TWM404278U - Structure of blade for wind power generation device - Google Patents

Description

M404278

Especially an application 5. New description: [New technical field] This case is about the airfoil structure of the wind turbine. [Prior Art]

Wind turbines, mainly by the kinetic energy of the natural wind speed of the gas, that is, the wind blows the wind blades, the wind full wheel)', through the fins, converts the wind kinetic energy into the rotating force, and then turns the generator to generate electricity#. The wing structure of the general wind power generation equipment is the reverse operation of the air supply equipment for self-study. Although it seems to be different from the air kinetic energy (4), the difference is actually large. The purpose of the air supply equipment is to generate air kinetic energy, and the wing structure of the wind power generation equipment is It is subjected to air kinetic energy and converts air kinetic energy into mechanical energy and electric energy output. Therefore, if the propeller of the air supply device is simply installed on the wind power generation and the rotor, the efficiency is inferior to that of the spiral purple device as the air supply device. Therefore, it is not possible to simply use the spiral music of the air supply equipment on the wind power generator. 'There is a need to re-set the phase for wind power generation. 爰The reason is that the applicant has created the application of the case due to the lack of the prior art. The airfoil aerodynamic structure of the small wind turbine is used to improve the lack of the above-mentioned conventional means. [New content] The purpose of the new model is to more effectively apply the kinetic energy of natural wind speed, that is, the airfoil drives the generator effectively. The conversion of gas kinetic energy into electrical energy can be performed on a rotating wing of a 200W~400W horizontal wind turbine. To achieve the above objectives, 'this creation provides a wing structure for a wind-powered 3 M4U4278 motor, including your hatred 4 10ϋ26 θ including a wing root 'located at the 螭-wing tip of the wing structure, located at the back μ , the other end of the fin structure; and a windward surface between the wing root and the wing tip and having an upwind angle wherein the angle of the welcome angle is gradually increased from the root of the wing to the tip of the wing And the airfoil of the wing root and most of the wing are both the airfoil S 8 3 1 of the National Renewable Energy Research Laboratory (NREL), and the fin structure is as described above, wherein the increase of the windward angle is a parabolic curve. Variation 〇 - a fin structure as described above, wherein the chord length of the wing root is greater than the chord length of the wing tip. The fin structure as described above, wherein the wing tip has a windward angle greater than the windward direction of the wing root Angle 17 degrees to 23 degrees. The fin structure as described above, wherein the fin structure has an effective span and the chord length of the It wing root is between one quarter and a fifth of the effective span. A fin structure as described above, wherein the chord length of the wing tip is The chord length of the wing root # is between eight and one-seventh. · The wing structure as described above, wherein the wing root further forms a joint. The wing structure further includes a leeward surface. The actual area of the leeward surface is greater than the actual area of the windward surface. The fin as described above, wherein the chord length of the wing tip portion and the reduction amount of the wing root portion are parabolically changed. a fan blade, wherein the blade has a wing leading edge and a wing trailing edge and each of the projected shapes on the plane of rotation is substantially parabolic, Μ4Ό4278 and the parabolic equation y = ax3 + bx2+cx + d, and χ represents The chord length is the amount of change, and y is the amount of change in the span direction. For the leading edge of the wing, the preferred value is: a=3E-07 ' b = -0.0004,c=〇.2;215 d = -47.824; as for the trailing edge of the wing, the preferred values for each coefficient are: a = -6E-07, b = 0,0009, c = -〇_5〇31, d=110.72. [Embodiment] * The following is a description of a preferred embodiment of the fin structure applied to the wind power generator of the present invention, please refer to the accompanying drawings, but the actual configuration and the adopted method are not necessarily completely in accordance with the description. The content, those skilled in the art can make various changes and modifications without departing from the actual spirit and scope of the case. Please refer to FIG. 1 , which is a schematic diagram of the arrangement of the wing structure of the present invention. It is disclosed that a wind rotor 1' includes a fairing 10, and a fin 2 is disposed on the fairing 1 through a connecting portion 20, generally in order to achieve a full-flow effect. The connecting portion 2 is buried in the fairing 10. Inside. Fig. 1 is a view showing the relative position and connection relationship of the wing Φ piece 2 and the fairing 10, whether the wing tip or the wing root of the airfoil 2 has a similar relative position and connection relationship. The flap 2 has a string 2'. It can be seen from Fig. 1 that the string 2' is rotated counterclockwise from the plane of rotation PR. Thus, when the wind is blown toward the flap 2 by the axial wind AW, the flap 2 is The rotation axis RA is rotated in the direction of the upper side of the drawing of FIG. 1, so that the airfoil 2 can be divided into a wing leading edge 21, a wing trailing edge 22, a windward surface 23, and a leeward surface 24. Furthermore, the windward surface 23 is closer to the string 2, and the leeward side 24 is further away from the string 2'. Therefore, the entire arc surface area of the leeward surface 24 is larger than the windward surface 23. 5 / 6 Years and Months Please refer to Figure 2 for the wings of this creation. It can be seen that the wing root portion 2a" is coupled with the connecting portion 2". If viewed from the right, the fin 2 can be seen to extend from the g-shaped root portion 2a to the wing tip 2b". In Fig. 2, the leading edge 21 and the trailing edge of the wing can be seen. The position of 22, the airfoil of the system shows the airfoil of the case, and the change of the size ratio of the different positions of the different positions on the different moons in the different months. In order to effectively make the wind blades at different wind speeds and The speed reaches the best power generation benefit, and the wing root 胄 &, has a longer length and gives the wing 2b a steeper and slower parabolic curve to shorten the chord length.

