CN1930394A - Turbine and rotor therefor - Google Patents

Abstract

The rotor comprises a central hub or shaft and a number of shoe-like integral blade/wing units which in combination with a significantly elongated wing tip extend substantially towards the incoming flow and the direction of rotation also forms a helix or pitch angle with respect to the centre line of the axis of rotation, preferably perpendicular and connected to the outer forward tip of the slightly backward inclined blade/wing section which is connected by its inner tip to the central hub of the shaft. The rotor is rotated about the axis of rotation by the incident gas/liquid stream, and most of the liquid stream is forced to move substantially outwardly and rearwardly so that it moves to and through the forward projecting airfoil tip at a substantial radial distance from the centerline of rotation. This maximum torque is generated and moved to the hub/shaft in a manner that does not substantially inhibit the shaft's through-flow, as the combined air/liquid flow discharge area (or slots between the blades/vanes) is much larger than the maximum rotor diameter, and essentially the rotor inlet area, which effectively increases the through-flow velocity and overall performance. The blade may have a slot therein.

Description

Turbines and rotors therefor

technical field

The present invention relates to a turbine and a rotor therefor having an axis of rotation substantially parallel to the gas/liquid flow. More particularly, the present invention relates to a non-hermetic wind/water turbine, or moving rotor/propeller housed in a duct and extracting energy from or converting energy to a moving gas or liquid flow.

Background technique

Most modern wind turbine rotors have low reliability and have a small number of airfoil sections with long straight blades around a central horizontal axis, with a large proportion of the wind turbine rotor blade area being in the inner half of its diameter. The very high tip speeds involved for maximum efficiency can greatly increase the noise of these turbine operating conditions.

The present inventors have recognized that the outer third of any turbine rotor does most of the useful work in converting kinetic energy from a moving gas/liquid flow into usable torque, with torque being a function of force times radius , and having increased gas/liquid flow velocities is more favorable for energy production than having increased overall size of the turbine rotor, the present invention seeks to locate the main working surface in front of the gas/liquid flow in this outer region to be effective in the design To achieve high mechanical efficiency, the design remains relatively basic, unimpeded, free-flowing, and independent of topmost velocity.

The maximum theoretical percentage of energy that can be extracted from the wind flow is 59.3% (BETZ limit), and the inventors have shown university supervised wind tunnel test results that support a maximum dynamic coefficient greater than 52%.

Contents of the invention

It is an object of the present invention to provide high efficiency output from any wind, hydro, steam or gas turbine having an axis of rotation generally parallel to the liquid/air flow through the use of a rotor design that increases DC velocity and through the The slot or cavity forms an overall flow output area larger than the inlet flow area predetermined by the maximum rotor diameter to increase the DC velocity and, for its size, its outer extremity maximum overall power output is also in the main working area, the rotor including the surrounding generally A central hub or shaft rotating parallel to the central axis of the gas-liquid flow, the central hub or shaft supports a number of equally spaced integral blade/wing units arranged radially around said hub or shaft, each The blade/wing unit comprises an integrally formed combination of typically short inner blade or "wing" portions extending substantially outwardly from the shaft hub or shaft, and the substantially forwardly extending outer "wing" portions are preferably perpendicular and connected to The outer, forward end of the inner portion, the integral wing/blade unit is mounted above the hub/shaft to form a helix between its outer radial end and the axial centerline of the hub/shaft or the angle of inclination, the angle is preferably between 0 and 6 degrees, and the angle due to rotation is greater than the resultant angle corresponding to the resultant amount of the inlet gas/liquid flow vector and the tangential gas/liquid flow "upwind" component, all relevant The rotor assembly moves the gas/liquid flow outward and rearward from its central axis generally parallel to it in an increasing "helical" path preferably through most of the forwardly projecting outer wing section openings , the outer wing sections preferably each include an appropriate inclination angle for each section along its longitudinal axis, to the resultant liquid/air flow vector passing through the same particular section, regardless of the location of the section or its particular section, most preferably at an inclination angle between Between 5 degrees and 15 degrees. Each blade/wing unit is preferably balanced between weight distribution and torsional (torque) forces generated by the "lift" from the fluid/air flow, around its own central mounting point perpendicular to the hub/shaft centerline, There is little or no need for the annular stiffened rim to connect it to the other blade/wing unit(s) at its forward-most periphery or mid-section, which simplifies manufacturing while retaining the ability to operate at higher angular velocities, other contemplated Yes, there is no excessive bending or damage due to large bending or torsion levels, and the design also leaves open the possibility of including blade/wing connections to different "protrusion" angles for speed bounding or start-up conditions purposes.

