M378284 五、新型說明： 【新型所屬之技術領域】 本案係關於翼片氣動力外型結構，尤指一種應用於風 力發電機的翼片結構。 【先前技術】 風力發電機’主要藉由氣體自然風速的動能，即風吹 動翼片（風力葉片、風力渦輪），透過翼片使風力動能轉換 -成旋轉的力量’進而轉動發電機以產生電能。一般風力發 電設備的翼片結構是自習用的送風設備逆向運用，雖然看 似都與空氣動能有關，實際上差異甚大，送風設備之目的 在於產生空氣動能，而風力發電設備的翼片結構則是承受 空氣動能並將空氣動能轉換為機械能及電能輸出，因此若 僅是簡單的將送風設備的螺旋槳（propeller)裝在風力發電 機的轉子上則效率比不上該螺旋槳作為送風設備時的效 率。故不能單純的將送風設備的螺旋槳轉用在風力發電機 φ 上，需要重新的設計以針對風力發電的情形。 爰是之故，申請人有鑑於習知技術之缺失，創作出本 案「應用於風力發電機的翼片a動力夕卜型結構」，肖以改善 上述習用手段之缺失。 【新型内容】 本新型之目的在於更 透過翼片帶動發電機有效 為了達到上述之目的 風力發電機的翼片結構， 有效的應用自然風速的動能，即 的將氣體動能轉換為電能。 ’本創作提供一種應用於水平式 包括一翼根部，具有一第一翼型 3 M378284 並位於該翼片結構的一端；一翼尖部且 位於該翼片結構的另—端；以及一缝—第二翼型並 自該翼根部延伸至該翼尖部其中翼後緣均 異月翼根部到置尘邱古 一扭角，該翼前緣自該翼根部至該翼尖部為逐 該翼後緣則自該翼根部至該翼尖部為逐漸；降漸上揚，而 如前所述的翼片結構，其中該翼前緣是呈直線上揚、 而該翼後緣則是直線下降。 深上揚 翼型更具有一第一 且該第一弦長大於 如前所述的翼片結構，其中該第 弦長’而該第二翼型具有一第二弦長 該第二弦長。 如前所述的翼片結構，其中該翼片結構具有一有效翼 展，而該第一弦長為該有效翼展的五分之一。 如前所述的翼片結構，其中該第二弦長為該第一弦長 的十六分之九。 如前所述的翼片結構，其中該翼根部更形成一轉軸部。 如前所述的翼片結構，其中該翼尖部更形成一整流部。 為了達到上述之目的，本創作又提供一種應用於風力 發電機的翼片結構’包括一翼根部，具有一第一翼型並位 於該翼片結構的一端；以及一翼尖部，具有一第二翼型並 位於該翼片結構的另一端，其中，該第二翼型的迎風角大 於該第一翼型的迎風角20。。 如上述的翼片結構，更包括一迎風面與一背風面，其 中为風面的實際面積大於該迎風面的實際面積。 為了達到上述之目的’本創作再提供一種應用於風力 發電機的翼片結構，包括一翼根部，具有一第—翼型並位 於該翼片結構的一#;以及一翼尖部，具有一第二翼型並 位於該翼片結構的另一端’丨中，自該翼尖部沿翼展方向 視向該翼根部，該翼片結構呈順時針扭轉狀。 如前所述的各式翼片結構，其中該第一翼型是美國國 家再f能源研究室（NREL)的翼型S831，而該第二翼型是美 國國豕再生此源研究室（NREL)的翼型§832。 【實施方式】 以下針對本案之應用於風力發電機的翼片結構的較佳 實施例進行描it ’請參考附圖，但實際之配置及所採行的 方法並不必須完全符合所描述的内容，熟習本技藝者當能 在不脫離本案之實際精神及^圍的情況下，做^種= 請參閱圖1，為本創作的翼片結構的設置示意圖。其 中揭不一風力旋翼i，包括一整流罩1〇，以及一翼片2透 過-轉軸部20極接在該整流罩…圖丨是揭*翼片：靠 近整机罩1 〇的αρ矢，也就是翼根部’因此翼根部的翼剖面 是第翼型2a，具有一第一弦線2a，，由圖1可見第一 弦線2a’是自轉動平面叹逆時針轉一角度，因此當風來以 轴向風向AW吹向翼片2時，翼片2是以轉^RA為轴向 圖面上方方向轉動，故而翼片2可分為翼前緣Μ、翼後緣 22'迎風面23、與背風面24。此外，迎風面门距離第一 弦線2a，較近而背風面24距離第一弦線2a，較遠，因此背風 面24的整個弧面面積是大於迎風面23的。 請參閱圖2,為本創作的翼片的平面圖。由於迎風面 /、#風面24僅有曲率的不同，故而圖2的平面圖均可 ，為迎風面23或背風面24的平面圖。又，圖2揭露翼根 部2a”的第一弦線2a，以及翼尖部“，，的第二弦線儿，，翼根 彳與翼大部分據翼# 2的兩端，以圖2的圖面而言即翼片 的左右兩端為了使翼尖部附近的氣流流暢，更在翼尖 邛。又置一整流部20’ ’同理為了氣流流暢，在翼根部與轉軸 邛20之間亦具有一轉換結構25 ^至於翼後緣22與翼前緣 21均是位於翼根部2a，，與翼尖部2b，，之間。 清參閱圖3’為本創作翼片結構的立體圖。其中轉輪 部20連接到翼根部2a，，而整個翼片2則延伸到翼尖部孔”， 而被風面24位於上表面。同時透過第一弦線2&，與第二弦 線2b可以看到兩者並不平行且第二弦線2b，在圖$上顯 示是更為平坦的，因此如自翼根部2a，，望向翼尖部2b，，可見 翼片2是自翼根部2a，，以順時針方向逐漸扭轉，意即翼前緣 21是呈上升狀而翼後緣22則是呈下降狀。 清參閱圖4 ’為本創作翼片結構的翼根部翼剖面圖。 其中翼根部2a”的翼型為第一翼型2a，而其具有的第—弦 線2a即是自翼前緣2丨至翼後緣的直線，而背風面μ 大致上呈現一圓弧凸起且距離第一弦線2a，較遠，至於迎風 面23距離第一弦線2a’較近且較背風面24更為平坦，此外 迎風面23僅略為凸起而在接近翼後緣22則向内凹並跨過 第一弦線2a’而與背風面24同側，之後迎風面23才與背風 面24父會於翼後緣22。本創作較佳實施例則是以美國國 M378284 - 家再生能源研究室（National p ^ ^ ^National Renewable EnergyM378284 V. New description: [New technical field] This case is about the aerodynamic external structure of the airfoil, especially the wing structure applied to the wind power generator. [Prior Art] Wind turbines mainly use the kinetic energy of the natural wind speed of the gas, that is, the wind blows the fins (wind blades, wind turbines), and the wind kinetic energy is converted into the rotating force through the fins to turn the generator to generate electric energy. . 