CN104334872A - A wind turbine with a ring airfoil shroud having a flap - Google Patents

A wind turbine with a ring airfoil shroud having a flap Download PDF

Info

Publication number
CN104334872A
CN104334872A CN 201380027360 CN201380027360A CN104334872A CN 104334872 A CN104334872 A CN 104334872A CN 201380027360 CN201380027360 CN 201380027360 CN 201380027360 A CN201380027360 A CN 201380027360A CN 104334872 A CN104334872 A CN 104334872A
Authority
CN
Grant status
Application
Patent type
Prior art keywords
edge region
flap
intermediate
trailing edge
wing
Prior art date
Application number
CN 201380027360
Other languages
Chinese (zh)
Inventor
W·M·小普雷兹
M·J·威尔
R·H·多尔德
E·达姆鲁皮纳
Original Assignee
奥金公司
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING WEIGHT AND MISCELLANEOUS MOTORS; PRODUCING MECHANICAL POWER; OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03DWIND MOTORS
    • F03D1/00Wind motors with rotation axis substantially parallel to the air flow entering the rotor 
    • F03D1/06Rotors
    • F03D1/065Rotors characterised by their construction, i.e. structural design details
    • F03D1/0675Rotors characterised by their construction, i.e. structural design details of the blades
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING WEIGHT AND MISCELLANEOUS MOTORS; PRODUCING MECHANICAL POWER; OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03DWIND MOTORS
    • F03D1/00Wind motors with rotation axis substantially parallel to the air flow entering the rotor 
    • F03D1/04Wind motors with rotation axis substantially parallel to the air flow entering the rotor  having stationary wind-guiding means, e.g. with shrouds or channels
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05BINDEXING SCHEME RELATING TO MACHINES OR ENGINES OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, TO WIND MOTORS, TO NON-POSITIVE DISPLACEMENT PUMPS, AND TO GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY
    • F05B2240/00Components
    • F05B2240/10Stators
    • F05B2240/12Fluid guiding means, e.g. vanes
    • F05B2240/122Vortex generators, turbulators, or the like, for mixing
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05BINDEXING SCHEME RELATING TO MACHINES OR ENGINES OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, TO WIND MOTORS, TO NON-POSITIVE DISPLACEMENT PUMPS, AND TO GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY
    • F05B2240/00Components
    • F05B2240/10Stators
    • F05B2240/12Fluid guiding means, e.g. vanes
    • F05B2240/123Nozzles
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05BINDEXING SCHEME RELATING TO MACHINES OR ENGINES OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, TO WIND MOTORS, TO NON-POSITIVE DISPLACEMENT PUMPS, AND TO GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY
    • F05B2240/00Components
    • F05B2240/10Stators
    • F05B2240/13Stators to collect or cause flow towards or away from turbines
    • F05B2240/133Stators to collect or cause flow towards or away from turbines with a convergent-divergent guiding structure, e.g. a Venturi conduit
    • YGENERAL 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
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02EREDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00Energy generation through renewable energy sources
    • Y02E10/70Wind energy
    • Y02E10/72Wind turbines with rotation axis in wind direction

Abstract

A ring airfoil with a voluminous leading edge region, an intermediate region, a trailing edge region including a flap. The ringed structural leading edge region combined with a rigid trailing edge region having intermediate discrete support portions extending therebetween provides sufficient rigidity to support the flap on the trailing edge region while using a membrane intermediate surface to form a portion of the intermediate region of the airfoil.

Description

带有具有襟翼的环形翼护罩的风力涡轮机[0001] 相关申请的交叉引用 Cross wind turbine with an annular shroud having a wing flap [0001] REFERENCE TO RELATED APPLICATIONS

[0002] 本申请分别要求于2012年4月5日提交的美国临时申请序列No. 61/620792和于2013年2月12日提交的美国临时申请序列No. 61/763805的优先权,其公开内容通过引用整体合并于此。 [0002] This application claims priority to US 2012 respectively 5 April filed priority to Provisional Application Serial No. 61/620792 and U.S. Provisional Application Serial No. on February 12, 2013 61/763805, filed, the disclosure of entirety is incorporated herein by reference.

背景技术 Background technique

[0003] 本发明涉及环形翼的技术领域,并且更特别地,涉及包括独特翼特性的护罩式涡轮机。 [0003] The present invention relates to the technical field of the annular wing, and more particularly, to a turbine shroud includes a unique characteristic of the wing. 更具体地,本发明教授的为针对改进的环形翼的实施例,所述改进的环形翼提供用于在维持性能同时减少侧向载荷和减少材料的使用的减小的横截面积。 More specifically, the present invention is a professor embodiment is directed to an improved annular wing, the wing is provided for an improved annular lateral load while reducing the cross sectional area reduction and a reduced use of material while maintaining performance. 带有与大致的弯曲平面表面接合的结构前缘的翼常见于轻型飞机和帆船领域。 Wing structure having a leading edge engageable with a generally planar surface of the curved light aircraft and boat common in the art. 弯曲平面表面定义为具有大致平行于下表面的上表面的那些。 It is defined as a curved surface having a plane substantially parallel to those on the surface of the lower surface. 与带有在上表面和下表面之间连续变化的距离的翼的横截面积相比,这种翼具有减小的横截面积。 Wing cross sectional area as compared to with the distance between the upper and lower surfaces of the continuous change, which wing has a reduced cross-sectional area. 用于发电机设备的公用级风力涡轮机具有包括转子的一至五个开放式叶片。 Utility grade wind turbine generator apparatus for machine having one to five open blades comprise a rotor. 转子将风能转换成驱动至少一个发电机的转矩,所述发电机直接地或通过传输装置可旋转地联结至转子以将机械能转化成电能。 The rotor converts wind into at least one driving torque of the generator, the generator is directly or rotatably coupled to the rotor through a transmission means to the mechanical energy into electrical energy.

[0004] 在美国专利申请序列No. 12/054050中已经描述了一种护罩式风力涡轮机,其公开内容通过引用整体合并于此。 [0004] In U.S. Patent Application Serial No. 12/054050 has described a shroud wind turbine, the disclosure of which is incorporated herein by reference in its entirety.

发明内容 SUMMARY

[0005] 本发明教授的实施例涉及一种带有横截面的环形翼,其横截面包括前缘部分(带有在上下表面之间变化的距离)、对称区域(关于穿过所述对称区域的弦线具有对称性,其中,在一种实施例中上表面大致平行于下表面)以及尾缘区域(在尾缘上设置有大致垂直于翼的弦线的襟翼)。 [0005] The teachings of the present invention relates to a wing having an annular cross section, which includes a leading edge portion of cross-section (with a distance variation between the upper and lower surfaces), symmetry area (on passing through the symmetric region having a chord line of symmetry, which in one embodiment is substantially parallel to the lower surface of the upper surface) and a trailing edge region (on the trailing edge disposed substantially perpendicular to the chord line of the wing flap embodiment). 与传统翼相比,在这种翼的尾缘上设置襟翼进一步减小了翼的横截面积。 Compared with a conventional wing flap arranged on the trailing edge of this blade is further reduced cross-sectional area of ​​the wing.

[0006] 当襟翼垂直于由此产生的翼的弦线设置时,中间对称区域中缺乏支撑结构将不允许襟翼发挥作用。 [0006] When the flap is provided perpendicular to the chord of the wing resulting lack of support structure of the intermediate region of the symmetrical flap allowed to play a role. 这样的在弯曲平面表面的尾缘上的襟翼将会弯曲,直到襟翼不能对越过翼的流动产生任何影响。 Such a flap on the trailing edge of a curved planar surface will bend until the flap does not have any influence on the flow over the wing. 在本发明教授的一种实施例中,襟翼的定向相对于环形翼的弦线可以是固定的。 In one embodiment of the present invention Professor embodiment, the orientation of the flap relative to the annular wing chord line may be fixed. 例如,在一种实施例中,环形翼可包括为襟翼提供足够结构的刚性尾缘,所述襟翼大致地垂直于翼的弦设置。 For example, in one embodiment, may include providing a rigid annular wing trailing edge structure is sufficient flap, the flap arranged substantially perpendicular to the chord of the wing.

[0007] 在一种实施例中,披露了一种空气动力学外形的环形翼。 [0007] In one embodiment, one kind is disclosed an annular wing aerodynamic profile. 绕中心轴线周向地延伸的主体具有由外表面和内表面形成的空气动力学结构。 Having aerodynamic structure formed by the outer and inner surfaces of the body about the central axis extending circumferentially. 外表面和内表面沿弧线相对于中心轴线轴向地延伸。 Outer and inner surfaces along an arc relative to the central axis extends axially. 主体包括前缘区域、尾缘区域以及在前缘区域和尾缘区域之间延伸的中间区域。 Body region includes a leading edge, a trailing edge region and an intermediate region between the leading edge region and trailing edge region extending. 前缘区域具有沿由主体的外表面和内表面限定的弧线延伸的不均匀的横截面厚度。 The leading edge region having a non-uniform cross-sectional thickness along an arc extending defined by the outer and inner surfaces of the body. 尾缘区域包括从其延伸并相对于主体的弦线成角度定向的襟翼,以允许流体流沿内表面流动来保持依附在内表面。 Comprises a trailing edge region and extending therefrom with respect to the chord line of the angled orientation of the body flap to allow flow of fluid along the inner surface of the flow remains attached to the inner surface.

[0008] 在一种示例的实施例中,披露了一种能量提取护罩式流体涡轮机,其包括能量提取总成和翼。 [0008] In one exemplary embodiment, the energy extraction shroud discloses a fluid turbine comprising an energy extraction assembly and the wing. 能量提取总成包括绕中心轴线径向地设置的转子。 Energy extraction assembly includes a rotor about a central axis disposed radially. 翼具有绕中心轴线周向地延伸的主体。 Having a flap body extends circumferentially about the central axis of. 主体具有由外表面和内表面形成的空气动力学结构。 The body having an aerodynamic structure formed by the outer and inner surfaces. 外表面和内表面沿弧线关于中心轴线轴向地延伸。 Outer and inner surfaces extending along an arc about the central axis axially. 主体包括前缘区域、尾缘区域以及在前缘区域和尾缘区域之间延伸的中间区域。 Body region includes a leading edge, a trailing edge region and an intermediate region between the leading edge region and trailing edge region extending. 前缘区域具有沿由主体的外表面和内表面限定的弧线延伸的不均匀的横截面厚度。 The leading edge region having a non-uniform cross-sectional thickness along an arc extending defined by the outer and inner surfaces of the body. 尾缘区域包括从其延伸并相对于主体的弦线成角度定向的襟翼,以允许流体流沿内表面流动来保持依附在内表面。 Comprises a trailing edge region and extending therefrom with respect to the chord line of the angled orientation of the body flap to allow flow of fluid along the inner surface of the flow remains attached to the inner surface.

[0009] 在一些实施例中,襟翼从尾缘区域垂直于弦线延伸,具有弦线长度的约十分之一至约三分之一的长度,并且/或者包括允许流体流过襟翼的至少一个穿孔。 [0009] In some embodiments, the flap extending from a trailing edge region perpendicular to the string, having about one tenth to about one third of the length of the chord line length, and / or permit fluid flow therethrough comprises a flap at least one perforation.

[0010] 在一些实施例中,襟翼从翼的尾缘延伸。 [0010] In some embodiments, the flap extending from the trailing edge of the blade.

[0011] 在一些实施例中,襟翼在第一环形结构和第二环形结构之间延伸,第一和第二环形结构向襟翼提供环向强度。 [0011] In some embodiments, the flap between the first and second annular structure extending annular structure, the first and second annular arrangement provides hoop strength to the flap.

[0012] 在一些实施例中,第一环形结构向主体的尾缘区域提供环向强度。 [0012] In some embodiments, the first annular ring to provide structural strength to the trailing edge region of the body.

[0013] 在一些实施例中,中间区域包括在前缘区域与尾缘区域之间延伸的至少一个中间支撑部分。 [0013] In some embodiments, the at least one intermediate support comprising a portion of the intermediate region between the leading edge region and trailing edge region extends. 在一些实施例中,中间支撑部分由刚性材料构成,并且/或者具有沿由主体的外表面和内表面限定的中弧线延伸的均匀的横截面厚度。 In some embodiments, the intermediate support portion is made of a rigid material, and / or having a uniform cross-sectional thickness extending defined by the outer and inner surfaces of the arc body.

[0014] 在一些实施例中,中间区域包括在前缘区域与尾缘区域之间延伸的至少一个中间膜部分。 [0014] In some embodiments, the intermediate film region comprises at least one intermediate portion extending between the leading edge region and the trailing edge region. 在一些实施例中,中间膜部分具有沿由主体的外表面和内表面限定的中弧线延伸的均匀的横截面厚度,并且/或者由非刚性材料构成。 In some embodiments, the intermediate film portion having a uniform cross-sectional thickness extending in an arc defined by the outer and inner surfaces along the body, and / or is made of non-rigid material.

[0015] 在一些实施例中,中间支撑部分向中间膜部分提供结构支撑。 [0015] In some embodiments, the intermediate portion of the support membrane provides structural support to the intermediate portion.

[0016] 实施例的任何结合或变换都是可以预想的。 [0016] or any combination of the alternative embodiment is envisioned to. 其它目的和特征从以下结合附图考虑的详细说明将会变得显而易见。 Other objects and features will become apparent from the following detailed description considered in conjunction with the accompanying drawings. 然而应该理解的是,附图仅作为示例说明而设计,并不作为本发明的范围的限定。 However, it should be understood that the drawings are designed merely as an illustration and not as limiting the scope of the present invention.

