298results about "Rotors" patented technology

A wind energy plant with a nacelle, a rotor, which features at least one rotor blade adjustable in its blade pitch angle, a central control device for controlling the wind energy plant and a control unit disposed in the rotor for controlling the blade pitch angle of the at least one rotor blade, wherein the central control device and the control unit in the rotor can exchange data with each other via a data link, which comprises at least one first sending and receiving device at the nacelle side and at least one second sending and receiving device at the rotor side, wherein a wireless network connection with a safety-oriented communication protocol is provided between the at least one first sending and receiving device and the at least one second sending and receiving device, and that one monitoring- and communication device at a time is associated to the first and / or the second sending and receiving device, which can monitor the function of the sending and receiving device and initiate a predetermined action in the case of an error.

The invention discloses a method and a system for automatically adjusting the rotation angle of an engine blade. The method for automatically adjusting the rotation angle of the engine blade comprises the following steps: collecting historical parameters of an engine, collecting real-time data of the engine, carrying out multi-dimensional data fusion on the data to extract key information, screening remarkable influence factors, and constructing a parameter influence network diagram; a four-channel long-short-term memory prediction model is established, four channels output corresponding prediction results respectively, and constraint and error correction are carried out on the prediction results; a corner angle is calculated according to a four-channel output prediction result, constraint limitation and a parameter influence network diagram, and an output corner instruction is directly mapped into actuator displacement; through compensation of a nonlinear actuator, the adjustment precision is guaranteed, and it is ensured that the actuator accurately executes a rotation angle instruction; and the model is lightened, so that the finally obtained decision tree model can efficiently run in an embedded system. The rotating angle of the engine blade can be automatically adjusted under different working conditions, and the adjusting efficiency of the rotating angle of the engine blade is improved.

An assembly for an aircraft propulsion system includes an open propulsor rotor and an open guide vane structure. The open propulsor rotor is rotatable about a rotational axis. The open guide vane structure is axially next to and downstream of the open propulsor rotor. The open guide vane structure includes a plurality of open guide vanes arranged circumferentially about the rotational axis. The open guide vanes include a first open guide vane. The first open guide vane includes a camber line, a leading edge, a trailing edge, a leading edge section and a trailing edge section. The first guide vane extends longitudinally along the camber line from the leading edge to the trailing edge. The leading edge section is configured to pivot about a pivot axis. The trailing edge section is configured to move relative to the leading edge section to change a camber of the first open guide vane.

An engine system for an aircraft includes a first turbofan engine and a second turbofan engine. The first turbofan engine includes a first low-pressure shaft, a first fan having a first fan shaft, and a counterclockwise gearbox assembly. The first fan shaft is drivingly coupled to the first low-pressure shaft through the counterclockwise gearbox assembly. The first low-pressure shaft rotates in a counterclockwise direction. The first fan shaft rotates in the counterclockwise direction such that the first fan rotates in the counterclockwise direction. The second turbofan engine includes a second low-pressure shaft, a second fan having a second fan shaft, and a clockwise gearbox assembly. The second fan shaft is drivingly coupled to the second low-pressure shaft through the clockwise gearbox assembly. The second low-pressure shaft rotates in the counterclockwise direction. The second fan shaft rotates in a clockwise direction such that the second fan rotates in the clockwise direction.

A gas turbine engine defining a centerline and a circumferential direction, the gas turbine engine comprising: a turbomachine comprising, in serial flow order, a compressor section, a combustion section, and a turbine section, the turbomachine defining a working gas flow path and a fan duct flow path; a primary fan driven by the turbomachine, the primary fan defining a primary fan tip radius R1 and a primary fan hub radius R2; a secondary fan downstream of the primary fan and driven by the turbomachine, at least a portion of airflow from the primary fan being configured to bypass the secondary fan, the secondary fan defining a secondary fan tip radius R3 and a secondary fan hub radius R4, wherein the secondary fan is configured to provide, during operation, a fan duct airflow through the fan duct flow path to generate a fan duct thrust, wherein the fan duct thrust is equal to a %Fn of a total engine thrust during operation of the gas turbine engine at rated speed during standard day operating conditions 3S ; wherein a ratio of R1 to R3 is equal to wherein EFP is between 1.5 and 11, wherein RqR Prim.‑Fan is a ratio of R2 to R1, and wherein RqR Sec.‑Fan is a ratio of R4 to R3.