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 related to the air kinetic energy, the difference is actually very 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 Withstand the kinetic energy of the air and convert the kinetic energy of the air into mechanical energy and electrical energy output. Therefore, if the propeller of the air supply device is simply mounted on the rotor of the wind power generator, the efficiency is inferior to that of the propeller as the air supply device. . Therefore, it is not possible to simply use the propeller of the air supply device on the wind turbine φ, and it is necessary to redesign it to target the wind power generation. For this reason, the applicant has created the "Flat-A-Power Structure for Wind Turbines" in view of the lack of the prior art, and Xiao has improved the lack of the above-mentioned conventional means. [New content] The purpose of this new type is to drive the generator more effectively through the airfoil. In order to achieve the above purpose, the wing structure of the wind turbine can effectively apply the kinetic energy of natural wind speed, that is, convert the gas kinetic energy into electric energy. 'This creation provides a horizontal application comprising a wing root having a first airfoil 3 M378284 and located at one end of the wing structure; a wing tip located at the other end of the wing structure; and a slit - second The airfoil extends from the root of the wing to the tip of the wing, wherein the trailing edge of the wing is different from the root of the moon to the dusting corner, and the leading edge of the wing is from the root of the wing to the tip of the wing. Then, from the root of the wing to the tip of the wing, it gradually rises; and as in the wing structure as described above, the leading edge of the wing is straight upward, and the trailing edge of the wing is linearly descending. The deep upward airfoil further has a first and the first chord length is greater than the fin structure as previously described, wherein the first chord length & the second airfoil has a second chord length and the second chord length. A fin structure as previously described, wherein the fin structure has an effective span and the first chord length is one fifth of the effective span. A fin structure as previously described, wherein the second chord is nineteenths of a sixth of the first chord. The fin structure as described above, wherein the wing root further forms a shaft portion. The fin structure as described above, wherein the wing tip further forms a rectifying portion. In order to achieve the above object, the present invention further provides a fin structure for a wind power generator comprising a wing root having a first airfoil and located at one end of the wing structure; and a wing tip having a second wing The type is located at the other end of the fin structure, wherein the windward angle of the second airfoil is greater than the windward angle 20 of the first airfoil. . The wing structure as described above further includes a windward surface and a leeward surface, wherein the actual area of the wind surface is greater than the actual area of the windward surface. In order to achieve the above object, the present invention further provides a fin structure for a wind power generator, comprising a wing root having a first airfoil type and located at one of the wing structures; and a wing tip having a second The airfoil is located in the other end of the fin structure, and the wing tip is viewed from the wing tip toward the wing root in a spanwise direction, and the fin structure is clockwise twisted. As described above, the various airfoil structures, wherein the