JPS61101684A - Azimuth controlling tail for horizontal shaft type windmill - Google Patents

Abstract

PURPOSE:To permit to balance a rotating moment with respect to the rotating torque of the windmill stably by forming the horizontal section of the tail blade so that the tail blade is capable of generating a lift efficiently. CONSTITUTION:A body 11, mounting a rotary shaft 12 securing the windmill 10, is attached to the upper end of a supporting pillar 9 so as to be pivotable in horizontal surface through a bearing. The tail blade 1 is attached to the rear end of the body 11 with a predetermined attaching angle. The torque of the windmill 10 is transmitted to a vertical shaft 15 in the supporting pillar 9. The rotating moment, as the reaction of transmission of the torque, is effected on the body 11. In order to balance with the rotating moment efficiently, the horizontal section of the tail blade 1 is constituted so as to obtain an aerofoil type equipped with a camber.

Description

[Detailed Description of the Invention] [Field of Industrial Application] The present invention relates to a sailing type or a stationary horizontal axis type wind turbine in which the vertical axis of the driving force transmission reservoir is provided at the azimuth rotation center of the horizontal axis type wind turbine. Concerning a direction control tail.

[Conventional technology]

A rotatable vertical shaft (hereinafter referred to as "vertical axis J") for transmitting driving force is provided at the azimuth rotation center of a horizontal axis type wind turbine (hereinafter referred to as [windmill J]), and is driven by a bevel gear from the horizontal axis of the windmill. When transmitting force, within the wind turbine azimuth plane (horizontal plane) centered on the vertical axis,
A moment (hereinafter referred to as "one rotation moment") which is a reaction force of the rotational torque is generated, and as a result, the wind turbine's horizontal axis center line and the wind direction are significantly different from each other, and the wind turbine output is significantly reduced.

Conventionally, wind turbines without a vertical axis do not generate the above rotational moment, so small wind turbines are installed upwind from the center of azimuth rotation, and a flat plate or symmetrical blade cross section is used at the rear end of the fuselage on the leeward side. Heading control tail (hereinafter referred to as 1 tail)
There is no problem in simply installing a wind turbine on the leeward side of the azimuth rotation center and using the restoring force of the wind turbine itself to control the azimuth.

However, in a wind turbine with a vertical axis, in order to obtain a moment that balances the rotational moment, normally in a small wind turbine (a) a tail blade using a flat plate or a symmetric row cross section is set at an angle of attack with respect to the wind direction. It attaches to the rear of the fuselage and generates lift.

(b) A resistance plate is fixed to the tip of a long arm protruding from the side of a wind turbine to generate a drag force.

(c) Use a combination of either a tail with no angle of attack fixed to the rear of the fuselage or the tail described in (a) and the resistance plate described in (b).

Methods using the apparatuses described in (a) to (.1) above can be considered, and there are also methods in which the actual K[i] is used.

[Problem that the invention seeks to solve]

In the case of item (a), the lift of the tail that balances the rotational moment must be 15+ must be set low. If the lift of the tail, which is in balance with the rotational moment, is set close to the maximum lift that the tail can obtain, even a slight increase in the rotational torque of the wind turbine will result in insufficient or negative stability (H), and the tail will not be able to achieve its purpose. Since the maximum value of lift that can be obtained from a tail with a symmetrical or symmetrical chord cross section is small, the lift needed to balance the rotational moment is also small, and therefore the area of the tail must be increased.

(With the device described in item 1, it is possible to balance the rotational moment when it is constant, but it is impossible to provide the stability to correct fluctuations in the rotational moment with slight changes in the azimuth angle. In addition, since the rotation force/toe is balanced by the drag force of the resistance plate, the drag force of the resistance plate is directly added to the drag force acting on the wind turbine device.
If you consider only air resistance in a navigation type wind power utilization device such as 2, when moving against the wind, the sum of the air resistance of each part acts as a drag force, so in order to prevent performance deterioration, it is necessary to reduce air resistance as much as possible. need to be reduced. For these reasons, this system using a resistor plate (c) has a more complex structure than the devices in (a) and (b), and has greater air resistance.

There were nine problems.

