DE3222007A1 - Wind energy plant with a wheel rotor and horizontal axis - Google Patents

Abstract

Wind energy plant with a wheel rotor and horizontal axis and with more than two vanes, the wheel consisting of a radially clamped ring and the vane circular diameter being greater than the wheel diameter and the centre of gravity of the aerodynamic force of the vanes lying outside the wheel diameter, the vanes being braced and mounted, capable of rotating individually about their longitudinal axis, and the angle of vane pitch being controlled automatically by the aerodynamic effect, and the power transmission being performed directly from the wheel ring by friction force closure, characterised by the following features: a) the wheel ring is constructed as a bearing track ring (40) with an outer cylindrical bearing surface, the vanes are arranged on the bearing track ring with an axial spacing on the lee side, and provision is made as means for mounting the rotor of an axial thrust bearing (71) only on the luff-side pole of the central rotor hub (10) and a roller drive (20, 21) which bears only radially and has cylindrical guiding rollers on the lower circular segment of the bearing track ring within an angular range of approx. 90 DEG , and the azimuth bearing (81) is arranged at the level of the roller drive (20, 21), b) provided in the circular segment of a roller drive as means for tapping power from the bearing surface of the bearing track ring (40) is a wrap-around belt mechanism which consists of an endless drive belt (210) in whose wrapping track at least two guiding rollers (214), an output roller (21) and a deflecting roller (213) are included, a friction force closure between the bearing track ring and drive belt being provided in such a way that one strand of the wrapping track is arranged between the bearing track ring and the guiding rollers included. <IMAGE>

Description

■ H β *

Erich thousand 7913 send

Designation: Wind energy system with wheel rotor and horizontal axis.

State of the art.

When converting wind energy into usable mechanical or electrical energy, significant technical problems arise due to the low specific energy density of the natural wind. In order to obtain practically useful performance values, must large flow cross-sections are detected, which inevitably results in large for the aerodynamically effective parts relative to the performance Dimensions result. .

On the basis of a given construction method and the same design data (wind speed, high speed, coefficient of performance) as well as the same Component structure can be seen with an enlargement ratio "i" et * derive the following relationship:

The rotor speed decreases in the ratio l / i; the performance grows

2
in the ratio i; for a certain wing cross-section in the area of the wing root, the bending moment increases from the air force im

3 - k

Ratio i, the bending moment from the wing's own mass in Ratio i (the latter periodically changing!), Where the section modulus at this point in relation to i, i.e. the stress on the root of the wing from the wing's own mass increases with the same structure proportional to the linear magnification.

At a given speed of the driven machine (generator, the gear ratio must also be increased in the ratio "i"; however, there are limits to this on the part of gear technology) can be enlarged at will.

Through extensive optimization on the aerodynamic side and with ' the material utilization are according to more recent project designs Blade circle diameter of 100 m with approx. 3MW power can be realized The last known increase in rotor performance is indicated by a project that has a single-blade rotor with over l'tOm provides wing circle diameter at approx. 5MW power. COPY

"3222UÜV

From the pictorial representation of a single-blade rotor system arises easily the impression that this concept is because of the simple appearance technically easy to control and should be particularly cheap to manufacture. Apart from the fact that single-bladed propellers and single-blade rotors for helicopters already belong to the state of the art, the investigation of the functional and Stress conditions but no particularly distinctive advantages. In the project descriptions, the related Disadvantages not highlighted, e.g .:

Extreme high-speed numbers with top sheet speeds of up to 130m / s places high demands on profile and surface quality; Weather-related erosive surface damage with a drop in performance as a result; Danger to birds! Performance value is approx. 25% worse than three-blade rotor; most precise blade setting

with a corresponding standard effort is a prerequisite; periodic speed fluctuation up to - 10 $ ί (during one revolution) requires' special generator; one blade must transfer the entire aerodynamic load to the rotor hub, which is why the supporting structure ^; door must be designed accordingly more complex; very unfavorable I start-up behavior (status report wind energy I980).