first airfoil is the airfoil S831 of the National Re-Energy Research Laboratory (NREL), and the second airfoil is the United States National Regeneration Research Laboratory (NREL) ) Airfoil § 832. [Embodiment] The following is a description of a preferred embodiment of the fin structure applied to a wind power generator of the present invention. Please refer to the attached drawings, but the actual configuration and the method adopted do not have to completely conform to the described content. Those who are familiar with the art can do the kind without changing the actual spirit of the case and the surrounding area. Please refer to Figure 1, which is a schematic diagram of the arrangement of the wing structure of the present invention. The wind rotor i is uncovered, including a fairing 1 〇, and a flap 2 is connected to the fairing through the shaft portion 20. The figure is a flap: close to the α ρ of the whole hood 1 , It is the root of the wing. Therefore, the wing profile of the wing root is the first airfoil 2a, and has a first string 2a. It can be seen from Fig. 1 that the first string 2a' is a self-rotating plane that sag counterclockwise and turns an angle, so when the wind comes When the axial wind direction AW is blown toward the airfoil 2, the airfoil 2 is rotated in the upward direction of the axial direction of the rotating shaft RA, so that the airfoil 2 can be divided into a wing leading edge Μ, a wing trailing edge 22' windward surface 23, With the leeward side 24. In addition, the windward side door is closer to the first chord 2a, and the leeward side 24 is further away from the first chord 2a, so that the entire arc surface area of the leeward surface 24 is larger than the windward side 23. Please refer to Figure 2 for a plan view of the flap of the present invention. Since the windward surface /, the wind surface 24 has only a difference in curvature, the plan view of Fig. 2 can be a plan view of the windward surface 23 or the leeward surface 24. 2, the first chord 2a of the wing root 2a", and the second chord of the wing tip ",", the wing root 彳 and the wing are mostly at both ends of the wing #2, as shown in FIG. In the figure, the left and right ends of the airfoil are swayed at the tip of the wing in order to make the airflow in the vicinity of the wing tip smooth. In addition, a rectifying portion 20'' is similarly provided for the airflow to have a conversion structure 25 between the wing root portion and the rotating shaft 邛20. The wing trailing edge 22 and the leading edge 21 are located at the wing root portion 2a, and the wing Between the tips 2b,. 3A is a perspective view of the structure of the inventive flap. Wherein the runner portion 20 is coupled to the wing root portion 2a, and the entire flap 2 extends to the wing tip aperture" while the windward surface 24 is located on the upper surface. At the same time, through the first string 2 & and the second string 2b It can be seen that the two are not parallel and the second string 2b is shown to be more flat on the graph $, so as seen from the wing root 2a, looking toward the wing tip 2b, it can be seen that the flap 2 is from the root of the wing. 2a, gradually twisting in a clockwise direction, that is, the leading edge 21 of the wing