A turbofan engine includes a fan and a fan actuation system. The fan has a plurality of fan blades. Each of the plurality of fan blades is rotatable about a pitch axis. The fan actuation system includes one or more actuators for rotating the plurality of fan blades about the pitch axis and one or more thrust bearings. The fan actuation system is characterized by a fan actuation system envelope in a range of 300 to 1860. The fan actuation system envelope is given byNFB×DFT×Mcruise(RTBNFB),where NFB is a number of the plurality of fan blades, DFT is a fan tip diameter of the plurality of fan blades, Mcruise is a Mach number of the turbofan engine at cruise operating conditions, and RTB is a thrust bearing radius of the one or more thrust bearings.

Systems and methods for measuring an axial position of a phonic wheel or other rotating component are provided. The system includes a phonic wheel rotatable about a rotation axis and translatable along the rotation axis, a first sensor, a second sensor and a computer. The phonic wheel includes an inclined tooth having an axially non-uniform radial height and a reference tooth having an axially uniform radial height. The first sensor generates a positioning signal indicative of a gap between the inclined tooth and the first sensor. The second sensor generates a reference signal indicative of a gap between the reference tooth and the reference sensor. The first and second sensors have different orientations. The computer generates an output indicative of the axial position of the phonic wheel based on the positioning signal and the reference signal.

A high performance die castable aluminum alloy is described, wherein the aluminum alloy is characterized as having a high yield strength and high conductivity compared to conventional aluminum alloys, and also a high flowability and low susceptibility to hot tearing when die cast. The aluminum alloy may contain 4-6 wt. % nickel, a yield strength of at least about 90 MPa, and an electrical conductivity of at least about 48% IACS.

Angular adjustment assembly with wheel and endless screw for variable pitch blade and associated adjustment method One aspect of the invention relates to an angular adjustment assembly (1) for an adjustable orientation blade (6) of a turbomachine or X-axis testing machine, comprising an adjustment device (19) capable of pivoting the blade about a Y axis perpendicular to and intersecting the X axis until the desired angular positioning is reached. The blade comprises at its base (8) a toothed wheel (15) of Y axis, the pivoting of which causes that of the blade. The adjustment device comprises a threaded rod (18) of X' axis parallel to X, engaged with the toothed wheel and the rotation of which about the X' axis causes the toothed wheel to pivot about the Y axis. Figure to be published with the abstract: Figure 2

A shaft guidance system is proposed. The shaft guidance system comprises a shaft, a first shaft bearing, and a second shaft bearing. The first shaft bearing is arranged at a first end of the shaft. The first shaft bearing comprises a preload element. The preload element is designed to preload the first shaft bearing. The second shaft bearing is arranged at a second end of the shaft, opposite the first end. The first shaft bearing and the second shaft bearing are arranged on the shaft in such a way that the preload element of the first shaft bearing creates a preload via the shaft onto the second shaft bearing.

A base station for an unmanned aerial vehicle (UAV) is disclosed that includes: an enclosure defining an internal cavity that is configured to receive the UAV; a door that is movably connected to the enclosure; actuators that extend between the door and the enclosure to facilitate opening and closure of the door; a cradle that is configured to receive the UAV and which is movable in relation to the enclosure such that the cradle is repositionable between a retracted position and an extended position to facilitate movement of the UAV into and out of the enclosure; and engagement members that are secured to the actuators and which are configured for contact with propeller assemblies on the UAV to facilitate folding of the propeller assemblies during movement of the UAV into the enclosure.