These adverse factors are not externally visible, increase but to a considerable extent the plant costs. Because of the disadvantages mentioned, the single-blade rotor cannot be considered the generally cheapest Solution for the use of wind energy are considered. ■

Cantilever blades are usually used for high-speed rotors. This is where the critical load conditions occur at the hub connection. As a result of the necessary concentration of material in connection with unavoidable power flow branches and diversions this wing area is most at risk of breakage, even with the most complex processing. To relieve the bending moment To reach the wing root and rotor hub, the rotor blades are also individually by means of so-called flapping joints or in the form of a pendulum hub (only possible with single or two-blade rotor). Through this the wings get an evasive mobility in axial! {ichtun.tr (= Wind direction). By coupling the sash to a fixed point. the rotor shaft can be a simultaneous Blade rotation (= change in the angle of attack) has the effect of wr? Rrl «: n.

BAD CHiSII! Al

- ¹ - copy

In DE-05 2715 5O ^ an optimization of this principle is proposed with the aim of achieving the largest possible ratio of angle of attack / flapping angle. Such wing suspensions however, they are not new in principle; they have already been proposed and used many times for helicopter rotors, regardless of this, however, those provided in the above-mentioned DE-OS are Means according to the invention, particularly for large designs problematic. In addition, the desired effect is achieved with both this and other similar constructions Air blast (gust) relief not achieved for the following reason:

As a result of the articulation of the wing in the area of the hub, the single wing achieves the maximum value possible for a given mass Mass moment of inertia Flapping or pendulum joint; in the case of a pendulum hub and a single-blade rotor with a counterweight, this is The mass moment of inertia is then about twice as large. From this mass inertia results in a time delay (phase shift between air force and sash adjustment. The desired Rotary adjustment, which can only arise from "force χ distance", only becomes effective when the structure is affected by the impact of air blasts is already claimed.

The constructions of single- and double-bladed rotors intended for large-scale systems reach such unfavorable dimensions in the wing root and hub area because of the unavoidable concentration of forces (e.g. wall thickness, bearing diameter) that from this because of the necessary Custom-made production is a high cost factor relative to wind power.

There are also known constructions where the wing struts to avoid unfavorable stress nodes on the hub connection are.

For slow runners, it is common to attach the wings to a wheel-like one To fasten frame or polygonal frame, which is braced radially and axially with the rotor shaft and the axial thrust and the torque transfers from the wings to the rotor shafts. There are in de Usually designs for smaller powers, where the rotor weight / power ratio is still relatively favorable and therefore the constructive task of rotor bearing, wing fastening, ver aspiration and truss nodes are still easily detachable; however, no satisfactory solutions can be found, e.g. for the flights control and for the speed ratio. In any case, these systems cannot be used for high performance.

3222U07

Other suggestions for solving the transmission problem have also become known:

There are wind turbines, especially low speed runners, where the rotor blades are arranged within a conically tensioned ring and where this ring also serves as a belt pulley (bicycle type). The disadvantage of this design is that a very long; Drive belt is required and therefore a practicable application ' only makes sense for small services. The exploitation of the driving

i belt is unfavorable and the rotor bearing is affected by the ι

Belt tension additionally burdened. i

The proposal is also similar in terms of the type of power transmission according to DE-OS 2,817,483 to be considered. !

After the earlier proposal DRP 632 3LA the performance \ transfer takes place by a rotor wheel to one or more friction wheels-related gear proposals is also available for vertical axis rotors, for example, to DE-OS 2,758,180. 'j

Wind energy plants in the design as so-called "Segelwacen" [ are based on the principle of vertical axis rotors with friction gear. 1 Criticism of these proposals: Elaborate, often constructive j unrealizable wheel or track constructions that can be ' Bare speed ratio is insufficient, with vertical axis systems only wind currents close to the ground can be used connected ι with unfavorable performance parameters.

The invention is based on the following object: For wind energy systems, preferably for large systems, with horizontaleijbzw. an approximately horizontal rotor axis, especially for high-speed runners with two to five blades, is a new rotor system to develop, with which a more favorable in terms of the material stress, but above all better controllable force dissipation to the working machine and the tower can be reached by rope. In the task This includes the requirement for a substantial reduction in the aerodynamically generated shock and vibration loads for the entire system. Is linked to the task Ultimately, the demand for an economically justifiable system expenditure relative to the wind power.