[Means to solve the problem]

The present invention has been made to solve the above-mentioned problems, and generates a moment that balances the rotational moment by using a tail blade having a cross section shown in claims 1, 2, and 3. It is an object of the present invention to provide a tail R constituting an azimuth control device that efficiently generates the lift force of the tail fins for the purpose of controlling the vehicle, and eliminates the drawbacks of the azimuth control devices shown in items (a) to (-1) above.

[Effect]

The wind turbine is located north of the azimuth rotation center.1. , a wind turbine device vCj that has a tail on the leeward side and does not have a vertical axis? In this case, if the center of the wind turbine's horizontal axis deviates from the wind direction, the stabilizing moment caused by the lift generated by the tail is made larger than the unstable moment caused by the resistance of the wind turbine itself, and the center of the wind turbine's horizontal axis can be aligned with the wind direction again. Bye. Furthermore, since the moment of instability caused by the resistance of the wind turbine is symmetrical with respect to the wind direction, the moment of stability caused by the lift generated by the tail to cancel out this moment of instability may also be symmetrical. Therefore, in order to satisfy the above condition, the area of the tail fin may be determined by making the horizontal cross section of the tail fin symmetrical.

However, in a wind turbine with a vertical axis, the reaction force of the rotational torque generates a rotation moment that attempts to rotate the wind turbine in one direction within the azimuth plane (horizontal plane). Therefore, in order to balance this rotational moment and generate a moment to keep the horizontal axis of the wind turbine aligned with the wind direction, it is necessary to generate lift on the tail.

In addition, in order to obtain stability, when the wind direction and the horizontal axis of the wind turbine are misaligned, it is necessary to always make the sum of the stable moments larger than the sum of the unstable moments in the wind turbine device. Regarding the rotational moment, since the wind turbine always tries to rotate in one direction, it can be considered as a stable moment on one side and an unstable moment on the other side with the wind direction as the center in the azimuth plane (horizontal plane). Therefore, the sum of the rotating moment and the symmetrical unstable moment due to wind turbine resistance is the sum of the stable moment and the unstable moment on one side, and the sum of the unstable moment and the unstable moment on the other side. , the total moment becomes asymmetrical. Therefore, it is possible to make the stabilizing moment caused by the lift force of the tail wing asymmetrical, so that the sum of the respective moments on the left and right sides becomes the stabilizing moment, and it can be made closer to bilateral symmetry.

The two-strip property of balance and stability is achieved by attaching a tail wing having a cambered cross section shown in claims 1, 2, and 3 to the rear of the fuselage at an angle of attachment. death,
necessary to efficiently generate lift, create a moment that balances the rotational moment, and obtain stability.
This can be achieved by effectively generating an asymmetrical stabilizing moment due to the lift generated by the tail.

〔Example〕

Embodiments of the invention will be described based on the drawings.

FIG. 1 shows a first embodiment of the present invention, and FIG. 1 is a side view of the tail fin 1a, and FIG. The shape and strength of the camber of the cross section 2 and the shape are not limited to those shown in this figure, but are matters to be designed as appropriate.

Fig. 2 shows a second embodiment of the present invention, and Fig. 2) shows a side view of the tail 1b, and Fig. 3) shows an enlarged cross-sectional view taken along the line X-X of the same figure. The strength and weakness of the capper in the side view and cross-section 3, the shape of the capper, and the external shape of the cross-section 3 are not limited to those shown in this figure, but are matters to be designed as appropriate.

FIG. 3 shows an example of the third embodiment of the present invention in which the groove-like gap 5 is located at - location, and IAI in the same figure is a side view of the tail IC, and FIG.
B+ shows an enlarged view of the cross section taken along the line Y-Y in FIG. The side shape of the tail IC, the strength and weakness 2 and shape of the capper in cross section 4,
The outer shape of the cross section 4, the shape of the groove-like gap 5, and the position on the cross section 4 are not limited to those shown in this figure, but are matters that can be designed as appropriate.

Fig. 4 shows an example of the third embodiment of the present invention in which the groove-like gaps 7.8 are provided at two locations. A cross section taken along the Z-Z line is shown.

