182 results about "Blade pitch" 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.

According to the electric direct-driven eVTOL rotor control device, a driving motor is an outer rotor motor, a stator of the driving motor is of a hollow structure, and a steering engine assembly is installed on the lower portion of the stator, upwards penetrates through the stator and is in driving connection with a variable-pitch mechanism assembly, so that the deflection angle of blades of a blade handle assembly is adjustable; the intermediate transmission link is reduced, the energy loss is reduced, the transmission efficiency is improved, and the reliability of the system is improved; the rotor mounting seat cylinder is upwards connected with the propeller hub lower cover and downwards connected with the stator mounting seat through a bearing, so that stable and reliable power transmission between the driving motor rotor and the propeller hub assembly is ensured, and vibration and noise are reduced; the anti-rotation rocker arm is arranged between the lead screw nut and the fixed ring sleeve, so that rotation interference is avoided, and the precision and stability of variable pitch control are improved; and the variable-pitch rocker arm is in running fit with the variable-pitch disc, so that the linear motion of the variable-pitch disc can be accurately converted into the deflection motion of the blades, and the accurate adjustment of the pitch angle of the blades is realized.

A fan section of an aeronautical propulsion system includes a fan rotor including seventeen blades to twenty blades and having a solidity strictly less than 1.0. The solidity is equal to a ratio between a chord at the blade tip and an inter-blade pitch at the blade tip. The fan section has a hub-tip ratio greater than or equal to 0.22 and less than or equal to 0.32, a pressure ratio greater than or equal to 1.05 and less than or equal to 1.5, and a peripheral speed at the blade tip greater than or equal to 260 m / s and less than or equal to 400 m / s. The pressure ratio and the peripheral speed are measured at cruising speed.

The invention provides for controlling a wind turbine comprising pitch-adjustable rotor blades. The invention involves determining, based on detected wind conditions, wind turbine control parameters for controlling the wind turbine in accordance with a defined wind turbine control strategy, where the control parameters include a reference pitch angle for the rotor blades. The invention involves obtaining bearing control parameters each indicative of a parameter for controlling pitch bearings of the wind turbine that is for adjusting pitch of the rotor blades. The invention involves determining whether a defined set of operational parameters of the wind turbine, including the bearing control parameters, in combination correspond to a combination of operational parameters defined to be indicative of a level of wear above a threshold wear level. The pitch bearings are then controlled based on the reference pitch angle and on the threshold determination.

The invention provides a floating fan strong wind resistance variable pitch control method based on an online optimization algorithm, and the method comprises the steps: describing main components of a floating fan structure, and building a high-fidelity nonlinear dynamic model of a floating wind generating set; carrying out linearization and discretization processing on the high-fidelity nonlinear dynamic model of the floating wind generating set near a cut-out wind speed working point, and giving a control-oriented linearization reduced-order model; constructing an augmented closed-loop control system model based on a standard proportional integral variable pitch control algorithm; performing residual error correction on the closed-loop control system model based on a Gaussian process; calculating a most unfavorable wind speed prediction value based on an online rolling optimization prediction control algorithm; calculating a minimum rotating speed reference derating value meeting security constraints; and calculating a final blade pitch angle instruction. According to the method, on the premise that the load does not exceed the safety upper limit under the strong wind working condition, the minimum necessary derating can be achieved through the online optimization algorithm, and the power generation capacity is kept to the maximum degree.

A circumferential row of vanes for a gas turbine engine, the circumferential row of vanes has non-uniform spacing. The circumferential row of vanes includes a plurality of stator vanes arranged circumferentially about an inner ring. The plurality of stator vanes include a first group of stator vanes having a first spacing between adjacent stator vanes of the first group of stator vanes and a second group of stator vanes having a second spacing between adjacent stator vanes of the second group of stator vanes. The second spacing is from two percent to eleven percent greater than a nominal uniform vane spacing or from two percent to eleven percent lesser than the nominal uniform vane spacing, the nominal uniform vane spacing being defined by a total number of the plurality of stator vanes. An engine includes the circumferential row of vanes.