is ascending and the trailing edge 22 of the wing is descending. See Figure 4 for a cross-sectional view of the wing root of the flap structure. The airfoil of the wing root 2a" is the first airfoil 2a, and the first chord 2a has a straight line from the leading edge 2丨 of the wing to the trailing edge of the wing, and the leeward surface μ generally presents a circular arc protrusion And farther from the first string 2a, as the windward surface 23 is closer to the first string 2a' and flatter than the leeward surface 24, and the windward surface 23 is only slightly convex and close to the trailing edge 22 of the wing It is concave and spans the first string 2a' and is on the same side as the leeward surface 24, after which the windward surface 23 and the leeward surface 24 are at the wing trailing edge 22. The preferred embodiment of the present invention is the United States M378284 - Home Renewable Energy Research Laboratory (National p ^ ^ National Renewable Energy
Laboratory、NREL)的翼型S831作為第一翼型h。此外， 第一翼型2a的第一弦線2a，與轉軸尺八的第一夾角A〗可透 過轉軸部20改變，亦即改變第一翼型與軸向風向aw 的迎風角。 請參閱圖5,為本創作翼片結構的翼尖部翼剖面圖。 其中翼尖部的翼型為第二翼型2b，而其具有的第二弦線2b, •即是自翼前緣21至翼後緣22的直線，而背風面24大致上 • 呈現一圓弧凸起且距離第二弦線2b’較遠，至於迎風面23 距離第二弦線2b’較近且較背風面24更為平坦，但此處的 第一翼型2b的迎風面23並不跨過第二弦線2b’並與背風面 24於翼後緣22交會。本創作較佳實施例則是以美國國家 再生能源研究室（NREL)的翼型S832作為第二翼型2b。此 外’第二翼型2b的第二弦線2b’與轉轴ra的第二夾角A2 可透過轉轴部20改變’亦即改變第二翼型2b與轴向風向 • AW的迎風角。 此外，將圖4與圖5兩相比較可知，翼尖部的翼前緣 '21的位置較翼根部的翼前緣21位置更高，相對的，翼尖 部2b”的翼後緣22位置較翼根部的翼後缘22位置更低， 亦即，翼根部2a”迎風面23與轉軸RA的第一夾角A1較 小，而翼尖部2b”迎風面23與轉軸RA的第二夾角A2較 大’簡而言之’就是第二夾角A2大於第一夾角A1’而其 中較佳者，第二夹角A2大於第一夹角A1二十度。 综上所述’本創作的「應用於風力發電機的翼片結構」 7 M378284 是透過計算流體力學反覆不斷的運算與模擬 w叨仔到兩個結 淪，其一是翼片的迎風角度在愈靠近翼尖時角度要愈大. 其二是翼片近根部的翼型與近尖部的翼型要有所不同， 常翼根部的翼型較厚、迎風面與背風面的彎曲程度較大· 而翼尖部的翼型較薄、且迎風面與背風面的彎曲程度較 小。更進一步而言，兩個翼型是呈線性變化，逐漸一翼型 轉變成另一個翼型。此外，兩處的弦線的長度也是自翼根 至翼尖呈線性縮短，也就是說弦長是自翼根至翼尖呈線性 漸縮狀》之所以在翼根部與翼尖部的迎風角與翼型要有變 化是因為在風力翼片的應用情況之下’兩者的風速與翼片 轉動合成氣流狀況不同所至，因此唯有透過本創作的概念 才可以將空氣動能發揮到極高的效率。 上述實她例僅係為了方便說明而舉例，雖遭熟悉本技 藝之人士任施匠思而為諸般修飾，然皆不脫如附申請專利 範圍所欲保護者。 【圖式簡單說明】 圖1，為本創作的翼片結構的設置示意圖； 圖2,為本創作的翼片的平面圖； 圖3,為本創作翼片結構的立體圖； 圖4，為本創作翼片結構的翼根部翼剖面圖；以及 圖5，為本創作翼片結構的翼尖部翼剖面圖。 【主要元件符號說明】 1 :風力旋翼 10 :整流罩 8 M378284 - 2 :翼片 . 20 :轉轴部 21 :翼前緣 22 :翼後緣 23 :迎風面 24 :背風面 25 :轉換結構 2a :第一翼型 φ- 2a，：第一弦線 2a” ：翼根部 2b :第二翼型 2b’ ：第二弦線 2b” ：翼尖部 A1 :第一夹角 A2 :第二夾角 AW :軸向風向 PR :轉動平面 RA :轉軸 9The airfoil S831 of Laboratory, NREL) is used as the first airfoil h. Further, the first chord 2a of the first airfoil 2a and the first angle A of the yoke 8 can be changed through the shaft portion 20, that is, the windward angle of the first airfoil and the axial wind direction aw is changed. Please refer to FIG. 5 , which is a cross-sectional view of the wing tip wing of the inventive wing structure. Wherein the airfoil of the wing tip is the second airfoil 2b, and the second chord 2b, that is, the straight line from the leading edge 21 of the wing to the trailing edge 22 of the wing, and the leeward surface 24 substantially presents a circle The arc is convex and is far from the second string 2b', and the windward surface 23 is closer to the second string 2b' and flatter than the leeward surface 24, but here the windward surface 23 of the first airfoil 2b is It does not cross the second string 2b' and meets the leeward surface 24 at the trailing edge 22 of the wing. The preferred embodiment of the