WO2003021105A1 - Mecanisme moteur a ecoulement - Google Patents

Mecanisme moteur a ecoulement Download PDF

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Publication number
WO2003021105A1
WO2003021105A1 PCT/EP2002/009903 EP0209903W WO03021105A1 WO 2003021105 A1 WO2003021105 A1 WO 2003021105A1 EP 0209903 W EP0209903 W EP 0209903W WO 03021105 A1 WO03021105 A1 WO 03021105A1
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WO
WIPO (PCT)
Prior art keywords
wing
axis
rotation
power machine
fluid power
Prior art date
Application number
PCT/EP2002/009903
Other languages
German (de)
English (en)
Inventor
Günter Pöschl
Original Assignee
Neue Spulentechnologie Beteiligungs Ag
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Neue Spulentechnologie Beteiligungs Ag filed Critical Neue Spulentechnologie Beteiligungs Ag
Publication of WO2003021105A1 publication Critical patent/WO2003021105A1/fr

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03D—WIND MOTORS
    • F03D1/00—Wind motors with rotation axis substantially parallel to the air flow entering the rotor 
    • F03D1/06—Rotors
    • F03D1/065—Rotors characterised by their construction elements
    • F03D1/0658—Arrangements for fixing wind-engaging parts to a hub
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03D—WIND MOTORS
    • F03D1/00—Wind motors with rotation axis substantially parallel to the air flow entering the rotor 
    • F03D1/06—Rotors
    • F03D1/0608—Rotors characterised by their aerodynamic shape
    • 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
    • F03D7/00—Controlling wind motors 
    • F03D7/02—Controlling wind motors  the wind motors having rotation axis substantially parallel to the air flow entering the rotor
    • F03D7/0204—Controlling wind motors  the wind motors having rotation axis substantially parallel to the air flow entering the rotor for orientation in relation to wind direction
    • 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
    • F05B2240/20—Rotors
    • F05B2240/24—Rotors for turbines
    • F05B2240/243—Rotors for turbines of the Archimedes screw type
    • 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
    • F05B2240/20—Rotors
    • F05B2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05B2240/301—Cross-section characteristics
    • 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
    • F05B2240/20—Rotors
    • F05B2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05B2240/31—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor of changeable form or shape
    • F05B2240/311—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor of changeable form or shape flexible or elastic
    • 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
    • F05B2250/00—Geometry
    • F05B2250/20—Geometry three-dimensional
    • F05B2250/24—Geometry three-dimensional ellipsoidal
    • 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
    • F05B2250/00—Geometry
    • F05B2250/20—Geometry three-dimensional
    • F05B2250/24—Geometry three-dimensional ellipsoidal
    • F05B2250/241—Geometry three-dimensional ellipsoidal spherical
    • 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

Definitions

  • the invention relates to a fluid flow machine according to the preamble of claim 1.
  • Such a flow machine is already known from DE 198 20 766 AI.
  • Such a flow machine is characterized by the unusual shape of its wings.
  • the wings are described in the prior art so that they extend on an imaginary spherical surface from the front to the rear end of the wing in an S-shape, of course a mirrored “S” should also fall under this definition.
  • the "S" shape is optimally visible when the point furthest away from the axis of rotation of each wing (apex) is used by looking perpendicularly to the axis of rotation from this apex.
  • the invention provides a fluid flow machine with an improved lift over the entire wing length and a lower flow resistance.
  • Each wing has a steadily decreasing wing thickness from its front longitudinal end to close to the apex and from the apex to the rear longitudinal end a steadily increasing wing thickness.
  • the wing thickness and the entire airfoil profile change constantly over the length of the wing. This has proven to be advantageous because the flow on the surface of the wing is the result of the flow speed and the peripheral speed of the wing rotating about the axis of rotation. With increasing distance from the axis of rotation, the peripheral speed becomes more important.
  • the wing will therefore to achieve optimal buoyancy from its longitudinal ends to near the apex increasingly thin and elongated, so optimized for the higher flow speeds, so that a less lossy rotation can be achieved.
  • a transition area can be provided in the area of the apex, in which the features mentioned in the characterizing part of claim 1 need not be present. Rather, it may be that the thickness is approximately the same in a transition region around the apex.
  • the angle of attack of the profile preferably also changes over the longitudinal extension of the wing to the resultant of the flow (superimposition of the wind speed in magnitude and direction on the circumferential speed of the inflow profile section).