The side shape of the tail 1d, the strength and shape of the capper on the cross section 6, the outer shape of the cross section 6, the shape P of the groove-like gaps 7 and 8, and the position on the cross section 6 are not limited to this figure and can be designed as appropriate. This is an important matter.

Even in the case where there are two or more groove-like gaps, the shape of each gap and the position on the cross section are matters to be appropriately designed as in the above example.

FIG. 5 is a partially cutaway 11111 side view for explaining the operating principle of the present invention, and FIG. 5 is a plan view for explaining the operating principle.

On board the ship 1, the fuselage 11 has a rotary shaft 12 to which a wind turbine 10 is fixedly attached to the top i14 of the support pillar 9, which is vertically installed on a foundation on the ground, so that it can rotate in the azimuth plane (horizontal plane). The tail 1 is attached to the rear end (leeward side) of this fuselage 11 at an installation angle θ.
Attach and fix. The bevel gear 13 is still fixed to the rotating shaft 12, and the bevel gear 14 meshing with the bevel gear 13 is fixed to the vertical shaft 15. If, lf (the tooth ratio of the wheel 13 and the bevel gear 14, and the mutual angle between the rotating shaft 12 and the vertical shaft 15 are matters to be appropriately designed.

When the wind hits the windmill 10 and rotates in the downward direction of the arrow, the vertical direction 11 (
1 + l A rotation force that attempts to rotate the fuselage 11 in the azimuth plane (horizontal plane) as a reaction force of the rotational torque of 5)
QR will be generated. 1. Center of vertical axis 15 (azimuth rotation center)
Let the distance ei be from to the center of the windmill 10, and similarly the vertical axis 1
5 to the wind pressure center of the tail 1 is defined as the distance e2. The angle between the wind direction and the extension of the center of the rotating shaft 12 in the azimuth plane (horizontal plane) is defined as angle β. Therefore, the angle of attack α of the tail with respect to the wind is α=θ−! in the right quadrant facing the wind.
Similarly, in the left quadrant, α-θ+β, and in the case of β-0°, α=θ.

When the wind hits the tail 1 at an angle of attack α, a wind pressure R is generated,
The wind force R can be decomposed into a lift force perpendicular to the extension line of the rotation @II I 2 center and a force parallel to it. Further, the wind force R can be decomposed into a drag force parallel to the wind and a force perpendicular to the wind. However, in the case of //-0°, the wind pressure R can be simultaneously decomposed into lift force and drag force, and in the case of β-90°, lift force and drag force are the same.

The seventh concave is the cross section of the tail plane of each embodiment of this invention.The angle of attack α and lift system of the 9τζ type as a reference? FIG. 2 is a general diagram showing the relationship between 2CLs. Cross section 2 is a cross section of the first embodiment, and curve 2C is a curve showing the relationship between angle of attack α and lift 1 series CL in the first actual #iI'll. Similarly, the second example is shown by cross section 3 and curve 3C, and the third leprosy example is shown by cross section 4 and curve 4C as a representative. Cross section Xs and curve, fi! XC is the first. Second. 3rd row cross section 3, 4 and curve 2c
, 3c, and 4C have a slightly symmetrical feel, and are listed together for reference.

The lift force L (kq) of the tail 1 is proportional to the lift coefficient CL of the cross section, L=CL l/2 f V2 A...
...The relationship is expressed by the formula ill. However, l... air density (k
q-82/m”!V... Wind speed hitting the tail (m/s)
A: Indicates the tail area (m゛).

FIG. 8 is a general azimuth restoration stability curve diagram of a wind turbine device using the tail of the present invention. The central horizontal line indicates stability, neutral positive (N), above this line indicates stability, E (+), and below this line indicates stability, negative (-).

The vertical line indicates angle I, and the central vertical line indicates angle β of 0°, right IU.
The vertical line No. 11 indicates that the angle β is 90 degrees (right), and the left vertical line indicates that the angle β is 90 degrees (left). Mometsu) MW is the wind is a windmill 10
The curve shows the moment about the azimuth rotation center that is generated due to the drag force pushing the tail 1 to the leeward side. Shown as a curve. Moment QR is
The rotational moment generated in the azimuth plane (horizontal plane) as a reaction force of the rotational torque of the vertical axis 15 is shown by a curve, and the moment M
A shows the sum of the above-mentioned MW, Ms, and QR as a curve. However, the stability of the fuselage Il itself, excluding the wind turbine lO and tail fin 1, is weakly positive (±) in this invention, but since the influence is small, it is set as neutral (N) to be on the safe side, and is omitted in Figure 8. be.

