RU2589569C2 - Method for conversion of kinetic flow energy into rotation of wing and apparatus for realising said method - Google Patents

Abstract

FIELD: energy.

SUBSTANCE: invention can be used as source of electric and mechanical energy in hydro-and wind turbines. Method for conversion of kinetic flow energy into rotation of wing consists in that in main shaft is installed perpendicular to direction of flow and at some distance from main shaft power plant is placed at least one wing, own axis which is parallel to main shaft, around which said wing under action of flow revolves at circular orbit and oscillatory movement about its axis. When wing moves along circular orbit its angle of attack α relative to resultant vector is set by flap, control unit of which through shaft of flap and plank of flap rotates flap, thus providing optimum value of angle of α attack during its motion along circular orbit, except wing shape change areas determined by unit axis position wing in extreme positions wing axis with bearing in this point is determined nature moment set wing working or brake, and according to this automatically selects appropriate control mode.

EFFECT: technical result consists in achieving maximum possible efficiency of converting kinetic energy of current flow.

9 cl, 7 dwg

Description

The invention relates to the field of alternative energy and can be used as a source of electrical and mechanical energy in hydro and wind turbines.

According to experts, the most common power plants (EA) with a horizontal axis of rotation, according to experts, so far cannot exceed a power of 5-7 MW, which, in turn, limits the possibility of reducing the cost of kWh to a competitive value. For example, the most powerful 5 MW wind turbine of this type commissioned today has been created in Germany. The length of the blades of its wind rotor is 61 m, the height of the tower is 120 m.

At the same time, the power of a power plant with a vertical axis of rotation (BOB) of a wind rotor (such as a Darier rotor) can reach 10-30 MW. You can list such advantages of these wind turbines as: independence of operation from the direction of action of the wind flow, the ability to switch from cantilever mounting the axis of the wind rotor to the double-bearing, the ability to place an energy consumer, such as an electric generator or pump at the base of the wind turbine, while reducing requirements for height, strength and rigidity support, simplifying the design of the blades and reducing their material consumption, and hence the cost, reducing the noise of a wind turbine with WWII.

One of the main drawbacks of wind turbines with DOM with rigidly fixed relative to the traverse blades is the high speed of the wind flow (VP), at which the rotor self-starts in rotation and a lower coefficient of energy use of the flow than conventional propeller wind turbines. As a result, designers are forced to supply such wind turbines with additional devices, for example, an electric motor, a Savonius rotor, etc., for spinning the rotor and putting it into operation.

The high self-starting speed of such a wind rotor is caused by the fact that the vertical rotor blades fixed rigidly relative to horizontal traverses in the static state cannot create (when the medium and low speed winds flow around them) the required magnitude and the desired direction of action of the aerodynamic forces on the blades and thereby sufficient torque on the shaft to bring the rotor into rotation. The use of a mechanism for controlling the position of the blades in the wind rotor design allows the blades to rotate relative to the traverse so that the magnitude and direction of the resulting aerodynamic force on the blades allow the wind rotor to self-start even at VP speeds of 3-4 m / s.

Known rotary wind turbine (see patent RU 2042044 C1, IPC F03D 3/00 F03D 3/06, from 08.20.1995), considered as an analogue. The rotary wind turbine contains a rotor mounted on a vertical axis with blades placed on radial rods, and a mechanism for changing the angle of attack of the blades by rotating the blades around their own axes parallel to the axis of rotation of the rotor, made in the form of a device changing the angle of attack connected to each blade connected to other similar devices with radial rods by means of a matching unit mounted on the axis of rotation of the rotor, each blade having an aerodynamic symmetrical profile Or, the axis of rotation of the blade is shifted to the leading edge, and the device for changing the angle of attack contains a housing mounted on each radial rod, in which a spatial crank-connecting rod mechanism of the swinging washer is connected, connected to the axis of the blade by means of a conical orientation gear sitting on the axis of the crank on which the bracket bearing is installed, the swinging washer is a sleeve with two radial trunnions mounted rotatably on an inclined axis located at an angle α = 45 to the axis of the blade, and on the axle two forked leads are hinged, the axis of one of which is mounted rotatably in a bearing placed on the housing base at an angle β to the line of the axis of the blade, and the axis of the second forked lead is mounted to rotate in a bearing of the arm, and the angle β does not exceed angle α , and the matching node is made in the form of a conical differential.

