Thomas, Petermaier Korbinian, Schramm Marco
Принадлежит:

An electrically driven aircraft includes at least one drive arrangement which has an aircraft propeller comprising a propeller shaft, a propeller bearing configured to radially and axially support the propeller shaft, a propeller hub which is driven by the propeller shaft, and a plurality of propeller blades attached to the propeller hub. A dynamoelectric rotary machine has a stator and a rotor which interacts with the stator and is coupled directly to the propeller shaft. The propeller bearing and the stator, are accommodated in a support structure which is mechanically coupled to an aircraft structure of the aircraft. 1. An electrically driven aircraft , comprising at least one drive arrangement which includes:an aircraft propeller comprising a propeller shaft, a propeller bearing configured to radially and axially support the propeller shaft, a propeller hub which is driven by the propeller shaft, and a plurality of propeller blades attached to the propeller hub,a dynamoelectric rotary machine having a stator and a rotor interacting with the stator and coupled directly to the propeller shaft, anda support structure configured to accommodate the propeller bearing and the stator, said support structure being mechanically coupled to an aircraft structure of the aircraft.2. The electrically driven aircraft of claim 1 , wherein the rotor is configured as an external or internal rotor.3. The electrically driven aircraft of claim 1 , wherein the propeller blades are each defined by a setting angle which is adjustable by a hydraulic mechanism or an electric mechanism.4. The electrically driven aircraft of claim 3 , wherein the hydraulic mechanism includes a hydraulic pump operatively connected to the propeller shaft and a governor operatively connected to the hydraulic pump.5. The electrically driven aircraft of claim 4 , wherein the propeller shaft is configured in the form of a hollow shaft.6. The electrically driven aircraft of claim 1 , wherein the support structure ...

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Номер записи: 86
28-03-2019 дата публикации

FLUID-DRIVEN DEVICE

Номер: US20190092452A1
Автор: XIE Xue Hui
Принадлежит:

A fluid-driven device is provided according to the present disclosure. The fluid-driven device includes: a transmission portion, which is driven to rotate in an axial direction of the transmission portion; blade portions, which are connected to the transmission portion and rotate in the axial direction of the transmission portion to generate a fluid power; and a pitch portion, which is connected to the blade portions and configured to change a frontal area of the blade portion in its rotation direction in the axial direction of the transmission portion so that the frontal area of the blade portion is switched between a maximum frontal area and a minimum frontal area. With the fluid-driven device according to the present disclosure, a frontal area of the blade portion is regulated to be maintained at a maximum frontal area in a desired motion direction for interaction with fluid, and is switched to a minimum frontal area in an undesired motion direction to avoid interaction with the fluid as much as possible. In this way, a resistance caused by the fluid is avoided as much as possible, and an action force generated by the fluid is still applied in the desired motion direction and is maximally utilized to promote a motion. 1. A fluid-driven device , comprising:a transmission portion, which is driven to rotate in an axial direction of the transmission portion;blade portions, which are connected to the transmission portion and rotate in the axial direction of the transmission portion; anda pitch portion, which is connected to the blade portions and configured to change a frontal area of the blade portion in its rotation direction in the axial direction of the transmission portion so that the frontal area of the blade portion is switched between a maximum frontal area and a minimum frontal area.2. The fluid-driven device according to claim 1 , wherein the transmission portion comprises a sleeve in which a receiving space is provided claim 1 , the pitch portion is ...