The solution to the problem emerges from the claims.

-13-COPY

Description using the example of a four-blade rotor.

The graphic representations to which the description is based relate to:

Fig. 1 (a, b): Overall views.

Fig. 2 (a-d): Belt drive.

Fig. 3 (a-d): rollers.

Fig. K (ah): Race ring.

Fig. 5 (a-g): Push console.

Fig. 6 (a-e): Wing control.

Fig. 7 (a-d): rotor structure.

Fig. 8 (): Tower head.

Fig. 9 (a, b): Protective jacket.

Fig.la, Ib : General views from the side and from the front (against the wind). Running ring ^ O with the radially braced ring spokes k

the four wings each with a wing strut 55 and a thrust bracket 50 and the rotor hub 10 together form a stat: a certain framework system for absorbing and diverting the air force and for supporting the rotor weight. Jec wing with wing strut 33 is a three-hinged frame independent of the running ring ho , which the related. Rotor axial Luftkraftkompc component takes up. Within this timber system of Laufrinj has to fix the function of the wings in the Urafangsrichtung and c in the peripheral direction acting air force components aufzunehmer The vertical rotor load is k over the running surface of the bearing ring from the roller drive 20, taken 21st Since this encloses the raceway along an angular sector of about 90, the transverse stabilization of the rotor is effected here at the same time. The aerodynamic axial thrust is transmitted directly to the axial thrust bearing 71 via the wing struts 55. This is part of the rotor frame 70, in which the roller carriage 20, 21 is also integrated. The rotor structure 70 is releasably connected on a three-point base with Turr gondola 80, which is rotatably mounted in the azimuth bearing 8l about the vertical tower axis on the tower.

Fig. 2a: Force diagram of the radial bearing pressures on the roller bearing, where F _T = driving force on the race; F _ROQ and ^F R21 ⁼ result c

Roller pressure forces; C ( _R2Q ^and ^ j ^ l ⁼ collet pressure angle (here

in symmetrical design); G = weight of the rotor weight supported on the rollers; P = the taken from the race «power = ^F _T * ^v _u ·,

The maximum value for F is reached when F ₀ (tank pressure on the outlet side) = 0; this corresponds to the maximum possible transferable power. Limit state: max. F = G χ S / rt <X% pf !

max.F _R = G _R χ _{COSOC R9f} j

Required coefficient of friction: y ^ o ~ ^F t ^ ^F R

A bearing pressure must always be applied to the rotor discharge side (roller drive 20)

be present so that the transverse stabilization of the rotor is guaranteed is. The discharge side is relieved when the service is withdrawn; l therefore the number of rollers can be smaller here. , j pressure angle CS ^ / T, and Cf ^ Ow can also be designed asymmetrically.

Fig. 2b, 2c , 2d show the scheme of the belt drive

This is only provided on the rotor run-up side. This includes:, at least two rollers 21 ^ (practically three to six), output roller 211 with rocker arm 215 and support roller 212; Deflection roller 213,;

Stretching or tensioning rollers 216, if necessary guide rollers 217i j drive belt (drive belt) 210. The size relationship between the roller diameter and the curvature of the race 40 is not shown to scale. The wrap-around belt drive, which is used here, represents the reverse function of a caterpillar drive with the following features: The chassis (here rollers 2l4) is stationary and the roadway (here raceway kO) moves, whereby the work performance is transmitted from the roadway to the chassis. To distinguish it from the state of the art (DRP 632 J> lk) , it should be noted that the useful power from the raceway kO is not transferred to the rollers 214, but exclusively to the drive belt 210, the drive belt being activated by the roller pressure acting only radially to the race the running surface of the race is pressed.

The number of included rollers 2l4 depends on the power to be transmitted or the radial load capacity (Service life of tread and bearing) of the single roller. The diameter of the rollers 21 ^ and pulley 213 have no Influence on speed ratio. This only results from the

■ ' f COPY

Ratio of raceway diameter / output roller diameter. The arrangement shown in Figure 2b: output roller 211 downstream and with driving force reversal and has the advantage that with a direct Coupling of the driven roller and generator G by means of a cardan shaft, the generator can be arranged close to the tower, Fig.2c. The pulley 213 also has the function of a safety roll against sideways running out of the rotor. Pulley and Support rollers 212 are rigid (not resilient) attached to the drive carrier and have no contact under normal operating conditions with the race.