This known device is equipped with complex and expensive mechanical components, the reliability of which is doubtful, and operation requires serious maintenance and is unacceptable for widespread use. In addition, the optimal angle of attack of the wing depends on the resulting airflow vector (RVVP), the value of which depends on the speed of the load, the speed of the air flow and a specific point on the trajectory. And in the analogue, these factors are not taken into account when choosing the angle of attack.

, -Прикладна гiдромеханiка. - 2010, Том 12, №4, с. 26-35), которая частично отражена в патенте Вiтросилова установка (см. Патент Украины №16097А на полезную модель, МПК F03D 3/00, F03D, 07.06.2006, №7. с. 174.), принятый за аналог.An interesting work on improving the Darier rotor was carried out at the Institute of Hydromechanics of the National Academy of Sciences of Ukraine (Kayan VP, Lebed AG "Optimization of the performance characteristics of a full-scale model of the Darier wind turbine with straight controllable blades." -

, -Applied Hydromechanics. - 2010, Volume 12, No. 4, p. 26-35), which is partially reflected in the Vitrosilov installation patent (see Ukrainian Patent No. 16097A for utility model, IPC F03D 3/00, F03D, 06/07/2006, No. 7. P. 174.), adopted as an analogue.

The wind power installation contains a rotor with a vertical shaft, with which, using traverses and pins, vertical blades are connected, which have vertical axes with hinged rings, with the help of which they are mounted on the traverses with the possibility of rotation around these axes, and additional axes mounted on the lower ends of the blades with forks and rollers that are joined with the ring-shaped guide in the form of a rigid rim having a circle shape in the plane, as well as the power plant control equipment, and the ring-shaped head ulation coupled with the mechanism controlling the position of the rotor blades so that a possibility of linear displacement along the direction of wind flow, and a mechanism disposed on rotatable platform rigidly connected with the vane. The mechanism for controlling the position of the rotor blades contains an electric motor, gearboxes and movable guides placed on the platform of the mechanism, and worm gears associated with an annular guide, which also has rollers for moving along the guides. The wind power installation control equipment contains a software device that determines the optimal displacement of the center of the annular guide depending on the operation parameters of the rotor of the wind power installation.

The efficiency of this wind power installation is significantly higher than that of the Darier wind turbine in the classic version. This is one of the options for a more or less successful experimental search for the limiting values of the wind rotor. The value of the eccentricity between the two axes of each wing is calculated, which provides the maximum value of the power of the wind rotor for the selected control method. In addition, the implementation of an electromechanical programmable control system is quite complicated.

A known method of converting the kinetic energy of a fluid into rotational movement of the wing and the installation for implementing this method according to patent RU 2157919, IPC F03D 3/00 publ. 10.20.2000 g.

The invention relates to the field of alternative energy, is used as a source of electrical and mechanical energy in hydro and wind turbines and is selected as a prototype.

This method consists in the fact that a fixed axis is established in the fluid perpendicular to the direction of flow of the fluid and a wing is placed at some distance from this axis, its own longitudinal axis (O-O) which is parallel to the fixed axis, around which this wing is under the action of hydrodynamic forces acting on it, performs a rotational motion in a circular orbit and oscillatory motion around its own longitudinal axis (O-O), and when the wing moves along an arc of a circular orbit facing the flow of learning the environment, the angle of attack angle α of the wing is kept constant with one sign, and when the wing moves along the opposite arc of a circular orbit, the sign of the constant value of the angle of angle α of attack of the wing is also changed to the opposite one, and on the arc of a circular orbit on which the wing moves against the direction of flow of the fluid environment, and on an arc of a circular orbit on which the wing moves in the direction of this stream, the angle of attack α is set to zero.

In some cases, it is more profitable to set the wing angle α of attack above the “critical” value of the stationary flow regime for the selected profile and shape of the wing (2) when the wing (2) moves in a circular orbit (3).

To increase the efficiency of the method, the value of the circumferential speed V _{t of the} wing (2) is chosen greater than the value of the velocity V _{o of the} fluid flow (A).

