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INVENTION
Russian Federation Patent RU2141059

WING (BLADE) for wind turbines With self-aligning AOA to the direction of the incoming flow ENVIRONMENT

WING (BLADE) for wind turbines With self-aligning AOA to the direction of the incoming flow ENVIRONMENT

Name of the inventor: Mikulenok VV .; Danilevich YA.B .; Kirichenko BE .; Sapozhnikov VA .; Yudin Y.
The name of the patentee: State Enterprise Division of electricity problems the Department of Physical and Technical Problems of Energy of Russian Academy of Sciences
Address for correspondence:. 191186, St. Petersburg, Palace Embankment, 18, OEEP RAS, Stankowski VM
Starting date of the patent: 1998.12.23

Wing (paddle) intended for energy power plants utilizing the energy of flow of the medium and convert it into mechanical energy, but also can be used as a rigid sail-wing type windmill, hydraulic motor, etc.. Wing with self-adjustment of the angle of attack to the direction of the incoming medium flow is set to moving structure rotatable about its own axis. Wing unit comprises changing the angle of attack of the wing by rotation of its axis by acting on it through the driving connection flap mounted on the wing trailing edge pivotable. The apparatus changes the angle of attack represents the axis, one end thereof being located inside the flap between the two plates and bent at an angle of 120-135 ° with the possibility of moving between the plates, and the axis is rotatable, and its second end is located inside the wing and is connected kinematically with a moving structure with stress-elastic return in excess of the rotation axis of rotation of the working torque. Kinematic device communication portion axis changes the angle of attack, which is located in the wing, with the moving structure is formed as a bevel gear mounted on an axis engaging with a bevel gear mounted in the housing of the moving structure, or a flexible connection. The device allows you to make maximum use of the energy of the incoming flow.

DESCRIPTION OF THE INVENTION

The invention relates to energy power plants using the energy stream medium and convert it into mechanical energy, and a Movement art and can be used as a rigid sail-wing type windmill, and other hydraulic motor.

Known wind power plant Copyright certificate USSR N 1442692/1 / having mounted on a vertical shaft rotor with rotating blades on horizontal carrying bar. wings turning device includes thrust pairs connected to one ends of the blades, wherein the apparatus is provided with turning crank mechanisms, each crank which by means of levers and joints connected to the other ends of each pair of rods.

This scheme allows for the complete independence of the aerodynamic modes of each blade of the wind direction. However, the mobility restriction prevents the creation of a separate wing of the traction on the whole path of the sweeping surface. This leads to a marked decrease in energy efficiency of the wind flow.

Known hinged blade with automatic adjustment of the angle of attack and camber of US Patent 5193978/2 / Adopted as a prototype comprising the front section, which with the help of parallelogram device is rotated about its vertical axis (parallel to the rotor axis of rotation, which is attached to the radial traverse wings ), and is set at an angle of attack to the oncoming flow. The rear section of the blade is connected to the front by a hinged device. The control lever is pivotally coupled to the blade axis by a parallelogram mechanism and the rear blade section. The rear section of the blade, simultaneously turning the front, is always parallel to the control lever, which leads to a change in blade angle of attack and the flow direction is parallel to the control lever - so that the curvature of the profile varies. At high angles of attack is possible to obtain maximum lift. The blade may be used to convert the flow of energy or motion to the stream.

Disadvantages of the prototype are:

1. The presence of protruding arms that create aerodynamic losses.

2. Bad stabilization of the blade position in the stream - the blade can leave a negative angle of attack.

3. When strong wind by feathering the flap at a right angle to the flow, which creates the possibility of structural failure.

4. Inability to make a full rotation around its axis, as the control lever has two rigidly fixed installation point.

All this allows maximum use of the energy of wind or hydraulic flow.

The task to be solved by the invention is the maximum utilization of the energy of wind or water flow by achieving the following technical result: significantly, to 0.8, improving energy efficiency of wind or hydraulic flow; the possibility of effective use as automatically installed on the wing flow.

The stated technical problem is achieved in that in the wing a self-adjustment of the angle of incidence to the free stream direction medium mounted on a moving structure is rotatable about its axis and comprising a device change the wing angle of attack by turning its axis by acting on it through the driving connection flap mounted at the trailing edge of the wing rotatably device changes the angle of attack represents the axis, one end thereof being located inside the flap between the two plates and bent at an angle (120-135) o C to move between the plates, with the axis of rotation is arranged to and its second end is located inside the wing and cinematically connected to the moving structure with stress-elastic return in excess of the rotation axis of rotation of the working torque.

Kinematic connection portion axis changes the angle of attack device disposed in the wing, with the moving structure is formed as a bevel gear mounted on an axis engaging with a bevel gear mounted in the housing in the moving structure or a flexible connection.

