CN1930394A

CN1930394A - Turbine and rotor therefor

Info

Publication number: CN1930394A
Application number: CNA2005800082744A
Authority: CN
Inventors: 弗兰克·丹尼尔·洛特里翁特
Original assignee: Individual
Current assignee: Individual
Priority date: 2004-03-18
Filing date: 2005-03-16
Publication date: 2007-03-14

Abstract

A rotor that consists of a central hub or shaft and a plurality of boot shaped integral blade/vane units that combine a pronounced elongated vane tip extending substantially toward the incoming flow and also the direction of rotation forming a helix or pitch angle to the rotation axis centreline, preferably normal to and joined to the outer frontward extremity of a slightly rearward tilted blade/wing section that is connected by its inner end to the central hub of shaft. The rotor revolves about the rotation axis by incoming gas/fluid flow as most of the fluid flow is encouraged to move substantially outward and rearward as it travels into and past the forwardly projecting vane tips located a substantial distance radially from the axis of rotation. This maximises the torque developed and transferred to the hub/shaft in a manner that does not greatly inhibit total through flow, because the combined gas/fluid flow exit area (or gaps between blades/vanes) is much greater than the maximum rotor diameter and subsequently the rotor inlet area, which has the effect of increasing the through flow velocity and thus overall performance. The blades may have slots within them.

Description

Turbine and the rotor that is used for it

Technical field

The present invention relates to turbine and the rotor that running shaft is in substantially parallel relationship to gas/liquid stream that has that is used for it.More particularly, the present invention relates to a kind of nonocclusive wind-force/water turbine, also or be contained in the pipeline and from the gas that moves or liquid stream extracts energy or be the rotor/propulsion device that moves of gas or liquid stream with transformation of energy.

Background technique

Most of modern wind turbine rotors reliability is low, and has the long prismatic blade of a small amount of wing part around central horizontal axis, and the wind turbine rotor blade zone of vast scale is in half place, inside of its diameter.Can greatly increase the noise of the working condition of these turbines for obtaining very high tip speed that maximal efficiency relates to.

The present inventor recognizes, to be converted in the available moment of torsion from the kinetic energy of the gas/liquid stream that moves, most useful work is done in 1/3rd of the outside of any turbine rotor, its moment of torsion is the function that power is taken advantage of radius, and the overall dimensions that the gas/liquid stream velocity ratio with increase has the turbine rotor of increase more helps the energy generation, the present invention seeks to be positioned at the groundwork surface before this perimeter comes across the gas/liquid stream interface, in design, effectively to realize high mechanical efficiency, this design keeps basic relatively, unencumbered, free-pouring, and do not rely on top speed.

Can extract to such an extent that the theoretical maximum percentage of energy is (BETZ boundary) in 59.3% from distinguished and admirable, and the present invention shown the results of wind tunnel of university's supervision, this result supports the maximum power coefficient greater than 52%.