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Номер записи: 87
28-03-2019 дата публикации

PROPELLER CONTROL UNIT

Номер: US20190092453A1
Автор: Flannery Brett A., Hoemke Brian
Принадлежит:

The present disclosure describes a propeller control unit for controlling the blade pitch of a propeller. The unit includes an electrohydraulic servo valve (“EHSV”) and is connected to a propeller actuator that adjusts the blade pitch of a propeller. The EHSV operates to allow pressurized fluid to flow from a pressurized fluid source to the actuator to adjust the blade pitch of the propeller in a flight pitch range and a ground pitch range, to allow pressurized fluid to flow from the source to the actuator to adjust the blade pitch of the propeller in a flight pitch range but not a ground pitch range, and to block the flow of pressurized fluid from the source to the actuator and drain pressurized fluid from the actuator to prevent adjustment of the blade pitch of the propeller in the flight pitch range or the ground pitch range. 1. A propeller control system for controlling the blade pitch of a propeller , the propeller control system comprising:a hydraulic pressure source;an electrohydraulic servo valve (“EHSV”) configured to receive pressurized fluid from the source and hydraulically adjust the blade pitch of a propeller via an actuator; allow pressurized fluid to flow from the source to the actuator to hydraulically adjust the blade pitch of the propeller in a flight pitch range and in a ground pitch range;', 'allow pressurized fluid to flow from the source to the actuator to hydraulically adjust the blade pitch of the propeller in a flight pitch range but not in a ground pitch range; and', 'block the flow of pressurized fluid from the source to the actuator and drain pressurized fluid from the actuator to prevent hydraulic adjustment of the blade pitch of the propeller in the flight pitch range or in the ground pitch range., 'wherein the EHSV is configured to operate to2. The propeller control system of claim 1 , further including an electronic control unit that controls the source claim 1 , the EHSV claim 1 , and the actuator.3. The propeller control system of ...

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Номер записи: 88
03-07-2014 дата публикации

SELF-POSITIONING DEVICE FOR WATER TURBINE

Номер: US20140186179A1
Автор: LIN SHUEEI-MUH
Принадлежит: KUN SHAN UNIVERSITY

A water generator assembly includes a water generator having two forwarding wings on the front end thereof and the forwarding wings are applied by current and generate a resistance force and a lifting force. The resistance force and the lifting force are combined as a composition force which has a forwarding component force in the X-axis to offset the drag force cause by the current applying to the water generator. A component force in Y-axis is offset by the forwarding wings. A balance wing is connected to the water generator to prevent the water generator from spinning about the X-axis. The water generator has a lifting wing to generate a lifting force to lift the water generator. A buoyant floats and indexes the water generator. A tail wing and two side wings keep the water generator facing the current and prevent the water generator from spinning about the Y-axis. 1. A water generator assembly comprising:a water generator having two forwarding wings on a front end thereof and the forwarding wins located on an X-axis of the water generator, the forwarding wings being applied by current and generating a resistance force and a lifting force, the resistance force and the lifting force being combined as a composition force which has a forwarding component force in the X-axis so as to offset a drag force cause by the current applying to the water generator, a component force in Y-axis of the water generator being offset by the forwarding wings.2. The assembly as claimed in claim 1 , wherein the water generator has a balance wing which prevents the water generator from spinning about the X-axis.3. The assembly as claimed in claim 1 , wherein the water generator has a lifting wing which generates a lifting force to lift the water generator.4. The assembly as claimed in claim 1 , wherein the water generator has a buoyant which provides floating force and indexes the water generator.5. The assembly as claimed in claim 1 , wherein a tail wing is connected to the water ...

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Номер записи: 89
03-07-2014 дата публикации

A DEVICE FOR FEEDING FLUID TO A HYDRAULIC ACTUATOR FOR CONTROLLING THE PITCH OF THE FAN BLADES OF A TWO-PROPELLER TURBOPROP

Номер: US20140186182A1
Автор: Gallet Francois, Rouesne Ivan Guy
Принадлежит: SNECMA