In a preferred form of the invention, the slightly curved slot is located at the outer rear end of the outer section or wing extending generally perpendicular to the "synthetic" flow in this region similar to the transverse section, the slotted wing or "Fuller" Flaps" (Flowler flap) greatly increase the lift force in this described area, so that the rearmost end of the blade/wing unit counteracts and balances the large torque force formed by using the unconventional significantly forward protruding wing section, if required, These forces are then fully overcome and the airfoil section is twisted to a lesser helix or "jump angle" empennage, the airfoil further to the velocity limit where the incoming flow can be maximized as the airfoil/blade bends at a predetermined flow velocity.

Preferably, the turbine rotor is designed as a wind turbine, however without eliminating its ability to provide alternative useful designs, any gas, liquid or steam turbine provided may be used in a variety of different environments where the maximum available space may be limited .

Description of drawings

Reference can be made to the accompanying drawings to aid understanding of the present invention, and details of some embodiments of the present invention are shown with reference to the accompanying drawings. However, it can be understood that the features shown and described in the accompanying drawings are only for explaining the present invention, and do not limit the present invention.

the scope of the invention.

Attached are:

Figure 1 shows a top view of the preferred embodiment;

Figure 2 shows the front view of the preferred embodiment, in this embodiment except several blades, #2 is the direction of rotation;

Figures 3a, 3b, and 4 show various partial cross-sectional views of the preferred integrated blade/wing unit, which depict the angle between syngas/liquid stream #11 and pitch angle  at the same location relative to the blade/wing section. relationship, Figure 3b also shows the portion adjacent to slot #5.

Figure 5 is an isometric view of the preferred embodiment;

Figure 6A depicts a simplified multi-stage turbine embodiment where the second stage has a different projection angle in the blades and direction of rotation than the first stage, maximizes the resultant lift to torque at the hub, and can have Pre-rotor wing.

Figure 6B shows a method of achieving prominent adjustment of the blade angle using a mounting shaft protruding from the central mounting line #8 of the blade/wing unit that can be connected by a mechanical device embedded in the hub.

Figure 6C shows a slotless embodiment, which can be more easily manufactured using pressed metal or vacuum forming methods, which also has an annular rim attached to the forwardmost perimeter of the blade/wing unit for added rigidity.

Figure 6D depicts a simplified secondary fan that can be nested in the duct for aircraft/hovercraft with a second rotor having a different rotation Expelling without sacrificing sloping length, and actually pushing backwards (composed of V1 axial plus V2 axial components).

Figure 7 shows a front view of the blade/wing unit of the preferred embodiment, according to the proportional design formula for any given turbine diameter:

"D" = Maximum rotor diameter

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

Y = the entire area behind the blade/wing where the center mounts dotted line #8

X = the entire area in front of the blade/wing where the center mounts dotted line #8

Ain = flow inlet area (= square of rotor radius multiplied by π)

Acirc = area of flow exiting outwards at the perimeter of the wing

Athru = area of flow discharged at the rear of the rotor

θ = angle of inclination or projection of the blade/wing unit relative to the central axis of the hub/shaft

ω = Angle between wing inner leading edge #7 to hub/shaft center axis #6

 = Angle between leading edge of blade section to centerline #8

#1 = Outer Wing Section

#3 = Inner Blade Section

#6 = Hub/Shaft Centerline

#8 = Centerline of the center of mass #10 passing through the area perpendicular to the center axis of the hub or shaft

#9 = Connection area between blade/wing and central hub or shaft

#10 = Center of mass of the area on which the overall area of the blade and airfoil section is considered to be centered

#11 = The vector for the "synthetic" flow consists of the sum of the axial flow velocity, the radial flow velocity and the tangential flow velocity produced by the rotation

#12 = Incoming stream direction

#14 = Angle between wing/blade outer wing trailing edge and hub center axis center axis

Figure 8 is the conclusion page of a wind tunnel test of a rotor with a diameter of 765mm supervised by the university.

