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 PDFInfo
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- CN104334872A CN104334872A CN201380027360.4A CN201380027360A CN104334872A CN 104334872 A CN104334872 A CN 104334872A CN 201380027360 A CN201380027360 A CN 201380027360A CN 104334872 A CN104334872 A CN 104334872A
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- wing
- trailing edge
- edge region
- wing flap
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03D—WIND MOTORS
- F03D1/00—Wind motors with rotation axis substantially parallel to the air flow entering the rotor
- F03D1/04—Wind motors with rotation axis substantially parallel to the air flow entering the rotor having stationary wind-guiding means, e.g. with shrouds or channels
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03D—WIND MOTORS
- F03D1/00—Wind motors with rotation axis substantially parallel to the air flow entering the rotor
- F03D1/06—Rotors
- F03D1/065—Rotors characterised by their construction elements
- F03D1/0675—Rotors characterised by their construction elements of the blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2240/00—Components
- F05B2240/10—Stators
- F05B2240/12—Fluid guiding means, e.g. vanes
- F05B2240/122—Vortex generators, turbulators, or the like, for mixing
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2240/00—Components
- F05B2240/10—Stators
- F05B2240/12—Fluid guiding means, e.g. vanes
- F05B2240/123—Nozzles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2240/00—Components
- F05B2240/10—Stators
- F05B2240/13—Stators to collect or cause flow towards or away from turbines
- F05B2240/133—Stators to collect or cause flow towards or away from turbines with a convergent-divergent guiding structure, e.g. a Venturi conduit
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind 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
The cross reference of related application
The application requires the preference in the U.S. Provisional Application sequence No.61/620792 of submission on April 5th, the 2012 and U.S. Provisional Application sequence No.61/763805 in submission on February 12nd, 2013 respectively, and its disclosure by reference entirety is herein incorporated.
Background technique
The present invention relates to the technical field of the annular wing, and more particularly, relate to the protective cover type turbo machine comprising unique wing characteristic.More specifically, that the present invention professor be the embodiment of the annular wing for improving, and the annular wing of described improvement is provided for maintaining performance and reduce simultaneously the cross-section area of the reduction of the use of lateral load and minimizing material.The wing with the structure leading edge engaged with plane of bending surface is roughly common in light airplane and sailing boat field.Plane of bending surface definition is have those of the upper surface that is roughly parallel to lower surface.Compared with the cross-section area with the wing of continually varying distance between upper surface and lower surface, this wing has the cross-section area of reduction.Public level wind turbine for gen-set has one to five the open blade comprising rotor.Wind resource change is become to drive the torque of at least one generator by rotor, and described generator directly or by transmitting set rotatably links to rotor so that changes mechanical energy is become electric energy.
In U.S. Patent Application Serial No.12/054050, described a kind of protective cover type wind turbine, its disclosure by reference entirety is herein incorporated.
Summary of the invention
The embodiment of the present invention professor relates to a kind of annular wing with cross section, its cross section comprises leading edge portion (distance with changing between the upper and lower surfaces), symmetrical region (has symmetry properties about the string of a musical instrument through described symmetrical region, wherein, upper surface is roughly parallel to lower surface in one embodiment) and trailing edge region (on trailing edge, being provided with the wing flap of the string of a musical instrument being approximately perpendicular to the wing).Compared with conventional flap, the trailing edge of this wing arranges the cross-section area that wing flap further reduces the wing.
When wing flap is arranged perpendicular to the string of a musical instrument of the consequent wing, lack supporting structure in intermediate symmetry region and wing flap will not be allowed to play a role.The wing flap on the trailing edge on plane of bending surface like this will bend, until wing flap can not produce any impact on the flowing of crossing the wing.In a kind of embodiment of the present invention professor, the orientation of wing flap can be fixing relative to the string of a musical instrument of the annular wing.Such as, in one embodiment, the annular wing can comprise for wing flap provides the rigidity trailing edge of enough structures, and described wing flap is generally arranged perpendicular to the string of the wing.
In one embodiment, a kind of annular wing of aerodynamic appearance is disclosed.The main body circumferentially extended around central axis has the aerodynamic structures formed by outer surface and internal surface.Outer surface and internal surface axially extend along camber line relative to central axis.The zone line that main body comprises front edge area, trailing edge region and extends between front edge area and trailing edge region.Front edge area has the uneven tranverse sectional thickness extended along the camber line limited by outer surface and the internal surface of main body.Trailing edge region comprises and to extend from it and relative to the wing flap of the angled orientation of the string of a musical instrument of main body, to keep being attached to internal surface to allow fluid stream along internal surface flowing.
In a kind of embodiment of example, disclose a kind of energy extraction protective cover type fluid turbine, it comprises energy extraction assembly and the wing.Energy extraction assembly comprises the rotor radially arranged around central axis.The wing has the main body circumferentially extended around central axis.Main body has the aerodynamic structures formed by outer surface and internal surface.Outer surface and internal surface axially extend along camber line about central axis.The zone line that main body comprises front edge area, trailing edge region and extends between front edge area and trailing edge region.Front edge area has the uneven tranverse sectional thickness extended along the camber line limited by outer surface and the internal surface of main body.Trailing edge region comprises and to extend from it and relative to the wing flap of the angled orientation of the string of a musical instrument of main body, to keep being attached to internal surface to allow fluid stream along internal surface flowing.
In certain embodiments, wing flap extends from trailing edge region perpendicular to the string of a musical instrument, has the length of about 1/10th to about 1/3rd of chord length, and/or comprises at least one perforation allowing fluid to flow through wing flap.
In certain embodiments, wing flap extends from the trailing edge of the wing.
In certain embodiments, wing flap extends between the first loop configuration and the second loop configuration, and the first and second loop configuration provide hoop intensity to wing flap.
In certain embodiments, the first loop configuration provides hoop intensity to the trailing edge region of main body.
In certain embodiments, zone line is included at least one intermediate support portions extended between front edge area and trailing edge region.In certain embodiments, intermediate support portions is made up of rigid material, and/or has the uniform tranverse sectional thickness extended along the mean camber line limited by outer surface and the internal surface of main body.
In certain embodiments, zone line is included at least one middle membrane portion extended between front edge area and trailing edge region.In certain embodiments, middle membrane portion has the uniform tranverse sectional thickness extended along the mean camber line limited by outer surface and the internal surface of main body, and/or is made up of nonrigid material.
In certain embodiments, intermediate support portions provides support structure to middle membrane portion.
Any combination or the conversion of embodiment all can be envisioned.Other object and feature will become apparent from the detailed description considered below in conjunction with accompanying drawing.But it should be understood that accompanying drawing only exemplarily illustrates and designs, not as the restriction of scope of the present invention.
Brief description
The present invention relates to a kind of annular wing, it has the wing section shape at leading edge and trailing edge place with the uniqueness of rigid element, provides support film intermediate portion and with respect to the hoop intensity of trailing edge flaps.In certain embodiments, can be used to be formed the exemplary annular wing (for providing in the control boundary layer, trailing edge place of the wing with for the suction increased compared to the center by the described annular wing of traditional annular wing) in conjunction with rigid structural component and non-rigid membranes part.This wing provides producing the aerodynamic force circulation time causing annular wing inside compared to the pressure difference of wing outside, uses the method for light material.