Summary of the invention

The present invention seeks to from any wind-force, waterpower, high efficiency output is provided in steam or the gas-turbine, the rotating shaft that turbine has the liquid/gas flow of being in substantially parallel relationship to by the rotor design of using increase direct current speed, and rotor design increases direct current speed by the bulk flow output area that slit between the blade/vane or cavity form greater than flowing the zone by the predetermined import of maximum rotor diameter, and for its size, its external end largest global power output also is in the groundwork zone, rotor comprises around the central hub or the axle of the central shaft rotation that is in substantially parallel relationship to the gas body fluid flow, central hub or axle support the integral blade/wing unit of several equal intervals, blade/vane unit around described propeller boss or the diameter of axle to layout, each blade/vane unit comprises that the short inner vanes of the typical case of integrated formation or " wing " part are from described arbor wheel hub or the outward extending in fact combination of axle, and the outside of Yan Shening " wing " part preferred vertical and be connected in the outside of described interior section in fact forward, end forward, continuous wing/blade unit be installed in propeller boss/axle above, form the angle of spiral or inclination between the longitudinal center line with and described propeller boss/axle terminal in its outer radial, angle is preferably spent between 6 degree 0, and angle is because rotation and greater than the synthetic angle corresponding to the synthetic quantity of inlet gas/liquid flow vector and tangent gas/liquid stream " against the wind " component, all associated rotor load module makes gas/liquid stream outwards and backward move in " spiral " path that increases from the central shaft that is parallel to it usually, " spiral " route optimization is planted the most of part openings that divide through outstanding forward outer limb portions, preferably each all comprises along the suitable angle of inclination of each part of its longitudinal axis the outer limb portions branch, pass identical specific part to synthetic liquid/gas flow vector, the not position of tubular portion or its specific part, most preferably the angle of inclination is spent between 15 degree 5.Each blade/vane unit is preferably turned round balance between (moment of torsion) power in weight distribution with by what " lifting " from liquid/gas flow produced, around it self center mounting points center line perpendicular to propeller boss/axle, for the less needs of annular sclerotic margin or need not connect it to other one or more blade/vane unit at its most preceding periphery or intermediate portion, this can simplify manufacturing, keep ability simultaneously with the running of higher angular speed, what other can be expected is, can not produce excessive bending or damage, and this design is also for speed envelope or start the operating mode purpose and keep and comprise that blade/vane is connected to the possibility of different " giving prominence to " angles owing to macrobending or torsion level.

In a preferred form of the invention, the slit of slight curvature is located at this zone that is similar to the transverse part branch and flows and the exterior section of extension or the outer-rear end of the wing perpendicular to " synthesizing " substantially, there are the wing or " Fowler flap " (Flowler flap) of slit to increase lifting force greatly in this described zone, the rear-most end of blade/vane unit is offset and the big torque force of balance by using unconventional obviously outstanding forward wing part to form, if desired, then overcome these power fully, and the distortion alar part is assigned to less spiral or " outstanding angle " empennage, because the wing/blade is crooked under predetermined flow velocity, the wing further can maximized speed envelope to going into jet.

Preferably, this turbine rotor is designed to wind turbine, does not provide other ability that can select useful design yet eliminate it, any gas, liquid or the steamturbine that is provided can be used in maximum available space can confined multiple varying environment under.

Description of drawings

Can come with reference to the accompanying drawings to assist to understand the present invention, show the details of some embodiments of the present invention with reference to the accompanying drawings, only be to explain the present invention yet can be regarded as the feature that shows in the accompanying drawing and describe, and do not limit this

Scope of invention.

Accompanying drawing is:

Fig. 1 has shown the plan view of preferred embodiment;

Fig. 2 has shown the plan view of preferred embodiment, and except that several blades, #2 is a sense of rotation in the present embodiment;

Fig. 3 a, 3b, with the 4 various phantoms that shown preferred integrated blade/vane unit, it has been described between synthetic gas/liquid stream #11 and tilt angle  in the relation of same position with respect to the blade/vane part, and Fig. 3 b has also shown the part at the contiguous place of slit #5.

Fig. 5 is the big view such as grade of preferred embodiment;

Fig. 6 A has described the multistage turbine embodiment who simplifies, and its second level is compared with the first order, has the different angles of giving prominence on blade and sense of rotation, will synthesize lifting force at propeller boss and be converted into moment of torsion the biglyyest, and can have the pre-rotor wing.

Fig. 6 B has shown the method that realizes the outstanding adjustment of blade angle from the outstanding installation shaft of the center hookup wire #8 of blade/vane unit of using, and blade/vane unit can be connected by the mechanical device that embeds propeller boss.

Fig. 6 C has shown the embodiment of no slit, and it can use pressed metal or vacuum forming method to be easier to make, and it also has the annular flange that is connected with the most preceding periphery of blade/vane unit with the increase rigidity.