[0017] 简要说明 [0017] Short Description

[0018] 本发明涉及一种环形翼,其具有在前缘和尾缘处带有刚性部分的独特的翼截面形状,提供支撑膜中间部分并顾及到尾缘襟翼的环向强度。 [0018] The present invention relates to an annular wing, which wing has a unique cross-sectional shape with a rigid portion of the leading edge and trailing edge, and an intermediate portion providing a support film having regard to the trailing edge flap hoop strength. 在一些实施例中,结合刚性结构部分和非刚性膜部分可用来形成示例性的环形翼(为在翼的尾缘处控制边界层和为相比于传统的环形翼的通过所述环形翼的中心增加的吸力提供)。 In some embodiments, the binding moiety and the rigid portion may be non-rigid film to form an exemplary annular wing (and to control the boundary layer at the trailing edge of the blade as compared to conventional annular blade through said annular blade Center to provide increased suction). 这种翼提供了在产生引起环形翼内部相比于翼外部的压力差的空气动力循环时,使用轻量材料的方法。 This method provides a wing in the generation of induced internal annular wing compared to the external pressure differential wing aerodynamic circulation, using lightweight materials.

[0019] 在一种实施例中,环形翼围绕护罩式流体涡轮机的转子和发电设备。 [0019] In one embodiment, an annular shroud surrounding the fluid-wing turbine rotor and a power generating apparatus. 流体涡轮机可具有单一护罩,或可包括多重护罩。 It may have a single fluid turbine shroud, or shroud may comprise multiple. 护罩通常由可包括涡轮机护罩和喷射护罩的环形翼组成。 Typically consists of an annular shroud may include a turbine shroud and airfoil jet shroud.

[0020] 在一种实施例中,涡轮机护罩覆盖转子并包括在环形翼的尾缘处的混合元件(与提供混合-喷射泵的喷射护罩流体流流体连通)。 [0020] In one embodiment, the turbine rotor and the shroud covers mixing element comprises a ring at the trailing edge of the wing (and providing a hybrid - jet shroud fluid flow communication with a fluid injection pump). 护罩产生在涡轮机护罩的内侧上引起吸力的空气动力循环,并且所述护罩是与混合-喷射泵结合的紧密结合系统的一部分,其允许相比于无护罩式设计通过涡轮机转子的更多的空气的加速,从而增加可由转子提取的能量的量。 Generating an aerodynamic shroud causes circulation suction on the inside of the turbine shroud, and the shroud is mixed with - closely bound jet pump part of a system that allows the design compared to the non-shield through the turbine rotor more air is accelerated, thereby increasing the amount of energy extracted by the rotor.

[0021] 在流体动力学领域,术语"失速"指流体流分离发生的条件。 [0021] In the field of fluid dynamics, the term "stall" means a fluid stream separation conditions occur. 也就是说,紧密地围绕翼流动的流体开始从表面分离并变为湍流。 That is, the wing closely fluid flow around the beginning and becomes separated from the surface turbulence. 本文所教授的实施例基于只有混合器的实施例和混合-喷射涡轮机实施例。 Example embodiments taught herein is based only Example mixer and mixed - embodiments jet turbine. 本领域的技术人员会意识到本发明的示例性实施例可容易地应用于包括任何数量的管道式或护罩式流体涡轮机应用的任何环形翼。 Those skilled in the art will appreciate that exemplary embodiments of the present invention may be readily applied to any number of annular wing any pipeline or shield fluid turbine applications. 只有混合器的实施例和混合-喷射涡轮机实施例的描述不旨在限制本发明的范围,其仅仅是为了便于说明本发明的示例实施例。 Example embodiments only and mixing mixer - Example jet turbine description is not intended to limit the scope of the present invention, which is merely for convenience of description of the present exemplary embodiment of the invention. 通过混合涡轮机和/或混合-喷射涡轮机(MET)可以基本上防止气流从空气动力表面的分离,以有利地维持涡轮机的效率并有利地缓和扩压器失速。 It can substantially prevent flow separation from the aerodynamic surface of the jet turbine (MET), in order to advantageously maintain the efficiency of the turbine and advantageously alleviate diffuser stall - by mixing the turbine and / or mixing.

[0022] Kutta-Joukowski定理描述了任何封闭表面周围的循环。 [0022] Kutta-Joukowski Theorem describes any circulation around the closed surface. 所述循环引起升力并增加通过护罩式涡轮机的气流。 The lift circulation caused by the air flow and increase the turbine shroud. 所述定理确定由封闭体内一个单位范围所产生的升力并说明当环量Γ ~为已知时,柱体的每单位范围的升力L(或L')可使用下式计算: The lift is determined by the theorem of a unit enclosure and described the scope of the generated amount when the ring Γ ~ is known, the lift cylinder per unit range L (or L ') can be calculated using the formula:

[0023] Lj = P ^V00 Γ ^ [0023] Lj = P ^ V00 Γ ^

[0024] 公式1 [0024] Equation 1

[0025] 这里P 和V00分别为柱体的远上游的流体密度和流体速度。 [0025] where P is the fluid density and V00, respectively, and far upstream of the fluid velocity of the cylinder. 环量Γ "在下式中定义为线性积分: Circulation Γ "is defined in the following formula as a linear integrator:

Figure CN104334872AD00061

[0026] [0026]

[0027] 公式2 [0027] Equation 2

[0028] 通过对混合和/或喷射护罩翼的尾缘上空气动力修改区域(AMR)的使用,改进的循环提供了护罩式润轮机的增强的性能。 [0028] using the modified region (AMR) by the trailing edge of the aerodynamic forces on the mixing and / or wings of the shroud injection, improved cycle provides enhanced performance shrouded turbine run. Kutta条件(为Kutta-Joukowski定理的函数) 控制由翼产生的循环并通常阻止来自空气动力表面的流动分离直到流动到达尾缘。 Kutta condition (as a function of Kutta-Joukowski theorem) generated by the control cycle and normally prevents flow from the wing aerodynamic surface of the separation until the flow reaches the trailing edge.

[0029] 流体移动通过或穿过翼形状并产生气动力。 [0029] or by moving through the fluid and generating aerodynamic blade shape. 气动力的垂直于流体流的方向的分力称为升力,并且平行于流体流的方向的分力称为阻力。 Component force component perpendicular to the direction of fluid flow in aerodynamic lift is referred to, and parallel to the direction of fluid flow resistance is referred to. 此外,翼具有吸力表面和压力表面(通过它们产生升力)。 In addition, the wing having a suction surface and a pressure surface (lift generated by them). 翼吸力侧由从当前流动转开的翼表面限定。 Airfoil suction side defined by the current flowing from the wing surface turned away. 通常顶部(或外部) 和底部(或内部)翼表面由弯曲的前缘和锐利的尾缘连接。 Typically the top (or outer) and a bottom (or inner) surfaces of wings connected by a curved leading edge and sharp trailing edge. 翼的弧线在一端剖切此尾缘并延伸至前缘的尖端或最上风点。 Arc taken at one end of the wing trailing edge and this extends to the tip or leading edge of the most upwind point. 空气动力循环是流动转向的结果,并通常被在翼吸力侧上的流动分离限制。 Aerodynamic flow circulation is diverted a result, flow separation and is typically limited to the suction side of the airfoil.

[0030] 本发明的示例实施例提供了通过修改穿过翼空气动力表面(尤其是接近尾缘的) 的压力侧的气流,来获得与传统翼结构相比增加的翼环量或有效率的流动折转。 [0030] exemplary embodiment of the present invention through the modification provided by the wing aerodynamic surface (especially near the trailing edge) side of the airflow pressure, to obtain increased compared to the conventional wing structure or wing circulation efficient turn off the flow. 在本发明的示例实施例中,环量的增加可通过增加翼的压力侧的表面折转实现。 In an exemplary embodiment of the present invention, the surface may be increased to increase the amount of the ring blade pressure side is achieved by folding. 在压力侧增加折转是可能的,因为表面转向流动方向并且流动不易于从压力侧上的表面分离。 Increasing the pressure side is folded possible, since the surface of the steering flow direction and the flow is not easily separated from the surface on the pressure side. 在一种实施例中,增加流动折转可通过在翼的顶部(或外部)表面(即压力侧)上使用尾缘襟翼实现。 In one embodiment, to increase the flow may be folded by using a trailing-edge flap wing implemented on top (or outer) surface (i.e., the pressure side).

[0031] 在示例实施例中,襟翼可以是平板或自尾缘的其它突出物。 [0031] In the exemplary embodiment, the flap can be flat or other projection from the trailing edge. 在一些实施例中,尾缘襟翼的长度可以是在翼的前缘与尾缘之间延伸的翼弦的长度的近似1-30%。 In some embodiments, the length of the trailing edge flap may be approximately 1-30% of the length of the chord between the leading edge and the trailing edge of the blade extends. 尾缘襟翼可垂直于弦线定向并可设置在位于或接近于尾缘处的翼压力侧上。 Trailing edge flap is oriented perpendicular to the string may be provided and may be located on or near the trailing edge of the airfoil pressure side. 在一些实施例中,尾缘襟翼是穿孔的。 In some embodiments, the trailing edge flap is perforated. 所述穿孔可以允许襟翼提供有效的高度以在提供减小的阻力同时产生增加的环量。 The perforations may allow the flaps to provide an effective height to provide a reduced resistance increased circulation produced simultaneously.

[0032] 襟翼的使用通过引入襟翼的反向旋转漩涡尾而有效地改变了环形翼的尾缘区域中的流场,所述襟翼的反向旋转漩涡尾改变了所述区域中的Kutta条件和环量。 [0032] The use of flap vortices by introducing a reverse rotation of the tail flap effectively changed the flow field region of the annular wing trailing edge in reverse rotation of the swirl flap has changed the tail region Kutta condition and circulation.

附图说明 BRIEF DESCRIPTION

[0033] 图1为本发明的示例性环形翼的前向透视图。 [0033] Figure 1 a front perspective view of an exemplary annular blade of the present invention.

[0034] 图2为图1的示例性翼的侧向截面视图。 [0034] FIG 2 is an exemplary sectional view of the wing 1 side.

[0035] 图3为图1的示例性翼的侧向截面视图。 [0035] FIG. 3 is a diagram of an exemplary cross-sectional view of the wing 1 side.

[0036] 图4为图1的实施例的示例性翼的详细侧向截面视图。 A detailed cross-sectional side view [0036] FIG. 4 is a diagram of an exemplary embodiment of the wing 1.

[0037] 图5为带有流线的图1的实施例的示例性翼的侧向截面视图。 [0037] FIG. 5 is a flow line with a lateral sectional view of an exemplary embodiment of the wing.

[0038] 图6为本发明的另一示例性环形翼的前向透视图。 Annular front wing according to another exemplary of the invention [0038] FIG. 6 to FIG perspective.

[0039] 图7为图6的示例性翼的侧向截面视图。 [0039] FIG. 7 is a diagram of an exemplary cross-sectional view of the wing 6 side.

[0040] 图8为示例性护罩式涡轮机的前向右侧透视图,其涡轮机护罩对应于图1的示例性翼。 [0040] FIG. 8 is a right side perspective view of the front to the exemplary turbine shroud, the turbine shroud corresponds to an exemplary airfoil of FIG.

[0041] 图9为示例性护罩式涡轮机的前向右侧透视图,其涡轮机护罩对应于图6的示例性翼。 [0041] FIG. 9 is a front shroud of an exemplary turbine to the right side perspective view of the turbine shroud which corresponds to an exemplary airfoil of FIG.

[0042] 图10为包括了图1和6的示例性翼的示例性混合-喷射涡轮机的前向右侧透视图。 [0042] FIG. 10 is an exemplary hybrid includes an exemplary blade 1 and FIG. 6 - right front perspective view of the jet turbine.

[0043] 图11为图10的示例性混合-喷射涡轮机的后向右侧透视图。 [0043] FIG. 11 is a diagram of an exemplary hybrid 10 - right side perspective view of the jet turbine.

[0044] 图12为经外翻混合翼部分截取的图10和图11的示例性混合-喷射涡轮机的详细截面侧向透视图。 [0044] FIG. 12 is everted by mixing wing portion taken exemplary hybrid FIGS. 10 and 11 - A detailed cross-sectional side perspective view of the injection turbine.

[0045] 图13为经内翻混合翼部分截取的图10和图11的混合-喷射涡轮机的详细截面侧向透视图。 [0045] FIG. 13 is mixed 10 and 11 turn, taken FIG mixing wing portion in Canon - detailed cross-sectional side perspective view of the jet turbine.

[0046] 图14为设置在图10和图11的示例性混合喷射涡轮机的尾缘区域上的襟翼的详细视图。 [0046] FIG. 14 is a detailed view of the flap is provided on the trailing edge region of an exemplary turbine jet mixing FIGS. 10 and 11.

[0047] 图15为另一示例性混合-喷射涡轮机的前向右侧透视图,其涡轮机护罩和喷射护罩具有小面构造。 [0047] FIG. 15 is another exemplary hybrid - the front right side perspective view of the jet turbine, which turbine shroud having a shroud and injection facet configuration.

[0048] 图16为经外翻混合翼部分截取的图15的示例性混合-喷射涡轮机的详细截面侧向透视图。 [0048] FIG. 16 is an exemplary hybrid 15 via the mixing wing portion everted FIG taken - detailed cross-sectional side perspective view of a jet turbine.

