CN101876292B - 分段式风力涡轮机叶片 - Google Patents
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Abstract
本发明涉及分段式风力涡轮机叶片。具体而言,一种用于风力涡轮机的转子叶片(10)包括多个单独的叶片区段(12),其中,各叶片区段限定在叶片区段的纵向端之间延伸的内部通道(22)。刚性翼梁部件(28)沿纵向延伸穿过单独叶片区段的内部通道,使得叶片区段在所述翼梁部件上端对端地对准和连接,用以限定完整的转子叶片(10)。翼梁部件所具有的截面轮廓键连接到叶片区段中的内部通道的截面轮廓上。翼梁部件包括对立地面对的翼梁缘条(34,36),该翼梁缘条(34,36)抵靠接合内部通道内的叶片区段内表面。
Description
技术领域
本发明主要涉及风力涡轮机转子叶片,并且更具体地涉及一种分段式风力涡轮机转子叶片。
背景技术
风力被认为是目前可用的最清洁、对环境最为友好的能源之一,故在此方面,风力涡轮机获得了日益增加的关注。现代风力涡轮机通常包括塔架、发电机、齿轮箱、机舱和一个或多个转子叶片。转子叶片使用公知的翼片原理来获取风中的动能。转子叶片传递旋转能形式的动能,以便使轴转动,该轴将转子叶片联接到齿轮箱上,或如果未使用齿轮箱,则该轴直接联接到发电机上。发电机然后将机械能转换成可调度到公用电网的电能。
现代转子叶片的构造大致包括表皮(skin)或壳体构件、翼梁缘条(spar cap),以及一个或多个抗剪腹板。通常由纤维复合材料层和轻质的芯材料所制成的表皮形成转子叶片的外部空气动力翼片形状。翼梁缘条通过结合一个或多个结构元件来提供增大的转子叶片强度,该结构元件在转子叶片的两内侧上沿转子叶片的长度延展。抗剪腹板为结构梁类构件,其基本上在顶翼梁缘条与底翼梁缘条之间垂直地延展,且延伸越过外表皮之间的转子叶片内部部分。翼梁缘条通常由玻璃纤维增强复合材料构成,但一些较大的叶片可包括由碳纤维增强复合材料构成的翼梁缘条。
转子叶片的尺寸、形状和重量是与风力涡轮机能量效率相关的因素。转子叶片尺寸的增大会增加风力涡轮机的能量生成,而重量减小还会提升风力涡轮机的效率。此外,当转子叶片尺寸增长时,需要给予转子叶片结构完整性额外关注。目前,大型商用风力涡轮机能够产生大约1.5兆瓦至5.0兆瓦的功率。这些较大的风力涡轮机可具有直径大于90米的转子叶片组件。此外,转子叶片形状的进展促使制造出从叶片的基部至末梢具有大致弓形外形的前掠形转子叶片,从而提供改善的空气动力特性。因此,增大转子叶片尺寸、减轻转子叶片重量以及提高转子叶片强度的努力,同时还改善转子叶片空气动力特性,有助于风力涡轮机技术的持续发展和采用风能作为替代能源。
随着风力涡轮机的尺寸增大,尤其是转子叶片的尺寸,风力涡轮机相应的制造成本、运输成本和组装成本也会增加。增大风力涡轮机尺寸的经济利益必须权衡克服这些因素。例如,预先形成、运输和架设具有范围在90米内的转子叶片的风力涡轮机的成本会极大地冲击较大的风力涡轮机的经济优点。
因此,需要一种特别适于较大的风力涡轮机的风力涡轮机转子叶片设计,并且该设计最大限度地降低了风力涡轮机的相关运输和组装成本,而不会损害风力涡轮机的结构刚度和能量效率。
发明内容
本发明提供了一种解决上述考虑的改进的风力涡轮机转子叶片设计。本发明的附加方面和优点将会在以下描述中部分地阐述,或可根据描述而变得明显,或可通过实施本发明而认识到。
根据本发明的方面,一种用于风力涡轮机的转子叶片包括多个单独叶片区段。各叶片区段均包括从叶片区段的第一端沿纵向延伸至第二端的内部通道,该通道具有键连接的截面轮廓。刚性翼梁部件沿纵向延伸穿过叶片区段的内部通道,使得多个叶片区段在翼梁部件上端对端地对准和连接,以便限定从连接到转子毂上的根部至叶片末梢的完整转子叶片。翼梁部件还限定对立地面对的翼梁缘条,该翼梁缘条抵靠接合内部通道内的叶片区段的内表面。翼梁部件具有的截面轮廓对应于内部通道的键连接截面轮廓。因此,翼梁部件的截面轮廓和叶片区段的内部通道相互键连接。