In one embodiment, the annular wing is around the rotor of protective cover type fluid turbine and power generating equipment.Fluid turbine can have single guard shield, maybe can comprise multiple guard shield.Guard shield is made up of the annular wing that can comprise turbomachine shroud and injection shield usually.
In one embodiment, turbomachine shroud cover rotor and be included in the trailing edge place of the annular wing hybrid element (with provide mix-the injection shield fluid stream fluid of jet pump is communicated with).Guard shield produces on the inner side of turbomachine shroud, causes the aerodynamic force of suction to circulate, and described guard shield is a part for the tightly coupled system be combined with mixing-jet pump, it allows the acceleration compared to designing without protective cover type by the more air of turbine rotor, thus increases the amount of the energy that can be extracted by rotor.
In hydrokinetics field, term " stall " refers to that Fluid flow is from the condition occurred.That is, closely start be separated from surface and become turbulent flow around the fluid of wing flowing.The embodiment taught herein is based on the embodiment and the mixing-injection turbine embodiments that only have mixer.Persons skilled in the art will recognize that exemplary embodiment of the present invention easily can be applied to any annular wing comprising any amount of pipe type or the application of protective cover type fluid turbine.Only have the description of the embodiment of mixer and mixing-injection turbine embodiments not to be intended to limit the scope of the invention, it is only used to be convenient to example embodiment of the present invention is described.Can substantially prevent air-flow from the separation on aerodynamic force surface by hybrid turbine machine and/or mixing-injection turbo machine (MET), advantageously to maintain the efficiency of turbo machine and advantageously to relax diffuser stall.
Kutta-Joukowski theorem describes the circulation around any closing surface.Described circulation causes lift and increases the air-flow by protective cover type turbo machine.Described theorem is determined the lift that produced by unit range in closure and is illustrated as circular rector Γ
∞for time known, the lift L (or L ') of the per unit scope of cylinder can use following formula to calculate:
L’＝ρ
∞V
∞Γ
∞
Formula 1
Here ρ
∞and V
∞be respectively fluid density and the liquid speed of the upstream far away of cylinder.Circular rector Γ
∞line integral is defined as in following formula:
Formula 2
By the use of trailing edge upper aerodynamic power modifier area (AMR) to mixing and/or the injection shield wing, the circulation of improvement provides the performance of the enhancing of protective cover type turbo machine.The circulation that Kutta condition (function for Kutta-Joukowski theorem) controls to be produced by the wing also stops the flow separation from aerodynamic force surface usually until flow arrive trailing edge.
Fluid moves by or passes wing-like and produce aerodynamic force.The component in the direction perpendicular to fluid stream of aerodynamic force is called lift, and the component being parallel to the direction of fluid stream is called resistance.In addition, the wing has suction face and pressure surface (producing lift by them).Wing suction side is limited by the wing surface turned on from now thereof.Usual top (or outside) is connected with sharp keen trailing edge by the leading edge bent with bottom (or inner) wing surface.This trailing edge of camber line at one end cutting of the wing also extends to the tip of leading edge or most windward point.Aerodynamic force circulation is the result of flow divert, and is usually limited by the flow separation in wing suction side.
Example embodiment of the present invention provides by the air-flow on the pressure side of amendment through wing aerodynamic force surface (especially close to trailing edge), and the wing circular rector or the efficient flowing that obtain increase compared with conventional flap structure are turned back.In an exemplary embodiment of the invention, the increase of circular rector to be turned back realization by increasing the surface on the pressure side of the wing.On the pressure side, increase is turned back is possible, is not easy to be separated from the surface of on the pressure side because surface turns to flow direction and flows.In one embodiment, increase top (or outside) surface (namely on the pressure side) of turning back by the wing of flowing and above use trailing edge flaps realization.
In the exemplary embodiment, wing flap can be flat board or other protrusion from trailing edge.In certain embodiments, the length of trailing edge flaps can be the approximate 1-30% of the length of the wing chord extended between the leading edge and trailing edge of the wing.Trailing edge flaps can be directed and can be arranged on and to be positioned at or the wing close to trailing edge place is on the pressure side gone up perpendicular to the string of a musical instrument.In certain embodiments, trailing edge flaps is perforation.Described perforation can allow wing flap to provide effective height with the circular rector providing the resistance of reduction to produce increase simultaneously.
The use of wing flap is by introducing the counterrotating whirlpool tail of wing flap and the flow field that effectively changes in the trailing edge region of the annular wing, and the counterrotating whirlpool tail of described wing flap changes Kutta condition in described region and circular rector.
Embodiment
The more thorough understanding of assembly of the present invention, technique and device is by obtaining with reference to accompanying drawing.These figure are intended to the present invention is described, instead of the scope of sizes related and size or restriction exemplary embodiment will be shown.
Although employ specific term in below describing, these terms only refer to the specified structure in accompanying drawing, are not for limiting the scope of the invention.Should be appreciated that, similar figure notation refers to the assembly of identity function.
When using together with quantity, term " approximately " comprises the value of statement and has by the meaning described in context.Such as, which comprises at least the degree of error be associated with the measurement of specific quantity.When in the context being used in a scope, term " approximately " also should be regarded as the open absolute value limited range by two end points.Such as, scope " from about 2 to about 4 " also discloses scope " from 2 to 4 ".
Protective cover type turbo machine can comprise turbomachine shroud (on the tail end of turbomachine shroud, with or without mixing leaf).As mentioned above, the protective cover type turbo machine comprising mixing guard shield is a kind of applicable example of the annular wing (wherein can use exemplary embodiment of the present invention).Described turbomachine shroud comprises arc guard shield, and wherein, guard shield is the annular wing roughly.Turbomachine shroud comprises rotor, and it extracts energy from primary fluid stream.With compared with protective cover type fluid turbine, due to higher flow velocity, turbomachine shroud provides the flowing of the increase of the energy extraction increased by the permission of rotor.
Mixing-spray turbo machine (MET) mixer/ejector pump can be used to provide the method for energy-producing improvement from fluid stream.As previously described, MET is a kind of applicable example of the annular wing (wherein can use exemplary embodiment of the present invention).Mixing-injection turbo machine comprises arc guard shield and the mixer/ejector pump of series connection, and wherein, each guard shield is the annular wing roughly.Main guard shield comprises rotor, and it extracts energy from primary fluid stream.With compared with protective cover type fluid turbine, due to higher flow velocity, the arc guard shield of series connection and sparger provide the flowing of the increase of the energy extraction increased by the permission of rotor.Energy is transferred to rotor wake flow from by-pass flow by mixer/ejector pump, and described rotor wake flow allows the energy by the higher per unit mass flow of rotor.These two kinds of effects strengthen the overall electrical production of turbine system.