The combination: output roller 211 with support roller 212 produces a self-tensioning effect of the drive belt 210. For this purpose, force diagram according to FIG. 2d. From the angular position CXf of the rocker arm 215 to the tension side of the drive belt 210, as a result of the driving force F_, the contact force F ₂ results. F ^ xyCfc results in the initial pre-tensioning force for the wrapping function on the driven roller. In the empty drive belt run! no preload is required; the maximum permissible tensile load for the belt can be fully utilized as a driving force. The tensile load on the drive belt and the bearing load on the deflection roller, the driven roller and the support roller, are then only dependent on the performance. If the drive belt is multi-row, each belt has its own stretching roller.

For small systems or with low power loads is the version Sufficient without support roller 212.

For small to medium outputs (range 100 KW) are considered Treu tape commercially available flat belts can be used, but made endless (without lock). Steel belt is advantageous for high outputs (MW range). Coating of the steel strip with rubber-like tape as corrosion protection; or profiled friction lining glued on the outside. In addition, the running surface of the running ring is smooth and harder than dex Drift belt covering.

The following also apply to the embodiment shown in FIG Variations possible:

a) output roller 211 on the run-up side, has the advantage that deflection roller is dispensable. Disadvantage: generator weight results in great; Weight moment in relation to the tower.

b) As a), but generator arrangement close to the tower, plus a second belt drive or bevel gearbox with cardan shaft for generators

i6

c) Version for high performance: two or more belt drives according to Figure 2b are arranged one behind the other on the circumference of the race, the output rollers being coupled to only one generator by means of bevel gears and cardan shafts or by means of belt drives are. * \

The large space requirement of the belt drive - generally cited as a disadvantage of belt drives - is not a disadvantage here Appearance, because the space (= center distance) is given due to the design and because of the rotor support an extended base is required anyway.

Fig. 3 (ad) - Structural design for roller 2lA to roller drive 20, 21 (Fig.la; Ib), or to the belt drive (Fig.2a-2c). The following conditions are decisive for this: a) The running surface of the bearing ring kO can no longer be machined after its final assembly. Run-out errors, misalignments and unevenness in the order of magnitude 0.001 * Rxng diameter must be expected, b) The inner circumferential circle on the rollers will also show radial deviations from the exact circular path. In order to guarantee a perfect running characterxstxk special constructive measures have to be introduced for the roller bearings and suspension. An embodiment according to the invention according to Fig.3a includes: a pendulum hub with bearing housing 310, pendulum joint "$ 11, the joint axis being oriented tangentially to the raceway, cup-shaped hub disk 312 with bearing pin 3131 on it the bearing elements (roller bearings) 31 ^ _t preferably in a symmetrical arrangement and hermetically sealed on the outside, centered and releasably attached to the hub disk, the roller body 315 in the form of a hollow cylinder with conical roller rims 3l6. The center of the bearing 31 ^ and the center of the pendulum joint 3 ¹ I lie in the line of action of the outer radial roller load! Solid rubber or hollow profile rings, glued on or clamped on by means of clamping rings; for optimal effect, many small-volume high-pressure pneumatic tires, with a central compressed air supply guided through the hub, as is already used in commercial vehicles. The roller suspension device according to FIG onsole 51ö, firmly integrated in the torsion-resistant running gear carrier, fork-shaped roller axle 3 ² O with pivot joint 521 in the pipe bracket 3l8, spring element 322 and adjustment device. c 5-3

-17- QOPfI

The rollers can be adjusted to an exact circular path by means of the adjusting device. In order to achieve an even roll Imlantun ^ to be obtained within a set of rollers (drive), can instead, but also in addition, be provided on the adjustment device ed load compensation, either mechanically in Foi by balancing rods or hydraulically. Spring element, adjusting device and possible load compensation are arranged on the windward side of the drive carrier and covered with protective hood 324. 3b shows the radial view of the roller axis 320 with a pendulum joint 311 and bearing housing 310.

