CN101213131A - 可缩回的涡流发生器 - Google Patents
可缩回的涡流发生器 Download PDFInfo
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- CN101213131A CN101213131A CNA2006800237307A CN200680023730A CN101213131A CN 101213131 A CN101213131 A CN 101213131A CN A2006800237307 A CNA2006800237307 A CN A2006800237307A CN 200680023730 A CN200680023730 A CN 200680023730A CN 101213131 A CN101213131 A CN 101213131A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
- B64C23/06—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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- Y02T50/10—Drag reduction
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Abstract
公开了一种流控制装置,其包括流控制表面(20),流体被设计成按预定方向(F)流过流控制表面(20)。涡流发生器(30)与流控制表面相联。各涡流发生器都具有相对于预定方向形成锐角(α)的枢轴(40),且能够被定位在伸展状态和缩回状态,在伸展状态,单个涡流发生器的作用是形成涡流流体流,在缩回状态,各涡流发生器经由枢轴旋转以便处于靠近流控制表面的位置。致动器与各涡流发生器相联,每个致动器都适合于将相联的涡流发生器定位在伸展状态和缩回状态之间。所公开的流控制装置将用于倾斜旋翼飞行器。
Description
相关申请的交叉引用
本申请要求2005年6月30日递交的美国临时专利申请No.60/695,181的优先权,该申请的全部内容在此以引用方式并入本文。
技术领域
本发明涉及带有可缩回的涡流发生器(retractable vortexgenerator)的流控制表面(flow control surface)。
背景技术
涡流发生器已与各种流控制表面一起使用,以便使与流控制表面的边界空气层有关联的低动量流体流和边界空气层外面的高动量流体流混合。这种涡流发生器在各种各样的航空器中的使用提高了机动效率。然而,永久安装的翼涡流发生器会产生阻力负担(drag penalty),且有可能会堆积例如冰形态的外来物质,这些外来物质显著地降低航空器的固有性能。
可缩回的涡流发生器已经研究出来弥补这些问题。
Bauer的US 4,039,161、Cox的US 5,253,828和Lisy等人的US6,105,904中的每一个都公开了可缩回到流控制表面中的涡流发生器。然而,这些文献中所描述的可缩回的涡流发生器需要修改在其上设置该涡流发生器的装置的结构以留出在涡流发生器不使用时涡流发生器可缩回到其中的内部空间。需要足够的空间来容纳涡流发生器的这种要求可能以消极方式影响翼或其它结构的设计。这还要求具有希望增加涡流发生器的流控制表面的翼或其它这种结构不能够针对这种涡流发生器轻易地进行改装。
Campbell的US 6,427,948公开了一种涡流发生器,其能够被选择性地移入偏转位置以产生顺流湍流,且能够被移入未偏转位置以减少阻力。Campbell的涡流发生器由形状记忆合金形成,当没有电信号施加到相联的加热器时,形状记忆合金处于偏转位置,且当电信号施加到相联的加热器时,形状记忆合金处于未偏转位置。然而,在偏转状态和未偏转状态下,涡流发生器都伸出流控制表面的外部,然而未偏转状态与偏转状态相比可产生较少阻力,但是伸出部分仍产生一些不希望的残余阻力,且没有减少暴露的涡流发生器上的积冰问题。
发明内容
本发明提供一种包括流控制表面的流控制装置,流体被设计成按预定方向流过流控制表面。涡流发生器与流控制表面相联。各涡流发生器都具有相对于预定方向形成锐角的枢轴,并且能够被定位在伸展状态和缩回状态,在伸展状态,各涡流发生器的作用是形成涡流流体流,在缩回状态,各涡流发生器经由枢轴旋转以便处于靠近流控制表面的位置。致动器与各涡流发生器相联,每个致动器用于将相联的涡流发生器定位在伸展状态和缩回状态之间。
在一个实施例中,当处于伸展状态时,涡流发生器与预定方向构成的锐角在5至45度之间。
在一个实施例中,致动器可以是启动由镍-钛合金制成的形状记忆材料的加热器。然而,也可使用其它类型的机电致动器。
在一个实施例中,涡流发生器可以是翼片形式,当处于缩回状态时,翼片与流控制表面平行,且当处于伸展状态时,翼片设置为0和180度之间的角度。
如所描述的,流控制装置使流控制表面上的阻力和积冰减少,而不需要在流控制装置中为缩回的涡流发生器留出空间。因此,本发明的可缩回的涡流发生器可应用于大量各种流控制表面,而不需要大量改装流控制表面。
附图说明
图1A是具有依据本发明的处于伸展或展开状态的涡流发生器的流控制装置的侧视图。
图1B是具有依据本发明的处于伸展或展开状态的涡流发生器的流控制装置的俯视图。
图2A是具有依据本发明的处于缩回状态的涡流发生器的流控制装置的侧视图。