Term used herein " rotor " refers to that wherein one or more attaching vanes can rotate to axle, allows any assembly from the electric power of wind rotation blade or the extraction of energy.Example rotor comprises the rotor or rotor/stator assembly that are similar to propeller cavitation.The rotor of any type all can be enclosed in the turbomachine shroud in fluid turbine of the present invention.
The leading edge of guard shield can be regarded as the front portion of the wing, and the trailing edge of the wing can be regarded as the rear portion of the wing.First assembly of the wing of more locating close to the front portion of the wing can be regarded as " upstream " (that is, the second assembly is " downstream " of the first assembly) of second assembly of more locating close to the rear portion of the wing.In addition, term used in the present invention " internal surface " limits the surface upcountry facing the annular wing of the central axis of the wing.Term used in the present invention " outer surface " limits the surface outwards deviating from the central axis of the wing, makes internal surface than outer surface closer to central axis.Similarly, (namely the term " suction side " of the annular wing used in the present invention or " low voltage side " refer to the inside of the wing, internal surface is radially-inwardly), and the term of the wing used in the present invention " on the pressure side " refers to the outside (that is, from outer surface radially outward) of the wing.
Term used in the present invention " hoop intensity " refers to that structure opposing is around the ability of the radial deformation power of the circumference of cylindrical shape roughly or annular shape structure and the ability providing dimensional stability.Such as, the exemplary embodiment of the wing of the present invention can comprise there is hoop intensity rigidity trailing edge region to resist the deformation force of fluid stream.
In one embodiment, the present invention relates to a kind of annular wing, it trailing edge region comprising the front edge area being generally rigid construction, the zone line formed by structural rigidity and structure nonrigid portions and be generally rigid construction.The annular wing also comprises the wing flap be positioned in trailing edge part, and it is generally perpendicular to the string of the wing.Wing flap can be fixing relative to the orientation of the string of a musical instrument.In one embodiment, the exemplary embodiment of the annular wing may be implemented as turbomachine shroud or turbo machine mixing guard shield, it comprises around the varus section of rotor and the section of turning up, and/or the exemplary embodiment of the annular wing may be implemented as injection shield, it is usually around the outlet of turbomachine shroud or turbo machine mixing guard shield.
Fig. 1 is the forward perspective view of the example annular wing 100.The wing 100 can have the main body 102 extended around central axis 105 circumference.Main body 102 comprises front edge area 112, has the zone line 115 of one or more middle membrane portion 138 and one or more intermediate support portions 139 and have the trailing edge region 116 of wing flap 136.Front edge area 112 can comprise the leading edge 162 of the wing 100, and trailing edge region 116 can comprise the trailing edge 166 of the wing 100.One or more intermediate portions 138 and 139 of zone line 115 can extend between front edge area 112 and trailing edge region 116, so that front edge area 112 is mechanically bonded to trailing edge part 116.One or more middle membrane portion 138 can be formed by such as one or more semi-rigid and/or nonrigid materials of the present invention, and one or more intermediate support portions 139 can be formed by such as one or more semi-rigid and/or rigid materials of the present invention.In a kind of exemplary embodiment, when making middle membrane portion form zone line 115 surperficial of the wing 100, the rigid leading edge region of loop configuration is combined with the discrete supporting part in rigidity trailing edge region and centre and provides enough rigidity, makes itself and the string of a musical instrument and camber line be fixing relation to support the wing flap 136 be positioned on tail edge area territory 116.Thus the structure of the wing 100 is convenient to form fixing angular dependence between wing flap 136 and the string of a musical instrument 140 and between wing flap 136 and mean camber line 170.The exemplary embodiment comprising the wing 100 of wing flap (such as wing flap 136 and 236) of the present invention can produce and show as having larger chord length and not having the annular wing of the similar performance characteristics of the conventional flap of wing flap.
In a kind of exemplary embodiment, described one or more intermediate support portions 139 can provide support structure, with supportive body 102 between leading edge portion 112 and trailing edge part 116.Intermediate support portions 139 can be spaced and circumferentially and discretely can distribute around central axis 105.Intermediate support portions 139 can be defined size and/or be arranged to specify the shape of spatial relationship between leading edge portion 112 and trailing edge part 116 and/or one or more middle membrane portion 138.As a kind of example in a kind of embodiment, described one or more intermediate support portions 139 can arrange the distance between the leading edge of the wing 100 and trailing edge, and it is equivalent to the string of a musical instrument of the wing 100.As another example in a kind of embodiment, described intermediate support portions 139 can be configured as towards trailing edge region 116 tapered distal decentre axis 105, makes the diameter of trailing edge part be greater than the diameter of leading edge portion 112.In certain embodiments, described one or more middle membrane portion 138 can generally according to the profile of intermediate support portions 139.In certain embodiments, described one or more intermediate portion 138 can form profile independent of described one or more intermediate support portions.
In certain embodiments, front edge area 112, trailing edge region 116 and one or more intermediate support portions 139 can integrally be configured as single integral unit, and one or more middle membrane portion 138 is attached to form main body 102 discriminably.In certain embodiments, front edge area 112, trailing edge region 116, one or more intermediate portion 138 and one or more intermediate support portions 139 can be the independent assemblies being mechanically combined together to form main body 102.
Can be used for being formed some examples of plastic materials of the front edge area 112 of the wing 100, trailing edge region 116 and/or one or more intermediate support portions 139, maybe can be used for being formed the front edge area 112 of the wing 100, polymer, carbon composite and/or metal that some examples of plastic materials of part of trailing edge region 116 and/or one or more intermediate support portions 139 can include, but are not limited to such as polyolefin or polyamide.More polyolefinic examples comprise polypropylene and polyethylene, such as high density polyethylene (HDPE) (HDPE) and Low Density Polyethylene (LDPE).Some examples of polyamide comprise nylon.In certain embodiments, PVC＝polyvinyl chloride and plastisol can be used for forming front edge area 112 and trailing edge region 116.
Some examples that can be used to the material forming middle membrane portion 138 can including, but not limited to fabric, polymer film, metal sheet, thin composite material, boats and ships shrink-packaging etc.For the embodiment using fabric, fabric can be impregnated with fluoropolymer resin (as PVC＝polyvinyl chloride) or polymer film (as modified Teflon).Some examples of polymer film include but not limited to the multilayer film etc. of PVC＝polyvinyl chloride (PVC), polyurethane, many fluorinated polymers, analogous composition.Polyurethane film can be durable and can have good weatherability.The aliphatic version of polyurethane film can be UV radiation usually.Some examples of many fluorinated polymers comprise polyvinylidene fluoride (PVDF) and polyvinylfluoride (PVF).On market, available trade mark is called
with
commodity.Many fluorinated polymers have low-down surface energy usually, thus allow its surface to keep not having dirt and chip to a certain extent, and can more easily make ice come off compared with the material with higher surface energy.
In the exemplary embodiment, one or more materials for the formation of the wing 100 and/or its part can strengthen with the reinforcing material of the polyvinyl fiber of such as high crystalline, polyarylamine fiber and Nomex.
Front edge area 112, trailing edge region 116, one or more intermediate support portions 138 and/or one or more middle membrane portion 139 can be formed by such as comprising multilayer material that is two-layer, three layers or more layers.Multi-ply construction can be gained in strength, water resistance, ultraviolet (UV) stability and other function.
