CN1612979B - 涡环发生器 - Google Patents
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- CN1612979B CN1612979B CN038019329A CN03801932A CN1612979B CN 1612979 B CN1612979 B CN 1612979B CN 038019329 A CN038019329 A CN 038019329A CN 03801932 A CN03801932 A CN 03801932A CN 1612979 B CN1612979 B CN 1612979B
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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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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
- F15D1/00—Influencing flow of fluids
- F15D1/009—Influencing flow of fluids by means of vortex rings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
- F15D1/00—Influencing flow of fluids
- F15D1/10—Influencing flow of fluids around bodies of solid material
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/02—Stabilising arrangements
- F42B10/22—Projectiles of cannelured type
- F42B10/24—Projectiles of cannelured type with inclined grooves
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- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/10—Drag reduction
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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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T137/00—Fluid handling
- Y10T137/0318—Processes
- Y10T137/0391—Affecting flow by the addition of material or energy
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Abstract
涡环发生器(11)可与检验流体的物体(12)结合在一起,涡环发生器(11)可产生涡环形式的流体流动,而流体从涡环发生器(11)起流过物体。
Description
发明领域
本发明涉及流体力学领域,更具体说涉及流体相对于物体的流动。更准确地说,本发明试图在物体与流体作相对运动时降低物体或机身上的阻力。
这里参照其在任何运动物体或机身上的应用来说明本发明,运动物体包括,但局限于诸如炮弹、导弹、鱼雷、潜艇及飞机。但是,本发明又不限制在运动的飞机机身,而可应用到减少静止物体如建筑物、桥桩及在水道、航线或其它流体流场内的固定障碍物上的阻力。这样的应用也意向属于本发明的范围,虽然未在此作专门说明
背景技术
设计流线型机身时得到最佳效能的最大障碍是表面摩擦。它可以有几种形式,但典型的是附面层阻力,表皮摩擦,粘性,表面张力,气穴与紊流。
现有技术试图通过尽可能使表面光滑,表面隆起最小或相反,使光滑表面变粗,有类似于鲨鱼、海豚或高尔夫球的波纹面,来降低此阻力,并优化运动物体或机身的能量效率。
目的是使流过的流体对阻力的影响最小。
另一减少阻力的努力是在机翼及机身其部分上装小的旋涡发生器。
另一努力是安装一个沿穿过流体的机身飞行方向向前伸的锥杆形突出物。
这些尝试的目的是使流过机身主体的流体保持连续的层流,并尽可能抑制分离或紊流。另一方面,通过应用波纹面或粗糙面及旋涡发生器,在机身表面附近产生大量旋涡,使附面层破坏,
实质上所有这些方法都是为了帮助流体以最小摩擦滑过物体。
发明的公开:
本发明的目的是减轻流体对于运动物体的阻力。本发明另一目的是使物体能利用涡环非比寻常的效能。
为此,物体,例如鱼雷或火箭在其头部及或四周装上根据本发明的涡环发生器。其目的是在物体头部产生涡环,载着流体流过物体,同时直接在头部前方形成低压区。该低压区事实上是环形涡的核心。
产生的涡环与组成它的流体相对运动并且交叉滚动,很象轮子而不象滑块。著名的流体动力学家雷诺曾经指出,关于环形涡“自然界喜欢滚动而不是滑动”。
正是这个特征对环形涡的效率产生很大影响。
目前使用的旋涡发生器由平直或弯曲材料的小调整片组成,诸如那些位于飞机机翼前缘上的调整片,它们产生旋涡的紊流场横过机翼表面流动。
本发明特别适用于产生环绕物体的涡环,使流体在产生的涡环中流过物体。这样的发生器最好按黄金分割或Φ几何形状设计。Φ形代表阻力,摩擦力或自然界的阻力,最小的途径,这也是自然出现的旋涡的形状。
因此,本发明属于一种与流过流体的物体结合的涡环发生器,该涡环发生器可产生涡环形的流动流体流过物体