Installation for converting the kinetic energy of a fluid into rotational movement of a wing (2), containing a fixed axis (1) mounted in a stream (A) of a fluid perpendicular to the direction of its movement, a wing (2), whose longitudinal axis (O-O) is parallel to the stationary axis (1), pivotally connected to the fixed axis (1) using at least one rod (4), and the wing (2) is equipped with a device for controlling its angle of attack, made in the form of a wing-shaped element (5), equipped with its own drive (6 ) to control its angular floor relative to the wing (2), characterized in that the actuator (6) controls the angular position of the wing-shaped element (5) relative to the wing (2) provides the angle α of attack of the wing (2) when it moves along an arc of a circular orbit (3) facing the stream (A) a fluid constant with one sign along the opposite arc with the opposite sign, and when the wing (2) moves from one arc to another, it is equal to zero. The drive (6) for controlling the angular position of the wing-shaped element (5) relative to the wing (2) provides a range of angles of attack α of the wing (2) above the “critical” values of the stationary flow regime for the selected profile and shape of the wing (2), and the wing (2) and / or the wing-shaped element (5) is provided with a flap (7) associated with the actuator (6).

The drive (6) for controlling the angular position of the wing-shaped element (5) relative to the wing (2) contains a cam mechanism, the cam (9) of which is fixed on the fixed axis (1), and the beam (11) is mounted on the rod (4) and connected with the lever having two shoulders (13 and 14), the axis of which coincides with the center (O-O) of the hinge connection of the rod (4) with the wing (2), and on the same axis (O-O) there is a link mechanism having a link (15 ) and two sliders (16 and 17), and one slider (16) is connected to the shoulder (14) of the two-shouldered lever and to the lever (20), which is mounted on the same axis (O-O) and connected is engaged with the pterygoid element (5), and the second slider (17) is connected with the rod (4) and with the wing (2).

Note the disadvantages of the method considered: 1. Despite the fact that the method is also proposed for wind turbines, there is no operation and device for orientation of the rocker mechanism that sets the angle of attack relative to the air flow (VP), while the direction of the current medium is uniquely set.

2. The optimal angle of attack α depends on the resulting flow vector, ie from the speed of the external flow and the speed of the installation. Therefore, the calculated function and the configuration of the master wings are designed for some optimal value of the angle of attack α for some, for example, the nominal value of the resulting vector of the current medium for the given ratios of the flow velocity and the installation speed. Obviously, the considered method does not optimize the angle of attack α in the general case for different airspace directions, different speeds and different ratios between the speed of the airspace and the peripheral speed of the device.

3. The considered method provides the angle of attack α of the wing when it moves along an arc of a circular orbit facing the fluid flow, constant with one sign, in the opposite arc with a opposite sign. When considering the known curves of FIG. 1 it can be seen that the coefficient C _y in the zone of negative values of the angle of attack α is several times less than with its positive value. In this regard, the efficiency of the installation is significantly reduced. However, in FIG. 4 of patent RU 2157919 on a graph of the dependence of torque on the position of the wing - this fact is not noticed (see Fig. 2).

The technical result of the proposed method is the maximum possible conversion efficiency of the kinetic energy of the current stream (air flow - VP in the general case, since in comparison with the hydroflow it is necessary to determine the direction of the VP during conversion to other types of energy). It is achieved by the fact that in the proposed method for converting the kinetic energy of the flow into rotational movement of the wing in the flow, the main shaft is installed perpendicular to the direction of flow and at least one wing is placed at a distance from the main shaft of the power plant, whose own axis is parallel to the main shaft, around which the wing under the influence of flow rotates in a circular orbit and oscillates around its own axis, while the movement of the wing in a circle in the orbit, its angle of attack α relative to the resulting flow vector is defined by the flap, the control unit of which rotates the flap through the flap shaft and flap flap, providing the optimal value of the angle of attack angle α of the wing when it moves in a circular orbit, with the exception of the zones of change in the shape of the wing determined by the axis position node wing, and in the extreme positions of the axis of the wing with a bearing in this node determines the nature of the moment specified by the wing, working or braking, and in accordance with this is automatically selected according current control mode.

As a result of the action on the wing of the VP during its movement in a circular orbit, a constant maximum possible lifting force R is formed up to the nominal value of the power plant over almost the entire circular orbit of its movement. The main shaft of the EA is perpendicular to the movement of the VP, in which the EA is placed, and the axis of each wing is parallel to the main shaft and rigidly clamped by the support disks from above and below.