In certain embodiments, the front edge area 112 of the wing can be the interlayer composite material of the alkali-free glass fibre matte of such as epoxy impregnation, and the space usable foam in interlayer composite material is filled.Such a construction provides the structure with overall low-density jowar rigidity.
Fig. 2 is the cross sectional view of the exemplary embodiment of the of the present invention annular wing of line 2-2 along Fig. 1, one of middle membrane portion 138 depicting the wing 100.Front edge area 112 can extend to zone line 115 from leading edge 162.Front edge area 112 can have with the Varying-thickness T between internal surface 132 (i.e. suction side surface 132) and outer surface 134 (i.e. pressure side surface 134)
lbulk form, thus form Varying-thickness T
lvolume.The leading edge 162 of the wing 100 can be circular, nose of an ox shape or other shape, to form the aerodynamic force surface for fluid being divided at least two strands (such as, along the suction side and along outer surface 134 on the pressure side of internal surface 132).The sectional shape of front edge area 112 can increase section thickness T along mean camber line 170
ltapered distal from leading edge 162, and then reduces section thickness T
ltaper is towards center camber line or mean camber line 170, and the junction point 131 between middle membrane portion 138, makes the section thickness T of front edge area 112
lgenerally change to junction point 131 from leading edge 162, front edge area 112 is mechanically bonded to middle membrane portion 138.Center camber line or mean camber line 170 be generally positioned at the wing 100 respectively along the neutral position between the outer surface 132 and internal surface 134 of the longitudinal extent of the wing 100.
As shown in Figure 2, string 140 is limited to the length of the wing 100 between the leading edge 162 of the wing 100 and trailing edge 166, and it can be determined based on mean camber line 170.The section thickness of the wing 100 may correspond to the distance in the internal surface 132 from the outer surface 134 of the wing 100 to the wing 100 measured by mean camber line 170, and can change along with the distance along mean camber line 170, the section thickness of the wing 100 is being changed from leading edge 162 to the length of the wing 200 of trailing edge 166.The inner region (or volume) 113 formed by the surface 132,134 in front edge area 112 can be hollow, or can with for providing the supporting part of structural rigidity and shape to fill.According to a kind of embodiment, a kind of foamed material 172 can be used to provide shape and structural rigidity to assembly.
In certain embodiments, one or more middle membrane portion 138 of zone line 115 can extend from front edge area 112 point-blank to trailing edge region 116.In certain embodiments, middle membrane portion 138 can have curvature between front edge area 112 and trailing edge region 116.Middle membrane portion 138 can have the roughly even and constant section thickness T along its length
iM.In the exemplary embodiment, surface 132,134 can location adjacent one another are and can contact to form middle membrane portion 138, makes the section thickness T of middle membrane portion 138
iMthe thickness of one or more materials between surface 132 and 134 can be approximated.In certain embodiments, middle membrane portion 138 can be formed by the one piece material with thickness, to make in middle membrane portion 138 not Existential Space or space.Such as, middle membrane portion 138 can be the plane of bending form with relative constancy thickness.
In one embodiment, middle membrane portion 138 can be fixing with nail, adhere to, frictional fit, or be otherwise attached or be fixed to front edge area 112, so that middle membrane portion 138 is fixed to front edge area 112.In one embodiment, the junction point 131 between front edge area 112 and middle membrane portion 138 can by being configured to receive and keeping the groove of the upstream extremity 143 of middle membrane portion 138 or passage 117 to be formed.Such as, upstream extremity 143 can have the circular cross-section corresponding with the circular cross-section of passage 117, the upstream extremity 143 of intermediate membrane region 138 can be slipped into, engage and kept by the passage 117 of front edge area 112.
In the exemplary embodiment, trailing edge region 116 can be formed as the loop configuration circumferentially extended around central axis 105, and trailing edge 116 can have and is greater than the diameter of leading edge 162 or the diameter of width or width.The one end relative with trailing edge 166 in trailing edge region 116 can comprise the recessed portion of such as groove or passage 182, and it is configured to receive and be mechanically bonded to middle membrane portion 138.In a kind of exemplary embodiment, trailing edge region can the trailing edge 166 of guide vane 100 provide rigidity to make trailing edge 166.
Trailing edge region 116 can comprise the wing flap 136 extended from it.In a kind of exemplary embodiment, wing flap 136 can extend radially outwardly near trailing edge 166 or its.Wing flap 136 can have the length L extended with angle θ relative to the string of a musical instrument 140.In a kind of exemplary embodiment, the angle θ between the string of a musical instrument 140 and wing flap 136 can be fixing.The length L of wing flap 136 can fewer than the length of the string of a musical instrument 140 about 10 to percent three ten.In a kind of exemplary embodiment, the length L of wing flap 136 can extend perpendicular to the string of a musical instrument 140, and can implement the air-flow along outer surface 134 is turned back.In the exemplary embodiment, wing flap 136 can comprise perforation 184 and reduces to allow some air to flow through wing flap 136 power be applied to by air-flow on wing flap.In the exemplary embodiment, wing flap 136 can be formed by with the same or similar material of middle membrane portion 138.
Fig. 3 is the cross sectional view of the wing of the Fig. 1 of line 3-3 along Fig. 1, which depict one of intermediate support portions 139 of the zone line 115 that can be arranged between front edge area 112 and trailing edge region 116.In a kind of exemplary embodiment, as described in Fig. 3, intermediate support portions 139 can form with front edge area 112, makes intermediate support portions 139 and front edge area 112 form overall structure and intermediate support portions 139 can mechanically be bonded to trailing edge region 116.In another kind of exemplary embodiment, intermediate support portions 139 is mechanically bonded to front edge area 112 and/or trailing edge region 116.In another exemplary embodiment, intermediate support portions 139 can form with front edge area 112 and/or trailing edge region 116.
Intermediate support portions 139 can be the wing 100 provides structural support to limit the distance between front edge area 112 and trailing edge region 116, and/or can be middle membrane portion 138 provide the structural support, such as, limit the profile of middle membrane portion 138.Middle rigid element 139 can be the elongated element with clavate roughly or rod configurations.Intermediate support portions 139 can be set to engage the passage 182 be formed in trailing edge region 116, so that intermediate support portions 139 is mechanically bonded to trailing edge region 116.In certain embodiments, intermediate support portions can form with front edge area 112 and/or trailing edge region 116.
In certain embodiments, intermediate support portions 139 can linearly extend to trailing edge region 116 from front edge area 112.In certain embodiments, intermediate support portions 139 can have curvature between front edge area 112 and trailing edge region 116.Intermediate support portions 139 can have the roughly even and constant section thickness T along length
iS.In the exemplary embodiment, the surface 132,134 of intermediate support portions 139 can be located adjacent to each other, and can contact the section thickness T that formation intermediate support portions 139 makes intermediate support portions 139
iSthe thickness of one or more materials between surface 132,134 can be approximately equal to.In certain embodiments, intermediate support portions 139 can be formed by the one piece material with thickness, to make in intermediate support portions 139 not Existential Space or space.Such as, intermediate support portions 139 can be the plane of bending form with relative constancy thickness.