Next, we will discuss the azimuth balance of the wind turbine system.

Explaining the principle of operation shown in Figures 5 and 6,
When the wind hits the windmill 10 and causes it to rotate, the rotation is transmitted to the rotating shaft 12, bevel gear I3, bevel gear 14, and vertical shaft 15 in this order. When the windmill 10 rotates in the direction of the arrow T', a moment QR in the direction of the arrow is generated as a reaction force of the rotational torque, which attempts to rotate the body 11 within the direction 1fi (horizontal plane). This Mometsu) QR is the reaction force of the rotational torque of the vertical axis 1b, so
Its value changes depending on the tooth force ratio of the small bevel teeth 13.147,
When the number of teeth of the bevel gear 13 is N1, the number of teeth of the bevel gear 14 is N2, and the wind turbine rotation torque is Qw, Q R = N 2 / N + Q W −
The set becomes (2). The wind turbine rotation torque Qw has an angle β of 00
It reaches its maximum at the position of , and when it approaches 90° and the rotation of the windmill stops, the curve changes to O, and also changes sharply (relative to rotational moment QRtd + tank rotational torque Qw). (Check formula (2)) If the drag force pushing the wind turbine 10 toward the wind F side is Dw, then the drag force Dw
changes in a t-shaped curve where the angle β becomes maximum at 00 and minimum at 90'', and this drag force Dw moves the wind turbine 10 in the azimuth plane (
A moment is generated that tries to rotate it to the leeward side in the horizontal plane). If the moment is Mw, hl w = D w sm βe+
``''''Equation 13) When the wind hits the tail 1 at an angle of attack Cχ, the moment that tries to rotate the fuselage 11 in the azimuth plane (horizontal plane) is generated due to the lift force, which is a component of the 1st thrust force R. occurs.If the moment is Ms, then M s = L (12-Kawaichi set (4) If the angle β is 00, according to equation (3), MW becomes 0, so the angle β maintains the state of 0°. In order to do so, the rotational moment QR due to the torque reaction force of the vertical axis 15 and the moment Ms due to the tail 1 must match approximately 9.Also, in order to maintain stability when the wind turbine torque Qw increases without changing the wind speed. As mentioned earlier, the lift force of the tail 1 at the point of equilibrium between the rotational moment QR and the moment Ms must be set sufficiently lower than the lift force at the stall point, which is its maximum value. Therefore, as shown in equation 1), the lift force is !3'lJ compared to the lift coefficient CL, so the tail 1 at the point of balance between the rotational moment QR and the IVI s is It is sufficient to set the lift coefficient CL to be sufficiently lower than its maximum value.

However, if the lift coefficient CL of the tail 1 at the balance point 2 cannot be set low, the lift 1 series coefficient CL can be set low by increasing the area of the array 1.

If the attachment angle θ of the tail 1 is, the lift factor at the balance point in FIG. 7 is t! Let the angle of attack α corresponding to JcLK be the mounting angle θ.

As a result, the angle β00 is maintained, the wind turbine generates power in a balanced state while directly facing the wind, and operates normally. Numerical determination of the lift coefficient CL at the balance point is a matter of appropriate design.

The above explanation is given in Sections 1 and 2. This is applied to each of the third embodiments, but in particular, the cross section 4 of the tail IC of the third body 1 @ 1 da, which is represented in FIG. Compared to cross section 2 and cross section 3 of the tail 1b of the second embodiment 1111 shown in FIG.
3. The maximum value of CL is large. Therefore, the rotational moment Q
The lift coefficient aCL at the point of balance between R and moment MS can be set larger than in the first and second embodiments. However, since the required lifting force is the same as in the twelfth and second embodiments, the rotational moment QR and the moment MS
Tail 1 at a ratio that sets the lift coefficient CL at the equilibrium point to a large value.
The area of 1 l (can be reduced. (Equation (1)
Also, since the required moment Ms is the same as in the twelfth and second embodiments, the distance e2 can be reduced without reducing the area of the tail 2X I C.
It is also possible to shorten the fuselage 11 by shortening the length. (formula(
(See 4)) Among the third embodiment shown in FIG. 4, regarding the tail 1d having two groove-like gaps 7 and 8 as shown in cross-section 6, and also regarding the case where there are two or more groove-like gaps. Also, the third
Since it has similar characteristics to the tail IC of the embodiment, the same method can be applied to it.

