316 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.

A blade pitch detection apparatus for an aircraft having a lower rotor hub assembly and an upper rotor hub assembly, the upper rotor hub assembly including a blade pitch adjustment linkage configured to maintain the rotor blades at a first blade pitch while a rotational velocity of the upper rotor hub assembly is below a threshold and to maintain the rotor blades at a second blade pitch while the rotational velocity is above a threshold. The pitch detection apparatus includes a magnet coupled to a component of the blade pitch adjustment linkage and a sensor coupled to a component of the lower rotor hub assembly and configured to generate a signal in the presence of the magnet. Processing circuitry in communication with the sensor can determine whether the plurality of rotor blades are at the first blade pitch or the second blade pitch based on the signals.

The invention discloses a model-free self-adaptive independent variable pitch control method and system for a wind turbine generator based on multivariable decoupling, and aims to solve the problem of blade fatigue damage caused by blade root asymmetric load under a high-wind-speed turbulence working condition. A multi-input multi-output control architecture is designed, control parameters are dynamically adjusted by using a model-free adaptive control (MFAC) algorithm, a cooperative adjustment instruction of an independent variable pitch angle is generated, optimal control of a three-blade pitch angle is realized, and power output stability is maintained while a blade root load is suppressed. Compared with traditional independent pitch control (IPC), the method has the advantages that model dependence is eliminated through pseudo-gradient matrix multivariable decoupling, the anti-interference capacity under the turbulent wind condition is remarkably enhanced, and technical guarantee is provided for safe operation of a large wind turbine generator.

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.

The invention discloses a fan blade icing prediction method and device and a medium, and relates to the technical field of equipment monitoring, and the method comprises the steps: obtaining historical meteorological data, blade tip speed, pitch angle and historical icing data, and taking the data as real samples; performing data expansion on the real sample by using the generative adversarial network model to obtain a generated sample; the real samples and the generated samples form a training sample set, the training sample set is used for training the long-short-term memory neural network, and a fan blade icing prediction model is obtained to predict the icing condition of the fan blade. According to the method, the blade tip speed and the pitch angle which reflect relative motion of the blade and the supercooled liquid drop are added in training data, a prediction model obtained through training comprises icing phase change characteristics and relative motion characteristics of icing of a rotating object, description of the icing process of the fan blade is more accurate, and prediction is more accurate; the adversarial generative network model is adopted to expand the training sample set of the prediction model, the problem of insufficient real samples is solved, and the prediction accuracy is further improved.

The invention provides a variable pitch control method and system of a wind generating set and the wind generating set. The variable pitch control method comprises the steps that wind speed data at the wind coming side of an impeller of the wind generating set and at the position away from the impeller by a preset distance in the current control period are determined; determining an estimated pitch angle of the current control period based on the wind speed data of the current control period; comparing the estimated pitch angle of the current control period with the reference pitch angle of the previous control period, and taking the comparison result as the reference pitch angle of the current control period; and on the basis of the reference pitch angle of the current control period, blade pitch variation of the wind generating set is controlled. According to the variable pitch control method of the wind generating set and the wind generating set, the problem that the reduction effect of the fatigue load of the whole machine is poor due to control hysteresis is solved, blade variable pitch can be controlled in advance, and the limit load and the fatigue load of the whole machine are better reduced.

A method for determining the pitch of a wind turbine blade. A first sensor (501) is provided on a blade root of a wind turbine, and at least one second sensor (502) is provided on a blade. The method comprises: obtaining a parameter of the current operating condition of a wind turbine, a first angular velocity collected by the first sensor (501) and at least one second angular velocity collected by the at least one second sensor (502); and, on the basis of target simulated blade pitch data, the first angular velocity and the at least one second angular velocity, determining first blade pitch data of the wind turbine, the first blade pitch data being used for representing the blade pitch of the wind turbine under the current operating condition, and the target simulated blade pitch data being matched with the parameter of the current operating condition. Thus, by means of the plurality of sensors mounted on the wind turbine blade and on the basis of the simulated blade pitch data corresponding to the current operating condition combined with the angular velocities collected by the sensors, the method reckons the blade pitch data capable of accurately reflecting the pitch of the wind turbine blade, allowing for more accurate and intelligent control on wind turbines. In addition, the present application further relates to an apparatus and device for determining the pitch of a wind turbine blade.

