CN102782312A - Fluid turbine - Google Patents
Fluid turbine Download PDFInfo
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- CN102782312A CN102782312A CN2011800092544A CN201180009254A CN102782312A CN 102782312 A CN102782312 A CN 102782312A CN 2011800092544 A CN2011800092544 A CN 2011800092544A CN 201180009254 A CN201180009254 A CN 201180009254A CN 102782312 A CN102782312 A CN 102782312A
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- section
- bandy
- aduncate
- sections
- fluid turbine
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- 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
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- 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
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- 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
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- 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
- F05B2260/00—Function
- F05B2260/96—Preventing, counteracting or reducing vibration or noise
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- 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 shrouded fluid turbine comprises an impeller and a turbine shroud surrounding the impeller. The inlet of the turbine shroud is flared. The shroud includes alternating inward and outward curving lobe segments along a trailing edge of the turbine shroud. The inward and outward curving lobe segments have exposed lateral surfaces, or in other words do not have sidewalls joining the inward and outward curving lobe segments. This allows for both transverse mixing and radial mixing of air flow through the turbine shroud with air flow passing along the exterior of the turbine shroud.
Description
Background technique
The preference of the U.S. Provisional Patent Application of the No.61/415610 that the application requires to submit on November 19th, 2010, the No.61/332722 that submits on May 7th, 2010 and the No.61/303339 that submits on February 11st, 2010.The application also is the part continuation in the U.S. Patent application No.12/983082 of submission on December 31st, 2010; This U.S. Patent application No.12/983082 is that the part of the U.S. Patent application No.12/914509 that submits on October 28th, 2010 of the preference of the U.S. Provisional Patent Application No.61/332722 that requires to submit on May 7th, 2010 continues, and also is that the part of the U.S. Patent application No.12/054050 that submits on March 24th, 2008 of the preference of the U.S. Provisional Patent Application No.60/919588 that requires to submit on March 23rd, 2007 continues.The application also is the part continuation in the U.S. Patent application No.12/054050 of submission on March 24th, 2008, and this U.S. Patent application No.12/054050 requires in the preference of the U.S. Provisional Patent Application No.60/919588 of submission on March 23rd, 2007.The application also is the part continuation in the U.S. Patent application No.12/749341 of submission on March 29th, 2010, and this U.S. Patent application No.12/749341 is that the part of three different patent applications continues.First; U.S. Patent application No.12/749341 is the part continuation in the U.S. Patent application No.12/054050 of submission on March 24th, 2008, and this U.S. Patent application No.12/054050 requires in the preference of the U.S. Provisional Patent Application No.60/919588 of submission on March 23rd, 2007.Second; U.S. Patent application No.12/749341 is the part continuation in the U.S. Patent application No.12/629714 of submission on December 2nd, 2009, and this U.S. Patent application No.12/629714 requires in the preference of the U.S. Provisional Patent Application No.61/119078 of submission on December 2nd, 2008.The 3rd, U.S. Patent application No.12/749341 is the part continuation in the U.S. Patent application No.12/425358 of submission on April 16th, 2009, and this U.S. Patent application No.12/425358 is that the part of two different patent applications continues.The first, U.S. Patent application No.12/425358 requires in the preference of the U.S. Provisional Patent Application No.61/119078 of submission on December 2nd, 2008.Second; U.S. Patent application No.12/425358 is the part continuation in the U.S. Patent application No.12/053695 of submission on March 24th, 2008, and this U.S. Patent application No.12/053695 requires in the preference of the U.S. Provisional Patent Application No.61/919588 of submission on March 23rd, 2007.The disclosure integral body of each in these patent applications all is incorporated into this by reference fully.
Horizontal axis wind turbine (HAWT) has 2 to 5 blades that are mounted to horizontal axis usually, and horizontal axis is attached to gear-box and generator.The employed turbo machine of wind power plant that is used for commercial electricity production generally includes the iron and steel tower of tubulose and points to three blades in the wind through computer controlled system.From 200 to 300 feet of the altitude ranges of the iron and steel tower of tubulose.Blade rotates with the speed of 10 to 22 rpms (RPM).Gear-box is generally used for the speed of generator is risen to 1500 to 18000RPM.Some horizontal axis wind turbine still can be collected more multipotency through the variable velocity turbo machine with constant speed operation, and wherein the variable velocity turbo machine utilizes solid-state power converter to be connected to transmission system.
Traditional HAWT has a plurality of shortcomings, is included near being difficult to operation in ground, the turbulent wind; Be difficult to transporter tower and blade; Be difficult to install Large Towers; High tower and radar interference; Receive local resident's repulsion owing to the sound of outward appearance and generation; Owing to turbulent fatigue and the structural failure that causes; Accumulation ice on generator and blade; Cause birds and bat dead; And owing to the unsettled power of the aeroelasticity power on the blade through the mechanical device transmission of turbo machine.