  • Each wing is otherwise S-shaped between its front and rear longitudinal ends, and the turning point of the "S" lies essentially on an equatorial circle formed by the rotating apex.
  • each wing is rotated in the direction of the axis of rotation according to claim 2 so that on a rear wing section (rear longitudinal end of the wing towards the apex) the front edge of the wing is closer to the imaginary surface and closer to the axis of rotation than the radially further trailing edge from the surface and further from the axis of rotation.
  • the front wing section (from the apex to the front longitudinal end) it is reversed.
  • the rear edge is closer to the imaginary surface and the axis of rotation than the front edge, which extends radially further from the surface and radially further away from the axis of rotation.
  • a transition area can be provided in the area of the vertex, in which the in the characterizing part of the features mentioned claim 2 need not be present. Rather, it may be that the leading edge and the trailing edge are approximately equally close and additionally on the surface.
  • the trailing edge lies on the front wing section and the leading edge lies on the imaginary surface on the rear wing section.
  • the course of the wing thickness over the longitudinal extent of the wing is essentially inversely proportional to the distance from the front edge to the axis of rotation.
  • the body of revolution can be an ellipsoid, including the sphere.
  • the rotating body is formed by a flexible cable, the ends of which are fastened to the axis of rotation and which rotates about the axis of rotation, like a jump cable.
  • the rope forms the previously mentioned curve rotating about the axis of rotation.
  • the profiles of the two wings are point-symmetrical to each other in each section plane perpendicular to the axis of rotation, based on the point of intersection of the axis of rotation with the section plane.
  • the course of the curve is, moreover, axisymmetric from the front end of the curve to the apex to the region from the apex to back of the curve, with the axis passing through the apex and perpendicular to the axis of rotation.
  • the "S" in the above-mentioned plan view should also be point-symmetrical from the vertex perpendicular to the axis of rotation to the vertex. This results in the shape of an "8" in a viewing direction parallel to the axis of rotation through the two wings, one wing the upper half and one wing the lower
  • wing shape seen in the axial direction is that the wings describe a loop.
  • a secure attachment of the fluid flow machine results from the fact that an arc-shaped mounting rod is provided which extends from the front to a rear rotary shaft bearing around the space through which the wings pass and that the mounting rod is clamped to a base via clamps.
  • the base should preferably have a V-shaped contact surface, seen transversely to the axis of rotation. It has been found that, due to the enormous flow velocity at which the fluid-flow engine according to the invention can work, welded connections are not to be regarded as optimal.
  • the clamp connection by means of the clamps, in particular with the V-shaped contact surface ensures permanent storage.
  • An electrical brake should brake the rotating shaft in the event of an overload.
  • the invention also provides a method for controlling the fluid flow engine according to the invention, the axis of rotation being pivotable about a vertical axis in order to change the angle of attack of the axis of rotation in relation to the direction of flow.
  • the control takes place as follows: until a predetermined flow velocity is reached, the axis of rotation is set in the direction of flow. When the specified flow velocity is exceeded, the axis of rotation is continuously adjusted at an increasing angle to the flow direction. Due to the shape of the wing, in which the profile constantly changes over the length, and the fact that the wing surface lies on the surface of the rotating body, the effective depth of the wing (from the front edge to the rear edge) is swept by the current becomes bigger.
  • the flow will not sweep the shortest distance from the leading edge to the trailing edge when the axis of rotation is inclined, but will graze along the wing surface at an angle to the longitudinal extension of the wing, so that another effective airfoil profile results, which can be represented if the wing along the resulting A cut is made in the direction of flow. Because of this effect and the method according to the invention, which uses this effect, the fluid flow machine can be operated over a substantially larger flow velocity range than previous fluid flow machines. Very good efficiencies can be achieved even at high flow speeds.
  • the axis of rotation must be set at an angle to the direction of flow so that the blades stop because the stall effect (suction effect) then occurs.
  • the fluid flow machine therefore does not necessarily need a brake for excessive flow velocities.
  • Angle of attack of the wing ensures an optimized, even self-optimizing performance.
  • the adjustment can be carried out manually or, as mentioned, automatically.
  • the adjustment mechanism has e.g. a coupling of the adjustment movements of both wings, the adjustment mechanism acting on the front and rear bearing points of the wings and providing a coupling of adjustment movements on the front and rear bearing points.