[0049] 图17为另一示例性护罩式涡轮机的前向右侧透视图,其涡轮机护罩具有小面构造。 [0049] FIG. 17 is a front of another exemplary turbine shroud, the turbine shroud having a small surface configured to right side perspective view.

具体实施方式 detailed description

[0050] 本发明的组件、工艺以及装置的更加透彻的理解可通过参考附图获得。 [0050] a more thorough understanding of the components, processes and apparatus of the present invention can be obtained by reference to the accompanying drawings. 这些图旨在说明本发明,而不是要示出相关大小和尺寸或者限制示例性实施例的范围。 These figures are intended to illustrate the invention and are not intended to illustrate the relevant sizes and dimensions or to limit the scope of the exemplary embodiments.

[0051] 尽管以下描述中使用了特定的术语,但这些术语仅仅指的是附图中的特定结构, 并不是用来限制本发明的范围。 [0051] Although specific terms used in the following description, these terms refer only to the particular structure of the drawings, it is not intended to limit the scope of the present invention. 应该理解,相似的数字标记指代相似功能的组件。 It should be understood that like numerals refer to like component functionality.

[0052] 当与数量一起使用时,术语"大约"包括声明的值并且还具有由上下文所述的意思。 [0052] When used with a quantity, the term "about" includes values ​​declared by the context, and also having the meaning. 例如,它至少包括与特定数量的测量相关联的误差度。 For example, comprising at least a certain degree of error associated with measurement of the number. 当用在一范围的上下文中时,术语"大约"也应被视为公开由两个端点的绝对值所限定的范围。 When used in the context of a range, the term "about" should also be considered to be disclosed by the absolute value of the two endpoints defined range. 例如,范围"从大约2至大约4"也公开范围"从2至4"。 For example, the range of "from about 2 to about 4" also discloses the range "from 2 to 4."

[0053] 护罩式涡轮机可以包括涡轮机护罩(在涡轮机护罩的尾端上,带有或不带有混合叶)。 [0053] The turbine shroud may include a turbine shroud (on the trailing end of the turbine shroud, with or without mixing blade). 如上所述,包括混合护罩的护罩式涡轮机是环形翼(其中可以使用本发明的示例性实施例)的一种适合的示例。 As described above, comprising mixing shrouded turbine shroud is an annular flap (which may be used exemplary embodiments of the present invention) A suitable example. 所述涡轮机护罩包括弧形护罩,其中,护罩是大致的环形翼。 The turbine shroud includes an arcuate shroud, wherein the shroud is substantially circular wing. 涡轮机护罩包含转子,其从主流体流中提取能量。 Turbine shroud comprising a rotor, which extracts energy from the primary stream. 与无护罩式流体涡轮机相比,由于更高的流速,涡轮机护罩提供通过转子的允许增加的能量提取的增加的流动。 Compared to non-fluid turbine shroud, due to the higher flow rates, the turbine shroud provides increased flow through the rotor to allow increased energy extraction.

[0054] 混合-喷射涡轮机(MET)可使用混合/喷射泵提供从流体流中产生能量的改进的方法。 [0054] Mixed - jet turbine (MET) can be mixed / jet pump provides an improved method of generating energy from the fluid stream. 如前面所述,MET是环形翼(其中可以使用本发明的示例性实施例)的一种适合的示例。 As previously described, MET is an annular flap (which may be used exemplary embodiments of the present invention) is a suitable example. 混合-喷射涡轮机包括串联的弧形护罩和混合/喷射泵,其中,每个护罩为大致的环形翼。 Mixed - jet turbine shroud includes an arcuate series of mixing and / jet pump, wherein each of the shroud is substantially circular wing. 主护罩包含转子,其从主流体流中提取能量。 A rotor comprising a main shield, which extracts energy from the primary stream. 与无护罩式流体涡轮机相比,由于更高的流速,串联的弧形护罩和喷射器提供通过转子的允许增加的能量提取的增加的流动。 Compared to non-fluid turbine shroud, due to the higher flow rates, a series of arcuate shroud and ejector provide increased flow allows for increased energy extracted by the rotor. 混合/喷射泵将能量从旁流转移至转子尾流,所述转子尾流允许通过转子的更高的每单位质量流量的能量。 Mixer / ejector pump rotor energy to move the sidelines wake flow, the rotor wake energy allows higher mass flow rate per unit rotor. 这两种作用加强了涡轮机系统的整体电力生产。 These two effects enhance the overall power production of the turbine system.

[0055] 本发明所用的术语"转子"指其中一个或多个叶片附接至轴并且能够旋转,允许对来自风旋转叶片的电力或能量的提取的任何总成。 [0055] As used herein, the term "rotor" refers to any assembly which one or more blades attached to a shaft and can be rotated to allow the extraction of power or energy from wind rotating the blades. 示例转子包括类似于螺旋桨的转子或转子/定子总成。 Example rotor comprises a rotor similar to a propeller or a rotor / stator assembly. 任何类型的转子都可被包围在本发明的流体涡轮机中的涡轮机护罩内。 Any type of rotor may be surrounded by the fluid turbine according to the present invention the turbine shroud.

[0056] 护罩的前缘可被视为翼的前部,并且翼的尾缘可被视为翼的后部。 [0056] The leading edge of the shroud may be regarded as the front portion of the wing, and the trailing edge of the blade may be regarded as a rear wing. 更加接近于翼的前部定位的翼的第一组件可被视为更加接近于翼的后部定位的第二组件的"上游"(即, 第二组件为第一组件的"下游")。 Positioned closer to the front wing of the first blade assembly may be regarded as a second component closer to the rear wing positioned "upstream" (i.e., the second component of the first component "downstream"). 另外,本发明所使用的术语"内表面"限定向内地面朝翼的中心轴线的环形翼的表面。 Further, terms used herein, "inner surface" defines an annular surface facing inwardly of the airfoil wing of the central axis. 本发明所使用的术语"外表面"限定向外地背离翼的中心轴线的表面,使得内表面比外表面更接近于中心轴线。 The terms used in the present invention, "outer surface" defines a surface outwardly away from the central axis of the blade, such that the inner surface closer to the center than the outer surface of the axis. 同样地,本发明所使用的环形翼的术语"吸力侧"或"低压侧"指翼的内部(即,内表面的径向向内),并且本发明所使用的翼的术语"压力侧"指翼的外部(即,从外表面径向向外)。 Likewise, the annular wing used in the present invention, the term "suction side" or "low pressure side" refers to the internal wing (i.e., the inner surface of the radially inwardly), and the blade used in the present invention, the term "pressure side" means an outer wing (i.e., radially outward from the outer surface).

[0057] 本发明所使用的术语"环向强度"指结构抵抗绕大致的圆柱形状或环形形状结构的圆周的径向变形力的能力和提供尺寸稳定性的能力。 The term used in the invention are [0057] present "hoop strength" refers to the ability to resist structural deformation of the radial force about the circumference of a generally cylindrical shape or a ring shape structure and ability to provide dimensional stability. 例如,本发明所述的翼的示例性实施例可包括具有环向强度的刚性尾缘区域以抵抗流体流的变形力。 For example, an exemplary embodiment of the wing according to the present invention may comprise a circumferential trailing edge region of the rigid strength to resist the deformation force of the fluid flow.

[0058] 在一种实施方案中,本发明涉及一种环形翼,其包括通常为刚性结构的前缘区域、 由结构刚性和结构非刚性部分形成的中间区域以及通常为刚性结构的尾缘区域。 [0058] In one embodiment, the present invention relates to an annular wing, which includes a generally rigid structure of the leading edge region, the intermediate region is formed by a non-rigid and rigid structure and the partial structure of the trailing edge region of the rigid structure generally . 环形翼还包括位于尾缘部分上的襟翼,其大致地垂直于翼的弦。 Further comprises an annular wing flap on the trailing edge portion, which is substantially perpendicular to the wing chord. 襟翼相对于弦线的定向可以是固定的。 Flap relative to the orientation of the strings can be fixed. 在一种实施例中,环形翼的示例性实施例可以被实施为涡轮机护罩或涡轮机混合护罩, 其包括围绕转子的内翻段和外翻段,并且/或者环形翼的示例性实施例可以被实施为喷射护罩,其通常围绕涡轮机护罩或涡轮机混合护罩的出口。 In one embodiment, an exemplary embodiment of the annular blade may be implemented as turbine shroud or the turbine shroud mixture comprising varus and valgus segments around the rotor section and / or the exemplary embodiment of the annular wing injection may be implemented as a shroud, which is usually mixed outlet shroud around the turbine shroud or the turbine.

[0059] 图1为示例性环形翼100的前向透视图。 [0059] FIG. 1 is a front perspective view of an exemplary annular wing 100. 翼100可具有绕中心轴线105周向延伸的主体102。 Wing 100 may have a circumferentially extending about the central axis 105 of the body 102. 主体102包括前缘区域112、具有一个或多个中间膜部分138和一个或多个中间支撑部分139的中间区域115以及具有襟翼136的尾缘区域116。 Body 102 includes a leading edge region 112 having one or more intermediate film portion 138 and one or more intermediate supporting portion 139 of the intermediate region 115 and a trailing edge region 116 of the flap 136. 前缘区域112可包括翼100的前缘162,并且尾缘区域116可包括翼100的尾缘166。 The leading edge region 112 may comprise a leading edge 100 of the wing 162 and the trailing edge region 116 may comprise a trailing edge 166 of the wing 100. 中间区域115的一个或多个中间部分138和139可在前缘区域112与尾缘区域116之间延伸,以将前缘区域112机械地结合至尾缘部分116。 An intermediate region 115 or more intermediate parts 138 and 139 may extend between the trailing edge regions 112 and 116 in the leading edge region to the leading edge region 112 is mechanically coupled to the trailing edge portion 116. 一个或多个中间膜部分138可以由例如本发明所述的一种或多种半刚性和/或非刚性材料形成,并且一个或多个中间支撑部分139可以由例如本发明所述的一种或多种半刚性和/或刚性材料形成。 One or more intermediate film 138 may be formed from the present invention, for example, one or more of the semi-rigid and / or non-rigid material, and one or more intermediate support portions 139 may be formed of one of the present invention e.g. or more semi-rigid and / or rigid material. 在一种示例性实施例中,当使中间膜部分形成翼100的中间区域115的表面时,环形结构的刚性前缘区域与刚性尾缘区域和中间离散支撑部分结合提供足够的刚性,以支撑位于尾缘区域116上的襟翼136使其与弦线和弧线为固定的关系。 In an exemplary embodiment, when the intermediate portion of the film forming surface of the intermediate region 115 of the wing 100, the rigidity of the leading edge region and trailing edge region of the rigid support and the intermediate portion of the annular structure the discrete binding provide sufficient rigidity to support region 116 is located on the trailing edge flap 136 so that the chord line and the arc to a fixed relation. 从而,翼100的结构便于襟翼136与弦线140之间以及襟翼136与中弧线170之间形成固定的角度关系。 Thus, the structure 100 facilitates the wing chord between the flap 136 and the flaps 140 and 136 are formed in a fixed angular relationship between the arc 170. 本发明所述的包括襟翼(例如襟翼136和236)的翼100的示例性实施例可产生表现出如具有更大弦长度且不具有襟翼的传统翼的相似性能特性的环形翼。 According to the present invention comprises flaps (e.g., flaps 136 and 236) of the exemplary embodiment of the wing 100 may generate exhibit a greater chord length and not having such a conventional wing flap having performance characteristics similar to the annular wing.

[0060] 在一种示例性实施例中,所述一个或多个中间支撑部分139可提供结构支撑,以在前缘部分112与尾缘部分116之间支撑主体102。 [0060] In an exemplary embodiment, the one or more intermediate support portion 139 may provide structural support to support the trailing edge portion 116 between the leading edge portion 112 in the body 102. 中间支撑部分139可彼此隔开并且可以绕中心轴线105周向地和离散地分布。 Middle support portion 139 may be spaced apart from one another and can be distributed circumferentially about the central axis 105 and discretely. 中间支撑部分139可被限定尺寸并且/或者设置成指定前缘部分112与尾缘部分116之间的空间关系和/或一个或多个中间膜部分138的形状。 Middle support portion 139 may be defined size and / or arranged to specify spatial relationships between the leading edge portion 112 and trailing edge portion 116 and / or the shape of one or more intermediate film portion 138. 如一种实施例中的一种示例,所述一个或多个中间支撑部分139可设置翼100的前缘与尾缘之间的距离,其相当于翼100的弦线。 An embodiment of an exemplary embodiment, the one or more intermediate supporting portion 139 may be disposed a distance between the leading and trailing edges of the wings 100, 100 which corresponds to the chord of the wing. 如一种实施例中的另一示例,所述中间支撑部分139可以被构形为朝向尾缘区域116锥形远离中心轴线105,使得尾缘部分的直径大于前缘部分112的直径。 An exemplary embodiment in another embodiment, the middle support portion 139 may be shaped to taper towards the trailing edge region 116 away from the central axis 105, such that the diameter of the trailing edge portion is larger than the diameter of the leading edge portion 112. 在一些实施例中,所述一个或多个中间膜部分138可大致地依照中间支撑部分139的外形。 In some embodiments, the one or more portions of the intermediate film 138 may be substantially in accordance with the outer shape portion 139 of the intermediate support. 在一些实施例中,所述一个或多个中间部分138可独立于所述一个或多个中间支撑部分形成外形。 In some embodiments, the one or more intermediate portion 138 may be independent of the one or more intermediate supporting portion is formed profile.