Detailed ways

Refer to Figure 1

Several equidistantly spaced integrally formed "hook" blade/wing units comprising the most preferred inner airfoil section blade #3 angled slightly rearward from central hub or shaft #4 substantially Extending radially outward, each inner vane has a leading edge and is also inclined rearwardly from normal between 5 and 60 degrees, and the substantially forward projecting wing section #1 is aligned with the central hub or shaft #4 is integrally formed and attached to its outer outward edge, and the entire blade/wing unit is generally twisted at a helical or oblique angle θ around hub/shaft centerline #6, which is preferably parallel to Air/liquid flow direction #12 to maximize the lift or deflection force derived from the resulting liquid flow and converted to applicable torque.

Airfoil section #1 is the preferred airfoil section that reduces the chord length in proportion to the distance from inner blade section #3 to form a curved outer point that introduces the approaching flow.

Refer to Figure 7

Wing #1 preferably includes one or more slots #5 in its outer rear portion, the slots #5 being disposed generally perpendicular to the resultant stream #11 passing through the same said portion and being bendable , each slot is quite narrow and has a smooth rounded leading edge to guide the air/liquid flow partly through to the rear of the wing/blade unit, which provides increased lift in this area (Fig. 3b), And in this area it is most preferred to form a second "curved" or wing section and in this rearmost wing area the lift coefficient can be greatly increased for balancing the distinct front portion of the wing area with a smaller unit lift coefficient, which can be due to the surrounding The moment or torsion of the centerline #8 is allowed to be maintained in balance through the integral airfoil/blade area centroid #10 perpendicular to the hub central axis #6.

Preferably, the total mass (area x-x) before centerline #8 is equal to the total mass (area y-y) after centerline #8, enabling a fully balanced blade design to allow centerline #8 to pass through the center of the center axis perpendicular to the hub Centroid #10 of the area of line #6.

Center hub #4 can be constructed in a variety of shapes and sizes, but preferably has a diameter between 0.2 and 0.4 of the overall rotor diameter, the increased diameter helping to direct flow outward and rearward in a smooth curved taper towards its rear Without causing additional turbulence, and providing a possible housing for the blade associated mechanism, generating unit or connection to a suitable output shaft and/or support bearing.

As can be seen from Figure 1, the general shape of all rotors is designed to induce a liquid or gas flow pattern with a substantially outward direction when moving further into and completely through the rotor.

Since the overall discharge flow area "A thru" plus "A Circ" is much larger than the entire inlet flow area "A in", the volume-in is equal to the volume-out, and the volume is equal to the velocity times the area, then according to Bernoullis principle that the speed inside/forward of the rotor or the pressure drop outside/backward of the rotor necessarily increases, all improved turbine rotors outperform the prior art.

All leading edges are preferably suitably rounded to minimize turbulence, and all parts have a good surface finish, and the inner vane part needs to be strong enough to switch adequately when the fluid/gas flow changes to torque at the hub or shaft , or translate deflection and "lift" forces from blades, wings, and slots, and withstand centrifugal and bending forces while rotating the monolithic mass at maximum rotational speed in extreme conditions.

claims

(Amended in accordance with Article 19 of the Treaty)

                                                                            

With reference to the filed invention titled "Turbine and Rotor Therefore", the claims were described and worded incorrectly, making the invention considered to lack novelty.

The claimed novelty has not been noticed by our inappropriate description in this filing and has not changed since the first provisional application was filed, so we did not seek the necessary changes to the filed drawings.

What is essential and essential to the novelty of the claimed matter is any relevant gas or fluid flow (or the direction of flow considered as the sum of inflow vector, outflow vector due to blade/wing rotation), if there is any radial Outward flow vector, then "in the first instance encounters the top, not the edge" and finally "passes the other tip on the same blade, not the edge", so that the working surface area of the blade is very large relative to its width The relative gas/fluid flow that occurs when long and well suited for circulation, not only the direction of the incoming flow, but also the speed with which the hull rises out of the water is unclear.

Also, we make the wrong claim that describes the inner wing or support portion as having a slight rearward slope, which is incorrect, so we amend the claim so that the direction of flow can occur when perpendicular to the flow that occurs when said circulation Rear tilt, which does not occur perpendicular to or adjacent to the central axis of the central hub or shaft, except possibly in its abnormal "on" or "off" mode due to abnormal blade connections, and in fact the inner section will There is a slight forward inclination towards the turbine or rotor inlet as the vertical centerline of the object, and some simple drawings and descriptions will be corrected accordingly hereafter.