The fluid turbine of the band guard shield of the problem of the HAWT that the present invention relates to demonstrate improved mixing and list above the solution.
Summary of the invention
The present invention relates to the fluid turbine with guard shield, it has turbomachine shroud, and this turbomachine shroud is formed with aduncate section and the bandy section along the tail edge of turbomachine shroud.Between aduncate section and bandy section, do not have sidewall, allow air stream laterally with radially to mix.
Disclose a kind of fluid turbine in the mode of execution, it comprises turbomachine shroud and sparger guard shield, and wherein turbomachine shroud comprises first construction element and a plurality of sections.First construction element limits the inlet of the expansion of guard shield.The tail edge of a plurality of sections paragraph qualification turbomachine shroud.A plurality of sections comprise the aduncate section and the bandy section of constructing with the mode that replaces.Aduncate section and bandy section allow air side to laterally mix.
Usually, each aduncate section has the lateral surface of two exposures, and wherein each bandy section has the lateral surface of two exposures.In specific mode of execution, a plurality of sections have totally nine aduncate sections and nine bandy sections.
Sometimes, bandy section is wideer than aduncate section on circumferential direction.
In some constructions, each sheet section comprises front end and mixes end, and the front end of a plurality of sections forms first construction element.In addition, the includable lip-deep groove of the front end of each sheet section.
The present invention also discloses a kind of fluid turbine, and it comprises turbomachine shroud and sparger guard shield, and wherein, turbomachine shroud comprises a plurality of aduncate sections and a plurality of bandy section.Each aduncate section has front end, mixes end and two lateral surface.Each bandy section has front end, mixes end and two lateral surface.Each aduncate section section is positioned between two bandy sections.Each bandy section section is positioned between two aduncate sections.The front end of the front end of aduncate section and bandy section forms first construction element of the inlet of the expansion that limits guard shield.The mixing end of aduncate section and the mixing end of bandy section form a plurality of sections of the tail edge that limits guard shield.Two lateral surface of aduncate section and two lateral surface of bandy section expose along tail edge.
Aduncate section and bandy section can be made up of composite material or web material.Composite material can be the mixture of glass fibre and polymer resin.Web material can be the glass fibre that fluoropolymer coating is arranged.
The present invention also discloses a kind of fluid turbine with guard shield, and it comprises impeller, centers on the turbomachine shroud and the sparger guard shield of impeller.Turbomachine shroud comprises first construction element and a plurality of sections.First construction element limits the inlet of the expansion of guard shield.The tail edge of a plurality of sections paragraph qualification turbomachine shroud.A plurality of sections comprise aduncate section and bandy section with the alternant structure.Two lateral surface of aduncate section and two lateral surface of bandy section expose along tail edge.The tail edge of turbomachine shroud extends in the entry end of sparger guard shield.
Each sheet section can comprise front end and mix end that wherein the front end of a plurality of sections forms first construction element.The also includable lip-deep groove of the front end of each sheet section.
In other mode of execution, the sparger guard shield comprises a plurality of sparger sheet sections.
The sparger guard shield has the shape of annular machine aerofoil profile usually.
A plurality of supporting members can extend between turbomachine shroud and sparger guard shield, and each supporting member is aimed at bandy section.
In mode of execution, impeller comprises cabin (nacelle) main body and a plurality of stator thin slices that between cabin main body and turbomachine shroud, extend.In other embodiments, the cabin main body comprises centre gangway.
To specifically describe these and other nonrestrictive characteristic or characteristic of the present invention below.
Description of drawings
Be brief description of drawings below, accompanying drawing is used to illustrate content disclosed herein and is not used in and limits its content.
Fig. 1 is the perspective exploded view of the fluid turbine of band guard shield of the present invention.
Fig. 2 A is the perspective view of aduncate section.
Fig. 2 B is the front elevation of aduncate section.
Fig. 2 C is the side view of aduncate section.
Fig. 2 D is the plan view of aduncate section.
Fig. 3 A is the perspective view of bandy section.
Fig. 3 B is the front elevation of bandy section.
Fig. 3 C is the side view of bandy section.
Fig. 3 D is the plan view of bandy section.
Fig. 4 is the front perspective view of second kind of exemplary mode of execution of the fluid turbine of band guard shield of the present invention.
Fig. 5 is the rear perspective of fluid turbine of the band guard shield of Fig. 4.
Fig. 6 is the front elevation of fluid turbine of the band guard shield of Fig. 4.
Fig. 7 is the rear view of fluid turbine of the band guard shield of Fig. 4.
Fig. 8 is the side view cutaway drawing of fluid turbine of the band guard shield of Fig. 4.
Fig. 9 is the less view of Fig. 8.
Fig. 9 A and Fig. 9 B are the enlarged side views of knuckle-tooth matrix of the fluid turbine of Fig. 8.