A device for feeding fluid to a hydraulic actuator for controlling a pitch of fan blades of a two-propeller turboprop, the device including: a fluid manifold secured to a rotor of the turboprop and including a cylindrical portion including at least two fluid-circulation grooves, each presenting an outlet orifice; a fluid-admission support secured to a stationary portion of the turboprop and including a cylindrical portion including at least two distinct fluid passages opening to fluid-admission tubes and each leading radially into one of the fluid-circulation grooves of the manifold; and a tub constrained to rotate with the fluid manifold and including a cylindrical portion including at least two fluid-flow channels, each fed with fluid by a respective one of the outlet orifices of the fluid dispenser, each fluid-flow channel leading to a respective chamber of a control actuator. 110-. (canceled)11. A device for feeding fluid to a hydraulic actuator for controlling a pitch of fan blades of a two-propeller turboprop , the device comprising:a fluid manifold constrained to rotate with a rotor of the turboprop and including a cylindrical portion provided on an outside surface including at least two annular fluid-circulation grooves that are longitudinally spaced apart, each fluid-circulation groove presenting at least one outlet orifice opening out radially to an inside of the cylindrical portion of the fluid manifold;a fluid-admission support secured to a stationary portion of the turboprop and including a cylindrical portion arranged around the cylindrical portion of the fluid manifold, being coaxial therewith and including at least two distinct fluid passages opening out to respective fluid-admission tubes and each leading radially to an inside of the cylindrical portion of the support in a respective one of the fluid-circulation grooves of the manifold; anda tub constrained to rotate with the fluid manifold and including a central portion arranged inside the ...

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Номер записи: 90
10-07-2014 дата публикации

Propeller Blade With Relatively Movable Counterweight

Номер: US20140193253A1
Автор: Carvalho Paul A.
Принадлежит: HAMILTON SUNDSTRAND CORPORATION

A propeller rotor has a hub mounting a plurality of blades. A counterweight is movably mounted on the blade. A pitch change mechanism for changing an angle of incidence of an airfoil is associated with each of the blades. The counterweight twists the blades toward an increased pitch direction should the pitch change mechanism fail. A stop member stops rotation of the counterweight as the blade moves to a feather position. 1. A propeller rotor comprising:a rotor mounting a plurality of blades, said blades having a root mounted in a hub of said rotor and a counterweight movably mounted on said blades;a pitch change mechanism for changing an angle of incidence of an airfoil associated with said blades and said counterweight for biasing said blades toward an increased pitch direction should said pitch change mechanism fail; anda stop member for stopping rotation of said counterweight and said counterweight with said blade as said blade moves to a feathered position.2. The propeller rotor as set forth in claim 1 , wherein said stop includes a stop pin mounted on said hub.3. The propeller rotor as set forth in claim 1 , wherein said blade in said feather position includes said airfoils being moved generally parallel to an approaching direction of air.4. The propeller rotor as set forth in claim 1 , wherein said counterweight is mounted to said blades through an arm claim 1 , and said arm being connected to a collar which is rotatable about a base of said blade.5. The propeller rotor as set forth in claim 4 , wherein said collar having a groove with circumferential ends claim 4 , and said hub including a hub pin claim 4 , said hub pin contacting one of said ends of said groove such that said counterweight transmits torque to said blade.6. The propeller rotor as set forth in claim 5 , wherein said counterweight contacts said stop claim 5 , said hub pin is spaced from said end.7. The propeller rotor as set forth in claim 6 , wherein said stop contacts said arm.8. The ...

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Номер записи: 91
10-07-2014 дата публикации

HYDRAULIC SYSTEM FOR CONTROLLING THE ORIENTATION OF FAN BLADES

Номер: US20140193261A1
Автор: Deldalle Regis Michel, Frantz Caroline, Paul
Принадлежит: SNECMA