The rest of the amended claims are merely further description of selected parts of the application, stating novelty and design principles.

1. A turbine or rotor consisting essentially of a number of relatively long curved wings or curved or airfoil profiled "wing sections" disposed circumferentially about a hub or shaft, the central axis of which is substantially Parallel to the incoming gas/liquid flow, each of said wings has at its ends a tip formed by the crossing of its longitudinal side tangents, and these two extreme ends rotate at a desired tip velocity relative to the apparent gas or The flow direction becomes the actual leading edge and trailing edge, these extremities are oriented to form an angle between 0° and 36° with respect to the apparent air flow, the longitudinal sides are oriented in relation to the relative to the direction of flow, and each of said wings protrudes substantially from a forward outer end of a second inner portion or wing connecting it to said shaft providing support for said outer portion On the hub or shaft, at the same time, give a minimum resistance or hindering effect on the gas/liquid flow;

In the forward region inside the turbine or rotor, the fully rotating outer part, inner part, hub/shaft assembly form a substantially circular cavity.

2. A turbine or rotor as claimed in claim 1 having a maximum proportion of the airfoil/blade surface area lying between 0.33 and 0.46 of the radial diameter of the central axis of rotation.

3. A turbine or rotor as claimed in claim 1 having an inner blade or support portion of width less than half the length of the outer airfoil portion and which can be manufactured in the most basic embodiment from the face of the airfoil/blade portion In the form of a shaft with the center of mass protruding downwards and perpendicular to the shaft/hub central axis, the wing/blade section can be fully formed and substantially balanced, due to lift/deflection forces, the mass distribution and the total amount of torque or torque around The centerline passes through the centroid of the face and also coincides with the centerline of the axis.

4. A turbine or rotor as claimed in claim 1 which does not require its substantially forward cantilevered outer wing portion to be balanced or solely supported by a wide inner blade (or support portion) because the additional narrow annular rim is fixed to Externally, the mostly outward ends of all external wing sections provide additional rigidity by making the structure integral.

5. A turbine and rotor as claimed in claim 1 with outer wings/inner sections radially positioned around a hub or shaft at a helix or inclination angle capable of being varied by means of a wing connection on the hub, or Changing the wing's projection angle by allowing the wing/blade to flex by pressure at a given speed, is available at a given speed change, final speed limit or optimized start/stop conditions.

6. A turbine or rotor as claimed in any one of claims 1 to 5 having fixed deflected wings generally within an internal cavity formed at its inlet, or a smaller rotor in its own relative direction Rotate so that the incoming air/liquid flow has a helical path on the opposite side of the apparent outward and/or rearward air/liquid flow so that the lift force produced by the wings is converted into a percentage of actual torque that is maximized at the turbine's The actual total thrust is maximized if the bearings are pushed backwards, or the rotor is pushed, because if there is any significant helix angle, a small amount of gas-liquid flow can escape.

7. A turbine or rotor as claimed in claim 1 , the outer wing portions comprising at their rearward ends one or more narrow fins oriented at an obtuse angle to the axis of rotation and converging generally towards the rear turbine or rotor central axis. The slots, exiting at their respective outer trailing edges, form another tiny "airfoil" section of radius or curvature, also with its own angle of inclination to the apparent gas/liquid flow, which increases at the rear of the wing to produce for maximum lift, helping it to counteract or balance the distorting effect caused by the combined action of the extraordinarily pronounced "leading ends".

8. A turbine or rotor as claimed in any one of claims 1-6 which may be adapted to operate in a pipe, cylinder, channel or housing and which may even include a discharge of fluid through the turbine into a chamber or channel The mesh that directs the flow back around the front inlet of the propulsion rotor is located substantially within the "inner cavity" formed at the inlet of the turbine so that the whole unit acts as a fluid drive coupling Or propagating effect, speed change may also include adjustment of turbine pitch or protrusion angle through wing connection as claimed in claim 5 .