[0061] 在一些实施例中,前缘区域112、尾缘区域116以及一个或多个中间支撑部分139 可整体地成形为单个整体单元,并且一个或多个中间膜部分138可分别地附接以形成主体102。 [0061] In some embodiments, the leading edge region 112, 116 and one or more intermediate trailing edge region of the support portion 139 may be integrally formed as a single integral unit, and one or more intermediate film 138 may be respectively attached to form the body 102. 在一些实施例中,前缘区域112、尾缘区域116、一个或多个中间部分138以及一个或多个中间支撑部分139可以是机械地结合在一起形成主体102的单独的组件。 In some embodiments, the leading edge region 112, 116, one or more intermediate parts 138 and one or more intermediate trailing edge region of the support portion 139 may be mechanically joined together to form a single assembly body 102.

[0062] 可以用来形成翼100的前缘区域112、尾缘区域116和/或一个或多个中间支撑部分139的塑料材料的一些实例,或可以用来形成翼100的前缘区域112、尾缘区域116和/ 或一个或多个中间支撑部分139的部分的塑料材料的一些实例可以包括,但不局限于诸如聚烯烃或聚酰胺的聚合物、碳复合材料和/或金属。 [0062] can be used to form the leading edge region 100 of the wing 112, the trailing edge region 116 and / or one or more intermediate supports Some examples of plastics material portion 139 or 100 may be used to wing leading edge region 112 is formed, Some examples of plastics material portion 139 of the trailing edge region 116 and / or one or more intermediate supports may include, but are not limited to, a polyolefin or polyamide polymer, carbon composite materials and / or a metal, such as. 聚烯烃的一些实例包括聚丙烯和聚乙烯,例如高密度聚乙烯(HDPE)和低密度聚乙烯(LDPE)。 Some examples of polyolefins include polypropylenes and polyethylenes such as high density polyethylene (HDPE) and low density polyethylene (LDPE). 聚酰胺的一些实例包括尼龙。 Some examples of polyamides include nylon. 在一些实施例中,聚氯乙烯和塑料溶胶可用于形成前缘区域112和尾缘区域116。 In some embodiments, a polyvinyl chloride plastisol, and it may be used to form the leading edge region and trailing edge region 112 116.

[0063] 可用来形成中间膜部分138的材料的一些实例可包括但不局限于织物、聚合物膜、薄金属板、薄复合材料、船舶热缩包装等。 [0063] Some examples may be used to form the intermediate portion 138 of the film material may include, but are not limited to, a fabric, a polymer film, a thin metal plate, a thin composite material, shrink packaging vessel. 对于使用织物的实施例,织物可以浸渍有聚合物树脂(如聚氯乙烯)或聚合物膜(如改性聚四氟乙烯)。 For embodiments using the fabric, the fabric may be impregnated with a polymer resin (e.g., polyvinyl chloride) or polymer film (e.g., modified polytetrafluoroethylene). 聚合物膜的一些实例包括但不限于聚氯乙烯(PVC)、聚氨酯、多氟代聚合物、类似组合物的多层膜等。 Some examples of polymer films include, but are not limited to polyvinyl chloride (PVC), polyurethanes, fluorinated polymers, multilayer films of similar composition. 聚氨酯膜可以是耐久的并且可以具有良好的耐候性。 Polyurethane film may be durable and may have good weather resistance. 聚氨酯膜的脂族版本通常可以是耐紫外线辐射的。 Version aliphatic polyurethane film may be generally resistant to ultraviolet radiation. 多氟代聚合物的一些实例包括聚偏二氟乙烯(PVDF)和聚氟乙烯(PVF)。 Some examples of polyfluorinated polymers include polyvinylidene fluoride (PVDF) and polyvinyl fluoride (PVF). 市场上可买到商标名为KYNAR⑧和TEDLAR⑧1的商品。 Available under the trade name KYNAR⑧ and TEDLAR⑧1 commodity on the market. 多氟代聚合物通常具有非常低的表面能,从而允许其表面在一定程度上保持没有污垢和碎屑,并且与具有较高表面能的材料相比可以更容易地使冰脱落。 Polyfluorinated polymers generally have a very low surface energy, so as to allow a surface kept free of debris and dirt to some extent, as compared with a material having a higher surface energy of the ice can be more easily detached.

[0064] 在示例性实施例中,用于形成翼100和/或其部分的一种或多种材料可以用例如高结晶性的聚乙烯纤维、聚芳基胺纤维和聚芳酰胺的增强材料来增强。 [0064] In an exemplary embodiment, for the 100 and / or one or more materials may be used, for example, part of a high crystallinity polyethylene fibers, poly arylamine fiber reinforcing material and aramid forming flap enhanced.

[0065] 前缘区域112、尾缘区域116、一个或多个中间支撑部分138和/或一个或多个中间膜部分139可以由例如包括两层、三层或更多层的多层材料形成。 [0065] The leading edge region 112, 116, one or more intermediate trailing edge region of the support portion 138 and / or one or more portions of the intermediate film 139 may be formed from a multilayer material comprising two, three or more layers . 多层构造可增加强度、 抗水性、紫外线(UV)稳定性和其它功能。 Increase the strength of the multilayer structure, water resistance, ultraviolet (UV) stability and other functions.

[0066] 在一些实施例中,翼的前缘区域112可以是诸如环氧浸渍的无碱玻璃纤维冰铜的夹层复合材料,并且夹层复合材料内的空间可用泡沫填充。 [0066] In some embodiments, the wing leading edge region 112 may be a sandwich, such as E-glass fiber composite matte epoxy impregnated, and the space available inside the sandwich composites filled with foam. 这种构造提供了具有整体低密度的高梁刚度的结构。 This configuration provides a structure having a low density of the overall stiffness sorghum.

[0067] 图2为沿图1的线2-2的本发明的环形翼的示例性实施例的截面视图,描绘了翼100的中间膜部分138之一。 Sectional view of an exemplary embodiment of the present invention, an annular blade [0067] Figure 2 is taken along line 2-2 of Figure 1, illustrating the intermediate portion of the membrane 100 is one of the wing 138. 前缘区域112可从前缘162延伸至中间区域115。 The leading edge region 112 may extend from the leading edge 162 to the intermediate region 115. 前缘区域112可具有带有在内表面132 (即吸力侧表面132)与外表面134 (即压力侧表面134)之间的变厚度ΊΥ的体积形式,从而形成变厚度IY的体积。 The leading edge region 112 may have the form of a volume with a variable thickness between the inner surface 132 (i.e., suction side surface 132) and the outer surface 134 (i.e., pressure side surface 134) ΊΥ to form a variable thickness IY volume. 翼100的前缘162可以是大致圆形的、 牛鼻形的或者其它形状的,以形成用于将流体分成至少两股(例如,沿内表面132的吸力侧和沿外表面134的压力侧)的空气动力表面。 The leading edge 100 of the wing 162 may be substantially circular, or other shapes bovine shaped to form (e.g. pressure side, the suction side along the inner surface 132 and along the outer surface 134) for fluid into at least two the aerodynamic surface. 前缘区域112的截面形状可沿中弧线170 增加截面厚度ΊΥ锥形远离前缘162,并且接着减小截面厚度IY锥形朝向中心弧线或中弧线170,至中间膜部分138之间的接合处131,使得前缘区域112的截面厚度IY大致地从前缘162到接合处131变化,将前缘区域112机械地结合至中间膜部分138。 Cross-sectional shape of the front edge region 112 may be increased in cross-sectional thickness of the arc 170 away from the leading edge 162 along the tapered ΊΥ, and then tapered to reduce the cross-sectional thickness toward the center IY arc or arcs 170, 138 between the intermediate portion of the film junction 131, such that the leading edge region 112 is substantially IY sectional thickness from the leading edge 162 to the junction 131 changes, the leading edge region 112 mechanically coupled to an intermediate portion of the film 138. 中心弧线或中弧线170大致地定位在翼100的分别地沿翼100的纵向范围的外表面132与内表面134之间的中间位置。 Center arc or arcs 170 are positioned substantially at an intermediate position between the outer surface of the wing 100 along the longitudinal extent of the wings 100 are respectively 132 and the inner surface 134.

[0068] 如图2所示,弦140限定在翼100的前缘162与尾缘166之间的翼100的长度,其可基于中弧线170确定。 [0068] As illustrated, the string 162 defines 1402, which may determine the length of the wing trailing edge 100 between the arc 166 based on the leading edge 170 of the wing 100. 翼100的截面厚度可对应于垂直于中弧线170所测量的从翼100 的外表面134到翼100的内表面132的距离,并且可随着沿中弧线170的距离变化,使得翼100的截面厚度在从前缘162到尾缘166的翼200的长度上变化。 Cross-sectional thickness of the blade 100 may correspond to 170 measured perpendicular to the mean camber line from the airfoil outer surface 100 to inner surface 134 of the wing 100 from 132, and may change with distance along the arc 170, such that flap 100 cross-sectional thickness variation over the length from the leading edge 162 to the trailing edge 166 of the flap 200. 由前缘区域112中的表面132U34形成的内部区域(或体积)113可以是中空的,或者可以用用于提供结构刚性和形状的支撑部件填充。 By the leading edge region of the inner region 112 is formed in a surface of 132U34 (or volume) 113 may be hollow, or may provide rigidity and shape for the support member with a structured packing. 按照一种实施例,可使用一种泡沫材料172向总成提供形状和结构刚性。 According to one embodiment, may be used as a foam material 172 provides structural rigidity to the assembly and shape.

[0069] 在一些实施例中,中间区域115的一个或多个中间膜部分138可以从前缘区域112 到尾缘区域116直线地延伸。 [0069] In some embodiments, a plurality of the intermediate region 115 or portion 138 intermediate film region 112 may extend from the leading edge to the trailing edge region 116 linearly. 在一些实施例中,中间膜部分138在前缘区域112与尾缘区域116之间可具有曲率。 In some embodiments, the intermediate film region 112 at the leading portion 138 and trailing edge 116 between the regions may have a curvature. 中间膜部分138可具有沿其长度的大致均匀并且恒定的截面厚度T im。 The intermediate film 138 may have a portion substantially uniform along its length and a constant cross-sectional thickness T im. 在示例性实施例中,表面132U34可彼此相邻定位并且可以接触以形成中间膜部分138,使得中间膜部分138的截面厚度T im可约等于表面132与134之间的一种或几种材料的厚度。 In an exemplary embodiment, the surface 132U34 may be positioned adjacent to each other and may contact the film to form an intermediate portion 138, such that the intermediate portion of the film cross-sectional thickness T im 138 may be approximately equal to one or more surfaces of the material between 132 and 134 thickness of. 在一些实施例中,中间膜部分138可由带有厚度的一片材料形成,使得中间膜部分138中不存在空间或空隙。 In some embodiments, the intermediate portion 138 may be formed with a film thickness of a material, such that portions of the intermediate film 138 does not exist in a space or gap. 例如,中间膜部分138可以是具有相对恒定厚度的弯曲平面形式。 For example, intermediate portion 138 may be a film having a relatively constant thickness bent planar form.

[0070] 在一种实施例中,中间膜部分138可以是用钉固定、粘附、摩擦配合,或以其它方式附接或固定至前缘区域112,以将中间膜部分138固定至前缘区域112。 [0070] In one embodiment, the intermediate film 138 may be a part of a nail, adhesive, friction fit, or otherwise attached or secured to a leading edge region 112 to the intermediate portion 138 is fixed to the leading edge of the film region 112. 在一种实施例中,前缘区域112与中间膜部分138之间的接合处131可以由设置成接收并保持中间膜部分138的上游端143的凹槽或通道117形成。 In one embodiment, the leading edge region 112 and the junction 131 between the intermediate membrane portion 138 may receive and hold the upstream end of the intermediate portion 138 of the film 143 is groove or channel 117 formed by the arranged. 例如,上游端143可具有与通道117的圆形截面对应的圆形截面,使得中间膜区域138的上游端143可以滑入、接合并由前缘区域112 的通道117保持。 For example, the upstream end 143 may have a circular cross-section corresponding to the cross-section of the channel 117, such that the upstream end 143 of the intermediate film region 138 can be slid into engagement by the leading edge region 112 of channel 117 remains.

[0071] 在示例性实施例中,尾缘区域116可形成为绕中心轴线105周向地延伸的环形结构,并且尾缘116可具有大于前缘162的直径或宽度的直径或宽度。 [0071] In an exemplary embodiment, the trailing edge region 116 may be formed as an annular structure extending circumferentially about the periphery of the central axis 105, and the trailing edge 116 may have a diameter or width or diameter greater than the width of the leading edge 162. 尾缘区域116的与尾缘166相对的一端可包括诸如凹槽或通道182的凹入部分,其配置为接收并机械地结合至中间膜部分138。 The trailing edge region and trailing edge 166 opposite the end 116 may include a recessed portion such as a groove or channel 182, configured to receive and mechanically coupled to an intermediate portion of the film 138. 在一种示例性实施例中,尾缘区域可向翼100的尾缘166提供刚性使得尾缘166。 In an exemplary embodiment, the trailing edge region 166 may be provided to the wing trailing edge 100 trailing edge 166 such that the rigidity.