  • a method according to the invention provides before that the wing of a fluid flow machine according to the invention is made of glass or carbon fiber fabric or mats.
  • the wing is hollow and ribbed between the top and bottom of the wing, the ribs also being made of a glass or carbon fiber fabric or mat.
  • the fabric or mat is positioned between the top of the wing and the underside of the wing in the soaked state (usually soaked in resin).
  • An expandable, flexible hose is positioned between the fabric or mat for the ribs and the wing top and / or underside, which is then filled so much (preferably with air) that it expands until the fabric or mat for the ribs are pressed against the top and / or bottom of the wing.
  • the wing is then hardened in this state. It can thus be achieved that the ribs rest securely on the upper and lower sides of the wing, ie on the corresponding glass or carbon fiber wall, and establish a connection therewith.
  • Hot air can also be blown in through the hose or preferably a plurality of hoses, which accelerates the hardening process. Later, the hoses could also run a heater that prevents the wings from icing up.
  • the manufacturing method according to the invention is otherwise not limited to the specially curved blades for the fluid-flow engine according to the invention; theoretically, aircraft wings, rotor blades could also be used. can be easily and securely ribbed using the hoses used.
  • the hose used preferably also consists of impregnated glass or carbon fiber.
  • the fibers run at an angle to the length of the tube so that it can expand. After expansion, the tube can be cured and form part of the ribs and reinforce them.
  • these can be composed of a plurality of sections adjoining one another in the longitudinal direction.
  • the hoses can connect adjacent sections to one another by acting on the one hand as a receptacle for connecting pins inserted into them or on the other hand, extend through several adjacent sections.
  • the tube is made of impregnated glass or carbon fiber and is then expanded by supplying compressed air or other suitable fluid until it lies against the ribs and / or the wing top and / or the wing underside before it is subsequently cured.
  • the tube passing through the sections thus forms a kind of supporting skeleton.
  • the invention also relates to a wing bearing, with a wing made of a tubular fiber material, a ring at the end of the hose on the bearing side being surrounded by the hose in that the hose end is put over the ring and connected to the hose near its end by curing, and wherein a cone and a counterpart, preferably a counter cone, are provided, between which the hose end and the section of the hose connected to it are clamped.
  • This idea is not only limited to a wing bearing but to any storage of a part made of fiber material, since there is always the problem of the transition between the fiber material and the adjacent steel part.
  • the idea according to the invention does not provide a conventional through-hole that weakens the fiber material. Rather, the fiber material is held over a large area by embedding a ring for holding and preferably self-locking friction and positive locking.
  • FIG. 1 is a perspective view of the turbo engine, designed as a wind turbine, obliquely from behind,
  • FIG. 2 is a side view of the fluid-flow engine according to FIG. 1 with several cuts (AA to EE) through the wing, which show the change in profile over the longitudinal extension of the wing
  • FIG. 3 is a top view of a wing viewed in one direction through the apex of the wing and perpendicular to the axis of rotation, the fictional body also being shown,
  • FIG. 4 is a cross section through the wing profile of the wings perpendicular to the axis of rotation
  • FIG. 5 is a side view of the fluid flow engine according to a second embodiment with an integrated adjustment mechanism for changing the angle of attack
  • FIG. 7 is a sectional view through a wing end and its storage.
  • FIG. 1 shows a fluid flow machine, more precisely a wind turbine.
  • the fluid flow machine has a rotary shaft 10 with an imaginary axis of rotation A, the rotary shaft 10 being accommodated in a front rotary shaft bearing 12 and a rear rotary shaft bearing 14.
  • the front rotary shaft bearing 12 and the rear rotary shaft bearing 14 also form the front and rear axle ends, respectively.
  • the term "front” refers to the optimal flow direction S, which runs parallel to the axis of rotation A.
  • the fluid flow machine has two vanes 16, 18 which are opposite to each other with respect to the axis A and which are of opposite construction. This means that in all sectional planes perpendicular to the axis of rotation A, the wing profiles of the wings are point-symmetrical to the point of intersection of the axis of rotation A with the sectional plane. Both wings 16, 18 have an airfoil profile, as is exemplarily shown in different sectional planes in FIGS. 2 and 4, with a front edge VK and a rear edge HK, the front edges VK of both wings 16, 18 pointing in the direction of rotation.