Please refer to Figure 3 for a stand-up view of another perspective of the created wing. Its "see wing root 2a" is connected with the connecting portion 2A. If viewed from the left and right in Fig. 3, it can be seen that the flap 2 extends from the wing tip 2b" to the wing root 2a, and can be seen in Fig. 3 The edge 21, the position of the trailing edge 22 of the wing on the flap 2. In addition, it can be seen that the wing 2 of the present case is at the wing tip 2b, and the inclination angle of the portion is also small, and the inclination angle of the hinge is closer to the root portion 2a". In Fig. 3, the chord length of the wing 2 is determined by the wing.

The tip 2b" to the wing root 2a is a parabolic curve that increases the chord length first and then sharply. See Figure 4 for the wing plan of the wing of the creation. Figure 4 can be said to be the windward side. Or a flat circle of the leeward surface, wherein the wing root 2&, is connected to the connecting portion 20, if the visible wing from the left and right sides of Fig. 4 extends from the wing root 2a to the wing tip 2b, The position of the trailing edge 22 of the wing leading edge 2 on the airfoil 2 can be seen in Fig. 4. And the shortening variation of the chord length from the soil root portion 2a" to the wing tip portion 2b can be clearly seen in Fig. 4 The first step is slow, that is, the amount of shortening near the wing root 2a" is larger, and close to the wing tip M404278

2b, the shortening of the chord length is small. ::. V ---^-—_«— 4 See Fig. 5' for the wing tip orientation view of the created flap. The airfoil drawn by the dotted line shows the change of the size ratio of the airfoil in the different positions of the airfoil 2 due to the change of the chord length. In Figure 5, it can be seen that the change of the chord length of the airfoil 2 is The wing root 2a" to the wing tip 2b" gradually becomes smaller, and the inclination of the flap 2 is seen to change in FIG. 5, and in FIG. 5, the leading edge 21 and the trailing edge 22 of the wing are visible in the flap 2 The location on the top. And in the wing

After the root ° 2a, a connecting portion 2 is recognized. In addition, the airfoil used in this case is the National Renewable Energy Research Laboratory (Nati〇naI Renewab丨e Energy).