应当认识到的是,本发明还包含用于形成在风力涡轮机上使用的完整转子叶片的转子叶片套件。该套件可包括多个单独叶片区段,其中,各叶片区段均具有内部通道,该内部通道具有从叶片区段的第一端沿纵向延伸至第二端的键连接截面轮廓。套件包括具有对立地面对的翼梁缘条的刚性翼梁部件,该翼梁部件具有的截面轮廓对应于越过叶片区段的内部通道的键连接截面轮廓。为了组装转子叶片,叶片区段以有序的顺序滑动到翼梁部件上,其中,翼梁缘条抵靠接合内部通道内的叶片区段上壳体构件和下壳体构件的内表面,以限定从连接到转子毂上的根部至转子叶片末梢的完整转子叶片。
还应当认识到的是,本发明包含如本文所述的单独叶片区段,由此,多个叶片区段可安装到翼梁部件上用以限定完整的转子叶片。
附图说明
在结合附图进行的如下详细说明中更为具体地描述了根据优选实施例和示例性实施例的本发明及其另外的方面和优点,在附图中:
图1为常规风力涡轮机的简图;
图2为根据本发明的方面的分段式风力涡轮机叶片的视图;
图3为分段式风力涡轮机叶片的实施例的局部构件视图;
图4A和图4B为具有键连接内部通道和对应构造的翼梁部件的叶片区段实施例的截面视图;
图5A和图5B为具有键连接内部通道和对应构造的翼梁部件的叶片区段备选实施例的截面视图;
图6A和图6B为具有键连接内部通道和对应构造的翼梁部件的叶片区段的又一个实施例的截面视图;
图7为相邻叶片区段的联锁端面的视图;以及
图8为相邻叶片区段的联锁端面的备选实施例的视图。
零件清单
10 涡轮叶片
12 叶片区段
14 第一壳体构件
16 第二壳体构件
18 末梢叶片区段
20 根部叶片区段
22 通道
24 腹板部件
28 翼梁部件
30 根部环
32 腹板
34 上翼梁缘条
36 下翼梁缘条
38 端面
40 凸形凸起
42 端面
44 凹形凹部
46 边缘
50 套件
52 支架(brace)
100 风力涡轮机
110 塔架
120 机器机舱
130 毂
140 转子叶片
141 根段
142 末梢端
具体实施方式
现参照本发明的特定实施例,在附图中示出了其中的一个或多个实例。各实施例均是通过论述本发明的方面来提供的,并且不应当看作是对本发明进行限制。例如,相对于一个实施例示出或描述的特征可结合另一个实施例使用来产生再一个实施例。期望的是,本发明包括对于本文所述的实施例的这些和其它的修改或变型。
图1为常规风力涡轮机100的简图。风力涡轮机100包括塔架110,其中,机器机舱120安装在塔架的顶部处。具有三个转子叶片140的毂130安装到机器机舱120的侧端上。
常规转子叶片140的典型构造包括用于将转子叶片140安装到毂130上的根部段141。转子叶片140的末梢端142设置成与根部段141相对。在根部段141与末梢端142之间延伸的转子叶片140的本体段通常包括在根部段141与末梢端142之间沿纵向延展的第一壳体构件和第二壳体构件。翼梁缘条沿各壳体构件的大致全部纵向长度延伸,且结合到壳体构件的内表皮或内表面上。沿纵向延伸的内部抗剪腹板在壳体构件之间延展,且以大致垂直的定向附着到翼梁缘条上。翼梁缘条和内部抗剪腹板给予涡轮叶片其结构刚度。
参看图2,示出了根据本发明的方面的分段式涡轮叶片10。分段式涡轮叶片10包括多个单独叶片区段12,这些叶片区段12从末梢叶片区段18至根部叶片区段20以端对端的顺序对准。其中的各个单独叶片区段12独特地构造成使得该多个区段12限定具有所设计的叶片轮廓、长度和其它期望特征的完整叶片10。完整的分段式叶片10可具有扫掠形状,扫掠形状给定其从叶片10的远端延展至近端的弯曲外形。在备选实施例中,分段式转子叶片10可具有非扫掠形状。
叶片区段10可包括限定内部通道的任何形式的内部腹板,或在叶片区段的上壳体构件与下壳体构件之间的其它支承腹板。