  • Each wing 16, 18 extends essentially along the surface of an imaginary rotating body, the axis of which coincides with the axis of rotation A and which is caused by the rotation of an arcuate, continuously curved curve, for example the Curve K arises.
  • the curve is a semicircle, so that through
  • Rotation creates a sphere, i.e. a special version of an ellipsoid.
  • Figure 3 is the curve K an outer semicircle, with a curve beginning KA as a section with the axis of rotation A and with a curve end KE as a second section with the axis of rotation A.
  • the curve has a point B that has the maximum distance from the axis of rotation A. Rotation of point B about the axis of rotation A results in an equatorial circle C.
  • Each wing 16, 18 extends from the front longitudinal end (wing start) 20 to the rear longitudinal end (wing end) 22 in an S-shape over the surface of the rotating body. The point of inflection of the S-shape lies on the equatorial circle C and forms the apex SP of the wing, that is, the point which is furthest away from the axis of rotation A.
  • the vertex SP is the center of the rotating curve K.
  • the view shown in FIG. 3 is therefore a plan view in the direction through the vertex SP and at right angles to the axis of rotation A.
  • the S shape is distinguished in the embodiment shown in FIG. 3 in that a section 34 of the wing 16, 18 before and after the apex SP in the view shown in FIG. 3 is linear (transition region) before the wing 16, 18 goes back into the curved areas.
  • the longitudinal ends of each wing 16, 18 are offset from one another by 90 °.
  • each wing 16, 18 is rotated in itself in the direction of the axis of rotation, so that, for example, the leading edge VK does not lie exactly on the surface of the rotating body over the entire length.
  • the front wing section 36 that is to say the curved area from the beginning of the wing 20 to the beginning of the linear section 34, optionally even as far as into the linear section 34, the rear edge HK lies closer to or even on the surface of the rotating body compared to the front edge VK , which is further away from the axis of rotation A, seen in each case in a sectional plane perpendicular to the axis of rotation A. This can also be seen in the sections AA and BB in FIG. 2, in which the surface of the rotating body, defined by curve K, is also drawn.
  • the leading edge VK moves ever closer to the surface of the rotating body, so that there is a constantly different angle of attack of the wing profile to the surface of the imaginary rotating body.
  • This adaptation is a function of the increasing distance of the wing from the axis of rotation A.
  • the maximum thickness d is shown in Figures 2 and 4.
  • L is the so-called skeleton line, i.e. the geometric location of the center points of all the circles inscribed in the profile.
  • the thickness d is the diameter of the largest inscribed circle.
  • Circumferential speed on the wing surface increases with rotating blades 16, 18, it was considered to allow this increase in the resulting flow velocity to flow into the wing profile.
  • the wing profile becomes increasingly thinner with increasing distance from the axis of rotation A, ie the thickness d and the depth t of the wing decrease from the front end 20 to close to the wing end 34 or even to the apex SP and then to the wing end 22 again.
  • the thickness d is continuous and preferably inversely proportional to the distance between the front edge VK and the axis of rotation A.
  • the so-called strack width to thickness ratio over the wing length
  • strack width to thickness ratio over the wing length
  • a housing 40 is provided, in which a generator 42 is accommodated.
  • the generator 42 can act as an electrical brake in the event of an overload, or in addition a separate electrical brake can also be provided which brakes the rotary shaft 10 in the event of an overload.
  • An arcuate support rod 50 connects the front and rear rotary shaft bearings and extends outside around the space through which the wings pass.
  • the mounting rod 50 is clamped on a base 54 via two clamps 52, which, seen perpendicular to the axis of rotation A, has a V-shaped bearing surface 56 which is adapted to the curvature of the mounting rod 50.
  • a bolt (not shown) which penetrates the base 52 and the holding rod 50 can additionally be provided as an additional safeguard.
  • the base 54 is connected to a vertical axis of rotation 60.
  • a rotary drive is provided in a housing 62 so that the flow machine can be pivoted about the vertical axis of rotation 60 into and out of the flow S.
  • the flow engine is controlled in such a way that the rotational axis A parallel to the flow direction S, i.e. remains aligned in the direction of flow.
  • the axis of rotation A is continuously adjusted obliquely to the flow direction S with increasing flow rate.
  • the flow power machine according to the invention also works at very high flow speeds. By tilting the axis of rotation A, the length covered by the flow on the wing surface is changed, so that a different effective wing profile results.