The invention is illustrated by the example vetrogidrodvigatelya drawings, in which:

WING (BLADE) for wind turbines With self-aligning AOA to the direction of the incoming flow ENVIRONMENT

FIG. 1 - general view vetrogidrodvigatelya;

FIG. 2 - top view with vector diagrams of velocities and forces;

FIG. 3 - wing flaps;

4 - the kinematic diagram of the device self-adjustment of the angle of attack.

The invention comprises a vertical rotor blades 1, the shaft 2 is mounted on the base 3. Inside the base 3 are arranged and an electric multiplier, not shown in the drawings. The lower end of the shaft is kinematically connected to the shaft of the multiplier. In the upper part of the shaft 2 mounted hub 4, which is rigidly attached to the radial rod 5, evenly spaced around the circumference. The number of radial rods 5 equal to the number of blades 1. In the described embodiment of wind turbine design is considered a three-bladed version of the rotor, but the number of vanes may be larger.

The blades 1 are mounted on the ends of the radial rod 5 in a freely rotatable roller 6 about axes parallel to the rotor shaft 2 of the rotor. Each blade 1 consists of the lower wing 7, the upper wing 8 and 9. The lower control flap 7 and 8, the upper wings are rigidly interconnected by a roller 6, rotating freely in a bearing 10 which is mounted in a housing 11 rigidly mounted on the end of the radial rod 5. Thus, each pair of wings 7 and 8 are freely rotatable around their axis parallel to the axis of the shaft 2 of the rotor. Trapezoid in terms of the wings 7 and 8 have Aerohydrodynamic symmetrical profile. wing axis of rotation 7 and 8 pass through the wing focus at a distance of 30% of the chord from the leading edge that does not cause displacement of the center of the dynamic pressure of the flow in the working angles of blade attack and feathering blades in heavy wind gusts provided mainly flap established for the trailing edge 8 wing.

The wings are balanced so that their centers of mass located on the axis of rotation, i.e. to the roll axis 6, this eliminates the influence of centrifugal forces on aerohydrodynamic force when the rotor rotates.

The control flap 9 located on the trailing edge of the wing 8, it has Aerohydrodynamic (mutually) profile. Area control flap 9 is approximately 10% of the area of ​​the lateral surface of the blade, which provides good handling and position the blade in the flow stabilization. The control flap 9 is designed to fit the blade 1 at an optimum angle of attack to the flow velocity vector apparent. Aerogidromehanicheskaya blade setting is performed by setting the angle of attack device disposed in the housing 12 within the casing 13 of the upper wing flap 8. Control 9 is pivotally mounted around axis 15, rotating in bearings 16 which are mounted on brackets 17 fixed to the rear edge of the wing 8 . Inside the flap 9 are mounted two parallel flat plates 18 with a guaranteed clearance between them. The gap between the plates 18 enters the crank axle 19 which is fixedly connected with the axis 20 at an angle mechanism (120-135) o, rotating in bearings 21. The vertex angle of intersection of the axes 19 and 20 located on the axial line of the hinge axis 15 and the rotation of the flap 9 an angle is converted to rotation axis 20 and vice versa. On the other end of the shaft 20 having a flat area on the side surface of the bevel gear 22 mounted rotatably in the working torque is exceeded. The toothed wheel 22 is provided with a tracking mechanism to control the time of rotation on the axis 20 for the blade feathering at squall and engages with the bevel gear 23. The bevel gear 23 is free to rotate on the shaft 6. The flange 23 bevel gear on the side surface 24 has a recess , through which the tightening device (for example, farm Mises) biased roller 25. The fixing roller 25 fixes gear 23, not allowing it to rotate relative to the housing 11 and can be pressed by its lever 26, a centrifugal regulator.

By increasing the angular velocity above the calculated centrifugal force F cf weight regulator 26 increases and the lever 27 against the force of a clip, press the roller 25 against the flange 23. The bevel gear pinion is rotated in the housing 11 and the wing flyugiruetsya, but remains in the feathered position only until is the angular velocity is decreased to the calculated value. control threshold amenable to regulation. In the initial position chord steal flap 8 and 9 are located on a straight line perpendicular to the center line of its radial rod, ie on the tangent to the circle of rotation.