图2B是具有依据本发明的处于缩回状态的涡流发生器的流控制装置的俯视图。
图3A是依据本发明一个实施例的当各涡流发生器处于缩回状态时沿其枢轴的视图。
图3B是当图3A的涡流发生器处于伸展或展开状态时沿其枢轴的视图。
图4A是依据本发明的另一个实施例的当各涡流发生器处于缩回状态时沿其枢轴的视图。
图4B是当图4A的涡流发生器处于伸展或展开状态时沿其枢轴的视图。
具体实施方式
图1A、1B、2A和2B显示了依据本发明的一个实施例的流控制装置10的示例。图1A显示了侧视图,以及图1B显示了流控制表面20的俯视图,流体介质设计成按矢量F所表示的方向流过流控制表面20。一列涡流发生器30示出处于伸展位置。涡流发生器30基本上为扁平结构,其在伸展时通常相对于控制表面的平面垂直。涡流发生器30的每一个都构造成可围绕枢轴40枢转。枢轴40与流动方向(或原始风向)F形成锐角α,以便方便产生流体涡流。锐角α可在5和45度之间(或-5到-45度,取决于所测量的方向),以在流控制表面20上产生涡流。在更具体的实施例中,角α在12和25度之间,且甚至更具体地在19和21度之间。图2A和2B显示了流控制表面20的侧视图和俯视图,流体介质设计成当一列涡流发生器30处于缩回状态时按预定方向F流过流控制表面20。如所显示的,涡流发生器围绕枢轴40枢转,以便通常处于与上部流控制表面20呈平行的、躺在其上的关系。在一个实施例中,缩回的涡流发生器处于与上部流控制表面20抵靠接触。在这种状态下,涡流发生器不阻挡流,因而基本上消除了来自涡流发生器的阻力影响。因此,涡流发生器在需要时被伸展,且在所有其它飞行状况下缩回,而不要求在流控制装置中具有任何空间用以储存在不用时的涡流发生器。在所示的实施例中,表面20具有基本上连续的、未修改的形状。因此,应当理解,如这里图中所示的涡流发生器可被改装到之前已经制造出的许多不同类型的表面20上。在另一实施例中(未显示),涡流发生器当展开时所置于其上的上部表面区域稍微凹进。这种凹进可具有与涡流发生器的厚度相同大小的深度,以便当缩回时涡流发生器的暴露表面基本上与表面20的相邻表面部分平齐。
图3A和3B显示了依据本发明的一个实施例在流控制表面20上操作涡流发生器30的示例。图3A是当涡流发生器30处于缩回状态时沿着涡流发生器30的枢轴40的方向得到的视图。图3B是当涡流发生器30处于伸展状态时沿涡流发生器30的枢轴40的视图。涡流发生器由马达或致动器50来致动,以便在缩回状态和伸展状态之间重新定位。伸展状态可以可变地选择,以使涡流发生器相对于流控制表面20倾斜角度θ。在本实施例中,致动器50可以是由电输入60(来自外部控制器)控制的电磁马达,且角θ可调节成相对于表面20处于0和180度之间。在一个实施例中,角θ以与表面20垂直(90°)的方位或角θ配置。在另一实施例中,涡流发生器30以相对于直角-4°到+4°的角度配置。
图4A和4B显示了用以将涡流发生器30定位在伸展位置和缩回位置之间的另一致动器的示例。在该示例中,致动器包括由电输入80(来自外部控制器)控制的加热器70。涡流发生器30由形状记忆合金如镍-钛合金形成,且在制造时初始变形成如图4B所显示的伸展位置。在图4B的伸展位置,涡流发生器30相对于表面20形成角θ。角θ可具有与如上述的图3A和3B的实施例相同的一个范围或多个范围。当由加热器70施加热量超过形状记忆材料的特定转变温度时,涡流发生器返回到未变形状态,如图4A所示的。在另一实施例中,形状记忆合金涡流发生器初始处于缩回(未展开)位置,如图4A所示的。当热量施加到形状记忆合金涡流发生器时,形状记忆合金涡流发生器从图4A的缩回位置移动到图4B的展开位置。
各种类型的致动器可用于执行如所描述的枢转功能,这对于本领域的普通技术人员是显而易见的。例如,热双压电晶片致动器(thermalbimorph actuators)、双压电晶片致动器(piezoelectric bimorphactuators)以及能够产生枢转动作的任何其它致动器都可用作本发明的致动器。
在一个实施例中,本发明的流控制装置用作倾斜旋翼航空器的翼的一部分。
尽管已经显示了涡流发生器的具体构造,但是本发明并不限于这种构造,且可使用各种各样的其它结构来产生同向旋转以及反向旋转效果。
尽管单个涡流发生器的形状已经显示为三角形,但是本发明并不限于这种形状,且可以使用其它形状的涡流发生器,例如矩形形状或其它形状。
尽管已经显示并描述了本发明的具体实施例,但是对于本领域的技术人员而言,很显然可进行各种改变而不偏离本发明的教导。
Claims (9)
1.一种流控制装置,其包括:
流控制表面,流体被设计成按预定方向流过所述流控制表面;
涡流发生器,其与所述流控制表面相联,各涡流发生器都具有相对于所述预定方向形成锐角的枢轴,并且能够被定位在伸展状态和缩回状态,在该伸展状态中,所述各涡流发生器起到形成涡流流体流的作用,在该缩回状态中,所述各涡流发生器经由所述枢轴旋转以便处于靠近所述流控制表面的位置;以及
致动器,其与所述各涡流发生器中的每个相联,每个致动器用于将相联的所述涡流发生器定位在所述伸展状态和所述缩回状态之间。
2.根据权利要求1所述的流控制装置,其中所述锐角在5度至45度之间。
3.根据权利要求1所述的流控制装置,其中所述涡流发生器由形状记忆材料形成,并且所述致动器包括启动所述形状记忆材料的加热器。