Fig. 6 D has described the secondary fan of simplifying, it can be inserted in the pipeline to be applicable to the aircraft/Hovercraft that possesses second rotor with different rotary direction and blade lean angle, so that the stream that produces by rotation discharge in typical smaller angle, and need not to sacrifice tilt length, and reality promotes (axially adding the V2 axial component by V1 constitutes) backward.

Fig. 7 has shown the plan view of the blade/vane unit of preferred embodiment, for any given turbine diameter according to proportional design formula is:

" D "=maximum rotor diameter

The maximum lift coefficient of CLmax=blade or wing unit area

The whole zone at the blade/vane rear portion of Y=center mounting points line #8

The whole zone of the blade/vane front portion of X=center mounting points line #8

Ain=flows to port area (=rotor radius square take advantage of π)

The zone of the stream that Acirc=discharges at wing periphery

The zone of the stream that Athru=discharges at the rotor rear portion

θ=blade/vane unit is with respect to the inclination or the outstanding angle of propeller boss/axle central shaft

Guiding edge #7 is to the angle between propeller boss/axle central shaft #6 in ω=wing

=blade-section guiding edge is to the angle between the center line #8

#1=outer limb portions branch

#3=inner vanes part

#6=propeller boss/shaft centre line

#8=passes the center line perpendicular to the barycenter #10 in the zone of propeller boss or axle central shaft

The join domain of #9=between blade/vane and central hub or axle

#10=is considered to the regional barycenter that the overall region of blade and wing part is felt relieved thereon

#11=" synthesizes " summation that the vector that flows comprises the tangent line flow velocity degree that axial flow speed, radial flow speed and rotation are produced

#12=goes into jet direction

The angle of #14=between the wing/blade exterior wing trailing edge and propeller boss central shaft central shaft

Fig. 8 is that the diameter of university's supervision is the conclusion page or leaf of the wind tunnel test of 765mm rotor.

Embodiment

With reference to figure 1

Integrally formed " hook-shaped " blade/vane unit of several spaced at equal intervals, it comprises that most preferred inner limb portions divides blade #3, blade #3 extends radially outwardly in fact from central hub or axle #4 with angle a little backward, each inner vanes has the guiding edge, and also between 5 degree and 60 degree, recede from normal, and, Tu Chu wing part #1 and central hub or the axle integrated formation of #4 and be connected to its outside outside edge in fact forward, and whole blade/wing unit twists with spiral or tilt angle theta around propeller boss/shaft centre line #6 usually, propeller boss/shaft centre line #6 preferred parallel is in gas/liquid flow path direction #12, so that from synthetic liquid stream that obtain and lifting or deflecting force maximum that be converted into suitable moment of torsion.

Wing part #1 is preferred airfoil portion, its with reduce chord length pro rata to the distance of inner vanes part #3, form the curved outer point of the approaching stream of importing.

With reference to figure 7

Wing #1 is preferably included in the one or more slit #5 in its outer posterior branch, slit #5 is set to substantially perpendicular to synthetic stream #11, stream #11 passes identical described part and can be bent, each slit is all quite narrow and have the limit passes through to the wing/blade unit with guiding gas/liquid stream part a back of drawing of smooth fillet, (Fig. 3 b) provides the lifting force of increase to the wing/blade unit in this zone, and most preferably form second " bending " or wing part in this zone and can roll up lift coefficient to be used for the tangible forward part that balance has the territory, pterion of less specific lift coefficient in this territory, last pterion, this can be owing to allowing to keep evenly around the moment of center line #8 or continuous wing/leaf area barycenter #10 that torsion passes perpendicular to propeller boss central shaft #6.

Preferably, the gross mass (regional x-x) before the center line #8 equals the gross mass (regional y-y) behind the center line #8, can the complete equilibrium Blade Design, pass barycenter #10 to realize center line #8 perpendicular to the zone of propeller boss central shaft center line #6.