[0072] 尾缘区域116可包括从其延伸的襟翼136。 [0072] The trailing edge region 116 may include a flap 136 extending therefrom. 在一种示例性实施例中,襟翼136可从尾缘166或其附近径向向外地延伸。 In an exemplary embodiment, the flaps 136 may extend outward radially near the trailing edge 166 or from. 襟翼136可具有相对于弦线140以角度Θ延伸的长度L。 Flap 136 may have a length extending at an angle Θ with respect to the chord line 140 L. 在一种示例性实施例中,弦线140与襟翼136之间的角度Θ可以是固定的。 In an exemplary embodiment, the angle between the chord line 140 and the flap 136 may be fixed Θ. 襟翼136的长度L可以比弦线140的长度少约百分之十至百分之三十。 From about ten percent to thirty percent of the length L 136 of the flap can be less than the length of the chord line 140. 在一种示例性实施例中, 襟翼136的长度L可垂直于弦线140延伸,并且可以实施使沿外表面134的气流折转。 In an exemplary embodiment, the length L of the flap 136 may extend perpendicularly to the chord line 140 and can be implemented so that the gas flow along the outer surface 134 of the folding. 在示例性实施例中,襟翼136可包括穿孔184以允许一些空气流过襟翼136来减少由气流施加在襟翼上的力。 In an exemplary embodiment, the flap 136 may include perforations 184 to allow some air to flow through the flap 136 to reduce the force exerted on the flap by the gas stream. 在示例性实施例中,襟翼136可以由与中间膜部分138相同或类似的材料形成。 In an exemplary embodiment, the flap 136 may be formed of the same film and the intermediate portion 138 or a similar material.

[0073] 图3为沿图1的线3-3的图1的翼的截面视图,其描绘了可以设置在前缘区域112 与尾缘区域116之间的中间区域115的中间支撑部分139之一。 [0073] FIG. 3 is a cross section along line 3-3 in view of the wing of FIG. 1, depicting 112 may be disposed in an intermediate region between the leading edge region and trailing edge region 116 of the intermediate portion 139 of the support 115 one. 在一种示例性实施例中, 如图3中描绘的,中间支撑部分139可与前缘区域112 -体地形成,使得中间支撑部分139 与前缘区域112形成整体结构并且中间支撑部分139可以机械地结合至尾缘区域116。 In one exemplary embodiment, depicted in Figure 3, the middle support portion 139 may be the leading edge region 112-- formed in the body, such that the intermediate portion of the support structure 139 is formed integrally with the leading edge region 112 and the intermediate portion 139 may support mechanically coupled to the trailing edge region 116. 在另一种示例性实施例中,中间支撑部分139可机械地结合至前缘区域112和/或尾缘区域116。 In another exemplary embodiment, the intermediate support portion 139 may be mechanically coupled to the leading edge region 112 and / or trailing edge region 116. 在又一种示例性实施例中,中间支撑部分139可与前缘区域112和/或尾缘区域116 一体地形成。 In yet another exemplary embodiment, the intermediate portion 139 may support 112 and / or trailing edge region 116 is formed integrally with the leading edge region.

[0074] 中间支撑部分139可为翼100提供结构性支撑以限定前缘区域112与尾缘区域116之间的距离,并且/或者可为中间膜部分138提供支撑结构,例如限定中间膜部分138 的轮廓。 [0074] The intermediate support portion 139 may provide structural support for the wing 100 to 112 define a distance between the leading edge region and trailing edge region 116, and / or the intermediate membrane portion 138 may provide structural support, for example, define a portion of the intermediate film 138 Outline. 中间刚性部分139可以是具有大致的棒形或杆形构造的细长部件。 Intermediate rigid portion 139 may have a generally elongated rod-shaped member or the rod-shaped configuration. 中间支撑部分139可以设置为接合形成在尾缘区域116中的通道182,以将中间支撑部分139机械地结合至尾缘区域116。 The intermediate support portion 139 may be provided to engage the channel region 116 is formed at the trailing edge 182 in order to support the intermediate portion 139 is mechanically coupled to the trailing edge region 116. 在一些实施例中,中间支撑部分可与前缘区域112和/或尾缘区域116 - 体地形成。 In some embodiments, the intermediate support portion 112 may be the leading edge region and / or edge region 116 - the body is formed.

[0075] 在一些实施例中,中间支撑部分139可从前缘区域112呈直线地延伸至尾缘区域116。 [0075] In some embodiments, the intermediate support portion 139 may linearly extend to the trailing edge region 116 from the leading edge region 112. 在一些实施例中,中间支撑部分139可在前缘区域112与尾缘区域116之间具有曲率。 In some embodiments, the intermediate support portion 139 may have a curvature in the region between the leading edge 112 and trailing edge region 116. 中间支撑部分139可具有沿长度的大致均匀且恒定的截面厚度T is。 Middle support portion 139 may have a substantially uniform cross-sectional thickness T is constant along the length. 在示例性实施例中,中间支撑部分139的表面132U34可彼此邻近地定位,并且可以接触形成中间支撑部分139 使得中间支撑部分139的截面厚度T is可近似等于表面132U34之间的一种或多种材料的厚度。 In an exemplary embodiment, the surface portion 139 of the intermediate support 132U34 may be positioned adjacent to each other, and may be formed in contact with the intermediate support the support portion 139 such that the intermediate cross-sectional thickness portion 139 may be approximately equal to T is between one kind or more surface 132U34 the thickness of the materials. 在一些实施例中,中间支撑部分139可由带有厚度的一片材料形成,使得中间支撑部分139中不存在空间或空隙。 In some embodiments, the intermediate support portion 139 may be formed with a material thickness is formed, so that the absence of the intermediate support portion 139 in a space or gap. 例如,中间支撑部分139可以是带有相对恒定厚度的弯曲平面形式。 For example, the support portion 139 can be intermediate a relatively constant thickness with a curved planar forms.

[0076] 在一种实施例中,中间膜部分138可包围或环绕中间支撑部分139。 [0076] In one embodiment, the intermediate film 138 may surround or partially surround the intermediate support portion 139. 在一些实施例中,中间膜部分138可用钉固定、粘附、摩擦配合,或以其它方式附接或固定至中间支撑部分139以将中间膜部分138固定至中间支撑部分139。 In some embodiments, the intermediate portion of the membrane 138 available nail, adhesive, friction fit, or otherwise attached or secured to the intermediate portion 139 to the intermediate support film 138 is fixed to the intermediate portion of the supporting portion 139. 例如,在一种实施例中,可将聚乙烯热缩塑料包用作中间膜部分138并且聚乙烯热缩塑料包可环绕中间支撑部分139,并且可向聚乙烯热缩塑料包施加热使聚乙烯热缩塑料包收缩在中间支撑部分139上形成紧摩擦配合。 For example, in one embodiment, it may be used as a shrink wrap polyethylene film of the intermediate portion 138 and may be polyethylene shrink wrap surrounding the intermediate support portion 139, and may apply heat to the shrink wrap polyethylene poly ethylene shrink wrap shrinkable support in a tight friction fit on the intermediate portion 139. 在一些实施例中,中间膜部分138可分别在一对中间支撑部分139之间从前缘区域112延伸至尾缘区域116。 In some embodiments, the intermediate film 138 may be respectively a portion intermediate between the support portion 139 extending from the leading edge to the trailing edge region 112 region 116.

[0077] 参考图4,描绘了图2的翼100的尾缘区域116的详细截面正视图。 [0077] Referring to Figure 4, depicts a detailed cross-sectional area of ​​the wing trailing edge 100 of the front 116 of FIG. 2 FIG. 该示例性实施例包括在尾缘116上的襟翼136。 This exemplary embodiment includes a flap 116 on the trailing edge 136. 襟翼136大致地垂直于翼截面的弦线140,或者换言之相对于翼截面的弦线140呈介于约85°与120°之间的角度Θ。 Flap 136 substantially perpendicular to the chord line of the blade section 140, or in other words with respect to the chord line of the blade section 140 form an angle of between about 85 ° and 120 ° Θ. 在一些实施例中,尾缘区域116可包括与中间膜部分138 (例如通过通道182)接合的刚性部件148。 In some embodiments, the trailing edge region 116 may comprise a membrane portion 138 and the intermediate member 148 rigidly joined (e.g. through the channel 182). 刚性部件148与环146接合,环146与襟翼136接合。 Engaging the rigid member 146 with the ring 148, ring 146 and the flap 136 engages. 环146向刚性部件148提供环向强度。 Ring 146 provides hoop strength to the rigid member 148. 襟翼136包含向襟翼136的外缘提供环向强度的至少一个环144。 Comprising flaps 136 provide strength to the outer edge of the ring 136 of the flap 144 at least one ring. 如上所述,中间支撑部分139形式的刚性结构支撑部件围绕邻近中间膜部分138的环形翼径向地隔开(图1和图3)。 A rigid structural support member described above, the intermediate support portion 139 in the form of radially spaced (FIG. 1 and FIG. 3) around the annular wing portion adjacent the intermediate film 138. 中间支撑部分139提供结构以支撑尾缘116的定位和结构。 The intermediate support portion 139 to provide structural support and positioning structure of the trailing edge 116. 由中间支撑部分139提供的结构性支撑维持襟翼136相对于弦140的角度Θ,并提供结构以支撑中间膜部分138。 Structural support provided by the intermediate portion 139 to maintain the support flap 136 with respect to the angle of the chord 140 Θ, and to provide structural support to the intermediate portion of the film 138.

[0078] 参考图5,描绘了示例性实施例100的环形翼的正截面。 [0078] Referring to Figure 5, depicts a positive section of the annular wing 100 of an exemplary embodiment. 翼100周围的从前缘112 到尾缘116的气流的方向和路径通过在吸力侧132(即,内表面132)上的箭头152,和在压力侧134 (即,外表面)上的箭头154进行表示。 From the leading edge 112 to the gas flow trailing edge 116 of the direction and path 100 around the wing through the suction side 132 (i.e., inner surface 132) arrow 152, and a pressure side 134 (i.e., outer surface) of the arrow on the 154 representation.

[0079] 再次参考图5,襟翼136在翼134的压力侧上的流动中引起滞流区域141。 [0079] Referring again to FIG. 5, the flow flaps 136 on the pressure side of the airfoil 134 in the region 141 to cause stagnation. 在翼100的尾缘166上或接近于翼100的尾缘166增加襟翼136还在翼100的尾缘116的下风处产生漩涡118。 On the trailing edge 166 of the wing 100 or wing 100 near the trailing edge 166 increases the wing trailing-edge flap 136 also downwind 100 116 118 creating a vortex. 襟翼136的增加使翼100的压力侧134上的气流154被向上推,从而允许翼100的吸力侧132上的流体流152保持依附在表面并产生流体流的改进的循环。 Gas stream 154 is pushed up on flap 136 increases the pressure side 134 of the airfoil 100, allowing fluid on the suction side 132 of wing 100 remains attached to the surface of the stream 152 and produce improved fluid flow loop.

[0080] 图6描绘了另一示例性翼200的透视图。 [0080] FIG 6 depicts a perspective view of another example of flap 200. 翼200的主体202可包括前缘区域212、 中间区域215以及尾缘区域216。 202 wing body 200 may include a leading edge region 212, intermediate edge region 215 and a tail region 216. 翼200可包括混合元件226、228,其可由中间区域215 和尾缘区域216形成。 Mixing member 200 may include a flap 226, 228, which is formed by the intermediate region 215 and a trailing edge region 216. 如图所示,混合叶可包括朝中心轴线205向内延伸的低能量混合叶228,和从中心轴线205向外延伸的高能量混合叶226。 As shown, may comprise a low energy mixing blade extending inwardly toward the central axis of the mixing blade 205 228, and 226 from the high energy mixing blade 205 outwardly extending central axis. 换言之,涡轮机护罩104的尾缘124 被成形以形成两组不同的混合叶。 In other words, the trailing edge 104 of the turbine shroud 124 is shaped to form two different mixing blade. 混合叶126U28可形成绕中心轴线205的大致的圆形锯齿的或圆周波浪的凹凸形状。 126U28 mixing blade may be formed in an uneven shape around the central axis of the substantially circular serrations 205 or circumferential waves.

[0081] 翼200的尾缘区域216可由刚性材料形成,并且可以具有绕中心轴线205的大致的圆形锯齿的或圆周波浪的凹凸形状,其可将混合叶126U28的结构性构造导入至中间区域215的中间膜部分238。 The trailing edge region 216 may be formed of a rigid material [0081] The flap 200 is formed, and may have a substantially circular saw blade about the central axis 205 of the circumferential wave or concavo-convex shape, which may be mixed leaf structural configuration is introduced into an intermediate region 126U28 the intermediate portion 215 of the film 238. 尾缘区域可包括一个或多个襟翼236。 The trailing edge region may comprise one or more flaps 236. 在一种示例性实施例中, 如图6中所示,每个低能量混合叶228可包括襟翼236之一并且高能量混合叶226可以没有襟翼236。 In one exemplary embodiment, shown in Figure 6, each of the low energy mixing blade 228 may comprise one of a high energy mixing flap 236 and 226 can not flap 236 leaves. 在另一示例性实施例中,高能量混合叶226和低能量混合叶228可包括襟翼236。 In another exemplary embodiment, the high energy mixing and low energy mixing blade 226 may include a flap 228 leaves 236. 在又一示例性实施例中,襟翼236可沿尾缘区域216连续地延伸以形成绕中心轴线205 连续地设置的单襟翼。 In yet another exemplary embodiment, the flap 236 may extend continuously to form a single flap continuously about the central axis 205 provided along the trailing edge region 216. 在一种示例性实施例中,当将中间膜部分实施形成翼的中间区域的表面时,环形结构的前缘区域212与刚性尾缘区域216以及中间区域215的中间离散支撑部分结合提供足够的刚性以支撑尾缘区域116上的襟翼136与弦线为固定关系。 In an exemplary embodiment, the wing is formed when the surface area of ​​the intermediate portion of the intermediate film embodiment, the leading edge region of the annular structure 212 and the discrete middle portion of the rigid support 216 and the trailing edge region of the intermediate region 215 to provide sufficient binding a rigid flap 136 to the chord line in the trailing edge region 116 of the support in a fixed relationship. 从而,翼100的结构便于提供襟翼136与弦线140之间以及襟翼136与中弧线170之间的固定角度关系。 Thus, the structure of the wing 100 and 136 facilitates providing a fixed angular relationship between the flap 170 and the flap 140 between the arc and the chord line 136. 包括襟翼236的翼200的示例性实施例可产生展示出与具有更大的弦长度并且没有襟翼的传统翼相似性能特征的环形翼。 It includes an exemplary embodiment of the flap 236 of the flap 200 may generate the conventional wing exhibit a greater chord length and having no flaps similar performance characteristics annular wing.