  • a maximum, predetermined flow rate from which the
  • the axis of rotation A is placed so obliquely to the flow direction S that the wings 16, 18 stop by themselves due to the suction effect.
  • the alternative brake provided may not have to intervene here.
  • the wings 16, 18 are produced by a special process. Each wing is made entirely of glass or carbon fiber or equivalent mats.
  • the wing top 70 and the wing bottom 72 are ribbed together.
  • a wavy glass or carbon fiber fabric or mat 74 is provided between the upper wing 70 and the lower wing 72, which alternately connects to the upper wing 70 and the lower wing 72 in sections 76.
  • the production can take place in the so-called prepreg process, for example by first producing the upper side 70 of the wing and the lower side 72 of the wing and then the fabric or mat between the two
  • wing top 70, wing underside 72 and the fabric or mat 74 for the ribs can also be impregnated and flexibly brought into a form in which they are later hardened. So that the fabric or mat
  • Hose is preferably also made of glass or carbon fiber fabric, the fibers running obliquely to the longitudinal extension of the hose.
  • the hose bears the reference symbol 80.
  • the hose 80 is preferably also soaked in liquid before insertion. Then it is filled with compressed air and inflated so that it widens and fills the cavity 78 until it is on the one hand on the upper side of the wing 70 and on the other hand on the fabric or mat 74 for the Formation of the ribs is in full contact. The hose 80 thus presses the fabric or mat 74 in the area 81 against the underside 72 of the wing, so that a good connection is created here.
  • the tubing 80 like the fabric or mat 74 for the fins, is integral with the adjacent glass or carbon fiber fabric or mats so that the tubing 80 can remain in the wing 16, 18 and the fins or the top or bottom of the wing 60 or 62 forms or strengthens.
  • the ribs could only be formed by a plurality of tubes 80.
  • the wing can also be assembled from several segments as just described, connecting pins 130 being driven into the cavities 78 or the hose 80.
  • FIG. 4 would represent a side view of a segment that is open on one side.
  • the invention also relates to a high-strength and wear-free
  • the wing 16 has the above-mentioned tube 80 made of a fiber material, the fibers F of which extend at approximately 45 ° to the longitudinal extent LE.
  • a ring 82 made of plastic or metal is pushed over the bearing-side end 84 of the hose 80, if the latter is still soaked in liquid.
  • the hose end 84 is turned outwards around the ring 82 and connected to the hose 80 near its end, in the overlap region, by curing, so that the ring 82 is completely surrounded by the hose 80.
  • a cone 86 with a shoulder 88, on which the ring 82 sits, is inserted into the interior of the hose 80 before it hardens.
  • the cone 86 (made of plastic or metal) widens outwards and provides a self-reinforcing effect when the wings 16, 18 are pulled in the longitudinal direction LE, because a counterpart in the form of a counter cone 90 is provided on the outside of the hose end 84 in the overlap area.
  • the hose 80 is clamped in the overlap area between cone 86 and counter-cone 90.
  • the counter cone 90 can be a metal tube or through a section of the wing top or bottom 70 or 72 forming mat 74. This idea does not provide for a conventional through-hole that weakens the fiber material. Rather, the fiber material is held over a large area by embedding a ring 82 for holding purposes and a preferably self-locking friction and form fit.
  • a metal sleeve 92 is fastened with a flange, which is screwed into a bearing block 94, in which the other wing 18, not shown, is also mounted.
  • the bearing block 94 is the bearing of the rear wing ends (longitudinal ends 22) and is located close to the rear rotary shaft bearing 14.
  • the bearing block 94 can be part of a preferably self-controlling
  • Adjustment mechanism to change the angle of attack ⁇ (FIG. 5) to the flow S.
  • the blades are set differently relative to the rotating body by means of the adjustment mechanism in order to change the angle of attack and angle of attack.
  • the adjustment mechanism acts on each wing 16, 18 at its front and rear bearing points (in the present case the front and rear longitudinal ends 20, 22 of each wing 16, 18).
  • the adjustment can be done by hand or by motor. Instead of the
  • Screw 96 provided a bevel gear 98 (Fig. 6) which is pivotable
  • Adjusting lever 110 is pivotally connected to sleeve 92 and can cause rotation thereof and thus the wing end (longitudinal end 22) shown in FIG. 7 and thus a change in the angle of attack.