单独叶片区段10的纵向端面可具有以便与相邻叶片区段的端面联锁的轮廓。例如,相邻叶片区段的配合端面可具有搭接边缘或凸-凹联锁部件,或确保叶片区段正确接合和对准在翼梁部件上的其它适合的结构。
例如参看图3,各单独叶片区段12均包括沿纵向延伸的内部通道22。该通道22从各叶片区段12的第一纵向端延伸至第二纵向端,且具有特定的截面轮廓。内部通道可由任何构造的内部腹板部件24限定。
刚性翼梁部件28沿纵向延伸穿过多个叶片区段12的内部通道22。单独叶片区段12在翼梁部件上以端对端的构造连接在一起,以限定图2中所绘出的完整的分段式叶片10。翼梁部件28和单独内部通道22的截面轮廓以特定轮廓相互键连接,该特定轮廓阻止叶片区段12相对于翼梁部件28旋转。翼梁部件28包括用于将完整叶片附接到转子毂上的根部环30。
翼梁部件28可采用各种形状和构造。在特定实施例中,翼梁部件为中空盒形梁结构,其中,穿过叶片区段的内部通道具有对应的键连接轮廓。例如,翼梁部件可具有中空的正方形或矩形构造,其中,翼梁缘条由盒形梁结构的相对侧限定。在备选实施例中,翼梁部件可具有中空梁结构,该中空梁结构具有在翼梁缘条之间延伸的凹壁或凸壁。在又一个实施例中,翼梁部件可为整体式腹板结构,该腹板结构例如具有工字梁或具有中心腹板的其它类似截面轮廓,其中,翼梁缘条从中心腹板的相对的纵向端沿横向延伸。在该实施例的情况下,穿过叶片区段的内部通道将具有对应形状的截面轮廓。
叶片区段10可通过任何常规附接方式连接或附连到翼梁部件28上。在特定实施例中,叶片区段可结合到翼梁部件上。
参看图3、图4A和图4B,各个单独叶片区段12可由第一壳体构件14和第二壳体构件16形成。这些壳体构件可单独地形成,且在涡轮叶片的前缘和后缘处连结在一起。单独壳体构件14,16可分别包括内表皮和外表皮,且例如可由干纤维材料构成。此外,各壳体14,16均可包括夹在内表皮与外表皮之间的芯材料。如本领域中所公知的那样,该芯材料例如可以是轻质材料,如轻木、挤出泡沫聚苯乙烯等。内部腹板24限定具有一定键连接轮廓的内部通道22,该键连接轮廓对应或匹配翼梁部件28的截面轮廓。腹板24可由通常用作风力涡轮机叶片的内部抗剪腹板的任何适合的材料形成。腹板24可使用任何适合的粘合材料或结合方法附着到壳体构件14,16的内表皮上。腹板24可直接附接到壳体构件14,16的内表皮表面上,或可附接到单独的腹板上,该单独的腹板附着到内表皮表面上用于增加支承和刚度。内部腹板24的构造限定了键连接到翼梁部件28的截面轮廓上的内部通道22截面轮廓。
在图3、图4A和图4B中示出的实施例中,内部通路22具有大致盒状的截面轮廓,以及翼梁部件28具有带对应键连接截面轮廓的大致中空的盒形梁结构。例如参看图4B,翼梁部件28包括上翼梁缘条34与下翼梁缘条36之间的抗剪腹板32。翼梁缘条34,36所具有的形状和曲率基本上匹配相应的壳体构件14,16的内部表皮或附着到内表皮表面上的任何附加内部腹板的形状和曲率。利用该独特构造,单独叶片区段12可容易地滑动到翼梁部件28上用以限定完整的涡轮叶片10。在组装过程中,单独叶片区段12可在翼梁缘条34,36与壳体构件14,16内表皮表面之间的接触面处结合到翼梁部件28上。键连接的截面轮廓还确保了叶片的结构刚度,且减小了相应叶片区段12之间的扭转。
具有一体式翼梁缘条34,36的翼梁部件28可由任何适合的材料形成。例如,翼梁缘条构件34,36可由碳纤维增强的基体或玻璃纤维增强的聚合物,或其它轻质的坚固材料形成。抗剪腹板构件32可由相同或不同的材料形成。
叶片区段12中的内部通道22和相应的翼梁部件28的键连接截面轮廓可采用各种轮廓。例如,在图5A和图5B中的实施例中,内部腹板24限定具有壁的内部通道22,该壁由于它们向外弯曲而基本上为凸起的。在备选实施例中,腹板24可限定具有凹壁的内部通道22的轮廓,该凹壁朝向彼此向内弯曲。图5B中的翼梁部件28具有对应的轮廓,且形成为大致中空的梁部件,该部件具有带一定曲率的抗剪腹板32和翼梁缘条34,36,以便结合到内部通道22内的壳体构件14,16的内表皮表面上。