根据本发明一优选特征,涡环发生器按黄金分割或Φ图形进行设计。
根据本发明一优选特征,涡环发生器工作时是向心的。
根据另一方面,本发明属于一种涡环发生器,它的构件可与物体结合以便影响流过流体的流体流动,该构件包括的作用面能影响流体流动且其形状符合至少一种黄金分割的对数曲线。
根据优选实施例,涡环发生器与物体结合且包括一片或多片有作用面的导向片,导向片绕物体并沿物体上升呈螺旋状。
根据一优选实施例,涡环发生器从物体向前伸出。
根据一优选实施例,导向片呈涡旋形。
根据本发明一优选实施例,导向片的作用面设计成遵循黄金分割。
根据一优选实施例,导向片设计成符合黄金分割比例。
根据一优选实施例,涡环发生器包括一条或几条与物体结合在一起的沟道,导向片的路线环绕物体并沿物体前进呈螺旋状。
根据一优选实施例,沟道的路线设计成符合黄金分割比例。
根据一优选实施例,由物体与涡环发生器产生的涡环起因于它们穿过流体的运动。
根据一优选实施例,流体流过与物体结合在一起的涡环发生器时便产生涡环。
根据一优选实施例,涡环发生器与物体相对固定。
根据一优选实施例,涡环发生器与物体相对运动。
根据一优选实施例,涡环发生器的运动产生涡环。
根据一优选实施例,涡环发生器在动力操纵下转动可产生涡环并产生推进力。
本发明可根据对以下几个特定实施例的说明得到充分了解。
附图简要说明
参照附图进行说明,其中:
图1示出黄金分割形状。
图2是根据第一实施例的涡环发生器的侧视图。
图3是根据第一实施例的涡环发生器的前端视图。
图4是根据第一实施例的涡环发生器的后端视图。
图5是根据第一实施例的安装在物体上的涡环发生器的侧视图。
图6是根据第二实施例的与物体接触的涡环发生器的侧视图。
图7是根据第二实施例的与物体接触的涡环发生器的前端视图。
图8是根据第三实施例的与物体接触的涡环发生器的侧视图。
图9是根据第三实施例的与物体接触的涡环发生器的前端视图。
图10是具有根据第一及第三实施例的涡环发生器的的物体,其四周涡环流动情况的示意图。
图11是具有根据第二实施例涡环发生器的物体其四周涡环流动情况的示意图。
图12是环绕根据第一实施例涡环发生器旁的旋涡生成过程示意图。
具体实施例的详细说明
各实施例所包括的涡环发生器与物体结合在一起且能在与物体相对运动的流体中产生涡环,本涡环发生器的流道有一作用面,可影响流体流动,流体流过物体时形成涡环。
如上所述,在自然界的自然力的作用下运动的一切流体力图沿螺线或涡旋运动。这些螺线或涡旋一般遵守叫做黄金分割(Golden Ratio)的数学级数或裴波那奇(Fibonacci)式的级数。
这里所述实施例的作用面的相当部分在很大程度上按黄金分割或黄金分割比例进行设计的,因此这些实施例的特征是作用面呈螺旋形,且至少在很大程度上符合黄金分割或黄金分割比例的特征。黄金分割的特征示于图1,图中示出根据黄金分割比例的螺旋曲线的展开。在展开螺旋线时在等角半径(如E、F、G、H、I、J)处测得的曲线半径增量是常数。这可从各序列间半径的三角形表示法中看出,它相当于公式a∶b=b∶a+b大致符合1∶0.618且整条曲线上是一致的。
这些实施例的特征是,不仅X轴和Y轴确定符合黄金分割几何关系,而且Z轴或纵深也如此,这就是说导向片在三维上均符合黄金分割。
这些实施例的一个目标是使环形涡中发现的涡旋线予以复制。为此作用面在任何方向以等角的黄金分割螺线呈对数状扩大或收敛。若在这些作用面的表面上取任何二点,它们的比例为1∶0.618。作用面长度和圈数是任意的,它们设计成可与旋涡固有的流线形流线相配。
在第一实施例中及图2至5所示,涡环发生器(11)包括一组位于物体(12)头部(13)的导向片,在本说明书中,头部这个术语用于表示迎着正在接近物体的来流方向那部分物体。
涡环发生器(11)通过干扰流体与产生涡环物体的相对流体来产生涡环。组成涡环发生器的导向片从物体头部向前伸出且其形状为螺旋形。每片导向片用固有的反作用面(14)构成,它是凹形的且有三维弯曲的凹形特征,因此每一方向按遵循黄金分割的对数曲线弯曲。因此,这些导向片(11)共同形成了涡环发生器的凹形内表面。
此外,导向片背后的反作用面(15)离开内侧反作用面(14),且也有三维弯曲的凹形特征。各维弯曲符合根据黄金分割的对数曲线。因此,各向弯曲部分的形状和各向内反作用面(14)的弯曲一样。因此,背后的反作用面(15)共同形成导向片的凸面。
第一实施例的更改形式中,涡环发生器并不固定在头部而可与物体轴线共轴旋转。此外可机械传动发生器旋转,因而在产生涡环的同时提供推进力。
在第二实施例中,如图6、7所示,涡环发生器包括一组或几组在物体表面中的沟纹或凹槽(21),始于物体(22)的头部(23)或其附近,终于物体尾部(24)或其附近。沟或槽沿物体的路线环绕物体呈螺旋形,大体上符合黄金分割比例。
在第三实施例中,如图8及图9所示,涡环发生器包括一片或多片由物体表面向外延伸的保护片(31),始于物体(32)的头部(33)或其附近,终于物体尾部(34)或其附近。导向片设计成符合黄金分割的比例环绕并沿物体盘旋。
以上各实施例中的物体最好按对数等角Φ形螺线设计。其形状与所有涡系共同的Φ形旋涡相似。换言之,物体所占空间是气穴管中看的见的旋涡所见空间。
如图11所示,物体13被安置在旋涡16的核心。利用上述实施例1、2、3,物体头部与环形涡的形状准确配合。物体可以是空心的锥形,使流体能进入涡环,穿过核心行进。
图10、11示出环形涡16的发生,它们沿着物体移动/滚动。
运行时由于流体与物体的相对运动,流体被作用面11、21、31接触开始沿对数形旋涡形式旋转。当流体接触作用面时,旋转运动在涡环发生器底部(发生器与物体头部之间)产生低压区。这样降低了物体的附面层阻力。环形涡及/或势涡形成,如图10所见,环形涡沿物体壁将附面层卷成滚珠轴承般的球。在许多场合,涡环会脱离并产生一连串的脱离的涡环。留在物体后面的尾迹有涡环形状。