The airfoil S831 of Lab〇ratory, NREL) is used as the airfoil of the entire fin 2. Figure 6 is another wing plan view of the flap of the present invention. Figure 6 can be said to be a plan view of the flap 2 as viewed from the leading edge 21 or the trailing edge 22 of the wing. Here, it can be seen that the wing root portion 2a" is coupled to the connecting portion 2A. As seen from the left side of Fig. 6, the flap 2 is seen to extend from the wing root portion 2a to the wing tip 2b". Since the airfoil 2, whether it is the windward surface 23 (please match the figure 1) or the leeward surface 24 (please cooperate with FIG. 1), is a convex curved surface, so the figure 6 cannot be clearly distinguished by the wing edge 21 or the 疋The trailing edge 22 of the wing, although it can be confirmed that the upper portion of the airfoil 2 generally belongs to the windward surface 23, and the lower portion substantially belongs to the leeward surface 24. The figure is a schematic diagram of the change of the inclination angle of the string of the created wing. 2b" has a tip angle change dA at 17 degrees

The wing root 2a" has a wing root string 2a, a string 2b' with an angle between dA and 23 degrees between the two, that is, when used, the g-tip is larger than the wing root. 2a" wind angle, and the difference between the two is between 17 degrees and 23 degrees. 7 M404278 Correction Please refer to Figure 8. Another month of the flap of the creation is shown in Fig. 8. The projection of the flap 2 is projected onto the plane of rotation (9) (please match the appearance of the sputum 7 and the spanwise direction is 8 The longitudinal direction, but: the horizontal direction is shown in Fig. 0. The wing tip portion 2b" is located near the upper position of Fig. 8 and is round 8

It is located near the lower position of FIG. The wing leading edge 21 and the portion V are located at the wing root portion 2a, and the wing tip portion 2b, the edge 22 is moving the sheep, and the pp L g wing edge 21 is projected on the rotation to be substantially a parabolic y=ax3+ Bx2+cx+d, and 乂 represents the 6 ° variation of the horizontal 6 square of the string county, which is the lateral direction of Figure 8, and y represents the weight of the spanwise direction, that is, the longitudinal direction of the circle 8. The preferred value of each coefficient is... ^ 07 * b = -0.0004 , c = 0.2215, d = _47, 824. The projection of the trailing edge 22 of the wing is substantially a parabola presented on the plane of rotation n, the equation is ..., and X represents the amount of change in the direction of the chord length, ie the lateral direction of the circle 8, and y represents the change in spanwise direction. The amount, that is, the longitudinal direction of FIG. The preferred values for each coefficient are: a = -6E-07, b = 0. 〇〇〇 9, 〇 = , d = ll 〇 72. Please see! 9, a front view of the wind rotor of the creation. The wind rotor i includes three fins 2 which are disposed on the fairing 1G through respective connecting portions 2'. The viewing direction of the front side of the wind rotor i is parallel to the rotating shaft RA (please refer to the figure υ, and the fin 2 rotates with the rotating shaft Ra as an axis, and naturally forms a rotating plane PR, and FIG. 8 and the wing thereof are illustrated The front/rear edge projection is projected onto this plane of rotation p R. In summary, the "wing structure applied to small wind turbines" of this creation is obtained through computational fluid dynamics and continuous calculation and simulation. Two conclusions, one is that the windward angle of the airfoil is closer to the wing tip when the angle is M404278^t. ►. The second is the near the root of the wing, 100. 1. 2 R chord length and near The chord length of the tip is different. Usually, the chord of the wing root is stalked. The blade culvert is longer and leads to a thicker thickness; while the chord of the wing tip is shorter and leads to a thinner thickness. In addition, the shape of the fin on the plane of rotation shows that the pattern of the leading edge of the wing and the trailing edge of the wing is substantially parabolic. In short, the variation of the chord length is from the wing. The root to the tip of the wing is tapered like a parabola. The reason for the windward angle at the root of the wing and the tip of the wing The shape of the airfoil chords must be changed because the wind speed of the two is different from the airflow of the airfoil in the application of the wind flaps. Therefore, the air kinetic energy can only be achieved through the concept of the original climbing. The above embodiments are merely exemplified for convenience of explanation, and those skilled in the art can modify them as they wish, but they are not intended to be protected as claimed. Brief description of the figure] Fig. 1 is a schematic view showing the arrangement of the wing structure of the present invention; Fig. 2 is a perspective view of one of the angles of the created wing piece; #Fig. 3, a perspective view of another perspective view of the created wing piece Figure 4 is a wing plan view of the wing of the present invention; Figure 5 is a wing-tip view of the wing of the present invention; Figure 6, is another wing plan view of the wing of the present invention; Figure 7, A schematic diagram of the variation of the inclination of the string of the created wing; Figure 8 is another wing plan view of the wing of the creation; and Figure 9 is a front view of the wind rotor of the present invention. [Main component symbol description] 1 : Wind Wing 9 Έ404278 ίο : 2 : j 20 : 21 : 22 : 23 : 24 : 2a,: 2a” 2b, 2b,, AW PR : RA dA : fairing I piece connecting wing leading edge wing trailing edge windward leeward : Wing root string: Wing root: Wing tip string: Wing tip: Axial wind direction Rotating plane: Shaft: Angle