  • the bevel gear 98 is part of a differential gear, which also includes a bevel gear 98 'and an adjusting lever 110 for the other wing and a drive bevel gear 100, so that the adjustment movements between the adjacent wing ends (longitudinal ends 22) are synchronized.
  • the drive bevel gear 100 is coupled to a manually or motor-adjustable drive shaft 102.
  • the drive bevel gear 100 is connected to a drive bevel gear of a corresponding differential in a bearing pedestal designed in accordance with the pedestal 94 106 for receiving the front wing ends (longitudinal ends 20) in permanent connection, so that not only a coupling of the adjusting movements of the two wings 16, 18 is achieved at one end, but also a coupling of adjusting movements at the front and rear wing ends.
  • the bearing blocks 94, 106 are arranged so that the axes of rotation DK1, DK2 of the bevel gears 16, 18 associated 90 ° to each other.
  • the front bevel gears are also pivotally connected to the front wing ends 20 via short pivotable adjusting levers 110 ', which are coupled to the wing ends via a pivot axis DF1 and DF2.
  • the assigned adjustment levers 110, 110 'of each wing are also at 90 ° to each other.
  • the adjustment movements are shown with arrows.
  • the angle of attack can be adjusted via the adjustment mechanism, but also the curve K, i.e. the wing curvature and thus the angle of attack.
  • the wings at the front and rear longitudinal ends 22, 24 are adjusted to the rotating body by means of the adjusting lever 110, 110 '. If, for example, the front adjusting lever 110 'is pivoted forward about the axis DK2, then the adjusting lever 110 is synchronized for this purpose pivoted forward, so that there is a superimposed pivoting movement about two axes, without an elastic deformation of the wings 16, 18 being associated therewith would.

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  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne un mécanisme moteur à écoulement pourvu d'un axe de rotation (A) et comprenant au moins deux pales opposées (16, 18). Chaque pale (16, 18) s'étend pratiquement le long de la surface d'un corps de rotation imaginaire dont l'axe coïncide avec l'axe de rotation (A) et qui est généré par rotation d'une courbe arquée, curviligne de manière continue. Le sommet de la courbe présente l'écart maximal par rapport à l'axe de rotation (A). Chaque pale (16, 18) s'étend en S entre son extrémité avant et son extrémité arrière et a une épaisseur (d) diminuant progressivement en allant de son extrémité longitudinale avant jusqu'à proximité du sommet, puis une épaisseur (d) augmentant à nouveau progressivement du sommet jusqu'à son extrémité arrière. L'invention concerne également un procédé de production pour une pale (16, 18), un procédé de commande pour le mécanisme moteur à écoulement, ainsi qu'un logement de pale.
PCT/EP2002/009903 2001-09-04 2002-09-04 Mecanisme moteur a ecoulement WO2003021105A1 (fr)

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DE10143349 2001-09-04

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Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2005026536A1 (fr) * 2003-09-10 2005-03-24 Fritz Kadletz Turbomachine
WO2009016372A2 (fr) * 2007-07-30 2009-02-05 Subsea Energy (Scotland) Limited Appareil de génération d'énergie éolienne
EP2028102A1 (fr) * 2006-03-28 2009-02-25 Zakrytoe Aktzionernoe Obshcestvo "Aviastroitel' Naya Korporatziya 'Rusich' Hélice de shpadi (et variantes) et développante de ces pales
WO2010023648A3 (fr) * 2008-08-27 2010-08-12 Bernard Mcguire Turbine et rotor de turbine
DE102010003991A1 (de) 2010-01-04 2011-07-07 TechTor GmbH, 90522 Flügel für eine Strömungskraftmaschine und Strömungskraftmaschine