Next, we will discuss the stability of the wind turbine system.

To explain with reference to the operating principle diagrams shown in Figures 5 and 6 and the azimuth restoration stability curve diagram of the wind turbine device shown in Figure 8, the rear part of the fuselage 11 is in the left quadrant with the line where angle β is 00 as the center. In this case, since the rotational moment QR is in one direction clockwise, the stability is negative (
-), and when it is in the right quadrant, the angle β tends to approach 0°, so it can be considered that the stability is positive (+). This is the illustration. Since the wind turbine is located on the windward side from the azimuth rotation center, Mw rotates directly to the leeward side when the angle β swings to the left or right from the line indicating 0°. Therefore, the state in which the stability is negative (-) is illustrated by a curve in FIG. 8 as a moment MW.

The tail 1 is located on the leeward side of the azimuth rotation center, so it has weathervane stability. However, since the tail fin 1 is fixed to the fuselage II at an attachment angle θ, the mono/) M s due to the tail fin 1 is 0
The angle β at which the lifting force of the Nardame becomes O is the angle /no of 0.
0 is an angle shifted from the indicator line by the mounting angle θ to the right quadrant. Therefore, the moment MS has positive stability in the left quadrant (
+). However, in the right quadrant, when the angle β is between 0° and θ (the attachment angle of the tail 1), the moment MS that causes the rear part of the fuselage 11 to move away from the line where the angle β is 0' is This is caused by the lifting force of Therefore, during this period, the stability of Mono/l-MS can be considered negative (-). When the angle β becomes thicker than the above θ, the tail 1
The direction of the lift force is reversed and becomes a negative (-) lift force, but in this case, the negative (-) lift force decreases the angle /3 and returns to the angle β where the lift force becomes O. Let it come to life. Therefore, the stability of moment MS in this case is positive (+).

As explained above, the angle β of Mometsu 1-Ms is 0°
Stability is positive (+) in the left quadrant centered on the line indicating
), and when the angle β becomes larger than θ, the stability becomes positive (+
) is illustrated in FIG. 8 as a curved moment Ms.

In order for the wind turbine device to have stability, the rotational torque
The value of the total moment MA, which is a total of 6 moments (moment (Mw) caused by the drag force Dw of the wind turbine 10, Ms (moment caused by the lift force generated by the tail 1), is such that the angle β, which is the equilibrium point, is 0.
It must be set so that it is always positive (+) and has an appropriate size, except for the state where it becomes 0 on the line indicating 0. The mono/to MA shown by the curve in FIG. 8 is a combination of the results explained above.

In this way, the stability of the wind turbine device is always positive (+),
In order to have an appropriate thickness formula, the characteristics of the cross section of the tail wing 1, area A,
Mounting angle θ and distance e1. (If 12 etc. is determined for a wind turbine 100 thick and its characteristics, the direction control of this wind turbine device can be carried out reliably and the purpose can be achieved. Selection of cross-sectional characteristics of the tail 1, area A, installation angle θ, still distance e,.

Determining the value of e2 is a matter of appropriate design.

An increase or decrease in the wind turbine rotation torque Qw due to a change in the blade pinch of the wind turbine 10 or a change in load conditions, etc.
If the stability of d is positive (+), the tail 1 is tilted to the left or right with respect to the wind direction, and the angle of attack α is fully automatically adjusted; JAI is adjusted, and the moment Ms is is increased or decreased, and equilibrium is reached at the point where the sum of the moments Mw, QR, and Ms becomes 0, and the angle I deviates from 0° by the angle by which the angle of attack α is automatically adjusted, and the wind turbine 10 continues to operate.