Central hub #4 can constitute with multiple shape and size, but preferred diameter be the integral rotor diameter 0.2 to 0.4 between, the diameter that increases helps towards its back pilot flow direction outside with the taper of smooth curved and causes extra turbulent flow backward and not, and for blade related organization, generating unit or be connected to suitable output shaft and/or spring bearing provides possible housing.

As seen from Figure 1, all the common shape of rotor is designed to cause liquid or flow pattern, and this pattern has direction outside in fact when further moving to and pass completely through rotor.

Because whole discharge currents zone " A thru " adds " A Circ " much larger than whole import stream zone " A in ", enter volume (Volume-in) and equal to discharge volume (Volume-out), and volume equals speed and takes advantage of area, then the pressure drop according to bernoulli law (Bemuilies principle) internal rotor/speed forward or the outside of rotor/backward must increase, and all improved turbine rotor performances are better than prior art.

All guiding edges are preferably suitable circle and minimize turbulent flow, and all parts adopt surface finish preferably, at propeller boss or axle, when liquid/gas flow becomes moment of torsion, inner vanes partly needs enough intensity enough to change, or be converted, and during with maximum rotational speed rotary integral quality, can bear centrifugal and bending force at extreme operating condition from deflection and " lifting " power of blade, the wing and slit.

Claims

(according to the modification of the 19th of treaty)

Statement about the 19th modification of international application

With reference to the invention of " the Turbine and Rotor Therefor " by name that submitted to, its claim description and word are improper, and this makes the present invention be regarded as lacking novelty.

Desired novel teachings is improper because of we describes in this submit applications not to be noted and not change since the first time, provisional application was submitted to that like this, we does not seek necessary change and has submitted accompanying drawing to.

Make necessity of having novelty in claimed and primary be that any associated gas or fluid stream (or are regarded as interior flow vector because of blade/vane ground rotates; the flow direction of outer flow vector summation;); if there is any radially outer flow vector; then " in first example, run into the top; rather than the edge "; and last " through another top on the same blade; rather than the edge "; thereby the described relative gas/fluid stream that circulation time occurs is grown and be suitable for very much to the working surface region of blade very much with respect to its width; be not only and enter flow direction, hull rises also unclear from water with speed.

And, we proposes inner wing or supporting part are described as having sweptback slightly wrong claim, but this is not right, thereby we will revise this claim, when occur perpendicular to described circulation time mobile the time can occur receding, perpendicular to or do not occur during the central shaft of contiguous central hub or axle, and may be because unusual blade connects except in its abnormal " startup " or " closing " pattern, and the cross section will have and turn forward slightly to turbine or rotor inlet with the vertical center line as object in fact, and will correspondingly correct some simple accompanying drawing and descriptions afterwards.

Other parts of modification right requirement only are that the application is further described selected part, statement novelty and design principle.

1. turbine or rotor, consist essentially of around propeller boss or spool several long relatively crooked wing or " wing parts " bending or the wing section profile of upwards being provided with in week, the central shaft of propeller boss or axle is parallel in fact introduces gas/liquid stream, each described wing has the end that its vertical side tangent line intersects to form at its two end part, and these two least significant ends become actual guiding edge and trailing edge with respect to tangible gas or liquid flow path direction when rotating with the terminal speed of hope, these described ends all are oriented and form 0 with respect to described tangible air-flow and spend to the angle between 36 degree, described vertical side positioning is in the angle with respect to described relative current direction, and each described wing outer end forward from second interior section or the wing in fact is outstanding, second interior section or the wing are connected on the described propeller boss or axle that provides support for described exterior section, simultaneously, on gas/liquid stream, give minimum drag or obstruction effect;

In forefoot area, Xuan Zhuan exterior section, interior section, propeller boss/axle load module form circular cavity in fact fully at turbine or internal rotor.