The axis of each wing passes through the node position of the axis of the wing (UPOK). The wing is three-layered. It is based on the wing base sheet, to which two-sided movable curly aerodynamic sheathing is attached to the hinges at the front and rear edges, and the wing aerodynamic shape changes abruptly symmetrically with respect to the base sheet when each wing moves in a circular orbit in the zone of change in the moment sign formed by the wing. The working moment formed by the wing exerts pressure on its axis with the working edge of the UPOK in the working direction of rotation of the entire EA mechanism within the movement in a circular orbit relative to the resulting VP vector (RVVP). A pressure sensor D. is fixed on the working edge of the UPOC

In this case, the angle of attack α is automatically adjusted relative to the RVVP according to the signal from pressure sensor D. This signal is transmitted to the extreme controller (ER) based on the controller, and the latter acts on the flap servomotor, providing maximum pressure on the wing axis by choosing the optimal value of the angle of attack α wing under the influence of its flap.

In the presence of an EU revolution sensor, it is possible to control the angles of attack α of all wings from the pressure sensor regulators D of one control wing by calculating the delay of the remaining wings to the position of this control wing on the trajectory of movement in a circle using the controller. Control commands with calculated delay are applied to the flap drives of the respective wings. At the same time, the control system of the entire EA is simplified, its reliability is increased, the design is simplified and the cost is reduced

When moving in a circle in the zones of 180 degrees + Δ and 360 degrees + Δ relative to the RVVP (where Δ is the zone of change in the shape of the wing when determining the braking torque), the wing forms a braking torque that counteracts the working direction of the power plant. The wing is displaced about its axis in the UPOK up to its brake edge, on which there is an electric reverse reverse switch (ECRR), and the EA briefly goes into braking mode.

The shape of the wing automatically changes abruptly in the Δ-zones of the braking torque developed by the wing. On command from the ECWR, an electromechanical trigger is triggered, changing the aerodynamic shape of the wing to a symmetrical one relative to the base sheet of the wing.

An effective protective mode is provided as follows. The signal from the pressure sensor D is limited by the nominal value U _n corresponding to the nominal moment on each wing. With a further increase in the RVVP speed to limit the signal from the pressure sensor D, instead of the ER, the tracking controller (PC) for the nominal signal U _{n is} turned on, also affecting the flap drive and changing the wing angle α, decreasing it to negative values.

Environmental protection is provided as follows. A wire mesh is attached around the outer circumference of the support discs, protecting the EU from birds and debris.

In the future, the patented invention is illustrated by the specific design of its implementation by the accompanying drawings, in which:

FIG. 3 is a general view of the EU according to the invention.

FIG. 4 - depicts the movement of a separate wing of the EU at the start of launch, when the speed of the airspace is close to the speed of the airborne landing gear.

FIG. 5 is a sectional view of the wing along BB, see FIG. 3.

FIG. 6 - wing structure without curly double-sided aerodynamic sheathing along section BB in FIG. 5.

FIG. 7 - the node of the position of the axis of the wing of the UPOC along the section EE in FIG. 6

The patented method is implemented by the design of the EU according to FIG. 3, where the frame 1 provides a vertical position of the main shaft 2, the ends of which go into the upper 3 and lower 4 bearings. The nuts of the main shaft 5 fix the upper 6 and lower 12 support discs to the main shaft. On the disks, the axles 7 of individual wings 8 are fixed using the nuts of the wing 11. From the bottom, each wing 8 is supported by its external support 10. An important structural detail is the flaps 9 adjacent to each wing. The axis of each wing 7 is rigidly connected to the main shaft 2 of the EA from above and below through the supporting disks 6, 12, and the EA can consist of one such set-tier or more. In this case, the modular principle of the formation of the design of power plants of the required power with the known power of a single-tier power plant is used.

In FIG. 4 shows the individual details of the design of the EU. The main shaft 2, the axis of each wing 7, the wings 8, flaps 9, the zone of change in the shape of the wing 13 symmetrical relative to the base sheet of the wing.

In FIG. 5 (section B-B) displays individual parts in the design of the wings. The axis of the wing 7, passing through the node of the position of the axis of the wing KLAA 16, the flap 9, the electromechanical trigger 15, the front aerodynamic cladding of the wing 17, the rear aerodynamic cladding of the wing 18, the axis of rotation of the aerodynamic cladding 19, the control unit flap 20, the shaft of rotation of the flap 24.