present invention is the airfoil S832 of the National Renewable Energy Research Laboratory (NREL) as the second airfoil 2b. Further, the second angle 2b' of the second airfoil 2b and the second angle A2 of the rotating shaft ra can be changed through the rotating shaft portion 20, i.e., the windward angle of the second airfoil 2b and the axial wind direction AW is changed. In addition, comparing FIG. 4 with FIG. 5, the position of the leading edge '21 of the wing tip portion is higher than the position of the leading edge 21 of the wing root portion, and the position of the trailing edge 22 of the wing tip portion 2b" is opposite. The position of the trailing edge 22 of the wing root is lower than that of the wing root portion 2a, that is, the first angle A1 of the windward surface 23 and the rotating shaft RA is smaller, and the second angle A2 of the windward surface 23 and the rotating shaft RA of the wing tip portion 2b" The larger 'in short' is that the second angle A2 is greater than the first angle A1' and wherein the second angle A2 is greater than the first angle A1 by twenty degrees. In summary, the application of the present invention The windshield structure of the wind turbine" 7 M378284 is through computational fluid dynamics and continuous calculation and simulation of the two knots, one of which is the angle of the windward angle of the airfoil closer to the wing tip. The second is that the airfoil near the root of the wing is different from the airfoil of the near tip. The airfoil at the root of the wing has a thicker airfoil, and the windward and leeward sides are more curved. Thin, and the windward and leeward sides are less curved. Furthermore, the two airfoils are linear and gradually change from one airfoil to another. In addition, the length of the two strings is also linearly shortened from the wing root to the wing tip, that is, the chord length is linearly tapered from the wing root to the wing tip. The windward angle at the root of the wing and the tip of the wing The change with the airfoil is because the wind speed of the two is different from the airflow of the airfoil in the application of the wind blade. Therefore, the air kinetic energy can be maximized through the concept of the creation. s efficiency. The above examples are merely examples for convenience of explanation, and those skilled in the art are all versatile, and are not intended to be protected as claimed. [Simple description of the drawing] Figure 1 is a schematic view of the arrangement of the wing structure of the present invention; Figure 2 is a plan view of the wing piece of the creation; Figure 3 is a perspective view of the structure of the creation wing; Figure 4 A cross-sectional view of the wing root of the fin structure; and Figure 5 is a cross-sectional view of the wing tip of the inventive flap structure. [Main component symbol description] 1 : Wind rotor 10 : fairing 8 M378284 - 2 : wing. 20 : Rotary shaft 21 : wing leading edge 22 : wing trailing edge 23 : windward surface 24 : leeward surface 25 : conversion structure 2a : first airfoil φ-2a,: first chord 2a": wing root 2b: second airfoil 2b': second chord 2b": wing tip A1: first angle A2: second angle AW : axial wind direction PR: rotation plane RA: shaft 9