Figure 10 is the rear perspective of the fluid turbine of band guard shield of the present invention, and it is illustrated in the mixing at the tail edge place of guard shield.
Figure 11 be before the front perspective view of wind turbine of disclosed band guard shield.
Figure 12 is the rear view of wind turbine of the band guard shield of Figure 11.
Embodiment
Can more completely understand parts disclosed herein, process and equipment with reference to accompanying drawing.Accompanying drawing is intended to illustrate the present invention, and is not meant to the scope that shows relative size and size or limit exemplary mode of execution.
Though used concrete term in the following explanation, these terms are intended to only refer to the specified structure in the accompanying drawing, and are not meant to restriction scope of the present invention.Similarly reference character is to be understood that to referring to the parts of similar functions.
When using with quantity, term " approximately " comprises described value, also has by the represented implication of context.For example, which comprises at least the levels of errors that is associated with the measurement of specific quantity.Under situation about using in scope, term " approximately " also should be considered to disclose the absolute value institute restricted portion of two end points.For example, scope " from about 2 to about 4 " also discloses scope " from 2 to 4 ".
Mixer sparger power system (MEPS) provides a kind of improved method from distinguished and admirable generation power.Main guard shield comprises the impeller that extracts power from main airstream.Comprise from the main airstream and the second mobile mixer eductor pump that flows and promote turbulent mixture of absorbing.This through increase flow through system air amount, reduce the noise that back pressure and minimizing system on the turbine bucket produce and improve power system.
Term used herein " impeller " refers to blade and is attached to axle and can rotates, thereby can be produced any assembly of power or energy by the fluid of rotor blade.Exemplary impeller comprises screw propeller or rotor/stator assembly.The impeller of any kind can be encapsulated in the turbomachine shroud of fluid turbine of the present invention.
The inlet of the expansion of turbomachine shroud can be considered to the front portion of fluid turbine, and the tail edge of sparger guard shield can be considered to the rear portion of fluid turbine.Orientating more first parts near the anterior fluid turbine of turbo machine as can be considered at " upper reaches " orientated as more near second parts at turbo machine rear portion.In other words, second parts are in " downstream " of first parts.
The fluid turbine of band guard shield of the present invention comprises impeller, centers on the turbomachine shroud of impeller and the optional sparger guard shield that centers on the tail edge of turbomachine shroud.Has the sheet section on the tail edge of turbomachine shroud.Especially, the sheet section comprises aduncate section or surface and bandy section or surface.Lateral surface on these crooked sheet sections exposes along tail edge.This allows through the air of turbomachine shroud and air mixing through the turbomachine shroud outside, with finally laterally with radially mix on the both direction, below with specific explanations.
Fig. 1 illustrates the fluid turbine of the turbomachine shroud of usage example property.Fluid turbine 100 comprises turbomachine shroud 110.Turbomachine shroud has first structure member 112, and it limits the inlet 114 of the expansion of guard shield.Inlet is " expansion ", and is bigger perpendicular to the cross-section area in the plane of central axial line 105 because guard shield has than at the impeller place in the ingress.Inlet 114 also can be described to limited the circular leading edge of turbomachine shroud.Guard shield is made up of a plurality of sections 118.The sheet section comprises a plurality of aduncate sections 120 and a plurality of bandy sections 130.Term " inwardly " and " outwards " are the central axial lines 105 with respect to turbo machine.As shown in the figure, nine aduncate sections and nine bandy sections are arranged.Aduncate section 120 constructed with bandy section 130 in an alternating manner.In other words, each aduncate section 120 is between two bandy sections 130, and each bandy section 130 is between two aduncate sections 120.The tail edge 116 of section paragraph qualification turbomachine shroud.Can find out aduncate section 120 and bandy section 130 be configured to allow air side to horizontal mixing.In other words, there is not sidewall that aduncate section linked together with the end that mixes of bandy section.
Radially with laterally mixing on (promptly circumferentially) both direction with air along the structure of the sheet section of tail edge allow the to flow through air of inside of turbomachine shroud along the flows outside of turbomachine shroud.The combination of the type of these sheet sections also can be called as the knuckle-tooth matrix.Can realize surpassing the efficient of four times of Betz restrictions according to the inswept area of rotor.
As shown in the figure, sheet section 118 also forms first construction element 112.In this, each aduncate section 120 can be believed to comprise front end 122 and mix end 124.Similarly, each bandy section 130 can be believed to comprise front end 132 and mix end 134.The front end 122,124 of these sheet sections forms first construction element 122.The mixing end 124,134 of sheet section forms tail edge 116.
Aduncate section and bandy section can comprise identical or different material.Aduncate section and bandy section can comprise the composite material such as the mixture of glass fibre and polymer resin.In some embodiments, glass fibre comprises E glass.E glass is to have the aluminium borosilicate glass that is less than 1% weight ratio alkali metal oxide.Polymer resin can be epoxy resin, vinylester resin or polyester.