In one embodiment, middle membrane portion 138 can surround or around intermediate support portions 139.In certain embodiments, middle membrane portion 138 can fixing with nail, adhere to, frictional fit, or be otherwise attached or be fixed to intermediate support portions 139 so that middle membrane portion 138 is fixed to intermediate support portions 139.Such as, in one embodiment, polyethylene shrink wrap can be used as middle membrane portion 138 and polyethylene shrink wrap can around intermediate support portions 139, and can apply heat to polyethylene shrink wrap and polyethylene shrink wrap is contracted on intermediate support portions 139 form tight friction fit.In certain embodiments, middle membrane portion 138 can extend to trailing edge region 116 from front edge area 112 respectively between a pair intermediate support portions 139.
With reference to figure 4, depict the detail section front view in the trailing edge region 116 of the wing 100 of Fig. 2.This exemplary embodiment is included in the wing flap 136 on trailing edge 116.Wing flap 136 generally perpendicular to the string of a musical instrument 140 of wing section, or in other words relative to the string of a musical instrument 140 of wing section in the angle θ between about 85 ° and 120 °.In certain embodiments, trailing edge region 116 can comprise the rigid element 148 engaged with middle membrane portion 138 (such as by passage 182).Rigid element 148 engages with ring 146, and ring 146 engages with wing flap 136.Ring 146 provides hoop intensity to rigid element 148.Wing flap 136 outer rim comprised to wing flap 136 provides at least one ring 144 of hoop intensity.As mentioned above, the rigid structural support parts of intermediate support portions 139 form radially separate (Fig. 1 and Fig. 3) around the annular wing being close to middle membrane portion 138.Intermediate support portions 139 provides structure to support location and the structure of trailing edge 116.The structural support provided by intermediate support portions 139 maintains the angle θ of wing flap 136 relative to string 140, and provides structure to support middle membrane portion 138.
With reference to figure 5, depict the normal section of the annular wing of exemplary embodiment 100.Around the wing 100 from leading edge 112 to the direction of the air-flow of trailing edge 116 and path by the arrow 152 in suction side 132 (that is, internal surface 132), and the arrow 154 on the pressure side 134 (that is, outer surfaces) represents.
Refer again to Fig. 5, wing flap 136 causes Stagnation zones 141 in the flowing of on the pressure side going up of the wing 134.Trailing edge 166 on the trailing edge 166 of the wing 100 or close to the wing 100 increases wing flap 136 also at the leeward of the trailing edge 116 of the wing 100 generation whirlpool 118.The increase of wing flap 136 makes the air-flow 154 on the pressure side on 134 of the wing 100 be pushed upwardly, thus allows the fluid stream 152 in the suction side 132 of the wing 100 to keep being attached to surface and the circulation producing the improvement of fluid stream.
Fig. 6 depicts the perspective view of another exemplary wing 200.The main body 202 of the wing 200 can comprise front edge area 212, zone line 215 and trailing edge region 216.The wing 200 can comprise hybrid element 226,228, and it can be formed by zone line 215 and trailing edge region 216.As shown in the figure, mixing leaf can comprise the low-yield mixing leaf 228 extended internally towards central axis 205, and from central axis 205 outward extending high-energy mixing leaf 226.In other words, the trailing edge 124 of turbomachine shroud 104 is shaped to the different mixing leaf of formation two groups.Mixing leaf 126,128 can be formed around central axis 205 circular sawtooth roughly or the concaveconvex shape of circumference wave.
The trailing edge region 216 of the wing 200 can be formed by rigid material, and can have around central axis 205 circular sawtooth roughly or the concaveconvex shape of circumference wave, the structural architecture of mixing leaf 126,128 can be directed into the middle membrane portion 238 of zone line 215 by it.Trailing edge region can comprise one or more wing flap 236.In a kind of exemplary embodiment, as shown in Figure 6, each low-yield mixing leaf 228 can comprise one of wing flap 236 and high-energy mixing leaf 226 can not have wing flap 236.In a further exemplary embodiment, high-energy mixing leaf 226 and low-yield mixing leaf 228 can comprise wing flap 236.In yet another exemplary embodiment, wing flap 236 can extend to form the single flap arranged continuously around central axis 205 along trailing edge region 216 continuously.In a kind of exemplary embodiment, when middle membrane portion is implemented zone line surperficial forming the wing, the discrete supporting part in centre of the front edge area 212 of loop configuration and rigidity trailing edge region 216 and zone line 215 is combined the rigidity that provides enough to support wing flap 136 on trailing edge region 116 and the string of a musical instrument for fixed relationship.Thus the structure of the wing 100 is convenient to provide the fixed angular relationship between wing flap 136 and the string of a musical instrument 140 and between wing flap 136 and mean camber line 170.The exemplary embodiment comprising the wing 200 of wing flap 236 can produce and show and have larger chord length and do not have the annular wing of the conventional flap similar performance characteristics of wing flap.
In a kind of exemplary embodiment, described one or more intermediate support portions 239 can provide structural support to the main body 202 between leading edge portion 212 and trailing edge part 216.Intermediate support portions 239 can be spaced and can distribute discretely and circumferentially around central axis 205.Intermediate support portions 239 can be defined size and/or be arranged to specify the spatial relationship between leading edge portion 212 and trailing edge part 216.As a kind of example, in one embodiment, described one or more intermediate support portions 239 can set the distance between the leading edge of the wing 200 and trailing edge, and it corresponds to the string of a musical instrument of the wing 200.
Fig. 7 is the cross sectional view of the wing 200 of Fig. 6 of 7-7 along the line.As shown in Figure 7, because front edge area comprises the volume of change and middle membrane portion 238 comprises roughly uniform volume, the cross section of the wing 200 generally corresponds to the cross section of the wing 100.The leading edge 262 of the wing 100 can be circular, nose of an ox shape or other shape to form the aerodynamic force surface for fluid being divided at least two strands (such as, along the suction side and along outer surface 134 on the pressure side of internal surface 132).The sectional shape of front edge area 212 can increase section thickness tapered distal from leading edge 262 along mean camber line 270, and then reduces section thickness taper towards center camber line or mean camber line 270 to zone line.Center camber line or mean camber line 270 be generally positioned at the wing 200 respectively along the neutral position between the outer surface 232 and internal surface 234 of the longitudinal extent of the wing 200.
As shown in Figure 7, string 240 limits the length of the wing 200 between the leading edge 262 of the wing 200 and trailing edge 266, and it can be determined based on mean camber line 270.Middle membrane portion 238 can have roughly all even constant section thickness along its length.In described exemplary embodiment, surface 232,234 can located adjacent one anotherly be located, and can contact to form middle membrane portion 238.