The shaftless propeller comprises a motor shell, a rotating cylinder, the hub-free guide vane, a steering nozzle and a sealed bearing assembly, the motor shell coaxially sleeves the rotating cylinder, an annular motor used for driving the rotating cylinder to rotate is arranged between the motor shell and the rotating cylinder, and the hub-free guide vane is arranged between the motor shell and the rotating cylinder. The rotating cylinder comprises a plurality of blades arranged on the inner wall of the rotating cylinder and a distance adjusting mechanism used for changing the pitch of the blades in the operation process, and the hub-free guide vane is fixedly arranged at a water inlet in the front end of the rotating cylinder and used for conducting pre-rotation rectification on water flow entering the rotating cylinder so as to counteract the circumferential induced speed generated by the rotating cylinder. The steering nozzle is arranged at the outlet end of the rotating cylinder and can be driven to deflect around the axis so as to change the jet flow direction, and the sealing bearing assembly is arranged between the motor shell and the rotating cylinder and used for supporting the rotating cylinder and preventing fluid from invading the interior of the motor shell; the propulsion efficiency can be improved, the vibration noise can be reduced, and the steering function can be integrated.

A fan section of an aeronautical propulsion system includes a fan rotor including seventeen blades to twenty blades and having a solidity strictly less than 1.0. The solidity is equal to a ratio between a chord at the blade tip and an inter-blade pitch at the blade tip. The fan section has a hub-tip ratio greater than or equal to 0.22 and less than or equal to 0.32, a pressure ratio greater than or equal to 1.05 and less than or equal to 1.5, and a peripheral speed at the blade tip greater than or equal to 260 m / s and less than or equal to 400 m / s. The pressure ratio and the peripheral speed are measured at cruising speed.

The invention discloses a large-scale wind turbine generator power load cooperative fault-tolerant control method. The method comprises the following steps: establishing a unit load and rotating speed control model considering a variable pitch actuator fault; according to the load and rotating speed control model, a fault-tolerant independent variable-pitch controller composed of a centralized variable-pitch ring, an independent variable-pitch ring and a fault-tolerant compensation ring is constructed for the three-blade variable-pitch actuator; and the fault-tolerant independent variable pitch controller inputs variable pitch given instructions corresponding to the blades to the corresponding variable pitch actuators, and the variable pitch actuators implement fault-tolerant variable pitch with the variable pitch given instructions as reference, so that power and load cooperative control under the fault working condition is achieved. According to the method, the optimization effect and the application capability boundary of pneumatic unbalanced load suppression of the wind wheel of the unit can be improved under the combined action condition of multi-source disturbance and variable-pitch actuator faults, meanwhile, the high stability of power output is guaranteed, and high-performance power-load cooperative control is achieved.

The invention provides a pitch angle measuring structure and method for a blade and an aero-engine. Wherein the blades are rotatably connected with the hub, and the rotating shaft is a Y axis; the pitch angle measuring structure comprises a visual mark and an optical measuring device. The visual mark comprises a first mark and a second mark which extend along the circumferential direction of the Y axis; the third mark extends in the axial direction of the Y axis; wherein the first mark, the second mark and the third mark form a pattern; in the pattern, the extending direction of the third mark passes through the first mark and intersects at a first intersection point, and passes through the second mark and intersects at a second intersection point; the distance between the first intersection point and the second intersection point varies synchronously with the pitch angle of the blade; the optical measuring device is configured to acquire an image of the pattern, so that the pitch angle of the blade is determined according to the distance between the first intersection point and the second intersection point in the pattern.

The utility model discloses a propeller blade mounting angle adjusting tool, which relates to the technical field of propellers and comprises a mounting bottom plate, a propeller hub driving mechanism is arranged on the rear side of the top of the mounting bottom plate, a propeller hub positioning mechanism is arranged on the rear side of the mounting bottom plate, and a semicircular angle adjusting plate is arranged on the front side above the mounting bottom plate. A semicircular angle adjusting plate is arranged on the mounting bottom plate, blades are arranged above the semicircular angle adjusting plate, a motor groove is formed in the mounting bottom plate, the propeller hub driving mechanism comprises a servo motor, the servo motor is fixedly mounted in an inner cavity of the motor groove, and an encoder is arranged on the outer wall of the servo motor. According to the utility model, the propeller hub driving mechanism and the propeller hub positioning mechanism are matched with each other, so that the propeller hub mounted with the propeller blades can be fixed and rotated at an accurate angle at the same time, the plurality of propeller blades can be conveniently and quickly butted and mounted, and the mounting efficiency when the plurality of propeller blades and the propeller hub are mounted is improved.