2. turbine according to claim 1 or rotor, its wing/blade surface zone with maximum ratio the rotary middle spindle radial diameter 0.33 to 0.46 between.

3. turbine according to claim 1 or rotor, it has half inner vanes or supporting part of length that width divides less than outer limb portions, and can in the most basic embodiment, be fabricated to from the form of the outstanding downwards axle of the barycenter of the face of the wing/blade-section, and perpendicular to axle/propeller boss central shaft, the wing/blade-section can completely form, and balance in fact, because lifting/deflecting force, the total amount of mass distribution and moment of torsion or torsion all centers on the barycenter that center line passes described, also coincides with the center line of described axle.

4. turbine according to claim 1 or rotor, it does not need to make its cantilever outer limb portions branch in fact forward by wide inner vanes (or supporting part) balance or support separately, because additional narrow annular edge is fixed in the outside, the most of outside end that all outer limb portions are divided provides extra rigidity by making the structure one.

5. turbine according to claim 1 and rotor, its the outside wing/interior section is radially placed with spiral or angle of inclination around propeller boss or axle, spiral or angle of inclination can change by the wing bindiny mechanism on propeller boss, or allowing the wing/bending blade to change the outstanding angle of the wing by the pressure on the given speed, this is in the velocity variations that provides, last speed envelope or optimize in the startup/parking operating mode all available.

6. according to each described turbine or rotor among the claim 1-5, it has the fixedly deflection wing that is usually located in the internal cavities that is formed on its ingress, or in the less rotor rotation of it self opposite direction, thereby the gas/liquid of introducing stream obviously outwards and/or the opposite side of the stream of gas/liquid backward have spiral path, so that the lifting force that is produced by the wing transforms the percentage that is produced as actual torque is maximum and be not wasted when promoting bearing backward under the situation of turbine, or advancing actual gross thrust maximum under the situation of rotor, this is that then gas-liquid flow can be discharged on a small quantity because if any tangible spiral angle is arranged.

7. turbine according to claim 1 or rotor; its outer limb portions branch is included in their end backward directed and converge one or more narrow slit towards back turbine or rotor center axle usually with the obtuse angle with respect to running shaft; in their outside trailing edge outlet separately; radius or curvature form another small " aerofoil " part; also have it and self arrive the angle of inclination of described tangible gas/liquid stream; increase the lifting force of the maximum that produces at wing rear portion, help the twisted effect that it is offset or balance is caused by especially tangible " guide tip " acting in conjunction.

8. according to each described turbine or rotor among the claim 1-6, it can be used to operate in pipeline, cylinder, passage or shell, and even can comprise fluid to pass turbine and be discharged to reticulated work in chamber or the passage, the reticulated work guided liquid-flow returns around the preceding inlet of the propelling rotor that is positioned at " internal cavities " in fact, " internal cavities " is formed on the inlet of described turbine, thereby whole unit can be used as fluid drives to be connect or dissemination, and velocity variations also may comprise by the described wing of claim 5 and connect the inclination of adjusting turbine or give prominence to the angle.

9. according to above description and described turbine of 1-7 or rotor with reference to the accompanying drawings.

Claims

1. turbine or rotor, comprise around the central hub or the axle of the central shaft rotation that is parallel to liquid/gas flow usually, propeller boss or axle support around described propeller boss or the diameter of axle to several integrally formed blade/vane unit of arranging, each comprises blade or " wing " part of outside stretching, extension in fact blade/vane unit, blade or " wing " part preferably have towards the inclination angle a little backward of gas/liquid outflow opening direction (0-45 degree), flat, the projection or most preferably the aerofoil profiled surface usually towards sense of rotation perpendicular to gas/liquid outflow opening direction, support and be integrally formed in its most external end forward, (being directed to introducing flows) in fact forward outstanding " wing " of obvious length, and preferably reduce usually perpendicular to synthetic gas/liquid stream and usually towards the protruding of sense of rotation or " aerofoil is shaped " surface, whole blade/wing unit is set on propeller boss/shaft portion, externally form the angle of spiral or inclination between the blade/vane end, and described propeller boss or axle axle can pass blade/vane by described gas/liquid stream and come to form lifting or deflecting force so that turbine or rotor rotate around its central shaft.