9. A turbine or rotor as hereinbefore described and with reference to the accompanying drawings 1-7.

Claims (12)

1. A turbine or rotor comprising a central hub or shaft rotating about a central axis generally parallel to a liquid/gas flow, the hub or shaft supporting a plurality of integrally formed blades arranged radially about said hub or shaft /Wing unit, the blades/Wing unit each substantially comprise outwardly extending blades or "wing" sections, preferably with a slight backward rake (0-45 degrees) towards the direction of the gas/liquid flow outlet , a flat, raised or most preferably airfoil-forming surface generally facing the direction of rotation perpendicular to the direction of the gas/liquid outflow outlet, supported and integrally formed at its outermost forward end, substantially forward ( leading to the incoming flow) protruding "wings", and preferably reducing convex or "airfoil-shaped" surfaces generally perpendicular to the resulting gas/liquid flow and generally facing the direction of rotation, the entire blade/wing unit is arranged on the shaft On the hub/shaft portion, a helical or inclined angle is formed between the outer blade/wing ends, and the hub or shaft can be lifted about its central axis by the gas/liquid flow through the blade/wing or deflection force to spin the turbine or rotor. 2. A turbine or rotor according to claim 1, which always has the same or longer length (from its outer tip to a fully integral blade/wing) than the length of the inner blade part from the same said center of mass The outwardly projecting outer wing portion of the face of the cell measured at the centroid of the face of the unit) so that the outward discharge flow area or the cavity area between its outer wing peripheries is always greater than one-third of the total exhaust gas/liquid flow area . 3. Turbines or rotors that, for a given application effectively, have balanced integral blade/wing units with weight distribution about centerlines through their centers of mass, perpendicular to the hub/shaft center axis, and formed by lift or deflection forces The total amount of torque or torsional force is equal about either side of the same centerline unless at a given flow velocity an imbalance condition comes into effect, thus causing wing/blade bending and thus maximizing rotational speed control. 4. Turbine or rotor according to claim 1, the main part section of its integral blade and each specific partial area of the airfoil unit is preferably set at an inclination angle between 0 degrees and 35 degrees, and always most preferably at 0 degrees and 15 degrees, in the same specific area, from syngas/liquid streams through the same specific area regardless of their fraction or size. 5. The turbine and rotor of claim 1 with integral "blades/wings" positioned radially about the hub/shaft at a permanently fixed helical or pitched angle, the lift or deflection force of said blades/wings producing Generally oriented in the direction of rotation on the gas/liquid flow, and through the turbine or rotor, whether the incident flow is given a helical path by the aforementioned fixed wing or rotating rotor, unless able to be centerline connected to the hub around their separate mounting points /axis up to the range that, when loaded, is capable of a maximum "speed bound" or beneficial "start" state. 6. A turbine or rotor as claimed in claim 1, where the blades and wings may or may not include one or more narrow "slots" with smooth curves, radii or wings at their respective rearward exits The face section, also has its own inclination angle to the flow, to increase the maximum "lift" force near the specific area of the wing/blade where they are located, and the slots are preferably oriented perpendicular to the gas/liquid flow through The same area where they are placed. 7. A rotor according to claim 1, in a blade/wing unit as claimed in claims 1-4, having raised or airfoil surfaces facing generally in opposite directions of rotation, and opposite or opposite angles of inclination Through its various parts as claimed in claim 4, when torque is applied in the direction of rotation as claimed in claim 1, gas/liquid flow can be given outward and rearward directions, with the numbers of the various stages, inclined Angle or direction of rotation is irrelevant. 8. A turbine or rotor according to claim 1 having a maximum proportion of blade/airfoil surface area between 0.3-0.45 of the radial diameter of the central axis of rotation. 9. A turbine or rotor as claimed in claim 1 which may be used in a variety of rotor turbine devices with embedded or multiple types of shafts, the rotors may not necessarily rotate around the same shaft, hub or in the same direction. 10. A turbine or rotor according to claims 1-9, which may have integral blade/airfoil units consisting of solid, part-solid or hollow, airfoiled, flat, concave or convex parts , or any quantity or mixture they provide, which satisfy the principles of aerodynamics and distribute the mass according to the requirements of claim 3. 11. A turbine or rotor according to claims 1-10, which may be made of metal, iron, alloys, composites, plastics, resins, laminates, organic materials, wood or any compound of these materials, any number of Any of the following methods: Rolling, cavity molded, injection molded, roto molded, vacuum formed, pressed, sheared, cast, embedded, blown, sintered, riveted, welded, fabricated, pasted, ultrasonically joined or machined , any whole unit or assembled from several parts. 12. A fan or rotor as hereinbefore described and with reference to accompanying drawings 1-7.

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