1. If the torque required by the load does not change even if the wind speed changes, and the stability of the wind turbine is positive (+), the increase or decrease in the lift of the tail 1 due to the change in wind speed will be due to the change in the tail 1 The angle α is automatically adjusted to suppress the increase or decrease in lift force, and each moment QR.

Balance is reached at the point where the sum of Ms and Mw becomes 0, and the angle β deviates from 0° by the angle by which the angle of attack α has been automatically adjusted, and the wind turbine 10 continues to operate. This result is the same as the operation of the tail 1 due to an increase or decrease in the wind turbine rotational torque Qw. A slight increase or decrease in the angle β has almost no effect on the performance of the wind turbine 10 and poses no practical problem, so the rate of increase in the moment MS should be considered so that the increase or decrease in the angle β does not become large.

Even if the angle β temporarily deviates from 0° due to an increase or decrease in the wind turbine rotation torque Qw due to a temporary change in wind direction or wind speed, as long as the stability is positive (+), the wind direction is fixed and the wind speed returns to the original angle β. returns to Oo and the wind turbine 10 continues to operate normally, so there is no problem.

Furthermore, it is easy to incorporate into the present invention the conventionally known measures for preventing destruction of the wind turbine device due to the wind turbine gyro effect that occurs when the wind direction suddenly changes.

In the present invention, the type of wind turbine 10 has been explained using an up-wind propeller type as an example, but it can also be applied to a down-wind propeller type and other types of horizontal axis wind turbines that require azimuth control. can.

〔Effect of the invention〕

By using the tail gla, Ib, lc, Id, etc. of the present invention, it is possible to efficiently generate the lift force required by the wind turbine device, and effectively generate the mono/) Ms needed to obtain stability. - It is possible to provide an azimuth control device with a simple structure and good stability, which has less deflection drag than the conventional azimuth 11jll l111 device used for a horizontal ill-type wind turbine with INl 15.

Furthermore, compared to the tail fin 1a of the first embodiment, the tail fin 1b of the second row can be made smaller, and the tail fin 1b of the third embodiment can be made smaller.
c, Id can be significantly downsized. size body 1
It is also possible to reduce the size of the azimuth control device by shortening 1.

Also, the azimuth side using tail gla, Ib, lc, Id, etc.
The use of a horizontal + l (1+ type wind east) with a vertical axis 15 and rIjH power source is a navigation type wind power system such as a wind 1V ship J that advances by a screw as a power source. When operating the device, there is less air resistance than when using a conventional azimuth control device, so performance can be improved, especially when traveling against the wind.

[Brief explanation of drawings]

Fig. 1 is a view of the tail plane showing the first embodiment of the present invention, Fig. (5) is a side view, Fig. (I3) is an enlarged cross-sectional view taken along line W-W of Fig. Figure 8) is a side view, Figure (13) is an enlarged cross-sectional view taken along the line X-X of the second embodiment of the invention, and Figure 3 is a view of the third embodiment of the invention. FIG. 4 is a diagram of a tail plane showing an example of a groove-like gap in - places, and FIG. 4 is a side view, FIG. Figure (At is a side view, Figure (Bl is a figure (
FIG. 5 is an enlarged Z-X cross-sectional view of AI, and FIG. 5 is a partially cutaway side view for explaining the operating principle of this invention. FIG. 6 is a plan view for explaining the operating principle of this invention. Fig. 7 shows a general lift coefficient/angle of attack curve diagram of the tail Z cross section of each embodiment of the present invention and a reference variant, and Fig. 8 shows a general diagram of a wind type device using the tail 9 of the present invention. FIG.

Claims (1)

[Scope of Claims] 1. An azimuth control tail blade for a horizontal axis type wind turbine, characterized in that the horizontal cross section consists of a cambered plate cross section. 2. The azimuth control tail blade for a horizontal axis wind turbine according to claim 1, wherein the horizontal cross section is formed of a cambered airfoil or a cross section similar to a cambered airfoil. 3. The horizontal cross section is characterized in that a cambered airfoil or a cross section similar to a cambered airfoil is provided with one or more slots. A tail blade for controlling the direction of a horizontal axis wind turbine.