Aduncate section and bandy section can comprise web material.In some embodiments, web material is the glass fibre that fluoropolymer coating is arranged.
Fig. 2 A to 2D illustrates perspective view, front elevation, side view and the plan view of aduncate section respectively.Aduncate section 200 has front end 202 and mixes end 204.Front end 202 is along front edge 206 location of aduncate section, and mixing end 204 is along rear edge 208 location of aduncate section.First lateral surface 210 and second lateral surface 212 are at front end 202 and mix extension between the end 204.Lateral surface radially curves inwardly towards the central axial line of fluid turbine, and can be described to have the shape of arc.Lateral surface 210,212 exposes along the mixing end 204 of aduncate section.In other words, lateral surface exposes along the tail edge of turbomachine shroud.This statement should not be understood that to require lateral surface all to expose.
Shown in the front elevation of Fig. 2 B, can see camber line 225 corresponding to the periphery of first construction element.The width 215 of aduncate section on circumferential direction is roughly the same along front edge and rear edge.Shown in the side view of Fig. 2 C, the front end of the crooked sheet section groove 220 on the surface 222 that included.Relative with internal surface is the outer surface 224 that extends to rear edge 208 from front edge 206.Shown in the plan view of Fig. 2 D, aduncate section has the shape of rectangle.
Fig. 3 A to 3D illustrates perspective view, front elevation, side view and the plan view of bandy section respectively.Bandy section 300 has front end 302 and mixes end 304.Front end 302 is along front edge 306 location of bandy section, and mixing end 304 is along rear edge 308 location of bandy section.First lateral surface 310 and second lateral surface 312 are at front end 302 and mix extension between the end 304.Lateral surface is crooked away from the central axial line radially outward of fluid turbine, and can be described to have the shape of arc.Lateral surface 310,312 exposes along the mixing end 304 of bandy section.In other words, lateral surface exposes along the tail edge of turbomachine shroud.
Shown in the front elevation of Fig. 3 B, can see camber line 325 corresponding to the periphery of first construction element.The width 315 of bandy section on circumferential direction is roughly the same along front edge and rear edge.Shown in the side view of Fig. 3 C, the front end of the crooked sheet section groove 320 on the surface 322 that included.Relative with internal surface is the outer surface 324 that extends to rear edge 308 from front edge 306.Shown in the plan view of Fig. 3 D, bandy section has the shape of rectangle.
Groove 220,320 in the crooked sheet section can be used for placing or location power or energy generation systems.Assembled when good when guard shield, the groove 220,320 on aduncate section and the bandy section is aligned with each other to form ring.
According to the profile of their forward sights, aduncate section can be distinguished with bandy section.Can find out by comparison diagram 2B and Fig. 3 B, during face to face to the front edge 206 of aduncate section 200, rear edge 208 with mix end 204 in the inboard of camber line 225, or camber line below.Relatively, the rear edge 308 of bandy section 300 holds 304 in the outside of camber line 325 with mixing, or the camber line top.In other words, the mixing end 204 of aduncate section 200 than front end 202 more near central axial line.Relatively, the front end 302 of bandy section 300 is than mixing end 304 more near central axial line.
In some embodiments, bandy section is wideer than aduncate section on circumferential direction.In different embodiment, aduncate section is wideer than bandy section on circumferential direction.Alternatively, aduncate section can have identical width with bandy section.Groove on the internal surface of crooked sheet section can engage with the ring type generator that for example obtains energy/power from fluid.
Fig. 4 to Fig. 8 is a plurality of views of second mode of execution with fluid turbine 400 of section type turbomachine shroud 410 and sparger guard shield 460.Fig. 4 is the left front perspective view.Fig. 5 is the left back perspective view.Fig. 6 is a front elevation.Fig. 7 is a rear view.Fig. 8 is a side view cutaway drawing.
Equally, guard shield 410 is made up of a plurality of sections 418.Sheet section 418 comprises a plurality of aduncate sections 420 and a plurality of bandy sections 430.Aduncate section and bandy section are constructed with the mode that replaces.The lateral surface 424,434 of aduncate section and bandy section exposes along the tail edge 416 of guard shield.First construction element 412 at inlet 414 places of the expansion of front end 422, the 432 formation turbomachine shrouds of sheet section.Guard shield 410 is around impeller 440 and have the cabin main body 450 of centre gangway 452.First end 454 of centre gangway is visible among Fig. 4.
Fluid turbine also comprises sparger guard shield 460.Sparger guard shield 460 has the shape of arc annular machine aerofoil profile.Supporting member 470 is connected to turbomachine shroud 410 with sparger guard shield 460.Should be noted that supporting member 470 aims at bandy section 430.The tail edge 416 of turbomachine shroud 410 or knuckle-tooth matrix or rear end 417 extend in the entry end 462 of sparger guard shield.Sparger guard shield 460, turbomachine shroud 410 and cabin main body 450 are coaxial with central axial line 405.