图12示出第一实施例涡环发生器11,可产生环形涡16,为此,在涡环发生器11与流体之间必须有相对运动。
这一运动的产生,可转动涡环发生器,使流体流过静止的涡环发生器,或推动物体及涡环发生器穿过流体。
应明白,本发明的范围不需要限于上述的特定范围。
本说明书中,除非上下文另有要求,包括这个词应理解为包含所述整体在内,但不排除其它的整体事物。
Claims (6)
1.一种涡环发生器,包括:具有前端和后端,及导向片的元件,导向片由元件向外伸出并由物体前端向后端伸展,该导向片具有螺旋构型,限定作用面具有弯曲部分符合黄金分割比例,其中,使用时,所述涡环发生器安装到物体的前端。
2.一种物体,其可减少流动流体中阻力,该物体具有与相对物体的流体流动方向成直线的轴;涡环发生器固定在物体上与物体相对固定,涡环发生器限定与轴同中心的螺旋形作用面,作用面由物体支撑的螺旋形导向片形成,该作用面附带流过物体的流体,该作用面的弯曲部分符合黄金分割比例或Φ形,所述流体流过所述物体时,由于物体和流体之间的相对运动,所述涡环发生器使作用面上流动的液体形成绕所述物体的涡环,涡环在所述物体上从所述涡环发生器向后运动。
3.一种物体,其可减少流动流体中阻力,该物体具有与相对物体的流体流动方向成直线的轴;涡环发生器固定在物体上与物体相对固定,涡环发生器限定与轴同中心的螺旋形作用面,作用面由形成在所述物体上的螺旋形槽形成,该作用面附带流过物体的流体,该作用面的弯曲部分符合黄金分割比例或Φ形,所述流体流过所述物体时,由于物体和流体之间的相对运动,所述涡环发生器使作用面上流动的液体形成绕所述物体的涡环,涡环在所述物体上从所述涡环发生器向后运动。
4.根据权利要求2所述的物体,其特征在于,涡环发生器由所述物体的前端向前伸出。
5.根据权利要求2至3中的任何一项权利要求所述的物体,其特征在于,形成的涡环发生器作为所述物体的一部分。
6.根据权利要求2至3中的任何一项权利要求所述的物体,其特征在于,涡环发生器作为分离部件固定于所述物体上。
Applications Claiming Priority (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
AUPR9827A AUPR982702A0 (en) | 2002-01-03 | 2002-01-03 | Vortex ring generator to reduce drag on a fuselage |
AUPR9827 | 2002-01-03 | ||
AUPS1352A AUPS135202A0 (en) | 2002-03-26 | 2002-03-26 | Vortex ring generator to reduce drag on a fuselage |
AUPS1352 | 2002-03-26 | ||
PCT/AU2003/000003 WO2003056190A1 (en) | 2002-01-03 | 2003-01-03 | Vortex ring generator |
Publications (2)
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CN1612979A CN1612979A (zh) | 2005-05-04 |
CN1612979B true CN1612979B (zh) | 2011-11-23 |
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CN038019329A Expired - Fee Related CN1612979B (zh) | 2002-01-03 | 2003-01-03 | 涡环发生器 |
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US (3) | US7673834B2 (zh) |
EP (1) | EP1470338A4 (zh) |
JP (1) | JP2005513385A (zh) |
CN (1) | CN1612979B (zh) |
AU (1) | AU2003201182B2 (zh) |
CA (1) | CA2471816C (zh) |
DE (1) | DE03726967T1 (zh) |
EA (1) | EA005545B1 (zh) |
IL (2) | IL162637A0 (zh) |
MX (1) | MXPA04006590A (zh) |
WO (1) | WO2003056190A1 (zh) |
ZA (1) | ZA200405898B (zh) |
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EA005545B1 (ru) | 2002-01-03 | 2005-04-28 | Пакс Сайентифик, Инк. | Генератор вихревого кольца |
AU2003903386A0 (en) | 2003-07-02 | 2003-07-17 | Pax Scientific, Inc | Fluid flow control device |
KR101168098B1 (ko) * | 2003-11-04 | 2012-07-24 | 팍스 싸이언티픽 인코퍼레이션 | 유체 순환 시스템 |
WO2005073560A1 (en) * | 2004-01-30 | 2005-08-11 | Pax Scientific, Inc | A vortical flow rotor |