In FIG. Figure 6 shows the wing structure (along section BB). The flap 9, the external wing support 10, the electromechanical trigger 15, the control gear 16, the axis of rotation of the aerodynamic skins 19, the control unit of the flap 20 with fasteners 14, the support of the axis of rotation 22, the flap of the flap 23, the rotation shaft of the flap 24 passing through the control unit of the flap 20 internal wing supports 25, the front of the base sheet of the wing 26, the rear of the base sheet of the wing 27.

In FIG. 7 (section EE), the design of the UPOC is given. The axis of the wing 7, the front part of the base sheet of the wing 26, the rear part of the base sheet of the wing 27, springs 30, pressure sensor D 31, electrical limit switch 32, pushers 33, bearing 34, the body UPOK 35.

In FIG. Figure 3 shows a simplified mode of motion of one wing 8 when starting the EC, when the airspace speed V _{TP is} much higher than the rotation speed ω (the resulting airspace vector acting on the wing is approximately equal to V _TP ). When the wing rotates, its axis 7 is shifted within the UPOC 16. On the axis 7 within the UPOC 35 body, a bearing 34 is fixed (see Fig. 7), which, when the UPOC moves relative to the wing axis, reduces friction between the axis and the UPOC parts (pushers 33) in the process of operation of EU. In the zone of change in the shape of the wing 13, when the braking moment of the wing occurs, the axis 7 with the bearing 34 is shifted towards ECR 32 and pressed to the corresponding push rod 33. ECR 32 closes its contact, transmitting a signal to trigger the electromechanical trigger 15, which, by the command of ECR 32, alternately extends the upper or lower mushroom stock, changing the configuration of the wing 8 in zones 13 symmetrically with respect to the base sheet of the wing 26, 27. At the same time, the front 17 and rear 18 wing aerodynamic covers on the axis of rotation of the aero Response Dynamic skins 19.

When changing shape, the wing sets the working moment. In the zone of changing the shape of the wing 13, when a working moment occurs, the axis 7 with the bearing 34 is shifted towards the pressure sensor 31 and pressed against the corresponding push rod 33, which acts on the sensor 31. The sensor 31 sets a signal to the extreme regulator in the flap control unit 20. This signal acts in the working direction of rotation of the EU within the movement of the wing along an arc of 0-180 degrees and from 180-360 degrees relative to the resulting VP vector.

Getting into the zone of 180 degrees + Δ, the braking moment again occurs. The value of Δ in degrees depends on the current speed of the installation and on the speed of its electromechanical trigger 15.

The extreme controller controls the flap servomotor, also located in the flap control unit 20, and provides maximum pressure on the sensor 31 in the zone of operating moments during wing movement, i.e. the maximum possible working moment on a particular section of the trajectory. The flap control unit 20, acting on the flap shaft of the flap 24, provides the optimal angle of attack of each wing at the moment, while the inertia of the flap 20 can be neglected, assuming a high power EC and a low nominal speed at a significant useful load moment.

With the speed sensor Vω on the main shaft 2 of the control unit, it is possible to control the angle of attack α of all wings from the pressure sensor 31 and the controller of one control wing by recording its trajectory of movement in time and calculating the delay for the other wings to the position of this control wing on the trajectory along circle using the controller. In this case, the flap control units 20 of the remaining wings will be controlled from the controller in all operating modes.

Upon receipt of a signal at the output of sensor 31 that exceeds the nominal value of pressure U _n , when the operating moment under the influence of the VP exceeds the nominal value, this signal switches to the input of the tracking controller, which is also located in node 20, and in this mode controls the flap through the servo-drive, rejecting angle of attack of the wing from the optimal value, i.e. reducing the angle α to zero and further to negative values and braking the EA at high wind loads, along with other means of protection.

A protective mesh screen, not shown in FIG. 5, so as not to obscure the main components of the EU design. It protects the details of PM from debris, hail and birds.

A patented method for converting the kinetic energy of a stream into rotational movement of a wing and an installation for its implementation can be successfully applied using renewable energy sources such as wind energy and the natural flow of rivers, seas, oceans, etc. Using the proposed method gives significant savings in energy resources.