3c shows an alternative design to the roller axle, in the form of a swing axle 325 with a pendulum joint 311 »axle joint 327 and axle strut 328. This axle system is only attached to the leeward side of the running gear carrier. The axle strut 3 ² B is supported on the outer edge of the carriage carrier with spring elements 329 and adjusting device 330; an axle damper or hydraulic load compensation can also be added here. Fig.3d shows <radial view of Fig.3c. Both fork axle 320 and Schwii axle 325 can be made so that they are self-resilient ui

Camp.

The storage of deflection roller and support roller can be similar to Fig.3a be carried out on a bracket, but with a rigid hub (without pendulum joint) »Bracket possibly braced for pulley. Since the Deflection pulley is not yet loaded at start-up, a version with a plain bearing can be advantageous here.

Fig.4 (ah) illustrates the structure of the race 4o (Fig.l) according to the invention. The raceway is one of the most complex, but also one of the most important assemblies within the rotor system. Eijerfü several functions: support frame for the rotor blades, gear drive wheel, rotor bearing. A training with regard to producibility at all, absolute operational reliability with optimal utilization of materials and cost-effective production is a mandatory prerequisite for the feasibility of the invention.

In Fig.4a the system of the raceway structure is on a ring section shown. The race is made of the same ring sections

_o .:. .:. '· .. · ". · · - ^: - 3222UU7 18

composed, which are coupled by means of the butt joints 4 11 free of play. The stabilization to the circular ring cause the radial spokes 412, with a spoke above each butt joint connected. Each spoke 4l2 is connected to two ring sections via symmetrically spread spoke tabs 413. The system is statically determined. The tension of the spokes creates a circumferential compressive stress in the ring, which stabilizes the ring. The introduction of the spoke force via the spoke lugs results in an additional one in the area of the ring joint Compressive preload. The resulting tangential compressive prestress F results in:

with F as spoke tension (Fig. 4a).

Fig. 4b (developed tangentially) and Fig. 4c (radial view, outside) show a ring joint enlarged in detail. The raceway has a triangular profile and the essential parts in terms of function are: Running track belts 4l5, roof belt 4l6, joint diagonals 4l7, butt plate 4 with bearing shells 420 and centering bolts or centering balls 421, as butt joints 4ll, each in a tangential continuation of the force flow to the running belts; the bearing shells 420 are only one-sided pressure loaded. To articulate the spoke plates 413 are in the raceway radial thrust webs 422 are provided, which are connected to the cleat. The ring sections are only tightened by the spoke tension held together positively, there are no additional ones Screw or weld connections required. The spoke bias F must be so great that under all external operation under load, a compressive stress is always maintained at the ring joint.

ι The line "S" in Fig.4a denotes the replacement grid system in the ring. With the selection of the spreading angle OC / the spoke lugs, the position of the replacement grid system with respect to the raceway can be determined in such a way that the bending moments within a ring section are reduced to a minimum value. It is planned to manufacture the spokes in fixed lengths (from steel cable or steel rods) and to tension them on the rotor hub using an eccentric or cam lever 4p0. The spoke brackets are made up of thin slats. Each ring gap is covered with a weatherproof (possibly flexible jacket 423 The spokes' »12 can / Ii in the · nm ·· -. Dvnamisch provided effective cladding, we

BATH ORIGINAL.

.1. Λ. "··. ¹¹ · - ' " - * · ^: "322200 ^!

Examples of door raceway profiles:

Fig. 4d: Triangular tile girder with tubular belts (steel), walkway gurte 4 15, Üachgurt 4l6, diagonal brace 427, 428, can also be made from made of corrugated sheet metal; Raceway plate Λ30 is independent of the truss structure, as a sandwich plate or fiber composite pate shear webs 422 (connection of the spoke brackets indicated), wings coupling 431, canopy (GRP) 432.

Fig. 4e: Running track belts 415, roof belt 4l6 as bent or rolled profiles, Shear walls 433, 434 made of perforated sheet metal, construction 1 suitable for automatic welding or riveting processes; Edge zones of the belt profiles are largely undisturbed. Raceway plate 430 is regardless of the support structure.