Similar with the zone line 115 of the exemplary wing 100 of the present invention, zone line 215 can comprise middle membrane portion 238 and intermediate support portions 239.Middle membrane portion 238 can be formed by semi-rigid and/or nonrigid material, and intermediate support portions 238 can be formed by semi-rigid and/or rigid material.The transition region that zone line 215 provides varus hybrid element 226 and turns up between hybrid element 228.Rigidity trailing edge region 216 provides structure to support the film surface of composition hybrid element 226 and 228.In the exemplary embodiment, trailing edge region 216 can be formed as the rigid construction that extends around central axis 205 with circumferential wave mode.In a kind of exemplary embodiment, trailing edge region 216 can the trailing edge 266 of guide vane 200 provide rigidity to make trailing edge 266.
Trailing edge region 216 can comprise the wing flap 236 extended from it.In a kind of exemplary embodiment, wing flap 236 can extend radially outwardly near trailing edge 266 or its.Wing flap 236 can have the length L extended with angle θ ' relative to the string of a musical instrument 240.In a kind of exemplary embodiment, the angle θ ' between the string of a musical instrument 140 and wing flap 236 can be fixing, and/or the length L of wing flap 236 can fewer than the length of the string of a musical instrument 240 about 10 to about percent 30.In a kind of exemplary embodiment, the length L of wing flap 236 can extend perpendicular to the string of a musical instrument 140, and can implement the air-flow along outer surface 234 is turned back.In the present example embodiment, wing flap 236 engages with the trailing edge 266 of the hybrid element 228 that turns up.Trailing edge 266 is made up of the similar assembly also described as shown in Fig. 3-Fig. 4.In the exemplary embodiment, wing flap 236 can comprise perforation 284 and reduces to allow some air to flow through wing flap 236 power be applied to by air-flow on wing flap 236.Wing flap 236 is defined size or is set to allow fluid stream along internal surface flowing to keep being attached to internal surface.
Fig. 8 depicts the forward perspective view of the exemplary protective cover type fluid turbine 300 of wind turbine form, and it has supporting structure 302, energy extraction assembly 345 and by the turbomachine shroud having front edge area 112, the exemplary wing 100 in zone line 115 and trailing edge region 116 is formed.Energy extraction assembly 345 can comprise gondola body 350 and rotor 340.Rotor 340 engages with gondola body 350 in the proximal end of rotor blade.The wing 100 can surrounding rotor 340.In a kind of exemplary embodiment, the leading edge 166 of the wing 100 can be positioned on the upstream of rotor 340, and/or the trailing edge 166 of the wing 100 can be positioned on the downstream of rotor 340.Leading edge 162 can form the entrance of protective cover type fluid turbine 300 and trailing edge 166 can form the exhaust port of protective cover type fluid turbine 300.Wing flap 136 allows fluid stream (such as air-flow) along the internal surface flowing of the wing to keep being attached to internal surface.In a kind of exemplary embodiment, the wing 100 can use elongated supporting structure 307 to locate relative to gondola body 350 and rotor 340, and gondola body 350, rotor 340 and the wing 100 are relative to each other located coaxially around central axis 105.
Fig. 9 depicts the forward perspective view of the exemplary protective cover type fluid turbine 400 of wind turbine form, and it has supporting structure 302, energy extraction assembly 345 and by the turbo machine mixing guard shield having front edge area 212, the exemplary wing 200 in zone line 215 and trailing edge region 216 is formed.The wing 200 can surrounding rotor 340.In a kind of exemplary embodiment, the leading edge 266 of the wing 200 can be positioned on the upstream of rotor 340, and/or the trailing edge 266 of the wing 200 can be positioned on the downstream of rotor 340.Leading edge 262 can form the entrance of protective cover type fluid turbine 400 and trailing edge 266 can form the exhaust port of protective cover type fluid turbine 400.As mentioned above, trailing edge 266 comprises varus hybrid element 226 and the hybrid element 228 that turns up.Varus hybrid element 226 to curve inwardly and the hybrid element 228 that turns up is bent outwardly from central axis 205 towards central axis 205.Wing flap 236 can allow fluid stream (such as air-flow) along the internal surface flowing of the wing to keep being attached to internal surface.In a kind of exemplary embodiment, the wing 200 can use elongated supporting structure 307 to locate relative to gondola body 350 and rotor 340, and gondola body 350, rotor 340 and the wing 200 are relative to each other located coaxially around central axis 205.
Figure 10 is the forward perspective view of the exemplary embodiment of protective cover type fluid turbine 500, and it comprises the exemplary embodiment of the annular wing 100 and 200 of the present invention.Figure 11 is the backward perspective view of the protective cover type fluid turbine of Figure 10.Figure 12 is the detail section lateral perspective of protective cover type fluid turbine 500 of the Figure 10 and 11 intercepted through the hybrid element 228 that turns up.Figure 13 is the detail section lateral perspective of protective cover type fluid turbine 500 of the Figure 10 and 11 intercepted through varus hybrid element 226.The detail section of Figure 12 and 13 depicts the of the present invention annular wing 100 and 200 be included in mixing-injection turbomachine shroud.The annular wing 100 comprises front edge area 112, zone line 115 and trailing edge region 116.The annular wing 200 comprises front edge area 212, zone line 215 and trailing edge region 216.
In a kind of exemplary embodiment, protective cover type fluid turbine 500 can refer to mixing/injection fluid turbine, and the wing 200 and the wing 100 form mixer/ejector pump here.With reference to figure 10-13, protective cover type fluid turbine 500 is supported by supporting structure 302, and the injection shield comprising the turbo machine mixing guard shield formed by the exemplary embodiment of the wing 200, the energy extraction assembly formed by gondola body 350 and rotor 340 and formed by the wing 200.Coaxially to each other, that is, they share central axis common 505 for rotor 340, the wing 200 (that is, turbo machine mixing guard shield) and the wing 100 (that is, injection shield).In a kind of exemplary embodiment, the wing 200 can use elongated supporting structure 307 to locate relative to gondola body 350 and rotor 340, and the wing 100 can use elongated supporting structure 506 to locate relative to the wing 200.
In a kind of exemplary embodiment, the leading edge 266 of the wing 200 can be positioned on the upstream of rotor 340, the trailing edge 266 of the wing 200 can be positioned on the downstream of rotor 340, and the leading edge 162 of the wing 100 can be positioned on the downstream of rotor 340, and/or the trailing edge 166 of the wing 100 can be positioned on the downstream of trailing edge 266.Leading edge 262 can form the entrance of the wing 200 in protective cover type fluid turbine 400, and trailing edge 266 can form the exhaust port of the wing 200 in protective cover type fluid turbine 400.
The injection shield formed by the wing 100 comprises the front end or entry end that are limited by leading edge 162, and the rear end limited by trailing edge 166 or exhaust port end.
Figure 14 depicts trailing edge region 116 and 216 in more detail to illustrate exemplary puncture 184 and 284 respectively.Perforation 184 and 284 is formed in wing flap 136 and 236 discriminably, flows through wing flap 136,236 reduce the power be applied to by air-flow on wing flap 236 to allow some air.