4.根据权利要求1所述的流控制装置,其中所述各涡流发生器都为翼片形式,当处于所述缩回状态时,所述翼片与所述流控制表面平行,当处于所述伸展状态时,所述翼片设置为相对于所述流控制表面成大于0度且小于180度的角度。
5.根据权利要求1所述的流控制装置,其中所述流控制表面是倾斜旋翼飞行器的一部分。
6.一种航空器,其包括:
倾斜旋翼的机翼;
流控制表面,其形成在所述倾斜旋翼的机翼上,流体被设计成按预定方向流过所述倾斜旋翼的机翼;
涡流发生器,其与所述流控制表面相联,各涡流发生器都具有相对于预定方向形成锐角的枢轴,并且能够被定位在伸展状态和缩回状态,在所述伸展状态中,所述各涡流发生器起到形成涡流流体流的作用,在所述缩回状态中,所述各涡流发生器经由所述枢轴转动以便处于靠近所述流控制表面的位置;以及
致动器,其与所述各涡流发生器相联,各致动器都适合于将相联的所述涡流发生器定位在所述伸展状态和所述缩回状态之间。
7.根据权利要求6所述的航空器,其中所述锐角在5度至45度之间。
8.根据权利要求6所述的航空器,其中所述致动器包括加热器,并且所述涡流发生器包括可基于所述加热器的启动而进行移动的形状记忆材料。
9.根据权利要求6所述的航空器,其中所述各涡流发生器都为翼片形式,当处于所述缩回状态时,所述翼片与所述流控制表面平行,当处于所述伸展状态时,所述翼片设置为相对于所述流控制表面成大于0度且小于180度的角度。
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- 2006-06-30 DE DE602006007353T patent/DE602006007353D1/de active Active
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- 2006-06-30 RU RU2008103327/11A patent/RU2008103327A/ru not_active Application Discontinuation
- 2006-06-30 JP JP2008519640A patent/JP2008544921A/ja active Pending
- 2006-06-30 EP EP06786059A patent/EP1896323B1/en active Active
- 2006-06-30 WO PCT/US2006/025730 patent/WO2007005687A1/en active Application Filing
- 2006-06-30 CN CNA2006800237307A patent/CN101213131A/zh active Pending
- 2006-06-30 BR BRPI0613492-0A patent/BRPI0613492A2/pt not_active Application Discontinuation
- 2006-06-30 US US11/477,806 patent/US7878457B2/en active Active
- 2006-06-30 AU AU2006265854A patent/AU2006265854A1/en not_active Abandoned
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CN107575341A (zh) * | 2016-07-05 | 2018-01-12 | 西门子公司 | 带有涡流发生器的风力涡轮机转子叶片 |
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CN110435876A (zh) * | 2019-08-26 | 2019-11-12 | 中国空气动力研究与发展中心低速空气动力研究所 | 一种带有伸缩式涡流发生器的共轴旋翼桨毂整流罩 |
CN110435876B (zh) * | 2019-08-26 | 2020-06-19 | 中国空气动力研究与发展中心低速空气动力研究所 | 一种带有伸缩式涡流发生器的共轴旋翼桨毂整流罩 |
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BRPI0613492A2 (pt) | 2011-01-11 |
US20070018056A1 (en) | 2007-01-25 |
AU2006265854A1 (en) | 2007-01-11 |
EP1896323B1 (en) | 2009-06-17 |
ATE433909T1 (de) | 2009-07-15 |
RU2008103327A (ru) | 2009-08-10 |
DE602006007353D1 (de) | 2009-07-30 |
US7878457B2 (en) | 2011-02-01 |
WO2007005687A1 (en) | 2007-01-11 |
CA2613446C (en) | 2016-11-22 |
CA2613446A1 (en) | 2007-01-11 |
JP2008544921A (ja) | 2008-12-11 |
EP1896323A1 (en) | 2008-03-12 |
KR20080025379A (ko) | 2008-03-20 |
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