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

Rotorcraft including a fuselage and at least three rotor system arms each having a rotor system. Each rotor system includes a mast having at least two rotor blades and an electric rotor motor. At least one rotor system arm includes a support mechanism for pivotally supporting a floating mast about at least one pivot axis whereby the floating mast is tillable relative to a fiducial tilt position. The floating mast has a controllable cyclic rotor blade pitch. A mast tilt measurement mechanism provides a mast tilt feedback signal regarding a measured tilt position of a floating mast relative to its fiducial tilt position. A flight control system continuously controls the at least three electric rotor motors and the floating masts cyclic rotor blade pitch in response to a desired input maneuver and its mast tilt feedback signal.

This application relates to a variable pitch controllable magnetic damping oscillating propeller clamp device, including a propeller clamp assembly, a motor assembly, and propeller blades. The propeller clamp assembly includes a propeller clamp seat assembly and an oscillating arm assembly. The oscillating arm assembly includes an inverted U-shaped oscillating arm and two propeller blade mounting seats. An axial connection assembly is provided between the propeller blade mounting seats and the two ends of the inverted U-shaped oscillating arm. A rotation limiting assembly is provided between the two ends of the inverted U-shaped oscillating arm and one end of the axial connection assembly. An electromagnet assembly is provided on the propeller clamp seat assembly, and permanent magnets adapted to the two end faces of the electromagnet assembly are provided at the two ends of the inverted U-shaped oscillating arm. This invention belongs to the field of unmanned aerial vehicle (UAV) technology. It achieves precise adjustment and locking of the propeller blade pitch angle through a gear disk and a limiting mechanism, adapting to different flight requirements and improving control performance. The damping force is directly generated by the magnetic repulsion between the electromagnet and the permanent magnet, without the need for additional mechanical parts, resulting in fast response and more direct damping effect.

The invention discloses a fault-tolerant variable-pitch constant-power operation control method for a large wind turbine generator. The method comprises the following steps: establishing a controllable affine model of the wind turbine generator considering a variable-pitch actuator fault; according to the controllable affine model, fault-tolerant variable-pitch controllers of variable-pitch actuators of the three blades are constructed, and any fault-tolerant variable-pitch controller is composed of a tracking control ring and a fault-tolerant compensation ring; and each blade variable-pitch actuator drives each blade to perform variable-pitch action by taking a variable-pitch given instruction output by the corresponding fault-tolerant controller as reference input, so that high-reliability constant-power control under a fault is realized. According to the method, extra disturbance introduced by faults can be reduced, the inhibition effect on actual low-frequency wind disturbance is enhanced, the power stability of the unit is remarkably improved, meanwhile, the originally inconsistent blade pitch angles tend to be consistent under the condition that part of actuators have faults, and the fatigue load of the unit introduced by pneumatic unbalance of the wind wheel face is greatly reduced.

This invention discloses a method for balancing and correcting a wind turbine rotor, comprising: acquiring vibration signals, rotor azimuth angle signals, and operating parameters of the wind turbine; performing azimuth synchronization processing on the vibration signals based on the rotor azimuth angle signals to extract the 1P vibration vector; performing operating condition normalization processing on the 1P vibration vector based on the operating parameters to obtain a normalized unbalance vector; applying a preset pitch disturbance to each blade and obtaining the change in the normalized unbalance vector before and after the disturbance; establishing an aerodynamic unbalance sensitivity matrix based on the change; decomposing the current normalized unbalance vector into an aerodynamic unbalance component and a mass unbalance component based on the aerodynamic unbalance component; determining the blade pitch offset correction amount based on the aerodynamic unbalance component, and determining the counterweight and counterweight orientation based on the residual mass unbalance component. This invention can distinguish between aerodynamic unbalance and mass unbalance, reduce blind counterweighting, and improve the accuracy and efficiency of rotor balancing and correction.

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.

A wind turbine (10) and a method of controlling a wind turbine (10) comprising a cable-supported rotor (22). The cable support rotor (22) includes a plurality of blades (26) and a plurality of cable assemblies (32) supporting the blades (26). A plurality of tension mechanisms (44) control the amount of tension in each cable assembly (32). Upon activation, the tension is increased until a tension setpoint is reached, and the tension level is balanced between the plurality of cable assemblies (32). The tension may be periodically readjusted and may be actively controlled during operation of the wind turbine (10) based on tension as a function of azimuth, wind speed, rotor or generator speed, and blade pitch angle.