[0082] 在一种示例性实施例中,所述一个或多个中间支撑部分239可向位于前缘部分212与尾缘部分216之间的主体202提供结构性支撑。 [0082] In an exemplary embodiment, the one or more intermediate body supporting portion 239 may be between 216 and edge portion 202 provides structural support to the leading edge portion 212. 中间支撑部分239可彼此隔开并且可绕中心轴线205离散地和周向地分布。 The intermediate support portion 239 may be spaced apart from one another and distributed circumferentially about the central axis 205 and the circumferential discretely. 中间支撑部分239可被限定尺寸并且/或者设置成指定前缘部分212与尾缘部分216之间的空间关系。 The intermediate support portion 239 may be defined size and / or the space portion 212 disposed 216 specifies the relationship between the leading edge and the trailing edge portion. 如一种示例,在一种实施例中,所述一个或多个中间支撑部分239可设定翼200的前缘与尾缘之间的距离,其对应于翼200的弦线。 As an example, in one embodiment, the one or more intermediate supporting portion 239 can set the distance between the leading edge and the trailing edge of the blade 200, which corresponds to the chord of the wing 200.

[0083] 图7为沿线7-7的图6的翼200的截面视图。 [0083] FIG. 7 is a sectional view along line 7-7 in FIG. 6 of the wing 200. 如图7所示,由于前缘区域包括变化的体积并且中间膜部分238包括大致均匀的体积,翼200的截面大致地对应于翼100的截面。 As shown in FIG 7, since the leading edge region including a volume change portion 238 and the intermediate film comprises a substantially uniform volume, the cross section of the wing 200 substantially corresponds to the cross section of the wing 100. 翼100的前缘262可以是大致圆形的、牛鼻形的或者其它形状的以形成用于将流体分成至少两股(例如,沿内表面132的吸力侧和沿外表面134的压力侧)的空气动力表面。 Wing leading 262,100 may be substantially circular, or other shapes bovine shaped to form a fluid into at least two (e.g. pressure, along the inner surface 132 and suction side surface 134 along the outer side) aerodynamic surface. 前缘区域212的截面形状可沿中弧线270增加截面厚度锥形远离前缘262,并且接着减小截面厚度锥形朝向中心弧线或中弧线270至中间区域。 Cross-sectional shape of the front edge region 212 of the curve 270 may be increased cross-sectional thickness along tapered away from the leading edge 262, and then tapered to reduce the cross-sectional thickness toward the center of the arc or arcs 270 to the intermediate region. 中心弧线或中弧线270大致地定位在翼200的分别地沿翼200的纵向范围的外表面232与内表面234之间的中间位置。 Center arc or arcs 270 are positioned substantially at an intermediate position between the outer surface of the flap along the longitudinal extent of the flap 200 are respectively 232 and 200 of the inner surface 234.

[0084] 如图7所示,弦240限定翼200的前缘262与尾缘266之间的翼200的长度,其可基于中弧线270确定。 [0084] As shown in FIG 7, the leading edge of the wing chord 240 200 262 defining the length between the trailing edge 266 of the flap 200, which may be determined based on the curve 270. 中间膜部分238沿其长度可具有大致均匀和恒定的截面厚度。 The intermediate portion of the film 238 along its length and may have a substantially uniform cross-sectional thickness constant. 在所述示例性实施例中,表面232、234可彼此邻近定位,并且可以接触以形成中间膜部分238。 In the exemplary embodiment, surfaces 232, 234 may be positioned adjacent to each other and may contact portion 238 to form an intermediate film.

[0085] 与本发明所述的示例性翼100的中间区域115类似,中间区域215可包括中间膜部分238和中间支撑部分239。 [0085] The intermediate region 115 of the present invention is similar to the exemplary airfoil 100, an intermediate film region 215 may include an intermediate portion 238 and an intermediate support portion 239. 中间膜部分238可由半刚性和/或非刚性材料形成,并且中间支撑部分238可由半刚性和/或刚性材料形成。 The intermediate film 238 may be formed of a semi-rigid portion and / or non-rigid material, and the intermediate support portion 238 may be semi-rigid and / or rigid material. 中间区域215提供内翻混合元件226与外翻混合元件228之间的过渡区域。 Total mixing element 226 with mixing the transition region between the everting element 228 in the intermediate region 215. 刚性尾缘区域216提供结构以支撑组成混合元件226 和228的膜表面。 Rigidity of the trailing edge region 216 to provide structural support to the film surface composed of mixing elements 226 and 228. 在示例性实施例中,尾缘区域216可形成为以周向波浪方式绕中心轴线205延伸的刚性结构。 In an exemplary embodiment, the trailing edge region 216 may be formed as a rigid structure Zhou Xiangbo waves way of a central axis 205 extending around. 在一种示例性实施例中,尾缘区域216可向翼200的尾缘266提供刚性使得尾缘266。 In an exemplary embodiment, the trailing edge region 216 may be provided to the trailing edge 266 of the flap 200 such that the rigidity of the trailing edge 266.

[0086] 尾缘区域216可包括从其延伸的襟翼236。 [0086] region 216 may include a trailing edge flap 236 extending therefrom. 在一种示例性实施例中,襟翼236可从尾缘266或其附近径向向外地延伸。 In an exemplary embodiment, the flaps 236 may extend outward radially near the trailing edge 266 or from. 襟翼236可具有相对于弦线240以角度θ'延伸的长度L。 Flap 236 may have a chord line 240 at an angle θ 'with respect to the extending length L. 在一种示例性实施例中,弦线140与襟翼236之间的角度θ'可以是固定的,并且/ 或者襟翼236的长度L可以比弦线240的长度少约百分之十至约百分之三十。 In an exemplary embodiment, the angle between the chord line 140 and the flap 236 θ 'may be fixed, and / or about ten percent of the length of flap 236 may be less than the length L of the chord line 240 to about thirty percent. 在一种示例性实施例中,襟翼236的长度L可垂直于弦线140延伸,并且可以实施使沿外表面234的气流折转。 In an exemplary embodiment, the length L of the flap 236 may extend perpendicularly to the chord line 140 and can be implemented so that the gas flow along the outer surface 234 of the folding. 在本示例性实施例中,襟翼236与外翻混合元件228的尾缘266接合。 In the present exemplary embodiment, the flap engaging element 236 with the everted mixing 228 trailing edge 266. 尾缘266由如图3-图4中所示并描述的类似组件组成。 The trailing edge 266 similar to the assembly shown in FIGS. 3 and 4 described composition. 在示例性实施例中,襟翼236可包括穿孔284 以允许一些空气流过襟翼236来减少由气流施加在襟翼236上的力。 In an exemplary embodiment, the flap 236 may include perforations 284 to allow some air to flow through the flap 236 to reduce the forces exerted on the flaps 236 by the gas stream. 襟翼236被限定尺寸或设置为允许流体流沿内表面流动以保持依附在内表面。 Flap 236 is defined or the size arranged to allow fluid flow along the inner surface of the flow remains attached to the inner surface.

[0087] 图8描绘了风力涡轮机形式的示例性护罩式流体涡轮机300的前向透视图,其具有支撑结构302、能量提取总成345、以及由具有前缘区域112、中间区域115和尾缘区域116的示例性翼100形成的涡轮机护罩。 [0087] FIG 8 depicts an exemplary form of a wind turbine shroud fluid turbine 300 to the front perspective view of a support structure 302 which, the energy extraction assembly 345, and 112 having a leading edge region, the intermediate region 115 and a tail exemplary turbine shroud edge region 116 of the wing 100 is formed. 能量提取总成345可包括吊舱体350和转子340。 Energy extraction assembly 345 can comprise a nacelle 350 and a rotor body 340. 转子340在转子叶片的近端处与吊舱体350接合。 The rotor body 340 at the proximal end of the rotor blade and the nacelle 350 engage. 翼100可环绕转子340。 Wings 100 may encircle the rotor 340. 在一种示例性实施例中,翼100的前缘166可定位在转子340的上游,并且/或者翼100的尾缘166可定位在转子340的下游。 In an exemplary embodiment, the leading edge 166 of the wing 100 of the rotor 340 may be positioned upstream of the trailing edge and / or 166 of the wing 100 may be positioned downstream of the rotor 340. 前缘162可形成护罩式流体涡轮机300的入口并且尾缘166可形成护罩式流体涡轮机300的排出口。 The leading edge 162 may be formed inlet shroud fluid turbine 300 and trailing edge 166 may form a fluid outlet of the turbine shroud 300. 襟翼136允许流体流(例如气流)沿翼的内表面流动以保持依附在内表面。 Flap 136 to allow fluid flow (e.g. air flow) flowing along the inner surface of the wing remains attached to the inner surface. 在一种不例性实施例中,翼100可使用细长的支撑结构307相对于吊舱体350和转子340定位,使得吊舱体350、转子340以及翼100绕中心轴线105相对于彼此同轴地定位。 In one exemplary embodiment is not an embodiment, the wings 100 may use an elongated support 307 with respect to the nacelle structure 350 and the rotor body 340 is positioned, such that the pod body 350, a rotor 340, and 100 about a central axis different from each other with respect to the wing 105 shaft positioning.

[0088] 图9描绘了风力涡轮机形式的示例性护罩式流体涡轮机400的前向透视图,其具有支撑结构302、能量提取总成345、以及由具有前缘区域212、中间区域215和尾缘区域216的示例性翼200形成的涡轮机混合护罩。 [0088] FIG 9 depicts an exemplary form of a wind turbine shroud fluid turbine 400 to a front perspective view, having a support structure 302, the energy extraction assembly 345, and 212 having a leading edge region, the intermediate region 215 and a tail edge region 216 of turbine airfoil 200 is formed of an exemplary shroud mixing. 翼200可环绕转子340。 The flap 200 may encircle the rotor 340. 在一种示例性实施例中,翼200的前缘266可定位在转子340的上游,并且/或者翼200的尾缘266可定位在转子340的下游。 In an exemplary embodiment, the leading edge 200 of the flap 266 of the rotor 340 may be positioned upstream of the trailing edge and / or 266 of the flap 200 may be positioned downstream of the rotor 340. 前缘262可形成护罩式流体涡轮机400的入口并且尾缘266可形成护罩式流体涡轮机400的排出口。 The leading edge 262 may be formed inlet shroud fluid turbine 400 and trailing edge 266 may form a fluid outlet of the turbine shroud 400. 如上所述,尾缘266包括内翻混合元件226和外翻混合元件228。 As described above, the trailing edge 266 comprising mixing elements 226 and varus valgus mixing element 228. 内翻混合元件226朝中心轴线205向内弯曲并且外翻混合元件228从中心轴线205向外弯曲。 Varus mixing element 226 is bent inwardly toward the central axis 205 and the mixing element 228 is bent outwardly everted from the central axis 205. 襟翼236可允许流体流(例如气流)沿翼的内表面流动以保持依附在内表面。 Flap 236 may allow fluid flow (e.g. air flow) flowing along the inner surface of the wing remains attached to the inner surface. 在一种示例性实施例中,翼200可使用细长的支撑结构307相对于吊舱体350和转子340定位,使得吊舱体350、转子340以及翼200绕中心轴线205相对于彼此同轴地定位。 In an exemplary embodiment, the wings 200 may use an elongated support 307 with respect to the nacelle structure 350 and the rotor body 340 is positioned, such that the pod body 350, a rotor 340 and flap 200 around the central axis 205 coaxial with respect to one another positioning.

[0089] 图10为护罩式流体涡轮机500的示例性实施例的前向透视图,其包括本发明的环形翼100和200的示例性实施例。 Before [0089] FIG. 10 is a shrouded exemplary embodiment of a fluid turbine 500 to perspective view an exemplary embodiment of the present invention, an annular flap 100 and 200. 图11为图10的护罩式流体涡轮机的后向透视图。 Figure 11 is a fluid turbine shroud of FIG. 10 to FIG perspective. 图12 为经过外翻混合元件228截取的图10和11的护罩式流体涡轮机500的详细截面侧向透视图。 12 is everted through the mixing elements 228 detailed cross-sectional side perspective view of FIG. 10 and 11, taken fluid turbine shroud 500. 图13为经过内翻混合元件226截取的图10和11的护罩式流体涡轮机500的详细截面侧向透视图。 13 is inverted through the mixing element 226 side perspective view, taken 10 and 11 a detailed sectional view of the fluid turbine shroud 500. 图12和13的详细截面描绘了被包括在混合-喷射涡轮机护罩中的本发明的环形翼100和200。 12 and 13 a detailed sectional view depicting the mixing is included in the - annular flap 100 and 200 jet turbine shroud of the present invention. 环形翼100包括前缘区域112、中间区域115以及尾缘区域116。 Annular wing 100 includes a leading edge region 112, middle region 115 and the trailing edge region 116. 环形翼200包括前缘区域212、中间区域215以及尾缘区域216。 Annular flap 200 includes a leading edge region 212, intermediate edge region 215 and a tail region 216.