Variable pitch fan blade (8a) for an unfaired turbomachine fan, the blade (8a) comprising an aerodynamic blade (9) and a base (10), the blade (9) comprising a recess opening simultaneously onto the upper and lower surfaces (14) and a leading edge (15) of the blade (9), the blade (8a) further comprising a measuring device (26) housed in the recess and clipped onto the blade (9), the measuring device (26) comprising a streamlined body (28) whose outer surface (29) is complementary to the outer surface (30) of the blade (9) to ensure aerodynamic continuity, the body (28) carrying at least one measuring instrument (31) configured to measure at least one parameter of an airflow upstream of the blade (9). Figure for the abstract: 2

An actuation system (1) for adjusting the pitch of the fan blades (20) of an aircraft engine, comprising a hydraulic power supply (3), a hydraulic cylinder (5), and a hydraulic circuit including a hydraulic channel equipped with a check valve (43) and a distribution valve (41) adapted to selectively adopt two configurations, such that when the distribution valve (41) is in the first configuration, the hydraulic cylinder (5) is configured to be position-controlled by the hydraulic power supply (3), and when the distribution valve (41) is in the second configuration, the control fluid can only flow from a retraction chamber (5f) to an extension chamber (5c) so that the piston of the hydraulic cylinder (5) moves in the first direction of travel, the fan blades orienting themselves towards a safety position known as the "feathered position." Figure for the abstract: Fig. 5

Electric motor comprising a squirrel-cage rotor in the form of a cage, which electrically conductively carries a plurality of rotor end rings formed as cast parts made of a casting material, wherein at least one reinforcing element made of a different material is cast into each of the cast parts, and wherein the casting material substantially forms the outermost free surface of the rotor end ring.

A module including a device for changing the pitch of the vanes about the pitch axes thereof, the device including: a hydraulic actuator capable of rotating about the longitudinal axis (X) and configured to rotate the vanes about their pitch axes (C), a supply pump for supplying fluid to the hydraulic actuator, the supply pump including a drive shaft capable of rotating about the longitudinal axis (X) and a shell that is rotationally fixed relative to the longitudinal axis (X), and an electric machine configured to operate the supply pump, the electric machine having a rotary member for driving the drive shaft and a fixed member that is rotationally fixed relative to the longitudinal axis (X).

A gas turbine engine including: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order; a fan defining a fan axis and comprising a plurality of fan blades rotatable about the fan axis; and a pitch change mechanism operable with the plurality of fan blades, the pitch change mechanism including a plurality of linkages, the plurality of linkages including a first linkage coupled to a first fan blade of the plurality of fan blades and a second linkage coupled to a second fan blade of the plurality of fan blades; and a non-uniform blade actuator system operable with one or more of the plurality of linkages to control a pitch of the first fan blade relative to a pitch of the second fan blade.

This description concerns a collective and cyclic blade pitch control system (2) for a turbomachine propeller (1), comprising: - a plate assembly (10) movable in translation along the propeller axis (R) so as to modify the collective pitch of the blades (2), the plate assembly (10) also being tiltable with respect to a plane normal to the propeller axis (R) so as to modify the cyclic pitch of the blades (2), - a jack (20) configured to move the plate assembly (10) in translation along the propeller axis (R), and - a tilting system (30) which cooperates mechanically with the plate assembly (10) and is configured to tilt the plate assembly (10) with respect to the plane normal to the propeller axis (R), the actuation of the jack (20) mechanically triggering the tilt of the plate assembly (10) by means of the tilting system (30). Figure for the abbreviation: Fig. 4