The present application belongs to the technical field of dynamic response prediction of marine engineering structures, and specifically discloses an intelligent prediction method for dynamic response of floating wind turbines under internal wave action. Firstly, the dynamic response prediction result given by the intelligent prediction model and the actual operating state of the wind turbine are obtained in real time, the error between the two is calculated and fed back to the control system, the control parameters such as the blade pitch angle are automatically adjusted according to the error and the size of the internal wave load to reduce the blade vibration. At the same time, the genetic algorithm is selected to optimize the control parameters, the objective function considering the power generation efficiency, structural safety and internal wave load is set, and the optimal parameter combination is found through selection, crossover, mutation and other operations. A real-time monitoring system is established to continuously collect internal wave and wind turbine operation data, and a trigger condition is set. When the condition is met, the control parameters are recalculated and adjusted according to the current data. The method focuses on real-time feedback and optimization control, effectively improving the operation stability and power generation efficiency of the floating wind turbine in complex marine environment.

The invention relates to adjusting collective pitch of the wind turbine rotor blades. A sensor signal is received, from wind turbine sensors, indicative of wind turbine rotor loading in a fore-aft direction. A first component is determined, based on the received sensor signal, in the fore-aft direction, the first component including high frequency collective content, greater than 2P frequency content, from the received sensor signal. A second component that is orthogonal to the first component is generated. The first and second components are rotated about a phase angle to obtain first and second phase-shifted components. A collective pitch reference offset value is determined for the three rotor blades based on the first or the second phase-shifted component. A control signal is transmitted to adjust collective pitch of the rotor blades based on the determined collective pitch reference offset value.

The invention relates to a hydraulic control circuit (11) for an orienting actuator (14) for orienting fan blades of a turbojet engine, the circuit (11) comprising an oil reservoir (17) and an axial piston pump (18) comprising a tiltable plate (23), as well as a control chamber (24) and a compensation chamber (27) for increasing the tilt of the plate (23) when the pressure inside these chambers increases, the pump (18) being supplied by the reservoir (17) and having its outlet configured so as to be able to be connected by a supply line (19) to one of the chambers (12, 13) of the orienting actuator (14), the other chamber of the orienting actuator (14) being connected to the reservoir (17), this control circuit comprising a valve (42) controlled by a computer (FADEC), which valve (42) allows the outlet of the pump (18) to be connected to the reservoir (17) in order to deactivate this pump (18).

A propeller blade pitch control mechanism configured to adjust and control the blade pitch of the blades of a multi-blade propeller simultaneously. The pitch control mechanism may have a pitch plate which is raised or lowered along a liner path along an axial direction using a linear drive, which may be a power screw. The pitch plate is coupled to the blade roots with kinematic links which transfer the linear axial motion of the pitch plate along the propeller spin axis into rotary motion of the propeller blade roots, thereby controlling the pitch of the propeller blades. The propeller pitch control mechanism may include springs or gas springs adapted to place the propeller blades in a low drag position in the event of failure of the blade pitch control mechanism.

Adjusting pitch of the wind turbine rotor blades to reduce fatigue of the wind turbine tower. Flap loading sensor data is received for the rotor blades, and a flap loading vector in a rotor coordinate frame of the wind turbine is obtained. The flap loading vector is transformed to obtain first and second mutually orthogonal components in a fixed wind turbine coordinate frame, and respective 3P (blade passing frequency) components in the fixed frame indicative of 3P frequency content of the wind turbine tower are determined. A control action is applied to obtain respective 3P control components for mitigating the 3P frequency content of the tower, an inverse transform is applied to the 3P control components to obtain pitch reference offset values for the respective rotor blades in the rotor coordinate frame, and blade pitch is adjusted based on the pitch reference offset values.

A pitch tube for a blade pitch control system of a wind turbine includes a tube body extending from a first axial end to a second axial end, for passing supply lines through a transmission. The tube body is designed in multiple parts and made of a non-conductive material only in an axial partial region in order to electrically insulate the first axial end in relation to the second axial end and / or in order to electrically insulate the tube body in relation to the transmission.

A system and method for controlling a VTOL aircraft to minimize acoustic noise. In a hover mode, the aircraft may be controlled to utilize a blade pitch angle and corresponding angle of attack range which minimizes variations in the boundary layer separation location to a point or narrow region, which reduces noise generation. The propeller blades used in the system are configured to have a reduced or no shift of the point of flow separation on the airfoil as a function of angle of attack during the hover mode. The blade design may trade off overall blade efficiency in exchange for the reduced noise during hover.