Referring now to Fig. 5, can see second end 456 of centre gangway 450 here.In addition, this rear view illustrates aduncate section 420 and is configured to allow air laterally and laterally to mix with bandy section 430.Two lateral surface 424 of aduncate section and two lateral surface 434 of bandy section expose along tail edge 416.
Section (being aduncate section and bandy section) can comprise the plastics that fiber is strengthened.In some embodiments, section comprises the molded or blown-mold polyethylene of rotational moulding.In other mode of execution, section is formed by punching press or metal solder.
Using an advantage of knuckle-tooth matrix is the axial length that can reduce the sparger guard shield.The minimizing of the axial length of sparger guard shield allows the higher energy supply at the tail of fluid turbine back.Therefore, can on shorter axial distance, realize from the low-yield air stream of turbomachine shroud inside and better mixing from the outside high-energy air air-flow of turbomachine shroud.This allows fluid turbine more near arranging each other.Shorter guard shield also reduces cost and weight, allows size and the weight of the tower of support fluid turbo machine also to reduce, the further cost savings of realization under the situation of sacrificing security not.In Fig. 8, turbomachine shroud 410 has axial length L
M, sparger guard shield 460 has axial length L
EIn mode of execution, L
MTo L
ERatio can from 0.8 to 1.5.
An advantage that the fluid turbine guard shield is divided into aduncate section and bandy section is to make guard shield handle more easily and transport.And this minimizing will be transported to the cost and the complexity of appropriate location with the fluid turbine of guard shield.
Though do not illustrate here, the sparger guard shield also can comprise the gongylodont mixing tab along outlet end.
Referring now to Fig. 8, impeller 440 is around cabin main body 450.Here, impeller is the rotor/stator assembly, comprises stator 442 with stator vane and the rotor 444 with rotor blade.Rotor " is in line " in downstream and with stator vane.In other words, the leading edge of rotor blade is roughly aimed at the tail edge of stator vane.Rotor blade keeps together through interior ring and outer shroud (not shown).Interior ring is installed on the cabin main body 450.Cabin main body 450 is connected to turbomachine shroud 410 through stator 442 or through other modes.
Turbomachine shroud and sparger shroud air power ground camber are to increase the flow through turbine rotor.The axial length L of turbomachine shroud
MBe equal to or less than the maximum outside diameter D of turbomachine shroud
MAnd, sparger guard shield L
EAxial length be equal to or less than the maximum outside diameter D of sparger guard shield
EThe outer surface aerodynamic force ground of cabin main body forms profile so that the flow separation phenomenon in fluid turbine downstream minimizes.The cabin main body can be configured to longer or shorter than turbomachine shroud or sparger guard shield or their combination length.
The inlet area of turbomachine shroud and discharge area are equal to or greater than the area of the occupied ring of impeller.The long-pending aerodynamic force of the formed internal flow passage sections of ring between the internal surface of cabin main body and turbomachine shroud ground is shaped and has minimum area with the place, plane at turbo machine, and gently changes to pelvic outlet plane from their planes of inlet separately in addition.The sectional area of sparger guard shield entry end is greater than the sectional area of the rear end of turbomachine shroud.
In the fluid turbine of band guard shield, can comprise several optional characteristics.The power output device of wheel shape structural type can be mechanically connected to generator at the outer rim place of impeller.Sound absorptive material can be attached to the internal surface of guard shield to absorb and to prevent the propagation of the relative high frequency sound wave that turbo machine produces.In order further to improve level of security, turbo machine also can comprise the blade contained structure.Guard shield will have aerodynamic profile to increase the flow of the inflow and the system that flows through.The cross section in the entrance and exit zone of guard shield can be non-circular, makes can easily regulate the guard shield installation through two guard shields are aimed at.Can comprise that on the lower external face of turbo machine swivel coupling to be used to being installed in a vertical rack/tower, extracts with maximizes power thereby allow turbo machine to redirect in the fluid.Vertically aerodynamic force stabilizer thin slice can be installed on the guard shield outside and point to fluid with the auxiliary turbo machine that keeps.
Sparger guard shield discharge area compares in the scope of 1.5-3.0 the area of turbomachine shroud discharge area.The quantity a of knuckle-tooth matrix can be between 6 to 14.The height-width ratio of sheet passage is between 0.5 to 4.5.Sheet penetrates between 50% to 80%.Cabin main body bolt tail edge angle is 30 degree or littler.The ratio of the length over diameter of whole turbo machine (L/D) is between 0.5 to 1.25.
Referring now to Fig. 8, the energy of the free air stream (roughly being represented by arrow 472) of process stator 442 is extracted by rotor 444.The high-energy air of arrow 474 expression is walked around turbomachine shroud 410 and stator 442 and is flow through the outside of turbomachine shroud 410 and by inwardly guiding.The low-yield air that the knuckle-tooth matrix causes leaving from the rotor downstream mixes with the high-energy air.