Principle aerohydrodynamic installing blade angle of attack is based on the difference in the location of the dynamic pressure of the flow centers on a symmetrical airfoil convex and symmetrical concave flap profile. If you change the angle of attack of the wing symmetrical convex profile to its supercritical values ​​of dynamic pressure along the center of the chord and the wing does not move does not feel the restoring force. At the center of the dynamic pressure flap with minimal deviation from the feathered position is moved to the trailing edge, and he seeks to recover his feathered position. Flap cinematically connected to the wing, which is rigidly mounted inside the housing mechanism kinematically associated with the radial bar in its azimuthal position relative to the direction of flow. The angle of attack depends on each wing 19 to a predetermined angle and the azimuthal axis 20 (course) of the angle of the wing to the wind velocity at a given rotor speed.

The invention operates as follows:

Consider the initial moment of the impact of the flow on the stationary rotor. The flow affects the flap 9, which is trying to take a directional position, rotates with the wing at an angle. Together with the flap 9 are rotated and the flat plate 18, which comes between the crank axle 19. The axle 19 rotates together with the plates 18 in the horizontal plane, while sliding on the surface of one of the plates in a vertical plane; with sine-cosine relationship. axis mechanism 20 communicates torque bevel gear 22 and pinion 23, a trial run until the flap chord is parallel flow. The maximum deflection angle of the flap relative to the wing chord 8 in this construction is 45 o.

If forced rotation relative to the wing flap 9 8 45 o gear 22 is rotated by 90 o and obkatyvayas on gear 23, rotates the blade 1 at 90 o from the initial position. When this flap itself 9 rotates in space at an angle of 90 o +o = 45 135 o. The average ratio between the angle of rotation of the wing 8 of 90 o C, and the total angle of rotation of the flap 9, equal to 135 o, equal to 0.66, and the angle of attack = -0.66 . When the rotor is stationary = = 90º, = 90º-59,4º = 30,6º. The wing is located in: an azimuth 0 o or 180 o dynamic pressure and the force on it is immediately converted into a thrust force directed tangentially to the circle of rotation of the rotor. The rotor starts to rotate at a circumferential speed V , Each wing induces a counter-flow -V = V and it affects the flow is equal to the algebraic sum of vectors V T and V, ie V A and making an angle a vector V Which in turn forms an angle c with the vector V T. Given that the greatest rate of flow is possible with the use of V The V t = 2 ·, t. E. The relative speed with Z = 2, and applying Theorem for ships sailing courses, we can calculate the thrust produced by each wing, and calculate the total thrust of the wings of one complete rotation. Thus, flaps, tracking the flow of V A, constantly creates turning point on the axis 20, the angle of attack Constantly providing T thrust directed along the vector V line . A strong gust of wind on the flap 9, there is an additional lateral dynamic pressure. Torque on the shaft 20 increases dramatically and the pinion gear 22 rotates on the axis 20. The flap 9 becomes rigid kinematic connection with the wing 8 and flyugiruetsya. For the angle of the wing 8 is currently zakritichny and it flyugiruetsya. A similar process occurs with other wings, that is, the rotor "obezvetrivaetsya", and after passing a flurry of wings, while in azimuth = 90º, again reduced its serviceability

By increasing the flow velocity V T or reducing electric stress it may increase the circumferential speed V = R. Increased - The angular velocity will increase the F cf - centrifugal force regulator 26, and he will press its lever 27, pinch roller 25 from the recess 24 on the flange of the bevel gear 23, and she provernetsya in the housing 11. Under the influence of the flap 9, the axis 19 and axis 20 of the wing freed of kinematic linkages in and go to feathered position until the rotor speed is reduced to the calculation, and then recover the function mechanisms when passing through the point = 90º.

The efficiency of the wing tried and tested models of sailing a catamaran and a carousel wind turbine.

LITERATURE

1. Author's certificate USSR N 1442692 -analog.

2. U.S. Patent N 5193978- prototype.

CLAIM

1. Wing (paddle) with self-aligning angle of attack to the incident flow direction of the medium, mounted on a moving structure is rotatable about its own axis, the device comprising: changing the angle of attack of the wing by rotation of its axis by acting on it through the driving connection flap mounted on the trailing edge wing pivotable, characterized in that the change in the angle of attack device is an axle, one end of which is disposed within the flap between the two plates and bent at an angle of 120 - 135 o to be movable between the plates, and the axis is rotatable, and its second end located inside the wing and cinematically connected to the moving structure with stress-elastic return in excess of the rotation axis of rotation of the working torque.

2. The wing (paddle) according to claim 1, characterized in that the kinematic connection shaft portion of the device changes the angle of attack, which is located in a moving wing design is formed as a bevel gear mounted on an axis engaging with a bevel gear mounted in the housing moving structure.

3. Wing (paddle) according to claim 1, characterized in that the kinematic connection shaft portion of the device changes the angle of attack, which is located in a moving wing design is formed as a flexible coupling.

print version
Publication date 31.01.2007gg