Fig.4f and 4g: alternatives to Fig.4e. Integral construction: Belts 4l5 and 4l6 as steel profile, but push walls 435 made of Fas composite material (fiber course diagonal), raceway plate 430 is integrated into the carrier structure (with diagonal fiber layers). Fig. 4h: Proposal for a wooden raceway.

For small systems with a blade diameter of approx. Io - 15 π The raceway is made in one piece from bent flat steel or in plywood with a rectangular or trapezoidal cross-section will. For medium-sized systems, raceway with solid wall triangular profile or plywood, but composed of ring sections.

The ratio: race-j £ / wing circle- $ i is influenced Wing stress, effort for wing; aerodynamic disturbance of the wings - loss of power; Gear ratio rotor / Output roller; Costs for the rotor itself. Favorable order of magnitude depending on requirements:

Race ring - ** / vane circle-ji = 0.35 to 0

Fig.5 (ag) shows the execution of the push bracket 50. This is the connecting link between the wing, wing strut and Lau ring. The functions: a) Radial decoupling of the raceway and wing, to compensate for the elastic deformations that occur periodically in particular on the raceway during a revolution; b) axial spacer bridge between the raceway and the wing to allow angular rotation of approx. 100 and to reduce aerodynamic interference from the raceway; c) Connection bridge for the wing strut, which with regard to the wing rotation (b)

COPV

* ...; ο c L c <j u /

must be offset to the rear with respect to the pivot bearing; d) Transfer of forces directly on the wing takes place with small cross-sections, so that flow disturbances on the wing are limited to a minimum will; e) The pusher bracket is the structural element with the most critical stress, requires a clear overview of the force distribution. Schematic division according to Fig. 5a (view against the direction of rotation) and FIG. 5b (view in the longitudinal axis of the wing against the rotor hub). Strut pivot bearing "A" is divided according to the load effect into bearing "A", which only contains force components in the tangential plane, and bearing "A", which has force components in the direction of the wing longitudinal axis and can accommodate in the tangential plane. Push plate 501, strut pull rod 510 and push rod 515 form the push bracket. Bearings "A" and "A" with compression rod 515 (= pivot bearing shaft) are half

3C Z-

sunk into storage recess 570 built into the underside of the wing. Articulating joint 505 is articulated coupling point of wing strut ^550; Thrust plate 501 and tension rod 510 and sits in the plane of the thrust plate within a circular recess 502. The strut force component acting in the wing longitudinal axis, transferred to wing j in bearing "A", is supported on the rotor hub in hub pivot bearing "B" is centered on the spokes 412 in the raceway kO. Wing couplings * t31 are detachable connecting joints to the push console. I Fig.5d shows the design of the strut pivot bearing "A" with the ■

x 1

Member node. Bearing housing 520, screw connection segments 521, only ^: radial bearing element 522, bearing journal 517 = part of the; Compression rod 515t journal cavity with ball socket 523, tension rod head , 531 with split clamping ring 512, bearing cover 524 with adjusting screw 525, shaft seal 526 and stuffing seal 527. Fig.5e shows the design of the strut pivot bearing "A" with node

point push plate 501 and pressure rod 515; Bearing housing 530, screw segments 521, bearing elements 531 for axial and radial loading (e.g. angular contact ball bearings or axial spherical roller bearings, or axial roller bearings + two radial roller bearings); Thrust shaft journal 532, thrust washer 533, shaft seal 53 ^ and support frame 535. Fig.5f shows the design of the strut flexion joint 505 = coupling point for the wing strut 550. In the thrust plate 501 centering ring 503 with spherical bore; Zugs tab-Gelenkau.ee 513 is in The centering ring can be pivoted on all sides with a small axial play centered. The wing strut is connected by means of strut struts 551 within of the centering ring 503.