[0090] 在一种示例性实施例中,护罩式流体涡轮机500可以指混合/喷射流体涡轮机, 这里翼200和翼100形成混合/喷射泵。 [0090] In one exemplary embodiment, fluid turbine shroud 500 may refer to mixing / injection fluid turbine, where the wing 200 and wing 100 is formed a mixed / ejector pump. 参考图10-13,护罩式流体涡轮机500由支撑结构302支撑,并包括由翼200的示例性实施例形成的涡轮机混合护罩、由吊舱体350和转子340形成的能量提取总成、以及由翼200形成的喷射护罩。 10-13, fluid turbine shroud 500 supported by the support structure 302, and comprises a turbine is formed by an exemplary embodiment of the mixing flap shroud 200, the energy from the nacelle 350 and a rotor body formed by extraction assembly 340, and an ejection flap 200 formed by the shroud. 转子340、翼200 (即,涡轮机混合护罩)和翼1〇〇(即,喷射护罩)彼此同轴,即,它们共用公共中心轴线505。 The rotor 340, flap 200 (i.e., mixing the turbine shroud) and a wing 1〇〇 (i.e., injection shroud) coaxial with each other, i.e., they share a common central axis 505. 在一种示例性实施例中,翼200可使用细长的支撑结构307相对于吊舱体350和转子340定位,并且翼100可使用细长的支撑结构506相对于翼200定位。 In an exemplary embodiment, the wings 350 and 200 may use the rotor 340 is positioned with respect to the elongated body of the nacelle support structure 307 and wing 100 may be elongated support structure 506 used with respect to wing 200 is positioned.

[0091] 在一种示例性实施例中,翼200的前缘266可定位在转子340的上游,翼200的尾缘266可定位在转子340的下游,翼100的前缘162可定位在转子340的下游,并且/或者翼100的尾缘166可定位在尾缘266的下游。 [0091] In an exemplary embodiment, the leading edge 200 of the flap 266 may be positioned upstream of the rotor 340, the trailing edge 266 of the flap 200 may be positioned downstream of the rotor 340, the leading edge 100 of the wing 162 may be positioned in the rotor 340 downstream and / or trailing edge 166 of airfoil 100 may be positioned downstream of the trailing edge 266. 前缘262可在护罩式流体涡轮机400中形成翼200的入口,并且尾缘266可在护罩式流体涡轮机400中形成翼200的排出口。 A leading edge flap 262 may be formed inlet 200 in fluid turbine shroud 400, and a trailing edge flap 266 may be formed in the discharge port 200 in fluid turbine shroud 400.

[0092] 由翼100形成的喷射护罩包括由前缘162限定的前端或入口端,以及由尾缘166 限定的后端或排出口端。 [0092] is formed by injection shroud 100 includes a wing leading edge 162 defines the front end or inlet end, and a trailing edge 166 is defined by the rear or outlet end.

[0093] 图14更详细的描绘了尾缘区域116和216以分别地示出示例性穿孔184和284。 [0093] FIG. 14 depicts in more detail the trailing edge region 116 and 216 respectively illustrate exemplary perforations 184 and 284. 穿孔184和284可分别地形成在襟翼136和236中,以允许一些空气流过襟翼136、236来减少由气流施加在襟翼236上的力。 Perforations 184 and 284 may be respectively formed in the flaps 136 and 236, to allow some air to flow through the flaps 136, 236 to reduce the forces exerted on the flaps 236 by the gas stream.

[0094] 图15为护罩式流体涡轮机600的另一示例性实施例的前向透视图,其包括本发明的示例性环形翼700和800。 [0094] FIG. 15 is a front shroud to another exemplary embodiment of the fluid to the turbine 600 of the perspective view an exemplary annular flap 700 and 800 of the present invention. 图16为图15的流体涡轮机的详细截面侧向正视图。 FIG 16 is a detailed cross-sectional side fluid turbine 15 is a front view of FIG. 参考图15-16,护罩式流体涡轮机600由支撑结构302支撑并包括具有转子340和吊舱体350的能量提取总成345。 15-16, fluid turbine shroud 600 supported by the support structure 302 and includes a rotor 340 and car body 350 of the energy extraction assembly 345. 环形翼700形成涡轮机护罩并且环形翼800形成护罩式流体涡轮机600 的喷射护罩。 Forming an annular flap 700 and the ring-wing turbine shroud 800 form the turbine shroud fluid ejection shroud 600. 转子340、涡轮机护罩(即,翼700)以及喷射护罩(即,翼800)彼此同轴,即共用公共中心轴线605。 Rotor 340, the turbine shroud (i.e., the wing 700) and an injection shroud (i.e., the wing 800) coaxial with each other, i.e., sharing a common central axis 605.

[0095] 翼700和翼800可以类似于本发明的示例性翼100和200的方式形成。 [0095] The flap 700 and the flap 800 may be formed similar to the exemplary embodiment of the present invention, the wings 100 and 200. 翼700可包括具有前缘762 (其形成翼700的前端或入口端)的前缘区域712。 Wings 700 may include a leading edge having a leading edge region 762 (which forms the blade tip or inlet end 700) 712. 前缘区域712可具有与本发明的前缘区域112和212的截面结构大致类似或相同的截面结构(如图16所示)。 The leading edge region 712 may have a cross-sectional structure of the present invention, the leading edge region 112 and 212 of substantially similar or the same cross-sectional configuration (FIG. 16).

[0096] 翼700还包括具有尾缘766的尾缘区域716,所述尾缘766形成翼700的后端或出口(排出)端。 [0096] 700 further includes a wing trailing edge region 766 having a trailing edge 716, the trailing edge 766 or rear wing outlet 700 is formed (discharge) end. 尾缘区域716可具有与本发明的尾缘区域112的截面结构大致类似或相同的截面结构(如图16所示)。 The trailing edge region 716 may have a cross-sectional structure of the trailing edge region 112 of the present invention are substantially similar or the same cross-sectional configuration (FIG. 16). 在本示例中,尾缘区域716可具有带有小面结构的多侧的多边形形状。 In the present example, the trailing edge region 716 may have a polygonal shape with a multi-sided facet structure. 例如,尾缘区域716可包括在节点777处连接的小面775。 For example, the trailing edge region 716 may include a facet 775 is connected at node 777.

[0097] 翼800包括具有前缘862 (其形成翼800的前端或入口端,以及后端)的前缘区域812。 [0097] The airfoil 800 includes a leading edge region 812 having a leading edge 862 (the front end or inlet end of the wing 800 which is formed, and a rear end) of. 翼800还包括具有尾缘866(其形成翼800的排出端或出口端)的尾缘区域816。 800 further includes a wing trailing edge region 816 having a trailing edge 866 (which forms the discharge or outlet end flap 800) is. 翼800包括小面环形翼,前缘区域812可具有与本发明的前缘区域112、212以及712大致地相类似或相同的截面。 Wing 800 includes an annular facets wing leading edge region 812 may have a similar or the same as the leading edge region 112, 212 and 712 according to the present invention is substantially the cross-section. 在本示例中,尾缘区域816可具有带有小面结构的多侧多边形形状。 In the present example, the trailing edge region 816 may have a polygonal shape with multiple sides of the facet structure. 例如,尾缘区域816可包括在节点877处连接的小面875。 For example, the trailing edge region 816 may include facets 875 at a node 877 is connected.

[0098] 翼700和800可分别地包括分别地在前缘区域712和812之间延伸,并分别地延伸至尾缘区域716和816的中间区域715和815。 [0098] wings 700 and 800 may each include a leading edge region between 712 and 812 extend, respectively, and extend to the trailing edge region 716 and intermediate region 816 and 715 815. 中间区域715和815可由中间支撑部分和中间膜部分形成。 And the intermediate region 715 is formed by the intermediate support portion 815 and the intermediate film portion.

[0099] 图16中描绘了图15的护罩式涡轮机的详细截面,并且示出了包含在混合-喷射涡轮机护罩中的小面环形翼700和800。 [0099] FIG. 16 depicts a cross-sectional detail of the turbine shroud of FIG. 15, and shows a contained in the mixed - facet annular wing jet turbine shroud 700 and 800. 翼700和800分别具有宽大的前缘区域712和812, 其分别地与中间区域715和815接合,所述中间区域715和815分别地在前缘区域712/812 与尾缘区域716/816之间形成过渡区域。 Wings 700 and 800 respectively have wide leading edge region 712 and 812, which are respectively engaged with the intermediate region 715 and 815, the intermediate region 715 and 815, respectively, in the leading edge region and trailing edge region 716/816 712/812 of forming a transition region between. 刚性尾缘区域716由如本发明所述的类似组件组成,并且提供结构以支撑中间区域715的中间膜部分。 Rigidity of the trailing edge region 716 of similar components as the composition of the present invention, and provide structural support to the intermediate portion 715 of the intermediate film region.

[0100] 在一些实施例中,中间支撑部分可包括在节点777和/或小面775中,其大致地形成中间膜部分。 [0100] In some embodiments, the intermediate portion may comprise support nodes 777 and / or facets 775, which is formed substantially intermediate film portion. 襟翼736与翼700的尾缘区域716接合来以相对于翼700的弦线的固定角度(例如垂直的)从尾缘延伸。 Flap 736 and 700 of the wing trailing edge region 716 joined to a fixed angle relative to the chord line of the airfoil 700 (e.g., perpendicular) extending from the trailing edge. 同样的,翼800由宽大的前缘区域812、中间区域815以及尾缘区域816组成。 Similarly, the wing leading edge 800 by a wide region 812, middle region 815 and the trailing edge region 816 components. 襟翼836与翼800的尾缘区域816接合来以相对于翼800的弦线的固定角度(例如垂直的)从尾缘延伸。 The trailing edge region 816 and the flap 836 to flap 800 engages a fixed angle relative to the chord line of the airfoil 800 (e.g., perpendicular) extending from the trailing edge. 中间区域815可包括描绘的如小面875和节点877的中间膜部分。 The intermediate region 815 may comprise an intermediate portion of the film depicted as facets 875 and node 877. 中间区域815的中间支撑部分839可绕中心轴线705径向地分配,并且还与翼700接合以将翼700连接至翼800。 The intermediate portion of the intermediate region 815 of the support 839 may be 705 radially distributed around a central axis, and further to the wing 700 is connected to the wing 800 and wing 700 engages.

[0101] 图17描绘了风力涡轮机形式的示例性护罩式流体涡轮机900的前向透视图,其具有支撑结构302、能量提取总成345、以及由具有前缘区域712、中间区域715和尾缘区域716的示例性翼700形成的涡轮机护罩。 [0101] FIG. 17 depicts a wind turbine 900 in the form of a forward perspective view of an exemplary fluid turbine shroud, having a support structure 302, the energy extraction assembly 345, and 712 having a leading edge region, the intermediate region 715 and a tail exemplary turbine airfoil trailing edge region 716 of the shroud 700 is formed. 能量提取总成345可包括吊舱体350和转子340。 Energy extraction assembly 345 can comprise a nacelle 350 and a rotor body 340. 转子340在转子叶片的近端处与吊舱体350接合。 The rotor body 340 at the proximal end of the rotor blade and the nacelle 350 engage. 翼700可环绕转子340。 Wings 700 may encircle the rotor 340. 在一种示例性实施例中,翼700的前缘766可定位在转子340的上游,并且/或者翼700的尾缘766可定位在转子340的下游。 In an exemplary embodiment, the leading edge 766 of the wing 700 of the rotor 340 may be positioned upstream of the trailing edge and / or the wings 700 766 340 may be positioned downstream of the rotor. 前缘762可形成护罩式流体涡轮机900的入口并且尾缘766可形成护罩式流体涡轮机900的排出口。 The leading edge 762 may be formed inlet shroud fluid turbine 900 and trailing edge 766 may be formed in the turbine shroud fluid outlet 900. 襟翼736可允许流体流(例如气流)沿翼的内表面流动以保持依附在内表面。 Flap 736 may allow fluid flow (e.g. air flow) flowing along the inner surface of the wing remains attached to the inner surface. 在一种不例性实施例中,翼700可使用细长的支撑结构307相对于吊舱体350和转子340定位,使得吊舱体350、转子340以及翼100绕中心轴线605相对于彼此同轴地定位。 In one exemplary embodiment is not an embodiment, the wings 700 may use an elongated support structure 307 with respect to the nacelle 340 and a rotor 350 is positioned such that the pod body 350, wings 100 and the rotor 340 about the center axis 605 with respect to one another shaft positioning.

[0102] 本发明的示例性实施例有利地提供了一种相对于传统环形翼通常具有轻重量结构的环形翼。 [0102] Exemplary embodiments of the present invention advantageously provides a phase-annular wing typically has a conventional annular wing structure lightweight. 包括襟翼的翼的示例性实施例可产生展示出与带有更长的弦长度并且不带有襟翼的传统翼相似的性能特征的环形翼。 Exemplary embodiments include a wing flap may generate and exhibit a longer chord length and having performance characteristics similar to a conventional wing flap without annular wing. 此外,本发明的示例性实施例相比于传统的翼,尤其是相对于中间膜部分和襟翼的维护和修理,提供了通常更容易和耗时更少的翼的维护和修理。 Further, exemplary embodiments of the present invention compared to conventional wing, particularly with respect to the intermediate portion of the film flaps and maintenance and repair, and is generally easier to provide a less time-consuming maintenance and repair of the wing.