A hydraulic system for controlling orientation of fan blades in a turbine engine including at least one set of adjustable pitch fan blades actuated by actuators that are connected to a hydraulic pump, and a small pitch protection valve controlled by an associated solenoid valve to make it possible on the ground, when the orientation of the blades is substantially perpendicular to the axis of the turbine engine, to pass from a first operating zone in which a speed of pitch variation of the blades is low to a second operating zone in which a speed of pitch variation is considerably higher, wherein operating pressure of the hydraulic pump is controlled by the solenoid valve controlling the small pitch protection valve to define two outlet levels corresponding to the two operating zones. 17-. (canceled)8. A hydraulic system for controlling orientation of fan blades in a turbine engine comprising:at least one set of adjustable pitch fan blades actuated by actuators that are connected to a hydraulic pump; anda small pitch protection valve controlled by an associated solenoid valve to make it possible on the ground, when the orientation of the blades is substantially perpendicular to the axis of the turbine engine, to pass from a first operating zone in which a speed of pitch variation of the blades is low to a second operating zone in which the speed of pitch variation is considerably higher,wherein operating pressure of the hydraulic pump is controlled by the solenoid valve controlling the small pitch protection valve to define two outlet levels corresponding to the two operating zones.9. A system according to claim 8 , wherein the hydraulic pump is an axial piston pump.10. A system according to claim 9 , further comprising a bypass duct between an inlet of the solenoid valve and a control inlet of the axial piston pump.11. A system according to claim 10 , further comprising a diaphragm mounted in a low-pressure return line of the axial piston pump and a diaphragm ...

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Номер записи: 92
30-04-2015 дата публикации

PIVOTING BLADE COUNTERWEIGHT

Номер: US20150118052A1
Автор: Carvalho Paul A.
Принадлежит: HAMILTON SUNDSTRAND CORPORATION

A propeller system includes at least one propeller hub having a plurality of hub arms formed therein. The plurality of hub arms are arranged circumferentially on the at least one propeller hub and are spaced apart from one another by a hub distance. The propeller system further includes a plurality of propeller blades. Each propeller blade includes a base portion rotatably disposed in a respective hub. At least one counterweight is coupled to the base portion of a respective propeller blade. The counterweight includes a hinge configured to pivot a portion of the at least one counterweight. 1. A propeller system comprising:at least one propeller hub including a plurality of hub arms formed therein, the plurality of hub arms arranged circumferentially on the at least one propeller hub and spaced apart from one another by a hub arm distance;a plurality of propeller blades each including a base portion rotatably disposed in a respective hub; andat least one counterweight coupled to the base portion of a respective propeller blade, the at least one counterweight including a hinge configured to pivot a portion of the at least one counterweight in response to contacting at least one of an adjacent propeller blade and an adjacent hub.2. The propeller system of claim 1 , wherein the at least one counterweight comprises:a fixed arm including a first end coupled to the base portion of a respective blade, and a second end coupled to the hinge; anda pivoting arm including a distal end having a weighted element coupled thereto, and a proximate end pivotably coupled to the hinge such that the pivoting arm pivots with respect to the fixed arm.3. The propeller system of claim 2 , wherein a length of the pivoting arm is greater than a length of the fixed arm such that the pivot arm pivots in response to contacting at least one of an adjacent propeller blade and an envelope of an adjacent hub.4. The propeller system of claim 3 , wherein the plurality of propeller blades are configured ...

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Номер записи: 93
09-06-2022 дата публикации

APPARATUS AND METHODS FOR AIRCRAFT PROPELLER CONTROL

Номер: US20220177155A1
Автор: JARVO James Robert, YAKOBOV Ella
Принадлежит:

An aircraft propeller control system for an aircraft propeller with adjustable blade angle has a blade angle feedback ring and a sensor, one of which is mounted for rotation with the propeller. The blade angle feedback ring moves longitudinally along with adjustment of the blade angle and has position markers circumferentially spaced apart at distances that vary along a longitudinal axis. The sensor is positioned adjacent the feedback ring for producing signals indicative of passage of the position markers. Intervals between signals are indicative of circumferential distances between position markers. A controller measures longitudinal position of the feedback ring based on the intervals and is configured to produce a warning signal if the longitudinal position is outside a first threshold range. 1. A propeller control system for an aircraft propeller rotatable about a longitudinal axis and having an adjustable blade angle , the control system comprising:a blade angle feedback ring coupled to the propeller to rotate with the propeller and to move along the longitudinal axis along with adjustment of the blade angle, said blade angle feedback ring comprising a plurality of position markers spaced around its circumference such that a circumferential distance between at least some adjacent ones of said position markers varies along said longitudinal axis;a sensor positioned adjacent said blade angle feedback ring for producing signals indicative of passage of said position markers, such that an interval between ones of said signals is indicative of a circumferential distance between adjacent ones of said position markers; anda controller in communication with said sensor to measure a longitudinal position of said feedback ring based on an interval between consecutive ones of said signal, said controller configured to produce a warning signal if said longitudinal position is outside a first threshold range.2. The propeller control system of claim 1 , wherein said warning ...

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Номер записи: 94
27-04-2017 дата публикации

SYSTEM FOR CONTROLLING A ROTORCRAFT ROTOR, A ROTORCRAFT FITTED WITH SUCH A SYSTEM, AND AN ASSOCIATED CONTROL METHOD

Номер: US20170113792A1
Автор: BYZERY Romeo, VALLART Jean-Baptiste
Принадлежит: AIRBUS HELICOPTERS

A control system for controlling at least one rotor of a rotorcraft, the control system comprising at least one piloting member suitable for operating at least one control for controlling movements of the at least one rotor. Such a control system comprises: at least one memory enabling information representative of a predetermined control margin threshold to be stored; calculation means for calculating a current control margin, which margin is defined as being the difference between a current position and a limit of the control for controlling movements of the rotor(s); comparator means for comparing the current control margin with the predetermined control margin threshold; and a control unit for modifying an operating relationship of the control for controlling movements of the rotor(s) when the current control margin is less than or equal to the predetermined control margin. 1. A control system for controlling at least one rotor of a rotorcraft , the control system comprising at least one piloting member suitable for operating at least one control for controlling movements of the at least one rotor , and further comprising:at least one memory enabling information representative of a predetermined control margin threshold to be stored;calculation means for calculating a current control margin, which margin is defined as being the difference between a current position and a limit of the control for controlling movements of the at least one rotor;comparator means for comparing the current control margin with the predetermined control margin threshold; anda control unit for modifying an operating relationship of the control for controlling movements of the at least one rotor when the current control margin is less than or equal to the predetermined control margin;wherein when the current control margin is less than or equal to the predetermined control margin threshold, the control unit modifies a sensitivity of the operating relationship of the control for ...

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Номер записи: 95
05-05-2016 дата публикации

Method For Controlling An Aircraft Propeller System During Thrust Reversal

Номер: US20160121998A1
Автор: Carlon Ortiz Eva, Lamonzie Vincent, Martin Moreno Miguel Angel, Silvestre Salas Manuel
Принадлежит:

The present invention refers to a method for controlling an aircraft propeller system during thrust reversal, wherein it is checked whether each power plant is ready for the transition to negative pitch, and where the propellers transition to negative pitch is controlled from a flight control system, such as only when both power plants are ready for the transition to negative pitch, the flight control system instructs the aircraft propeller system to reverse thrust. If a power plant failure is detected before a reversal order is received, then the flight control system is informed of that failure condition, and then the flight control system will disable the thrust reversal operation as long as the failure condition remains. The method of the invention improves the aircraft controllability during landing operations, reduces pilot workload, and improves passenger comfort during landing and taxing. 1. A method for controlling an aircraft propeller system during thrust reversal , wherein the propeller system includes at least two power plants , each power plant having a variable-pitch propeller and an engine for the propeller to drive the same , the method for controlling an aircraft propeller system comprising the steps of:checking whether each power plant is ready for a transition to negative pitch, and informing a flight control system of a detected positive readiness condition of any one of the at least two power plants;receiving a thrust reversal order in the flight control system;checking, in the flight control system, the readiness condition of the at least two power plants for the transition to negative pitch, andcontrolling the propellers transition to negative pitch from the flight control system, such as only when the at least two power plants are ready for the transition to negative pitch, the flight control system instruct the aircraft propeller system to reverse thrust.2. The method of further comprising the steps of:checking an operation condition of ...