In Fig. 9 A, roughly draw tangent line 480 by the internal surface of 481 expressions along aduncate section 420.Turbomachine shroud has back plane 482.The line 483 that point that formation is met perpendicular to back plane and with aduncate section and bandy section 484 is tangent.Tangent line 480 intersects formation angle φ with line 483
2This angle φ
2Between 5 to 65 degree.In other words, aduncate section forms the angle φ between 5 to 65 degree with respect to turbomachine shroud
2In specific mode of execution, angle φ
2For about 35 spend about 50 the degree.
In Fig. 9 B, roughly draw tangent line 485 by the internal surface of 486 expressions along bandy section 430.Tangent line 485 intersects formation angle φ with line 483.This angle φ is between 5 to 65 degree.In other words, aduncate section forms the angle φ between 5 to 65 degree with respect to turbomachine shroud.In specific mode of execution, angle φ be about 35 spend about 50 the degree.
Figure 10 is the backside perspective view of exemplary fluid turbine, and the air-flow at the tail edge place of guard shield is shown.Fluid turbine 500 comprises turbomachine shroud 510 and sparger guard shield 560.Turbomachine shroud 510 comprises aduncate section 518 and bandy section 520.High-energy air H externally arrives the tail edge of turbomachine shroud 510, promptly between turbomachine shroud 510 and the sparger guard shield 560, that is to say high-energy air H do not flow through expansion inlet or walk around impeller.Low-yield air L promptly through the inlet of expansion with through impeller, arrives the tail edge of turbomachine shroud 510 through the inside of the turbomachine shroud 510 of flowing through.Enlarged view illustrates the horizontal mixing of high-energy air air-flow 599 and low-yield air stream 598.In comprising the mode of execution of centre gangway, the air of the centre gangway of flowing through is the high-energy air.
Figure 11 and Figure 12 are a kind of diagrams of mode of execution of the wind turbine 1000 of disclosed band guard shield among the U.S. Patent application No.12/054050.To assist the structure of further this fluid turbine of qualification to the discussion of special characteristic.
With reference to Figure 11, this mode of execution uses propeller-type impeller 1002 to replace the rotor/stator assembly.Turbomachine shroud 1010 has ten high-energy mixing tabs 1012 of a cover that the central axial line towards turbo machine extends internally.Turbomachine shroud also has away from ten low-yield mixing tabs 1014 of the outward extending cover of central axial line.High-energy mixing tab and low-yield mixing tab replace around the tail edge of turbomachine shroud 1010.Impeller 1002, turbomachine shroud 1010, sparger guard shield 1020 coaxially to each other, promptly they have common central axial line.
Referring now to Figure 12, the tail edge of turbomachine shroud can be described to comprise a plurality of circumferentially isolated interior circular arc portions 1032, and circular arc portion has identical radius of curvature in each.These interior circular arc portions are the equispaced each other.A plurality of external arc parts 1034 are between part 1032, and each external arc partly has identical radius of curvature.The radius of curvature of interior circular arc portion 1032 is different with the radius of curvature of external arc part 1034, but interior circular arc portion partly has identical center (promptly along central axial line) with external arc.Interior part 1032 and external arc part 1034 are connected to each other through extension 1036 radially.This forms crenature (crenellated) shape, promptly descends the tail edge 1016 of shape or left and right sides shape haply.This zigzag structure forms two groups of mixing tabs, i.e. high-energy mixing tab 1012 and low-yield mixing tab 1014.
Referring now to the rear view of Fig. 7, tail edge 414 also can be described as comprising a plurality of circumferentially isolated interior circular arc portions 492 and a plurality of circumferential isolated external arc parts 494.Circular arc portion 492 has identical radius of curvature in each, and spaced apart fifty-fifty each other.Each external arc part 494 has identical radius of curvature, and spaced apart fifty-fifty each other.The radius of curvature of interior circular arc portion 492 is different with the radius of curvature of external arc part 494, but interior circular arc portion partly has identical center (promptly along central axial line 405) with external arc.
But the fluid turbine of Fig. 7 is different with the wind turbine of Figure 11, because the sheet section of turbomachine shroud of the present invention does not comprise sidewall, and mixing tab shown in Figure 11 comprises sidewall.In other words, the tail edge 416 of the turbomachine shroud of cutting apart of the present invention has interior circular arc portion 492 and external arc part 494, but does not have radially extension.The part that seems among Fig. 7 radially to extend (by reference character 496 expressions) is actually the optical illusion that the edge by the sheet section forms, rather than owing to there being sidewall.Lacking radially, the extension causes the lateral surface 424,434 of sheet section 418 to expose the circumferential mixing of permission air stream.Tail edge 416 can be described to have circular merlons shape (merlonated) shape (referring to the entity part of sheet section) thus, but not crenature shape shown in Figure 11.