8.2 1-

View of the flexion joint perpendicular to the flexion plane Further developments for the push bracket: All joint parts as well as d: highly stressed rod elements are with a weatherproof umman lung 5 ^ 0 provided; Tension rod rait joint eye from one part, tension rod head and clamping ring 512 with threaded connection; Tension rod composed of a hollow shaft, joint eye and ball head and Tensioning screw clamped; Flexural elasticity of the thrust plate 501 perpendicular to the plane of the plate is achieved by making the plate Fiber composite material or is made from plate lamellas. The flexion joint can also be fixed using a handlebar.

The thrust bracket according to the invention allows limited cardanic mobility within the node wing-race ring-wing strut. It does not look like a rigid triple frame.

Fig.5c shows the view of the underside of the wing with the bearing recess 570. If the wing is made of a fiber composite shell construction is, the continuous fibers, rovings or fiber strands 571 are guided in a flat curvature around the storage trough, so that the flow of force is not interrupted and there is no loss of strength at the point that is most stressed for the wing: Optimal Material utilization!

Fig. 6 (ae) illustrates the principle of the statically determined three-point support with the angle of attack control of a wing. Fig. 6a ί View of the wing nose (against the direction of rotation), Fig. 6b: View of the upper side of the wing (against the wind). S =

a · c ·

Center of gravity of the total air force attacking the wing; F = acting as a point load replaces air force; a.c. = Air force

^a ® ti ti

center line along the wing; A = strut pivot bearing on the running belt: (Sliding bracket A, A); "B" = pivot bearing on the rotor hub, axial

3C Z

and radially supporting, gimbal swiveling through a small angle of approx. -3; Axis "AB" = axis of rotation of the wing, has a lead angle ^ P- r compared to line a. / AB, whereby an effective aer <dynamic self-control is achieved. The axis of rotation "AB" came to be regarded as a very / steeply inclined wing pendulum axis. The size ^: e of the supporting force in the bearing "C" results from the formula Fig.6c. It is not a prerequisite that the axis of rotation "AB" the

.: ο c ι. /. uu /

a.c. -Line intersects exactly at bearing point "A". The interpretation is but to be met in such a way that the supporting force F is a compressive force under all conceivable wind loads on the wing,

so that the stability of the wing is guaranteed.

6d shows the scheme of the adjustment device for a wing.

The aerodynamically generated force F is supported in the actuator "C" on the control linkage, whereby: flange 610 atn wing with crank arm 6ll and actuator "C", control rod 612, spring element 6l3, servomotor 6 Ik common for all wings, controller with control valve 615 , Throttle 6l6 (if servomotor hydraulic or pneumatic).

With the wind speed and, for example, the operating voltage or frequency as a setpoint generator, a nominal pitch angle is set collectively on all blades by means of the servomotor 61. The travel range s _o covers the entire pitch angle range. The air force acting on the wing is elastically supported by the spring element 613. In the case of air force fluctuations, which result from irregularities in the wind, the wing part, which lies outside the race, can give way in the direction of impact (pendulum effect), which, due to the support geometry, simultaneously results in a rotation of the wing "from the wind" (reduction of the angle of attack).

A ratio of rotation angle / pendulum angle of approx. 20/1 and greater is possible. ·

The following can be used as servomotor 6l4: Ε-motor with gear and Screw spindle; Hydraulic or pneumatic cylinders. The latter result the advantage that when the fluid pressure is removed, the wings automatically Turn in idle position or O-running position without assistance by an external energy (optimal storm protection!). This automatic shutdown is also effective in the event of a fault or Failure in the control fluid supply system. The elastic travel s> covers only a small part of the total angle of attack range, around 20 to 30 are sufficient for controlling the strongest gusts of wind.

The following can be used as spring element 613: steel or rubber springs with very flat identification in the nominal load range; A gas or low pressure air spring with a diaphragm piston would be better. With the last System can spring element 613 and servomotor 6I ^ in one unit are carried out, the spring effect resulting from the compressibility of the air. Advantage: Fluidum is clean undtetets

-25-

COPY ^Ί

available. Disadvantage: large installation volume; is negligible here, because there is sufficient installation space available on or in the rotor hub. Advantage of this rotor system over the technical status

The low-pressure air spring as the adjustment and control is in effect comparable to that used in commercial vehicles air suspension. :

The drive of the fluid pump is expediently provided directly by the driven roller 211 of the belt drive.