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Номер записи: 96
05-05-2016 дата публикации

AN AIR PROPELLER BLADE PIVOT IN THE SHAPE OF A SPHERICAL CAP

Номер: US20160121999A1
Автор: Fabre Adrien Jaccques Philippe, Jacquemard Christophe, Laurenceau Adrien, Tajan Sebastien
Принадлежит: SNECMA

A pivot for an air propeller blade, the pivot including a rotary support for mounting radially on a propeller hub while being suitable for pivoting about a pivot axis; and a blade support including a housing for receiving a blade root and at least one arm extending laterally relative to the pivot axis and carrying a flyweight forming a counterweight; the arm and its flyweight presenting the general geometrical shape of a spherical cap. 1. A pivot for an air propeller blade , the pivot comprising:a rotary support for mounting radially on a propeller hub while being suitable for pivoting about a pivot axis; anda blade support including a housing for receiving a blade root and at least one arm extending laterally relative to the pivot axis and carrying a flyweight forming a counterweight;wherein the arm and its flyweight present the general geometrical shape of a spherical cap.2. The pivot according to claim 1 , wherein the arm and its flyweight have a section that is curved in a longitudinal plane and a section that is curved in a transverse plane.3. The pivot according to claim 2 , wherein each of the curved sections presents a respective radius of curvature lying in the range 200 mm to 400 mm for a turboprop propeller blade claim 2 , and lying in the range 700 mm to 900 mm for a propeller blade of a turboprop having two contrarotating propellers.4. The pivot according to claim 1 , wherein at least the blade support is made of organic matrix composite material.5. The pivot according to claim 1 , wherein the blade support comprises two opposite arms extending laterally relative to the pivot axis and each carrying a flyweight forming a counterweight.6. The pivot according to claim 1 , wherein the blade support arm is connected to the housing via a portion of curved profile.7. The pivot according to claim 1 , wherein the blade support arm is connected to the housing via a portion of rectilinear profile.8. The pivot according to claim 1 , wherein the blade support ...

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Номер записи: 97
03-05-2018 дата публикации

FAN MODULE WITH ADJUSTABLE PITCH BLADES AND POWER SYSTEM

Номер: US20180118363A1
Автор: Keller Richard K., Sands Jonathan S.
Принадлежит:

A fan module for an aircraft is disclosed herein. The fan module includes a fan rotor and an optional power supply system. The fan rotor is mounted for rotation about a central axis and configured to couple to a rotational power source. The fan rotor includes a plurality of variable-pitch fan blades each movable from a thrust-generation orientation to a power-generation orientation. 1. A fan module comprisinga fan rotor mounted for rotation about a central axis and configured to couple to a rotational power source, the fan rotor including a plurality of variable-pitch fan blades each movable from a thrust-generation orientation to a power-generation orientation, anda power supply system including a torque transmitting device configured to selectively couple the fan rotor to the rotational power source so that rotation of the fan rotor is driven by the rotational power source, a generator coupled to the fan rotor and configured to produce electrical power in response to a mechanical load applied by the fan rotor to the generator, an actuator coupled to the plurality of variable-pitch fan blades to move the fan blades from the thrust-generation orientation to the power-generation orientation, and a controller coupled to the torque transmitting device, the generator, and the actuator,wherein the controller is configured to disengage the torque transmitting device to de-couple the fan rotor from the rotational power source and to move the variable-pitch fan blades to the power-generation orientation when the mechanical load is applied to the generator so that the fan rotor is free to rotate about the central axis and is aerodynamically optimized to rotate in response to ram air interacting with the fan rotor.2. The fan module of claim 1 , wherein the controller is configured to disengage the torque transmitting device and to move the variable-pitch fan blades to the power-generation orientation so that pressurized air discharged by the fan blades when the fan blades are ...