图5A中的实施例示出为包括位于壳体构件14,16之间的附加腹板或支架52。应当认识到的是,在单独叶片区段12的壳体构件14,16之间的任何数量或构造的附加内部支架或腹板都在本发明的精神和范围内。
在图6A和图6B的实施例中,叶片区段12中的内部通道22具有由内部腹板24限定的基本上为工字梁的构造。图6B中的翼梁部件28具有对应的键连接工字梁轮廓。在该特定实施例中,相比于图4B和图5B中的中空梁构造,翼梁部件28为结实的整体式部件。正如其它实施例那样,翼梁缘条34,36具有一定的曲率和轮廓,以便对应于内部通道22内的壳体构件14,16的内表皮表面的曲率和轮廓。
在附图中示出的各种实施例中,内部通道22的截面轮廓围绕轮廓的整个圆周完全键连接到相应的翼梁部件28的截面轮廓上。换言之,轮廓围绕它们的整个圆周相互匹配。然而,应当理解的是,这并非为必要条件。例如,图6A的实施例中的内部通道22的大致矩形的轮廓可与如图6B中所示的工字梁翼梁部件28进行键连接。该构造仍然认作是″键连接″的,其原因在于工字梁翼梁部件28的翼梁缘条34,36具有一定的曲率和轮廓使得叶片区段12滑动到翼梁部件28上,其中,用于翼梁缘条34,36的结合接合表面限定在通道22内的内部腹板24之间,且叶片区段不可绕翼梁部件28旋转。换言之,键连接轮廓所确保的是保证了叶片区段12处在翼梁部件28上的期望的相对位置上。
参看图7和图8,在特定实施例中,相邻叶片区段12的纵向端面38,42可具有联锁构造,以确保叶片区段12正确接合在翼梁部件28上。例如,在图7的实施例中,纵向端面38包括凸形凸起40,该凸形凸起40配合到限定在相邻叶片区段12的端面42中的凹形凹部44中。在此方面,可使用任何类型的常规燕尾构造。在图8的实施例中,联锁构造由端面38的边缘46与相邻区段12的端面边缘48之间的互搭接头连结限定。相邻的叶片区段12可在其相应端面的联锁构造处结合在一起。
应当容易认识到的是,本发明包含文中示为和描述为独立构件的单独涡轮叶片区段,其中,多个叶片区段12可安装到翼梁部件上用以限定完整的涡轮叶片。
参看图3,还应当认识到的是,本发明包含套件50,该套件包括随后组装成如图2中所示的完整叶片10所需的多个构件。例如,套件50可包括多个单独叶片区段12,具有根部环30的翼梁缘条28,以及形成如图2中所绘出的完整叶片10所需的任何其它构件。
尽管已经参照具体示例性实施例及其方法详细描述了本主题,但应当认识到的是,本领域的技术人员在获得对前文的理解时,可容易地制作出对这些实施例的改进、变型和等效布置。因此,本公开内容的范围是通过举例的方式,而非通过限制,且正如本领域的普通技术人员将容易明白的那样,所述公开内容对于本主题而言并不排除包括此类修改、变型和/或附加体。
Claims (16)
1.一种用于风力涡轮机的转子叶片,包括:
多个单独叶片区段,各个所述叶片区段均包括在所述叶片区段的前缘和后缘处连结的第一壳体构件和第二壳体构件;
所述多个叶片区段中的各个叶片区段均包括从各个所述叶片区段的第一端沿纵向延伸至第二端的内部通道,所述通道沿其在所述第一端和所述第二端之间的长度具有键连接截面轮廓;
刚性翼梁部件,其沿纵向延伸穿过各个所述叶片区段的所述内部通道,使得所述多个叶片区段在所述翼梁部件上端对端地对准和连接,且限定从连接到转子毂上的根部至叶片末梢的完整转子叶片;
所述翼梁部件还包括抵靠所述内部通道内的所述叶片区段的内表面相接合的对立地面对的翼梁缘条;
所述翼梁部件具有的截面轮廓对应于所述内部通道的所述键连接截面轮廓;以及
所述内部通道由沿着所述内部通道的长度在所述第一壳体构件和所述第二壳体构件之间延伸的内部腹板所限定。
2.根据权利要求1所述的转子叶片,其特征在于,所述翼梁部件包括中空的盒形梁结构,所述翼梁缘条由所述盒形梁结构的相对的侧所限定,以及各个所述叶片区段的所述内部通道具有对应的盒形截面轮廓。