The present invention has been described according to illustrative embodiments.Reading and understanding under the above-mentioned situation about specifying and to know correction of the present invention and distortion.The present invention is intended to be believed to comprise all these corrections and the distortion in the scope of claims of the present invention and equivalence thereof.
Claims (20)
1. fluid turbine comprises:
Turbomachine shroud, said turbomachine shroud comprises:
First construction element, said first construction element limits the inlet of the expansion of said guard shield; With
A plurality of sections, the tail edge of the said turbomachine shroud of said a plurality of section paragraph qualifications; And
Sparger guard shield, said sparger guard shield are arranged on the downstream of said turbomachine shroud and concentricity around said turbomachine shroud;
Wherein, said a plurality of sections comprise aduncate section of constructing and bandy section with the mode that replaces with allow air side to horizontal mixing.
2. fluid turbine according to claim 1, wherein, each aduncate section has the lateral surface of two exposures, and each bandy section has the lateral surface of two exposures.
3. fluid turbine according to claim 1, wherein, said a plurality of sections have totally nine aduncate sections and nine bandy sections.
4. fluid turbine according to claim 1, wherein, bandy section is wideer than aduncate section on circumferential direction.
5. fluid turbine according to claim 1, wherein, each sheet section comprises front end and mixes end, and the front end of said a plurality of sections forms said first construction element.
6. fluid turbine according to claim 5, wherein, the front end of each the sheet section lip-deep groove that included.
7. fluid turbine according to claim 1, wherein, aduncate section and bandy section comprise composite material or web material.
8. fluid turbine according to claim 7, wherein, composite material is the mixture of glass fibre and polymer resin.
9. fluid turbine according to claim 7, wherein, web material is the glass fibre that fluoropolymer coating is arranged.
10. fluid turbine comprises:
Turbomachine shroud, said turbomachine shroud comprises:
A plurality of aduncate sections, each aduncate section have front end, mix end and two lateral surface; With
A plurality of bandy sections, each bandy section have front end, mix end and two lateral surface; And
Sparger guard shield in said turbomachine shroud downstream;
Wherein, each aduncate section section is positioned between two bandy sections, and each bandy section section is positioned between two aduncate sections;
Wherein, the front end of the front end of aduncate section and bandy section forms first construction element of the inlet of the expansion that limits guard shield;
Wherein, the mixing end of the mixing end of aduncate section and bandy section forms a plurality of sections of the tail edge that limits guard shield; And
Wherein, two lateral surface of two of aduncate section lateral surface and bandy section expose along tail edge.
11. the fluid turbine with guard shield comprises impeller, around the turbomachine shroud and the sparger guard shield of impeller, wherein, said turbomachine shroud comprises:
First construction element of the inlet of the expansion of qualification guard shield; And
Limit a plurality of sections of the tail edge of turbomachine shroud;
Wherein, said a plurality of sections comprise aduncate section and the bandy section with the alternant structure;
Wherein, two lateral surface of two of aduncate section lateral surface and bandy section expose along tail edge; And
Wherein, the tail edge of turbomachine shroud extends in the entry end of sparger guard shield.
12. fluid turbine according to claim 11, wherein, the sparger guard shield comprises a plurality of sparger sheet sections.
13. fluid turbine according to claim 11, wherein, the sparger guard shield has the shape of annular machine aerofoil profile.
14. fluid turbine according to claim 11, wherein, said a plurality of sections have totally nine aduncate sections and nine bandy sections.
15. fluid turbine according to claim 11, wherein, bandy section is wideer than aduncate section on circumferential direction.
16. fluid turbine according to claim 11, wherein, each sheet section comprises front end and mixes end that the front end of said a plurality of sections forms first construction element.
17. fluid turbine according to claim 16, wherein, the front end of each the sheet section lip-deep groove that included.
18. fluid turbine according to claim 11 also is included in a plurality of supporting members that extend between turbomachine shroud and the sparger guard shield, each supporting member is aimed at bandy section.
19. fluid turbine according to claim 11, wherein, impeller comprises cabin main body and a plurality of stator thin slices that between cabin main body and turbomachine shroud, extend.
20. fluid turbine according to claim 19, wherein, the cabin main body comprises centre gangway.