Turbomachine module, this module having a longitudinal axis (X) and comprising: a propeller (3) comprising a plurality of variable-pitch blades (30), a speed reducer (34), a pitch change system (50) for the blades (30), a fluid transfer device (94) configured to supply fluid to the hydraulic actuator (52) of the pitch change system (50), this transfer device (94) comprising a stator part (96) engaged in a rotor part (97), and a member (99) for mechanically connecting the stator part (96) of the transfer device (94) to the planet carrier (38) of the speed reducer (34), and for fluidically connecting a fluid inlet port (98a) of the transfer device (94) to fluid pipes (95) configured to be connected to a fluid reservoir (91). Figure for abstract: Figure 4

The invention relates to an assembly comprising a propeller blade (10) and a pitch adjustment system (34) for setting the pitch of the blade (10), wherein the root (14) of the blade (10) has a bulb (32) and the pitch adjustment system (34) for setting the pitch of the blade (10) comprises: - a cup (58) having an upper opening (58c); - a retaining ring (82) extending around the bulb (32), the retaining ring being at least limited in axial movement relative to the cup (58) towards the opening (58c) and having a bearing face (84) to hinder axial movement of the root (14) towards the opening (58c); the pitch adjustment system (34) being characterized in that it further comprises a lower seat (88) by which the root (14) is engaged with the cup (58), the seat (88) and / or the retaining ring (82) being mounted so as to be axially translatable relative to the cup (58) by at least one clamping mechanism (90).

The invention relates to a turboprop (10) comprising a propeller (12), a propeller shaft (13) carrying the propeller (12), the propeller being a variable-pitch propeller having a propeller pitch, a rotating electric machine (19) having at least a first configuration in which it is mechanically coupled to the propeller shaft (13) and at least one oil pump (21, 21B) configured to supply a hydraulic circuit for adjusting the pitch of the propeller (12). The oil pump is configured to be electrically operated. The invention further relates to an aircraft comprising such a turboprop (10) and to the methods for controlling such a turboprop (10) and such an aircraft.

A variable pitch fan for a gas turbine engine includes a hub, a fan blade supported by the hub, the fan blade including a blade root, and a retention system including a bearing and a retainer, the retainer securing the bearing to the blade root. The hub is rotatably supported by the bearing.

A system (34) for controlling the pitch of a propeller blade (10) of an aircraft turbine engine is disclosed, characterized in that the system comprises: - a cup-shaped portion (58) having an annular wall (58a) extending about an axis (A) intended to set the pitch of the blade, the annular wall (58a) having a lower axial end enclosed by a bottom wall (58b) and an open upper axial end configured such that the root (14) of the blade (10) can be mounted within the cup-shaped portion (58); and - a retaining ring (152) extending about the axis (A) and configured to be mounted around the root (14), the retaining ring (152) being a double-claw clutch ring comprising two annular rows of external claw teeth (154, 156), the two annular rows of external claw teeth constituting an active claw tooth and a safety claw tooth, respectively.

The present invention describes a system for controlling the cyclic pitch of the blades (1) of a propeller of a turbomachine, the blades (1) being arranged in a plane orthogonal to the axis of rotation (r) of the propeller, the system comprising: - a plate assembly (40) capable of tilting relative to the orthogonal plane (P), - a hinge system (50) that hinges the plate assembly (40) relative to the blade (1) such that tilting of the plate assembly (40) changes the pitch of the blade (1), - a force sensor (5) designed to measure the force exerted by the air flow at the inlet of the blades (1) of the propeller in the orthogonal plane (P), - a cylinder (60) adapted to tilt the plate assembly (40) in response to the force measured by the force sensor (5).

The invention relates to an aircraft turbomachine assembly comprising a propeller constituting a non-fan, the turbomachine comprising a cyclic pitch control device (50) for the propeller blades, the cyclic pitch control device (50) comprising at least two actuators (52), each actuator being fixed to a stator (70), the stator (70) being rotationally fixed relative to a bearing support supporting the rotating shaft, the stator (70) comprising a rim (70C) connected to a hub (70D) by a set of spokes (70E), the rim (70C) being fixed to the bearing support, the hub being rotationally mounted about the rotating shaft, at least two sets of two adjacent spokes (70E) being configured for the attachment of an actuator (52) of the variable pitch control device, each actuator (52) being at least partially inserted between the two corresponding adjacent spokes (70E). Figure 3.