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Номер записи: 98
25-08-2022 дата публикации

BLADE PITCH CONTROL

Номер: US20220266982A1
Автор: Bouloc Romain, MARGER Thibaut
Принадлежит:

A blade pitch control assembly includes a pitch control actuator having a coarse actuator chamber having a coarse chamber area and a fine actuator chamber having a fine chamber area. The coarse chamber area is biased to a feather position. The assembly also includes a primary pitch control valve configured to control the flow of pressurised fluid to the coarse actuator chamber and the fine actuator chamber, respectively via a coarse fluid line and a fine fluid line. The assembly further includes a hydraulic protection system located between the actuator and the primary pitch control valve, configured to bypass the primary pitch actuator in response to a trigger. The hydraulic protection system has a hydraulic protection system valve located between the fluid lines and when activated fluidly connects the fluid lines to balance fluid pressure between the coarse chamber and the fine chamber. 1. A blade pitch control assembly comprising:a pitch control actuator having a coarse actuator chamber having a coarse chamber area and a fine actuator chamber having a fine chamber area;a course fluid line and fine fluid line;a primary pitch control valve configured to control the flow of pressurised fluid to the coarse actuator chamber and the fine actuator chamber, respectively, via the coarse fluid line and the fine fluid line; and 'a hydraulic protection system valve located between the coarse fluid line and the fine fluid line, wherein activation of the hydraulic protection system valve fluidly connects the coarse fluid line and the fine fluid line so as to balance fluid pressure between the coarse chamber and the fine chamber.', 'a hydraulic protection system located between the actuator and the primary pitch control valve, the system configured to bypass the primary pitch actuator in response to a trigger, wherein the hydraulic protection system comprises2. The blade pitch control assembly of claim 1 , wherein the trigger is a pilot command or a failure event requiring ...

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Номер записи: 99
25-04-2019 дата публикации

OIL TRANSFER FOR A CONTROL SYSTEM REGULATING THE PROPELLER PITCH OF A TURBINE ENGINE

Номер: US20190118934A1
Автор: HERT Xavier Paul Lucien, MOREAU DE LIZOREUX Aldric Renaud Gabriel Marie, MORELLI Boris Pierre Marcel
Принадлежит:

Oil transfer tube for a system to control the regulation of a turbine engine propeller pitch, in particular of an aircraft, the tube being intended to be mounted coaxially inside a tubular shaft of the propeller, the tube having an elongated shape and including a first male longitudinal end part intended to be inserted in a female housing of a stator casing equipped with an oil supply circuit of the tube, and a second male longitudinal end part around which is intended to be mounted a hydrodynamic bearing to guide the tube in the shaft, wherein the first end part includes a free annular end with a convex rounded cross-section intended to bear axially against an annular bottom of said housing, and in that said second end part comprises an outer axial annular bearing surface of an inner ring of the bearing, the annular bearing surface presenting in cross-section a convex curved shape. 1. Oil transfer tube for a system to control the regulation of a turbine engine propeller pitch , in particular of an aircraft , the tube being intended to be mounted coaxially inside a tubular shaft of the propeller , the tube having an elongated shape and comprising a first male longitudinal end part intended to be inserted in a female housing of a stator casing equipped with an oil supply circuit of the tube , and a second male longitudinal end part around which is intended to be mounted a hydrodynamic bearing to guide the tube in the shaft , wherein said first end part comprises a free annular end with a convex rounded cross-section intended to bear axially against an annular bottom of said housing , and in that said second end part comprises an outer axial annular bearing surface of an inner ring of said bearing , this annular bearing surface presenting in cross-section a convex curved shape.2. The tube according to claim 1 , wherein the first end part comprises an outer annular groove housing an O-ring seal claim 1 , this seal being intended to cooperate with a wall of said housing ...

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Номер записи: 100