At the same time, the high efficiency of devices using the optimal flow around the wing makes it possible to create economically feasible installations at low flow rates. The method, as well as the plants implementing it, are universal, since they can be applied without any modification to the currently widely used electronic controllers, programmable devices, pressure and speed sensors, electromechanical triggers, limit switches, electric generators, etc. .

No waste polluting the environment. The rotation of the wing caused by the low-speed flow has such a low noise level that it has no effect on the surrounding flora and fauna.

Claims (9)

1. A method of converting the kinetic energy of a stream into rotational movement of a wing, which consists in installing a main shaft perpendicular to the direction of flow and placing a wing at a certain distance from the main shaft of the power plant, whose own axis is parallel to the main shaft around which this wing acts the flow rotates in a circular orbit and oscillates around its own axis, characterized in that when the wing moves in a circular orbit, its angle a where α relative to the resulting flow vector is defined by a flap, the control unit of which rotates the flap through its shaft and bar, providing the optimal value of the angle of attack angle α of the wing when it moves in a circular orbit, with the exception of the zones of change in the shape of the wing determined by the node position of the wing axis, and in extreme positions the wing axis with a bearing in this unit, the nature of the moment specified by the wing, working or braking, is determined, and in accordance with this, the corresponding control mode is automatically selected. 2. The method according to p. 1, characterized in that in the areas of changing the shape of the wing when the braking moment of the wing occurs, the axis with the bearing is shifted towards the electrical reverse switch of the reverse and pressed to the corresponding push rod, the contact of the electrical terminal of the reverse switch is closed, transmitting a signal for the operation of the electromechanical trigger, which, at the command of the electric reverse limit switch, alternately extends the upper or lower mushroom rod, changing the wing configuration in the zones symmetrically o relative to the base sheet, while changing its
the position of the front and rear aerodynamic wing skins on the axis of rotation of the aerodynamic skins. 3. The method according to p. 1, characterized in that in the areas of changing the shape of the wing when a working moment occurs, the axis with the bearing is shifted towards the pressure sensor and pressed against the corresponding follower, acting on the sensor that sets the signal to the extreme pressure regulator in the flap control unit, which provides maximum wing pressure in the working direction of rotation of the power plant within the limits of the wing movement along a circular path relative to the resulting airflow vector. 4. The method according to p. 1, characterized in that to simplify the control system of the power plant and increase reliability in the presence of a speed sensor on its main shaft, it is possible to control the angles of attack α of all wings from the regulators and the pressure sensor of one control wing by storing its trajectory during time and calculating the delay for the remaining wings to the position of this control wing on the trajectory of movement in a circle using a special controller that generates commands to servomotors in the control units krylkom remaining wings in all operating modes. 5. The method according to p. 1, characterized in that in a power plant when it receives a signal at the output of the pressure sensor that exceeds the nominal pressure value, its signal is switched to the input of the tracking regulator, which is also located in the flap control unit, and in this mode also controls servo by flap position, deflecting the angle of attack of the wing from the optimal value, i.e. reducing the angle α to zero and then to negative values. 6. Power plant for converting the kinetic energy of the flow into rotational movement of the wing, containing a frame that provides a vertical position of the main shaft, the ends of which go into the upper and lower bearings, and the nuts of the main shaft are fixed
the upper and lower supporting disks are attached to the main shaft, and the axis of the wings is fixed with the help of wing nuts; in addition, each wing is supported by its external support from below; an important part of the power plant design is the flaps attached to each wing using the flap shaft and the flap . 7. Power plant according to claim 6, characterized in that the wing axis position assembly includes the wing axis proper with a bearing mounted on it, which, in the process of moving the wing along a circular path, is pressed alternately to the pushers, compressing the corresponding springs and acting on the pressure sensor or an electrical end switch of the reverse, and all the details of this node are placed in its housing. 8. The energy installation according to claim 6, characterized in that the wing structure includes a flap, which is connected through the bar to the flap turning shaft, which leaves the flap control unit, and the wing axis passes through the position of the wing axis and the wing supports, to which are fixed the front and back of the base sheet, and on the base sheets are the electromechanical trigger and the axis of rotation of the aerodynamic skins with their supports. 9. The power plant according to claim 6, characterized in that a protective grid is attached along the outer circumference of the support discs, which protects the details of the power plant from debris, hail and birds.

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