Figure 15 is the forward perspective view of another exemplary embodiment of protective cover type fluid turbine 600, and it comprises the example annular wing 700 and 800 of the present invention.Figure 16 is the detail section side elevation of the fluid turbine of Figure 15.With reference to figure 15-16, protective cover type fluid turbine 600 is supported by supporting structure 302 and comprises the energy extraction assembly 345 with rotor 340 and gondola body 350.The annular wing 700 forms turbomachine shroud and the annular wing 800 forms the injection shield of protective cover type fluid turbine 600.Rotor 340, turbomachine shroud (that is, the wing 700) and injection shield (that is, the wing 800) coaxially to each other, namely share central axis common 605.
The mode that the wing 700 and the wing 800 can be similar to the exemplary wing 100 and 200 of the present invention is formed.The wing 700 can comprise the front edge area 712 with leading edge 762 (it forms front end or the entry end of the wing 700).Front edge area 712 can have the cross section structure (as shown in figure 16) roughly similar or identical with the cross section structure of 212 with front edge area 112 of the present invention.
The wing 700 also comprises the trailing edge region 716 with trailing edge 766, and described trailing edge 766 forms rear end or outlet (discharge) end of the wing 700.Trailing edge region 716 can have the cross section structure (as shown in figure 16) roughly similar or identical with the cross section structure in trailing edge region 112 of the present invention.In this example, trailing edge region 716 can have the polygonal shape of the many sides with facet-structure.Such as, trailing edge region 716 can be included in the little face 775 that node 777 place connects.
The wing 800 comprises the front edge area 812 with leading edge 862 (front end of its formation wing 800 or entry end, and rear end).The wing 800 also comprises the trailing edge region 816 with trailing edge 866 (it forms exhaust end or the outlet end of the wing 800).The wing 800 comprises little the annular wing, and front edge area 812 can have the cross section generally similar or identical with front edge area 112,212 and 712 of the present invention.In this example, trailing edge region 816 can have the many sides polygonal shape with facet-structure.Such as, trailing edge region 816 can be included in the little face 875 that node 877 place connects.
The wing 700 and 800 comprises extension between front edge area 712 and 812 respectively discriminably, and extends to the zone line 715 and 815 in trailing edge region 716 and 816 respectively.Zone line 715 and 815 can be formed by intermediate support portions and middle membrane portion.
Depict the detail section of the protective cover type turbo machine of Figure 15 in Figure 16, and show the annular wing 700 and 800 of little of being included in mixing-injection turbomachine shroud.The wing 700 and 800 has roomy front edge area 712 and 812 respectively, and it engages with zone line 715 and 815 respectively, and described zone line 715 and 815 forms transition region respectively between front edge area 712/812 and trailing edge region 716/816.Rigidity trailing edge region 716 is made up of similar assembly as described in the present invention, and provides structure to support the middle membrane portion of zone line 715.
In certain embodiments, intermediate support portions can be included in node 777 and/or little face 775, and it generally forms middle membrane portion.Wing flap 736 engages with the trailing edge region 716 of the wing 700 to extend from trailing edge with the tilt fixing of the string of a musical instrument relative to the wing 700 (such as vertical).Same, the wing 800 is made up of roomy front edge area 812, zone line 815 and trailing edge region 816.Wing flap 836 engages with the trailing edge region 816 of the wing 800 to extend from trailing edge with the tilt fixing of the string of a musical instrument relative to the wing 800 (such as vertical).Zone line 815 can comprise the middle membrane portion as little face 875 and node 877 of description.The intermediate support portions 839 of zone line 815 radially can distribute around central axis 705, and engages that the wing 700 is connected to the wing 800 with the wing 700.
Figure 17 depicts the forward perspective view of the exemplary protective cover type fluid turbine 900 of wind turbine form, and it has supporting structure 302, energy extraction assembly 345 and by the turbomachine shroud having front edge area 712, the exemplary wing 700 in zone line 715 and trailing edge region 716 is formed.Energy extraction assembly 345 can comprise gondola body 350 and rotor 340.Rotor 340 engages with gondola body 350 in the proximal end of rotor blade.The wing 700 can surrounding rotor 340.In a kind of exemplary embodiment, the leading edge 766 of the wing 700 can be positioned on the upstream of rotor 340, and/or the trailing edge 766 of the wing 700 can be positioned on the downstream of rotor 340.Leading edge 762 can form the entrance of protective cover type fluid turbine 900 and trailing edge 766 can form the exhaust port of protective cover type fluid turbine 900.Wing flap 736 can allow fluid stream (such as air-flow) along the internal surface flowing of the wing to keep being attached to internal surface.In a kind of exemplary embodiment, the wing 700 can use elongated supporting structure 307 to locate relative to gondola body 350 and rotor 340, and gondola body 350, rotor 340 and the wing 100 are relative to each other located coaxially around central axis 605.
Exemplary embodiment of the present invention advantageously provides a kind of annular wing usually relative to the traditional endless wing with lightweight construction.The exemplary embodiment comprising the wing of wing flap can produce show to longer chord length and without the annular wing of the similar behavior characteristics of the conventional flap of wing flap.In addition, exemplary embodiment of the present invention, compared to traditional wing, especially relative to the maintenance and repair of middle membrane portion and wing flap, provides usually more easily and the maintenance and repair of less wing consuming time.
As previously described, the present embodiment is not specific to the sparger of a kind of MET, and it can be applied to the pipe type or protective cover type fluid turbine understood those related domains.The present invention reference example embodiment is described.Obviously, other staff can expect remodeling and conversion above on the basis to the reading described in detail and understanding.When they are in the scope of appended claims or its equivalent, the present invention includes all these remodeling and conversion.
Accompanying drawing explanation
Fig. 1 is the forward perspective view of the example annular wing of the present invention.
Fig. 2 is the lateral cross-sectional views of the exemplary wing of Fig. 1.
Fig. 3 is the lateral cross-sectional views of the exemplary wing of Fig. 1.
Fig. 4 is the detailed lateral cross-sectional views of the exemplary wing of the embodiment of Fig. 1.
Fig. 5 is the lateral cross-sectional views of the exemplary wing of the embodiment of Fig. 1 with streamline.
Fig. 6 is the forward perspective view of another example annular wing of the present invention.
Fig. 7 is the lateral cross-sectional views of the exemplary wing of Fig. 6.
Fig. 8 is the forward direction right side perspective view of exemplary protective cover type turbo machine, and its turbomachine shroud corresponds to the exemplary wing of Fig. 1.
Fig. 9 is the forward direction right side perspective view of exemplary protective cover type turbo machine, and its turbomachine shroud corresponds to the exemplary wing of Fig. 6.
Figure 10 is the forward direction right side perspective view of the exemplary mixing-injection turbo machine of the exemplary wing including Fig. 1 and 6.
Figure 11 is the backward right side perspective view of the exemplary mixing-injection turbo machine of Figure 10.
Figure 12 is the detail section lateral perspective through the exemplary mixing-injection turbo machine mixing Figure 10 and Figure 11 that wing part intercepts that turns up.
Figure 13 is the detail section lateral perspective of the mixing-injection turbo machine mixing Figure 10 and Figure 11 that wing part intercepts through varus.
Figure 14 is the detailed view of the wing flap on the trailing edge region of the exemplary mixing jetting turbo machine being arranged on Figure 10 and Figure 11.