Applications Claiming Priority (13)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US30333910P | 2010-02-11 | 2010-02-11 | |
| US61/303,339 | 2010-02-11 | ||
| US12/749,341 US20100270802A1 (en) | 2007-03-23 | 2010-03-29 | Wind turbine |
| US12/749,341 | 2010-03-29 | ||
| US33272210P | 2010-05-07 | 2010-05-07 | |
| US61/332,722 | 2010-05-07 | ||
| US12/914,509 | 2010-10-28 | ||
| US12/914,509 US20110085901A1 (en) | 2007-03-23 | 2010-10-28 | Shrouded wind turbine with scalloped lobes |
| US41561010P | 2010-11-19 | 2010-11-19 | |
| US61/415,610 | 2010-11-19 | ||
| US12/983,082 | 2010-12-31 | ||
| US12/983,082 US20110135458A1 (en) | 2007-03-23 | 2010-12-31 | Fluid turbine with shroud having segmented lobes |
| PCT/US2011/024509 WO2011100536A1 (en) | 2010-02-11 | 2011-02-11 | Fluid turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102782312A true CN102782312A (en) | 2012-11-14 |
Family
ID=44368144
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011800092544A Pending CN102782312A (en) | 2010-02-11 | 2011-02-11 | Fluid turbine |
Country Status (5)
| Country | Link |
|---|---|
| EP (1) | EP2534372A4 (en) |
| CN (1) | CN102782312A (en) |
| CA (1) | CA2787948A1 (en) |
| RU (1) | RU2012138698A (en) |
| WO (1) | WO2011100536A1 (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110085901A1 (en) * | 2007-03-23 | 2011-04-14 | Presz Jr Walter M | Shrouded wind turbine with scalloped lobes |
| EP3473848B1 (en) | 2017-10-20 | 2022-09-07 | FlowGen Development & Management AG | Flow energy installation, in particular a wind turbine with a jacket |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5230937A (en) * | 1983-04-13 | 1993-07-27 | Chemfab Corporation | Reinforced fluoropolymer composite |
| US20070041823A1 (en) * | 2005-08-22 | 2007-02-22 | Miller Donald C | Fluid energy converter |
| US20080121301A1 (en) * | 2004-04-09 | 2008-05-29 | Norris Thomas R | Externally Mounted Vortex Generators for Flow Duct Passage |
| WO2008118405A2 (en) * | 2007-03-23 | 2008-10-02 | Flodesign Wind Turbine Corporation | Wind turbine with mixers and ejectors |
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|---|---|---|---|---|
| US4976587A (en) * | 1988-07-20 | 1990-12-11 | Dwr Wind Technologies Inc. | Composite wind turbine rotor blade and method for making same |
| JPH0632355A (en) | 1992-07-06 | 1994-02-08 | Tdk Corp | Case and method for its production |
| US5771681A (en) * | 1996-09-17 | 1998-06-30 | The Boeing Company | Aircraft turbofan engine mixing apparatus |
| DE50110023D1 (en) * | 2000-12-01 | 2006-07-20 | Ebm Papst St Georgen Gmbh & Co | Fan housing, especially for axial fans |
| GB0105349D0 (en) * | 2001-03-03 | 2001-04-18 | Rolls Royce Plc | Gas turbine engine exhaust nozzle |
| CA2640643C (en) * | 2004-09-17 | 2011-05-31 | Clean Current Power Systems Incorporated | Flow enhancement for underwater turbine generator |
| EP1894616A1 (en) * | 2006-08-30 | 2008-03-05 | Fachhochschule Zentralschweiz | Static mixing device |
| US8021100B2 (en) * | 2007-03-23 | 2011-09-20 | Flodesign Wind Turbine Corporation | Wind turbine with mixers and ejectors |
| WO2010005289A2 (en) * | 2008-07-11 | 2010-01-14 | Donqi Quandary Innovations Bv | Wind turbine with di ffuser |
-
2011
- 2011-02-11 RU RU2012138698/06A patent/RU2012138698A/en not_active Application Discontinuation
- 2011-02-11 CA CA2787948A patent/CA2787948A1/en not_active Abandoned
- 2011-02-11 EP EP20110742856 patent/EP2534372A4/en not_active Withdrawn
- 2011-02-11 WO PCT/US2011/024509 patent/WO2011100536A1/en active Application Filing
- 2011-02-11 CN CN2011800092544A patent/CN102782312A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5230937A (en) * | 1983-04-13 | 1993-07-27 | Chemfab Corporation | Reinforced fluoropolymer composite |
| US20080121301A1 (en) * | 2004-04-09 | 2008-05-29 | Norris Thomas R | Externally Mounted Vortex Generators for Flow Duct Passage |
| US20070041823A1 (en) * | 2005-08-22 | 2007-02-22 | Miller Donald C | Fluid energy converter |
| WO2008118405A2 (en) * | 2007-03-23 | 2008-10-02 | Flodesign Wind Turbine Corporation | Wind turbine with mixers and ejectors |
Also Published As
| Publication number | Publication date |
|---|---|
| RU2012138698A (en) | 2014-03-20 |
| CA2787948A1 (en) | 2011-08-18 |
| EP2534372A4 (en) | 2014-09-03 |
| EP2534372A1 (en) | 2012-12-19 |
| WO2011100536A1 (en) | 2011-08-18 |
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Application publication date: 20121114 |