[0103] 如前面所述,本实施例并不特定于一种MET的喷射器,并且其可以应用于那些本领域所理解的管道式或护罩式流体涡轮机。 [0103] As described above, the present embodiment is not specific to one MET injector, and it may be applied to those pipeline or shield fluid turbine according understood in the art. 本发明已参考示例性实施例进行了描述。 The present invention has been described with reference to exemplary embodiments described. 显然, 其他人员可以在对前面详细描述的阅读和理解的基础上想到改型和变换。 Obviously, other modifications and variations may occur to others upon reading and understanding the preceding detailed description of the. 当它们在所附权利要求书或其等同物的范围内时,本发明包括所有这些改型和变换。 When they are within the claims in the appended claims or the equivalents thereof, the present invention includes all such modifications and variations.

Claims (21)

  1. 1. 一种空气动力学地成形的环形翼,其包括: 主体,其绕中心轴线周向地延伸,具有由外表面和内表面形成的空气动力学结构,所述外表面和内表面沿弧线相对于中心轴线轴向地延伸,所述主体包括前缘区域、尾缘区域以及在前缘区域与尾缘区域之间延伸的中间区域; 前缘区域,其具有沿着由主体的外表面和内表面限定的弧线延伸的非均匀的截面厚度;以及尾缘区域,其包括从其延伸并且相对于主体的弦线成角度定向的襟翼,以允许流体流沿内表面流动来保持依附在内表面。 An aerodynamically shaped annular wing, comprising: a body, which extends circumferentially about a central axis, an aerodynamic structure formed by the outer and inner surfaces, said outer surface and an inner surface along an arc line with respect to the central axis extends axially, said body region comprising a leading edge, a trailing edge region and an intermediate region extending between the leading edge region and trailing edge region; the leading edge region, having along an outer surface of the body non-uniform cross-sectional thickness and extending in an arc defined by an inner surface; and a trailing edge region which extends therefrom and includes a string body with respect to the angular orientation of the flap to allow flow of fluid along the inner surface of the flow remains attached to the inner surface.
  2. 2. 根据权利要求1所述的翼,其中,襟翼从尾缘区域垂直于弦线延伸。 2. A wing according to claim 1, wherein the flap extends perpendicularly to the chord line from the trailing edge region.
  3. 3. 根据权利要求1所述的翼,其中,襟翼的长度为弦线长度的约十分之一至约三分之〇 3. The airfoil according to claim 1, wherein the length of the flap is about one-tenth to a third of the chord length of approximately square
  4. 4. 根据权利要求1所述的翼,其中,襟翼包括至少一个穿孔以允许流体流过襟翼。 4. The airfoil of claim 1, wherein the flap comprises at least one perforated to allow fluid flow through the flap.
  5. 5. 根据权利要求1所述的翼,其中,襟翼从翼的尾缘延伸。 The wing according to claim 1, wherein the flap extends from a trailing edge of the blade.
  6. 6. 根据权利要求1所述的翼,其中,襟翼在第一环形结构与第二环形结构之间延伸,第一环形结构和第二环形结构向襟翼提供环向强度。 6. A wing according to claim 1, wherein the flap between the first ring structure and second ring structure extends, the first ring structure and second ring structure to provide hoop strength to the flap.
  7. 7. 根据权利要求6所述的翼,其中,第一环形结构向主体的尾缘区域提供环向强度。 7. A wing according to claim 6, wherein the first annular ring to provide structural strength to the trailing edge region of the body.
  8. 8. 根据权利要求1所述的翼,其中,中间区域包括在前缘区域与尾缘区域之间延伸的至少一个中间支撑部分。 8. The airfoil of claim 1, wherein the intermediate region comprises at least one intermediate support portion extending between the leading edge region and the trailing edge region.
  9. 9. 根据权利要求8所述的翼,其中,中间支撑部分由刚性材料组成。 9. The airfoil of claim 8, wherein the intermediate support portion composed of a rigid material.
  10. 10. 根据权利要求8所述的翼,其中,中间支撑部分具有沿中弧线延伸的均匀的截面厚度,所述中弧线由主体的外表面和内表面限定。 10. A wing according to claim 8, wherein the intermediate support portion having a uniform cross-sectional thickness extending along an arc, the camber line is defined by an outer surface and an inner surface of the body.
  11. 11. 根据权利要求8所述的翼,其中,中间区域包括在前缘区域与尾缘区域之间延伸的至少一个中间膜部分。 11. The airfoil of claim 8, wherein the intermediate film region comprises at least one intermediate portion extending between the leading edge region and the trailing edge region.
  12. 12. 根据权利要求11所述的翼,其中,中间膜部分具有沿中弧线延伸的均匀的截面厚度,所述中弧线由主体的外表面和内表面限定。 12. A wing according to claim 11, wherein the intermediate film portion having a uniform cross-sectional thickness extending along an arc, the camber line is defined by an outer surface and an inner surface of the body.
  13. 13. 根据权利要求11所述的翼,其中,中间区域由非刚性材料组成。 13. A wing according to claim 11, wherein the intermediate region consists of a non-rigid material.
  14. 14. 根据权利要求11所述的翼,其中,中间支撑部分向中间膜部分提供结构性支撑。 14. A wing according to claim 11, wherein the intermediate portion of the support membrane provides structural support to the intermediate portion.
  15. 15. -种能量提取护罩式流体涡轮机,其包括: 能量提取总成,其包括绕中心轴线径向地设置的转子;以及翼,其具有绕中心轴线周向地延伸的主体,主体具有由外表面和内表面形成的空气动力结构,外表面和内表面沿弧线相对于中心轴线轴向地延伸,主体包括前缘区域、尾缘区域以及在所述前缘区域与尾缘区域之间延伸的中间区域; 前缘区域具有沿弧线延伸的非均匀的截面厚度,所述弧线由主体的外表面和内表面限定;以及尾缘区域包括从其延伸并相对于主体的弦线成角度定向的襟翼,以允许流体流沿内表面流动来保持依附在内表面。 15. - kind of energy extraction shroud fluid turbine, comprising: an energy extraction assembly, which includes a rotor disposed radially around the central axis; and a wing, having a body extending circumferentially about the central axis, the body having a aerodynamic structure formed in the outer and inner surfaces of the outer and inner surfaces along an arc relative to the central axis extends axially, the body includes a leading edge region and trailing edge region and trailing edge region between the leading edge region an intermediate region extending; leading edge region having a non-uniform cross-sectional thickness extending along an arc, the arc is defined by an outer surface and an inner surface of the body; and a trailing edge region comprises extending therefrom with respect to the chord line of the body angular orientation of the flap, to allow fluid flow along the inner surface of the flow remains attached to the inner surface.
  16. 16. 根据权利要求15所述的流体涡轮机,其中,襟翼从尾缘区域垂直于弦线延伸。 16. A fluid turbine according to claim 15, wherein the flap extends perpendicularly to the chord line from the trailing edge region.
  17. 17. 根据权利要求15所述的流体涡轮机,其中,襟翼的长度为弦线长度的约十分之一至约三分之一。 17. A fluid turbine according to claim 15, wherein the length of the flap is about one tenth of the chord length to about one-third.
  18. 18. 根据权利要求16所述的流体涡轮机,其中,襟翼包括至少一个穿孔以允许流体流过襟翼。 18. The fluid turbine according to claim 16, wherein the flap comprises at least one perforated to allow fluid flow through the flap.
  19. 19. 根据权利要求15所述的流体涡轮机,其中,襟翼从翼的尾缘区域延伸,襟翼在第一环形结构与第二环形结构之间延伸,第一环形结构和第二环形结构向襟翼提供环向强度, 并且第一环形结构向主体的尾缘区域提供环向强度。 19. A fluid turbine according to claim 15, wherein the flap extends from the wing trailing edge region, the flap extends between the first ring structure and second ring structure, a first ring structure and second ring structure to the flap provides hoop strength, and the first annular ring to provide structural strength to the trailing edge region of the body.
  20. 20. 根据权利要求15所述的流体涡轮机,其中,中间区域包括由刚性材料组成的至少一个中间支撑部分和由非刚性材料组成的至少一个中间膜部分,中间支撑部分和中间膜部分在前缘区域与尾缘区域之间延伸。 20. A fluid turbine according to claim 15, wherein the intermediate region comprises at least one intermediate support portion and at least a portion of the intermediate film, an intermediate support portion and the intermediate portion of a film of a non-rigid material of a rigid material at a leading edge region extending between the trailing edge region.
  21. 21. 根据权利要求20所述的流体涡轮机,其中,至少中间支撑部分或中间膜部分之一具有沿中弧线延伸的均匀截面厚度,所述中弧线由主体的外表面和内表面限定。 21. A fluid turbine according to claim 20, wherein the at least one intermediate support portion or the intermediate portion having a uniform film thickness in the cross-section extending in an arc, the camber line is defined by an outer surface and an inner surface of the body.
CN 201380027360 2012-04-05 2013-04-05 A wind turbine with a ring airfoil shroud having a flap CN104334872A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
US201261620792 true 2012-04-05 2012-04-05
US201361763805 true 2013-02-12 2013-02-12
PCT/US2013/035464 WO2013152297A1 (en) 2012-04-05 2013-04-05 A wind turbine with a ring airfoil shroud having a flap

Publications (1)

Publication Number Publication Date
CN104334872A true true CN104334872A (en) 2015-02-04

Family

ID=48143640

Family Applications (1)

Application Number Title Priority Date Filing Date
CN 201380027360 CN104334872A (en) 2012-04-05 2013-04-05 A wind turbine with a ring airfoil shroud having a flap

Country Status (5)

Country Link
US (1) US20130266438A1 (en)
EP (1) EP2834516A1 (en)
CN (1) CN104334872A (en)
CA (1) CA2869608A1 (en)
WO (1) WO2013152297A1 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150023789A1 (en) * 2013-07-16 2015-01-22 Massachusetts Institute Of Technology Wind Turbine Power Augmentation

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1893065A (en) * 1931-04-03 1933-01-03 Zap Dev Company Aircraft and control thereof
US1893064A (en) * 1931-04-03 1933-01-03 Zap Dev Company Aircraft
US4411588A (en) * 1978-04-28 1983-10-25 Walter E. Currah Wind driven power plant
US4482290A (en) * 1983-03-02 1984-11-13 The United States Of America As Represented By The United States Department Of Energy Diffuser for augmenting a wind turbine
JPH0632355A (en) 1992-07-06 1994-02-08 Tdk Corp Case and method for its production
JP3621975B2 (en) * 2002-03-22 2005-02-23 株式会社産学連携機構九州 Wind turbine generator
EP2031241A1 (en) * 2007-08-29 2009-03-04 Lm Glasfiber A/S Blade for a rotor of a wind turbine provided with barrier generating means
EP2213872A4 (en) * 2007-11-15 2013-09-04 Univ Kyushu Nat Univ Corp Fluid machine utilizing unsteady flow, wind turbine, and method for increasing velocity of internal flow of fluid machine
US8393850B2 (en) * 2008-09-08 2013-03-12 Flodesign Wind Turbine Corp. Inflatable wind turbine
CN102365452B (en) * 2009-03-24 2014-03-19 国立大学法人九州大学 Fluid machine utilizing unsteady flow, windmill, and method for increasing velocity of internal flow of fluid machine

Also Published As

Publication number Publication date Type
EP2834516A1 (en) 2015-02-11 application
WO2013152297A1 (en) 2013-10-10 application
US20130266438A1 (en) 2013-10-10 application
CA2869608A1 (en) 2013-10-10 application

Similar Documents

Publication Publication Date Title
US7914259B2 (en) Wind turbine blades with vortex generators
US20090274559A1 (en) Rotor blade of a wind energy unit
US6749401B2 (en) Hydrodynamically and aerodynamically optimized leading edge structure for propellers, wings, and airfoils
US7094018B2 (en) Wind power generator
US20090180869A1 (en) Inlet wind suppressor assembly
US5890875A (en) Blade apparatus
US20090280009A1 (en) Wind turbine with different size blades for a diffuser augmented wind turbine assembly
WO2000050769A1 (en) Diffuser for a wind turbine
US20100209236A1 (en) Impulse turbine for use in bi-directional flows
US20110008164A1 (en) Wind turbine
US20110255975A1 (en) Turbines
US20100284802A1 (en) Inflatable wind turbine
GB2451670A (en) A fluid driven rotor
US20120128500A1 (en) Turbines
US8777580B2 (en) Secondary airfoil mounted on stall fence on wind turbine blade
US20140056710A1 (en) Propeller For Ventilator, With A Variable Chord Length
US20110014038A1 (en) Wind turbine with skeleton-and-skin structure
US20070217917A1 (en) Rotary fluid dynamic utility structure
US20110229332A1 (en) Wind Turbine Rotor Blade
US20120198810A1 (en) Strut airfoil design for low solidity exhaust gas diffuser
GB2068502A (en) Fan pump and turbine blades
US20110002781A1 (en) Wind turbine with pressure profile and method of making same
CN101344014A (en) Airfoil for use in rotary machines and method for fabricating same
US20100247289A1 (en) Segmented wind turbine
GB2099929A (en) Turbine

Legal Events

Date Code Title Description
C06 Publication
C02 Deemed withdrawal of patent application after publication (patent law 2001)