Assembly for an aircraft turbomachine propeller (10), this assembly comprising a variable-pitch blade (14), a blade pitch control system (76) comprising a sleeve (80) engaged in a metal body (102) forming the blade root, and a tie rod (120) passing through the sleeve (80) and the metal body (102) to connect the blade to the control system (76) and pre-stress the metal body (102). Figure for the abbreviation: Figure 4

A propeller for an aircraft turbine engine having a hub, vanes, bearings for guiding the roots of the vanes into orifices in the hub, and systems for retaining the roots of the vanes in the orifices in the hub along the pitch axis, this system for retaining the root including a ring configured to be fitted in a groove in the root, and a screw-nut system mounted on the root between the ring and one of the bearings.

The invention relates to an assembly for a turbomachine, in particular for an aircraft, the assembly comprising at least one variable-pitch blade (3) provided with a cylindrical-shaped stud (8), and a ring (2) with a longitudinal axis (X) provided with housings (12) each intended to receive the stud (8) of a blade, the stud (8) being mounted to pivot about a setting axis (A), the assembly further comprising pivoting elements (38) configured so as to promote free pivoting of the stud about the setting axis and in each housing (12). According to the invention, the ring (2) comprises a first annular part (43) and a second part (44) which are coaxial, the second part (44) comprising a plurality of sectored portions (44a, 44b, 44n) arranged adjacently around the longitudinal axis (X), each sectored portion (44a, 44b, 44n) being removably fixed to the first part and defining with the first part a housing (12).Figure for abstract: Figure 3.

Rotor blade (14) for a propeller (10) of an aircraft turbomachine, this blade (14) comprising a blade (20) connected to a root (40) which is housed in a platform (22), the blade (20) and the root (40) being made of a composite material comprising a fibrous body (50) embedded in a polymer matrix, the root (40) having a generally elongated shape, the platform (22) comprising a housing (38) for receiving said root (40), this housing (38) having a shape complementary to this root (40), the platform (22) being configured to define a setting axis (Y) of the blade (10) which extends along an elongation axis of the blade (20), characterized in that the platform (22) comprises orifices (62) which extend from an external surface (34) of the platform (22) into the housing (38). Figure for abstract: Figure 2

An assembly (1) of variable-pitch blades for an unfaired aircraft turbomachine, the assembly comprising a rotor (3) movable about a radial axis (X) of the turbomachine, a stator (4) fixed about said radial axis (X), and at least one lightning arrester (5). The lightning arrester (5) comprises a pin (6), at least one face of said pin (6) being in contact by friction with the rotor (3), a screw (7) radially extending from said pin (6), and a means (8) for connecting the pin (6) and the screw (7), said means (8) comprising a spring interposed between the pin (6) and the screw (7). Figure for the abbreviation: Fig 1

This disclosure relates to a rocker arm assembly for adjusting the angle of engine blades and an engine blade assembly. The rocker arm assembly includes: a rocker arm with a groove at one end of its bottom for receiving a boss of a blade; the groove has a longitudinal first through hole and engages with the boss to rotate the blade; a bushing with a second through hole coaxial with the first through hole, the bushing passing through the first through hole and having a clearance fit with the inner wall of the first through hole; a stud with a first thread at its top and a second thread at its bottom, passing through the second through hole, the second thread being used for threaded connection with a threaded hole in the blade extending longitudinally from the top of the boss; and a nut connected to the first thread of the stud, its bottom surface abutting against the top surface of the bushing. The rocker arm assembly of this disclosure includes a bushing, which improves the accuracy of installation and positioning between components, prevents loosening of fasteners, avoids safety accidents, and thus improves the reliability of torque transmission by the rocker arm.