Figure 15 is the forward direction right side perspective view of another exemplary mixing-injection turbo machine, and its turbomachine shroud and injection shield have faceting formation.
Figure 16 is the detail section lateral perspective through the exemplary mixing-injection turbo machine mixing Figure 15 that wing part intercepts that turns up.
Figure 17 is the forward direction right side perspective view of another exemplary protective cover type turbo machine, and its turbomachine shroud has faceting formation.
Claims (21)
1. the annular wing be shaped aerodynamically, it comprises:
Main body, it circumferentially extends around central axis, there is the aerodynamic structures formed by outer surface and internal surface, described outer surface and internal surface axially extend along camber line relative to central axis, the zone line that described main body comprises front edge area, trailing edge region and extends between front edge area and trailing edge region;
Front edge area, it has the section thickness heterogeneous of the camber line extension limited along outer surface and the internal surface by main body; And
Trailing edge region, it comprises and to extend from it and relative to the wing flap of the angled orientation of the string of a musical instrument of main body, to keep being attached to internal surface to allow fluid stream along internal surface flowing.
2. the wing according to claim 1, wherein, wing flap extends from trailing edge region perpendicular to the string of a musical instrument.
3. the wing according to claim 1, wherein, the length of wing flap is about 1/10th of chord length to about 1/3rd.
4. the wing according to claim 1, wherein, wing flap comprises at least one perforation to allow fluid to flow through wing flap.
5. the wing according to claim 1, wherein, wing flap extends from the trailing edge of the wing.
6. the wing according to claim 1, wherein, wing flap extends between the first loop configuration and the second loop configuration, and the first loop configuration and the second loop configuration provide hoop intensity to wing flap.
7. the wing according to claim 6, wherein, the first loop configuration provides hoop intensity to the trailing edge region of main body.
8. the wing according to claim 1, wherein, zone line is included at least one intermediate support portions extended between front edge area and trailing edge region.
9. the wing according to claim 8, wherein, intermediate support portions is made up of rigid material.
10. the wing according to claim 8, wherein, intermediate support portions has the uniform section thickness extended along mean camber line, and described mean camber line is limited by the outer surface of main body and internal surface.
11. wings according to claim 8, wherein, zone line is included at least one middle membrane portion extended between front edge area and trailing edge region.
12. wings according to claim 11, wherein, middle membrane portion has the uniform section thickness extended along mean camber line, and described mean camber line is limited by the outer surface of main body and internal surface.
13. wings according to claim 11, wherein, zone line is made up of nonrigid material.
14. wings according to claim 11, wherein, intermediate support portions provides structural support to middle membrane portion.
15. 1 kinds of energy extraction protective cover type fluid turbines, it comprises:
Energy extraction assembly, it comprises the rotor radially arranged around central axis; And
The wing, it has the main body circumferentially extended around central axis, main body has the aerodynamic structure formed by outer surface and internal surface, outer surface and internal surface axially extend along camber line relative to central axis, the zone line that main body comprises front edge area, trailing edge region and extends between described front edge area and trailing edge region;
Front edge area has the section thickness heterogeneous extended along camber line, and described camber line is limited by the outer surface of main body and internal surface; And
Trailing edge region comprises and to extend from it and relative to the wing flap of the angled orientation of the string of a musical instrument of main body, to keep being attached to internal surface to allow fluid stream along internal surface flowing.
16. fluid turbines according to claim 15, wherein, wing flap extends from trailing edge region perpendicular to the string of a musical instrument.
17. fluid turbines according to claim 15, wherein, the length of wing flap is about 1/10th of chord length to about 1/3rd.
18. fluid turbines according to claim 16, wherein, wing flap comprises at least one perforation to allow fluid to flow through wing flap.
19. fluid turbines according to claim 15, wherein, wing flap extends from the trailing edge region of the wing, wing flap extends between the first loop configuration and the second loop configuration, first loop configuration and the second loop configuration provide hoop intensity to wing flap, and the first loop configuration provides hoop intensity to the trailing edge region of main body.
20. fluid turbines according to claim 15, wherein, zone line comprises at least one intermediate support portions be made up of rigid material and at least one middle membrane portion be made up of nonrigid material, and intermediate support portions and middle membrane portion extend between front edge area and trailing edge region.
21. fluid turbines according to claim 20, wherein, at least one of intermediate support portions or middle membrane portion have the uniform cross-section thickness extended along mean camber line, and described mean camber line is limited by the outer surface of main body and internal surface.
Applications Claiming Priority (5)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US201261620792P | 2012-04-05 | 2012-04-05 | |
| US61/620,792 | 2012-04-05 | ||
| US201361763805P | 2013-02-12 | 2013-02-12 | |
| US61/763,805 | 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 CN104334872A (en) | 2015-02-04 |
Family
ID=48143640
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201380027360.4A Pending 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 (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20150023789A1 (en) * | 2013-07-16 | 2015-01-22 | Massachusetts Institute Of Technology | Wind Turbine Power Augmentation |
| CH713477B1 (en) * | 2017-02-17 | 2021-10-15 | Venturicon Sarl | Wind turbine. |
Family Cites Families (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1893064A (en) * | 1931-04-03 | 1933-01-03 | Zap Dev Company | Aircraft |
| US1893065A (en) * | 1931-04-03 | 1933-01-03 | Zap Dev Company | Aircraft and control thereof |
| US4411588A (en) * | 1978-04-28 | 1983-10-25 | Walter E. Currah | Wind driven power plant |
| SE430529B (en) * | 1982-12-30 | 1983-11-21 | Vindkraft Goeteborg Kb | DEVICE FOR WIND TURBINES |
| 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 power generator |
| US8393850B2 (en) * | 2008-09-08 | 2013-03-12 | Flodesign Wind Turbine Corp. | Inflatable wind turbine |
| 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 |
| US8672622B2 (en) * | 2007-11-15 | 2014-03-18 | Kyushu University, National University Corporation | Fluid machine, wind turbine, and method for increasing velocity of internal flow of fluid machine, utilizing unsteady flow |
| JP5030122B2 (en) * | 2009-03-24 | 2012-09-19 | 国立大学法人九州大学 | Fluid machine, windmill, and internal flow speed increasing method of fluid machine using unsteady flow |
-
2013
- 2013-04-05 EP EP13718012.1A patent/EP2834516A1/en not_active Withdrawn
- 2013-04-05 CN CN201380027360.4A patent/CN104334872A/en active Pending
- 2013-04-05 US US13/857,750 patent/US20130266438A1/en not_active Abandoned
- 2013-04-05 CA CA2869608A patent/CA2869608A1/en not_active Abandoned
- 2013-04-05 WO PCT/US2013/035464 patent/WO2013152297A1/en active Application Filing
Also Published As
| Publication number | Publication date |
|---|---|
| WO2013152297A1 (en) | 2013-10-10 |
| US20130266438A1 (en) | 2013-10-10 |
| CA2869608A1 (en) | 2013-10-10 |
| EP2834516A1 (en) | 2015-02-11 |
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Application publication date: 20150204 |