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 floating fan pool test model blade optimization design method and device based on an NSGA-III algorithm, a medium and a program. The method comprises the steps that firstly, the aerodynamic coefficient of a real fan blade airfoil and the Reynolds number of a floating fan model blade are calculated; selecting an appropriate low-Reynolds-number fan blade airfoil to replace a model blade airfoil and calculating an aerodynamic coefficient; calculating a target thrust value and a torque value of the floating fan model under different test required wind speeds; performing linear fitting to obtain a linear function of a lift coefficient linear region of the real type and the model blade relative to the attack angle; calculating the final chord length of the model blade; and finally, on the basis of an NSGA-III algorithm, the rotor rotating speed and the blade pitch angle of the floating fan model at different wind speeds are optimized by taking the minimum relative error of the thrust and the torque as a target. According to the invention, the thrust and torque of the model fan are matched with the target thrust and torque under different wind speed scales, the test accuracy is improved, and resources are saved.

The invention discloses a wind turbine generator blade variable pitch adjusting method and device based on wind direction turbulence intensity, and belongs to the technical field of wind power generation. Calculating the variable pitch angle of the optimal output power under the current wind field condition by using the optimal variable pitch angle calculation model according to the unit operation data and the wind direction turbulence intensity of the wind turbine generator; predicting the variable-pitch angle of the dynamic blade of the wind turbine generator in a specified time period through a variable-pitch angle prediction model according to the condition change of the wind field; and according to the predicted dynamic blade variable-pitch angle of the wind turbine generator, a blade variable-pitch angle adjusting instruction is sent to the wind turbine generator, and a prediction result of the blade variable-pitch angle is verified and corrected through a feedback mechanism, so that power output optimization of the wind turbine generator is achieved. The dynamic load influence of wind direction turbulence on the fan is considered, the adaptability is high, optimal control under different wind conditions is achieved, and complex wind condition changes can be flexibly dealt with.

A propulsion system is provided, the propulsion system including a rotor assembly configured to rotate relative to the engine centerline axis, and wherein one or more blades of the rotor assembly are configured to rotate along a blade pitch angle axis. A vane assembly is positioned in aerodynamic relationship with the rotor assembly. The vane assembly includes one or more vanes, wherein each vane includes a vane pitch angle. A controller is configured to execute operations, the operations including moving each blade to a reverse thrust position about its respective blade pitch axis, and adjusting each vane about its respective vane pitch axis when the plurality of blades is in the reverse thrust position to modify an amount of reverse thrust generated by the propulsion system.

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 tower bottom limit load reduction method based on blade pre-variable pitch automatic optimization. The method comprises the steps that an initial variable pitch power interval and an initial pre-variable pitch angle are set; calculating a plurality of tower bottom combined bending moment loads under different wind speeds under the working condition of DLC1.3, and respectively drawing a power-load scatter diagram and a power-load envelope curve diagram according to the maximum load value of the tower bottom combined bending moment and the power of the wind turbine generator when the load value appears; after the pre-variable pitch angle is adjusted, the multiple tower bottom combined bending moment loads under the DLC1.3 working condition and different wind speeds are calculated again, and the maximum value in the multiple tower bottom combined bending moment loads is taken as the maximum tower bottom combined bending moment load value; the maximum load value of the tower bottom combined bending moment is compared with the target load of the tower bottom combined bending moment, and if the maximum load value is smaller than the target load value, calculation of tower bottom limit load reduction is completed. The blade pitch angle can be controlled to change along with the change of power, so that the aerodynamic force borne by the wind wheel is reduced, the tower bottom load is reduced, and the purpose of reducing the tower bottom limit load is achieved.