2. turbine according to claim 1 or rotor, it always has with the inner vanes length partly from identical described barycenter compares, the outwards outstanding outer limb portions branch of identical or length (measuring to the barycenter of the face of complete integral blade/wing unit from its external end) is so discharge stream zone or the cavity area between its outside wing periphery always greater than all discharging 1/3rd of gas/liquids stream zone.

3. turbine or rotor are in effective given application, integral blade/wing unit with balance, weight distribution is passed their barycenter around center line, perpendicular to propeller boss/axle central shaft, and by promote or the total amount of moment of torsion that deflecting force forms or torsion equal about the either side of identical described center line, unless come into effect, therefore cause the wing/bending blade, and therefore maximize rotational speed control in given flow velocity degree non-equilibrium state.

4. turbine according to claim 1 or rotor, the subregional major component section of each particular portion of its integral blade and wing unit preferably is arranged on the tilt angle between 0 degree and 35 degree, and always most preferably between 0 degree and 15 degree, in identical location, it is irrelevant with their part or size to pass identical location from synthetic gas/liquid stream.

5. turbine according to claim 1 and rotor, its integral body " blade/vane " centers on propeller boss/diameter of axle to placement with the spiral or the angle of inclination of permanent fixation, the lifting of its described blade/vane or deflecting force produce usually towards the sense of rotation on gas/liquid stream, and pass turbine or rotor, whether go into jet by aforesaid fixed-wing or the given spiral path of rotor, unless can be connected to around their independent mounting points center line on propeller boss/axle to this scope, when loading, can maximum " speed envelope " or be of value to " startup " state.

6. turbine according to claim 1 or rotor, its blade and the wing can comprise or not comprise one or more narrow " slits " there, they respectively backward outlet have smooth curve, radius or airfoil portion, also has it self angle of inclination to stream, near the location of the wing/blade, increase maximum " lifting " power, they are set up there, and these slit preferred orientation are passed the same area that they are placed perpendicular to gas/liquid stream.

7. rotor according to claim 1, in the described blade/vane unit of claim 1-4, it has projection or aerofoil surfaces, usually towards the opposite direction that rotates, and opposite or reversed dip angle is passed described its various parts of claim 4, and when torque applications during in the described sense of rotation of claim 1, gas/liquid stream outwards can be given and direction backward, with the numeral in each stage, angle of inclination or irrelevant to rotation direction.

8. turbine according to claim 1 or rotor, its blade/vane surface area with maximum ratio is between the 0.3-0.45 of rotary middle spindle radial diameter.

9. in turbine according to claim 1 or the rotor, that it can be used for embedding or polytype multiple rotor turbine device, rotor can center on same axis, propeller boss or rotate with equidirectional.

10. according to described turbine of claim 1-9 or rotor, it can have integral blade/wing unit, it is made of solid, that part is solid or empty, part aerofoil, flat, recessed or protruding, or their any amount or mixing of providing, they satisfy aerodynamic principle, and according to the distributed mass that requires of claim 3.

11. according to described turbine of claim 1-10 or rotor, it can use any amount of any following method by any compound of metal, iron, alloy, synthetic, plastics, resin, pressure layer material, organic material, timber or these materials:

Roll, die (cavity moulded), injection mould, wheel revolving die (roto moulded), vacuum forming, compacting, shearing, casting, embedding, blowing, sintering, riveted joint, welding, manufacturing, stickup, ultrasound connection or machining, arbitrary whole unit or by several parts assemblings.

12. according to above description and described fan of 1-7 or rotor with reference to the accompanying drawings.