EA009581B1 (ru) | 2004-01-30 | 2008-02-28 | Пакс Сайентифик, Инк. | Корпус для центрифугальных вентиляторов, насосов или турбин |
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WO2008042251A2 (en) | 2006-09-29 | 2008-04-10 | Pax Streamline, Inc. | Axial flow fan |
DE102010008623A1 (de) | 2010-02-19 | 2011-08-25 | Airbus Operations GmbH, 21129 | Anordnung von aerodynamischen Hilfsflächen für ein Luftfahrzeug |
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- 2003-01-03 IL IL16263703A patent/IL162637A0/xx active IP Right Grant
- 2003-01-03 CN CN038019329A patent/CN1612979B/zh not_active Expired - Fee Related
- 2003-01-03 CA CA 2471816 patent/CA2471816C/en not_active Expired - Fee Related
- 2003-01-03 EP EP03726967A patent/EP1470338A4/en not_active Withdrawn
- 2003-01-03 AU AU2003201182A patent/AU2003201182B2/en not_active Ceased
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2004
- 2004-06-20 IL IL162637A patent/IL162637A/en not_active IP Right Cessation
- 2004-07-02 US US10/884,032 patent/US7673834B2/en not_active Expired - Fee Related
- 2004-07-23 ZA ZA200405898A patent/ZA200405898B/en unknown
-
2007
- 2007-10-29 US US11/980,168 patent/US7766279B2/en not_active Expired - Fee Related
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2010
- 2010-08-02 US US12/848,943 patent/US7934686B2/en not_active Expired - Fee Related
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5139215A (en) * | 1982-11-26 | 1992-08-18 | The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Northern Ireland | Guided missiles |
US5100242A (en) * | 1987-03-20 | 1992-03-31 | Brian Latto | Vortex ring mixers |
CN1193377A (zh) * | 1995-07-10 | 1998-09-16 | 杰丹·D·哈曼 | 叶轮 |
Also Published As
Publication number | Publication date |
---|---|
IL162637A0 (en) | 2005-11-20 |
US20050269458A1 (en) | 2005-12-08 |
CA2471816A1 (en) | 2003-07-10 |
US20080265101A1 (en) | 2008-10-30 |
US7934686B2 (en) | 2011-05-03 |
US7766279B2 (en) | 2010-08-03 |
MXPA04006590A (es) | 2005-03-31 |
AU2003201182A1 (en) | 2003-07-15 |
AU2003201182B2 (en) | 2008-05-01 |
CN1612979A (zh) | 2005-05-04 |
US7673834B2 (en) | 2010-03-09 |
DE03726967T1 (de) | 2005-05-04 |
EP1470338A1 (en) | 2004-10-27 |
ZA200405898B (en) | 2006-06-28 |
EA200400903A1 (ru) | 2004-12-30 |
JP2005513385A (ja) | 2005-05-12 |
EA005545B1 (ru) | 2005-04-28 |
IL162637A (en) | 2007-10-31 |
US20110011463A1 (en) | 2011-01-20 |
EP1470338A4 (en) | 2012-01-11 |
CA2471816C (en) | 2011-04-19 |
WO2003056190A1 (en) | 2003-07-10 |
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