10

Claims (1)

M404278 Supplementary amendment application date: 100 years March 8 曰 _ 6, the scope of the patent: ΐ · A wing structure applied to wind turbines, including: I ~, ~ ... There are: fixed j a wing root, located in One end of the fin structure; a wing tip located at the other end of the fin structure; and a windward face between the wing root and the wing tip and having an upwind angle H from the wing The root to the tip of the wing is larger than the yarn, and the airfoil of the wing root and the wing tip are both national renewable energy research: Room (NREL) airfoil S83 1. 9. The fin structure of claim 1, wherein the fin structure has a parabolic variation. For example, if the patent application range is a ° °, the parabolic curve with the leading edge of the wing and the leading edge of the wing projected on a plane of rotation is y=ax3 + bx2 + cx + d, % χ Indicates the amount of change in the direction of the chord length, and y represents the amount of change in the span direction. 4. The fin structure as described in claim 3, wherein a = 3E - 〇 7, b = - 〇. 〇〇〇 4, c = 〇.2215, d = -47.824. The fin structure according to claim 2, wherein the fin, the trailing edge of the wing, and the trailing edge of the wing projected on a plane of rotation is y=axW+cx+d' It also indicates the amount of change in the direction of the chord length, and y represents the amount of change in the span direction. • If the wing piece is as described in item 5 of the patent application, ^ ^ a = 兵 兵 兵 , , 07 07 07 07 07 07 07 07 07 07 07 07 07 07 07 07 07 07 07 07 07 07 07 07 07 07 07 07 07 07 07 07 07 07 07 07 L. The fin structure of claim 1, wherein the wing root σ chord length is greater than the chord length of the wing tip. 11 ϋ 404278 Supplementary Amendment Application Date: March 3, 100. 8. For the wing structure described in the scope of patent application, the windward angle of the part is greater than the windward angle of the wing root from 17 degrees to 23 degrees. The fin structure described in claim 1 has an effective span, and the chord length of the wing root is between one and one fifth of the effective wing. 10. The wing structure of claim 1, wherein the chord length of the wing is from one eighth to one seventh of the chord length of the wing root. The wing of claim 1 is as claimed in claim 1. The sheet structure has a connecting portion formed therein. 12. The wing structure as described in claim 1 of the patent scope, the wind surface 'where the actual area of the leeward surface is greater than the windward surface ^ [W ^ ^ of the wing tip in the wing tip of the wing exhibition In the tip of the wing - between. The wing root includes a back f area. 12