The invention discloses a water turbine speed regulation system and method based on dynamic modeling, the water turbine speed regulation system comprises a speed regulator model, and the speed regulator model comprises a frequency load controller configured to adjust the load demand of a water turbine set based on the frequency change of a power grid; the frequency load controller compares the power grid frequency with the nominal frequency, and adds the power grid frequency and the nominal frequency with a load set value after passing through a dead zone and an attenuation gain to generate a unit load demand; the gate position controller is configured to control the position of a water inlet gate based on the hydraulic turbine set load demand; the gate position controller is used for comparing the actual gate position with a reference signal and controlling the position of a water inlet gate in a PID (Proportion Integration Differentiation) mode; and the blade pitch angle controller is configured to control the blade pitch angle of the hydraulic turbine based on the load demand of the hydraulic turbine set so as to control the input water flow. The dynamic characteristics of the hydropower station can be reflected more accurately, and the precision and applicability of the model are improved.

This invention discloses a synchronous adjustment mechanism for the blade spacing of an automatic compound circular blade shearing machine, belonging to the technical field of shearing machines, and includes a base. By setting up a transmission mechanism and a linkage compensation mechanism, the invention enables the active and driven worm gears to drive the upper and lower eccentric sleeves to rotate in opposite directions, thereby achieving synchronous and precise adjustment of the distance between the upper and lower blade shafts. Furthermore, when the blade cutting load generates torque in the opposite direction, the cutting reaction force is transmitted to the linkage shaft through the driven worm gear, causing the planetary carrier to experience a disturbance torque and generate a rotational tendency. This transmits the opposite torque on the upper and lower blade shafts to the compensation gear. Simultaneously, the toothed plate in the elastic preload mechanism provides a reverse compensation torque to the compensation gear under the action of a compression spring, effectively counteracting the slight offset of the eccentric sleeve caused by the cutting reaction force, ensuring the stability of the preset gap during the cutting process, and eliminating gap errors caused by load changes.

This invention provides a method for predicting the power of a vertical axis wind turbine based on multidimensional environmental data. It relates to the field of vertical axis wind turbine power technology using multidimensional environmental data. The invention utilizes a sensor network to collect multidimensional data in real time, including environmental parameters such as wind speed, turbulence intensity, temperature, and humidity; operating states such as rotor speed and blade pitch angle; and structural responses such as blade strain and vibration acceleration. Next, empirical mode decomposition is performed on the vibration acceleration signal to construct a physical information neural network. Using environmental data and the frequency domain energy spectrum of aerodynamic loads as input, the real-time wind energy utilization coefficient and aerodynamic coefficients are output. Finally, based on the time domain signal of the aerodynamic loads, online rainflow counting with dynamic window length is used to extract the load cycle spectrum. Combined with a humidity-corrected fatigue damage model, the cumulative damage value is calculated. When the remaining lifetime is below a threshold, the load peak suppression and power generation efficiency are balanced through the coordinated control of linear decay of magnetoresistive torque and fuzzy PID control of the flaps.

This application discloses a simulation calculation method and system for a dual-rotor wind turbine. The method includes: calculating the target blade pitch angle and target generator torque of the front and rear wind turbines based on the basic parameters of the front and rear wind turbines, and generating control commands to control the simulation model of the dual-rotor wind turbine; calculating the blade aerodynamic forces and structural loads of the front and rear wind turbines in the simulation model based on the target blade pitch angle and target generator torque of the front and rear wind turbines; obtaining the blade aerodynamic torque of the front and rear wind turbines based on the blade aerodynamic forces, and calculating the current rotational speed of the front and rear wind turbines based on the blade aerodynamic torque, target generator torque, moment of inertia, and moment of inertia of the transmission system to update the basic parameters of the front and rear wind turbines; repeating the above operations iteratively to calculate the blade aerodynamic forces and structural loads of the front and rear wind turbines until the simulation time reaches a preset value, thus completing the time-domain simulation of the fully coupled dynamics of the dual-rotor wind turbine.

A pitch tube for a blade pitch control system of a wind turbine includes a tube body extending from a first axial end to a second axial end, for passing supply lines through a transmission. The tube body is designed in multiple parts and made of a non-conductive material only in an axial partial region in order to electrically insulate the first axial end in relation to the second axial end and / or in order to electrically insulate the tube body in relation to the transmission.