DE102010003993A1 (de) 2010-01-04 2011-07-07 TechTor GmbH, 90522 Strömungskraftmaschine und Verfahren zur Herstellung eines Flügels
DE102010003994A1 (de) 2010-01-04 2011-07-07 TechTor GmbH, 90522 Flügel für eine Strömungskraftmaschine und Verfahren zur Drehzahlregulierung
DE102010003992A1 (de) 2010-01-04 2011-07-07 TechTor GmbH, 90522 Flügel für eine Strömungskraftmaschine
DE10344674B4 (de) * 2003-03-14 2017-02-02 Carsten Dethloff Strömungskraftmaschine/Strömungserzeugungsma- schine
WO2018080699A1 (fr) * 2016-10-27 2018-05-03 Ge Aviation System Llc Ensemble hélice
DE102020131271A1 (de) 2020-11-25 2022-05-25 Daniela Neldner Wasserkraftturbine
DE102022110984A1 (de) 2022-05-04 2022-06-30 Otto Molerus Windkraftanlage

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FR2424470A1 (fr) * 1978-04-26 1979-11-23 Amf Inc Articles manufactures presentant des dimensions exterieures non uniformes ainsi que des surfaces incurvees, et procede de fabrication
US4260332A (en) * 1979-03-22 1981-04-07 Structural Composite Industries, Inc. Composite spar structure having integral fitting for rotational hub mounting
DE3617186A1 (de) * 1986-05-22 1987-12-10 Alfred Frohnert Kegelfoermige windkraftanlage mit hohlfluegeln
US4728263A (en) * 1986-08-25 1988-03-01 Basso Robert J Wind turbine blade construction
FR2609506A1 (fr) * 1987-01-08 1988-07-15 Lepoix Louis Turbine multi-usage
DE3919157A1 (de) * 1988-06-11 1989-12-21 Guenter Zillner Windkraftmaschine
EP0486765A1 (fr) * 1990-11-22 1992-05-27 Franz Mroz Eolienne
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US5405246A (en) * 1992-03-19 1995-04-11 Goldberg; Steven B. Vertical-axis wind turbine with a twisted blade configuration
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Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10344674B4 (de) * 2003-03-14 2017-02-02 Carsten Dethloff Strömungskraftmaschine/Strömungserzeugungsma- schine
DE10342113A1 (de) * 2003-09-10 2005-04-28 Fritz Kadletz Windkraftmaschine
DE10342113B4 (de) * 2003-09-10 2009-08-20 Fritz Kadletz Windkraftmaschine
WO2005026536A1 (fr) * 2003-09-10 2005-03-24 Fritz Kadletz Turbomachine
EP2028102A4 (fr) * 2006-03-28 2013-07-17 Zakrytoe Aktzionernoe Obshcestvo Aviastroitel Naya Korporatziya Rusich Hélice de shpadi (et variantes) et développante de ces pales
EP2028102A1 (fr) * 2006-03-28 2009-02-25 Zakrytoe Aktzionernoe Obshcestvo "Aviastroitel' Naya Korporatziya 'Rusich' Hélice de shpadi (et variantes) et développante de ces pales
WO2009016372A2 (fr) * 2007-07-30 2009-02-05 Subsea Energy (Scotland) Limited Appareil de génération d'énergie éolienne
WO2009016372A3 (fr) * 2007-07-30 2009-07-30 Subsea Energy Scotland Ltd Appareil de génération d'énergie éolienne
US8690541B2 (en) 2008-08-27 2014-04-08 Bri Toinne Teoranta Turbine and a rotor for a turbine
AU2009286346B2 (en) * 2008-08-27 2014-08-07 Bri Toinne Teoranta A turbine and a rotor for a turbine
WO2010023648A3 (fr) * 2008-08-27 2010-08-12 Bernard Mcguire Turbine et rotor de turbine
DE102010003994A1 (de) 2010-01-04 2011-07-07 TechTor GmbH, 90522 Flügel für eine Strömungskraftmaschine und Verfahren zur Drehzahlregulierung
DE102010003992A1 (de) 2010-01-04 2011-07-07 TechTor GmbH, 90522 Flügel für eine Strömungskraftmaschine
DE102010003993A1 (de) 2010-01-04 2011-07-07 TechTor GmbH, 90522 Strömungskraftmaschine und Verfahren zur Herstellung eines Flügels
DE102010003991A1 (de) 2010-01-04 2011-07-07 TechTor GmbH, 90522 Flügel für eine Strömungskraftmaschine und Strömungskraftmaschine
WO2018080699A1 (fr) * 2016-10-27 2018-05-03 Ge Aviation System Llc Ensemble hélice
DE102020131271A1 (de) 2020-11-25 2022-05-25 Daniela Neldner Wasserkraftturbine
DE102022110984A1 (de) 2022-05-04 2022-06-30 Otto Molerus Windkraftanlage
DE102022110984B4 (de) 2022-05-04 2023-03-23 Otto Molerus Windkraftanlage

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