The invention discloses an integrated planning control method for dynamic stability of a floating wind turbine generator, which comprises the following steps of: accessing an integrated planner outside a controller, and cooperatively and dynamically adjusting core control parameters of three sub-control systems, namely blade pitch control, generator torque control and cabin yaw control; a planner based on a nonlinear dynamics mathematical model can be adopted to dynamically adjust controller parameters to realize comprehensive optimization of a dynamic stable target. Under the condition that an existing floating type wind turbine generator industrial controller architecture is not changed, by dynamically adjusting a series of core control parameters of the industrial controller, comprehensive improvement of the dynamic stability of operation of the floating type wind turbine generator is achieved, movement of a floating body platform-supporting structure is restrained, wind wheel rotating speed / active power fluctuation is reduced, and the wind turbine generator industrial controller architecture is optimized. And the operation stability and the high energy efficiency of the floating type wind turbine generator are improved, and important engineering application value is achieved.

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.

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.

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.

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.

A towed earth moving implement features a longitudinal pull tongue, a winged blade assembly with a transverse center blade and a pair of angled outer wing blades, and a wheeled frame on which the blade assembly is carried. A pivotal blade-pitch between the pull tongue and the blade assembly defines a transverse blade pitch axis about which the blade is adjustable in pitch-angle relative to the pull tongue. In a pitch-neutral position, working edges of the wing blades reside in a same horizontal working plane as a working edge of the center blade, for ground leveling purposes. In an upwardly pitched position, the working edges of the wing blades reside in forwardly inclined relation to the horizontal working plane, for ditching purposes. In a downwardly-pitched position, the working edges of the wing blades reside in forwardly declined relation to the horizontal reference plane, for crowning purposes.

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.

An impeller includes a main plate, an annular side plate and blades. The blades each have: an inner circumferential end; an outer circumferential end; a sirocco blade portion formed as a forward-swept blade portion, and having an outlet angle that is greater than 90 degrees; and a turbo blade portion formed as a swept-back blade portion and including the inner circumferential end. The blades include a first blade portion and a second blade portion that are provided on respective sides of the main plate. The impeller including a region in which a first inter-blade distance is greater than a second inter-blade distance, where an inlet-blade distance is a distance between any adjacent two of the blades in the circumferential direction, the first inter-blade distance is the inter-blade distance of the first blade portion, and the second inter-blade distance is the inter-blade distance of the second blade portion.

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.

A turbomachine module with a longitudinal axis comprising an unducted propeller rotated about the longitudinal axis and at least one straightener. The module includes a plurality of unducted variable-pitch stator blades extending along a radial axis, perpendicular to the longitudinal axis, from a fixed casing. The module includes a first stator blade pitch-changing system. The pitch-changing system includes at least one first control that includes a first fixed body connected to the fixed casing and a first body which is axially mobile in relation to the first fixed body and at least one first joining mechanism joining each stator blade to the first mobile body of the first control. The first joining mechanism includes: a joining ring centered on the longitudinal axis, joined to the feet of each stator blade and at least one lever joined, on one hand, to the joining ring and, on the other hand, to the first mobile body of the first control.

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 discloses a wind speed correction method based on similar thrust under a Froude criterion reduced scale, and belongs to the technical field of test methods. The method comprises the following steps: acquiring a wind speed-thrust relation under a wind tunnel test by using a Froude criterion scaling model; fitting a wind speed-thrust curve by using an exponential function; converting the target thrust and the corresponding wind speed into a model scale according to a Froude criterion; determining a model wind tunnel test wind speed when the thrust under the target blade pitch angle is similar; calculating the ratio of the model wind tunnel test wind speed under similar thrust to the model wind speed after Froude scale reduction, and obtaining a wind speed scale correction coefficient; the correction coefficient is applied to a model test, and the multi-physics field test requirement is met. According to the method, the defects that the thrust is inconsistent and the wind-induced vibration physical process is distorted due to the fact that the Froude criterion and the Reynolds criterion cannot be met at the same time in a fan model test are overcome, and theoretical support and technical means can be provided for multiple fields such as floating fans and the like.

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.