3.根据权利要求1所述的转子叶片,其特征在于,所述翼梁部件包括具有在所述翼梁缘条之间延伸的凹壁或凸壁的中空梁部件,以及各个所述叶片区段的所述内部通道具有对应形状的截面轮廓。
4.根据权利要求1所述的转子叶片,其特征在于,所述翼梁部件包括中心腹板,其中,所述翼梁缘条从所述中心腹板的相对的纵向端沿横向延伸,以及各个所述叶片区段的所述内部通道具有对应形状的截面轮廓。
5.根据权利要求4所述的转子叶片,其特征在于,所述翼梁部件和各个所述叶片区段的所述内部通道包括工字梁截面轮廓。
6.根据权利要求1所述的转子叶片,其特征在于,所述多个叶片区段结合到所述翼梁部件上。
7.根据权利要求6所述的转子叶片,其特征在于,所述转子叶片还包括在相邻的所述叶片区段的端面之间的联锁连结。
8.一种用于形成在风力涡轮机上使用的转子叶片的转子叶片套件,包括:
多个单独叶片区段,各个所述叶片区段均包括在所述叶片区段的前缘和后缘处连结的第一壳体构件和第二壳体构件;
各个所述叶片区段均包括从各个所述叶片区段的第一端沿纵向延伸至第二端的内部通道,所述通道沿其在所述第一端和所述第二端之间的长度具有键连接截面轮廓;
所述内部通道由沿着所述内部通道的长度在所述第一壳体构件和所述第二壳体构件之间延伸的内部腹板所限定;
包括对立地面对的翼梁缘条的刚性翼梁部件,所述翼梁部件具有的截面轮廓对应于各个所述叶片区段的所述内部通道的所述键连接截面轮廓;以及
其中,所述多个叶片区段可采用有序的顺序滑动到所述翼梁部件上,其中,所述翼梁缘条抵靠接合所述内部通道内的各个所述叶片区段的内表面,以限定从连接到转子毂上的根部至转子叶片末梢的完整转子叶片。
9.根据权利要求8所述的转子叶片套件,其特征在于,所述翼梁部件包括中空盒形梁结构,所述翼梁缘条由所述盒形梁结构的相对的侧所限定,以及各个所述叶片区段的所述内部通道具有对应的盒形截面轮廓。
10.根据权利要求8所述的转子叶片套件,其特征在于,所述翼梁部件包括具有在所述翼梁缘条之间延伸的凹壁或凸壁的中空梁部件,以及各个所述叶片区段的所述内部通道具有对应形状的截面轮廓。
11.根据权利要求8所述的转子叶片套件,其特征在于,所述翼梁部件包括中心腹板,其中,所述翼梁缘条从所述中心的相对的纵向端沿横向延伸,以及各个所述叶片区段的所述内部通道具有对应形状的截面轮廓。
12.根据权利要求8所述的转子叶片套件,其特征在于,所述转子叶片套件还包括各个所述叶片区段的端面上限定的联锁连结轮廓。
13.一种用于风力涡轮机转子叶片的单独叶片区段,所述风力涡轮机转子叶片由在刚性翼梁部件上端对端地对准的多个所述单独叶片区段形成,所述翼梁部件延伸穿过所述单独叶片区段,所述单独叶片区段包括:闭合的表皮结构和沿着所述叶片区段的长度在所述闭合的表皮结构的相对侧之间延伸的内部腹板,所述内部腹板限定在所述叶片区段的相对端之间沿纵向延伸的内部通道,所述通道沿着所述叶片区段的长度具有匹配所述翼梁部件的截面轮廓的键连接截面轮廓;以及联锁连结轮廓,其限定在所述表皮结构的纵向端面上,使得相邻的叶片区段联锁在所述翼梁部件上。
14.根据权利要求13所述的叶片区段,其特征在于,所述内部通道包括盒形截面轮廓。
15.根据权利要求13所述的叶片区段,其特征在于,所述内部通道包括在所述表皮结构之间延伸的凹壁或凸壁。
16.根据权利要求13所述的叶片区段,其特征在于,所述内部通道包括工字梁截面轮廓。
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US20100143143A1 (en) | 2010-06-10 |
CN101876292A (zh) | 2010-11-03 |
EP2249027A2 (en) | 2010-11-10 |
EP2249027B1 (en) | 2017-11-22 |
US7854594B2 (en) | 2010-12-21 |
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