Fig.öe shows an embodiment with a so-called hydro-pneumatic Spring as an adjusting and spring element. Same principle as with vehicle springs Common: hydraulic cylinder 620, diaphragm 621, gas cushion 622.

Important for the function of the self-control: The self-control is all the more effective, i.e. the dynamic wing loading is ura & o smaller, the smaller the moment of inertia of the wing with respect to. the rotary pendulum axis is "AB". With the means of the invention kanr this condition can be met to a far greater extent compared to the state of the art, because this is the center of gravity of the wing near the pivot bearing "A" is where the axial pendulum motion is approx.

Due to the design, the center of gravity of the wing is not in the axis "AWAY". In order to avoid periodic self-control by the wing mass, the wing should be regarding. Axis "AB" statically balanced be; achievable through a) slight curvature of the wing's longitudinal axis against the wind direction, b) through a counterweight on the root flange 610

The automatic control function of the blades (= turning out of the wind the single wing) when the servomotor 61A has no reaction force to F is only guaranteed if the blades are aligned radially, i.e. in the direction of action of the centrifugal force (V-angle = 0). It is advantageous ■ the wings with a small negative V-position set up (2 to 3 against the wind). The rotor can only be brought to operating speed when the servomotor builds up a supporting force. Advantage compared to the technical standard!

Fig. 7 (ad) shows the system of the rotor structure. 7a: side view (perpendicular to the wind); Fig.7b: View against the wind. Rotor axis Ml, middle race Mk.

The central A-iiahmen consists of a base plate 710, two rigid side bars 711, 712, a thrust bearing housing 713 and an A-frame strut 714. Tilt shaft 715 is the base edge on Α-frame and at the same time forms the bearing shaft for supporting the rotor support structure to the nacelle frame 810. Drive beam 720 and 721, torsion Fachwerks- or plate girders are mounted on base ¹¹ J "on the side edges of the base plate 710 in The radial plane of the rotor can be pivoted, braced to the A-frame by means of drive struts 722 and 723. Fig. 7c shows the connection point of the drive strut on the drive carrier in such a way that the line of action of the strut is as close as possible to the center of the roller bearing M3; this reduces the torsional stress on the carrier reduced.

The rotor structure has an "H" and A frame strut over the bearing base 714 a statically determined three-point support on the nacelle frame. The articulation point 717 of the strut 7l4 on the gondola frame is equipped with a spring element and a vibration damper. Through this the rotor structure with rotor above the bearing base "H" can carry out luffing vibrations.

7d shows a further development of the supporting structure strut. On the gondola frame crank arm 730 with counterweight 731 is rotatably mounted. A-frame strut 714 is hinged to the short lever arm of the crank arm. The illustration shows the counterweight position at approximately nominal load. In addition to an effective decoupling of the oscillating masses Another advantage is that the counterweight overhang creates a relief torque for the azimuth bearing and tower, its Size changes with the rotor thrust load.

Fig.8 ι execution of the tower head with azimuth bearing, here only functional requirements are taken into account. Azimuth bearings as Trunnion bearing offers in connection with the rotor system according to the invention Advantages. Special feature: the nacelle with rotor support structure (Fig. 7) is mounted "hanging" on the tower head.

Gondola frame 810, gondola hood 820 with main plate 821, gondola strut 83O form a rigid framework system over which the spacious distributed air and mass forces are concentrated and supported on the tower on a relatively small basis. Tower head 84o has main bearing journals 841 inserted; this exists made of electrically insulating material (e.g. GRP) and carries the slip rings 842. The main bearing is made of radial roller bearing 84j

-OPY J

and thrust roller bearings 844 assembled. Bearing pin 845 with K bund, ball socket 822 in the main plate 821. It is also possible to design in the form that the main bearing pin 841 is screwed onto the tower head by means of a flange. The azimuth support bearing only bears radially and is arranged at the level of the Go: frame: the support bearing ring 846 is the radial bez main bearing on the tower adjustable, support bearing shells 847 (possibly with part Roller bearing cages), nacelle rotary drive 815. On the nacelle frame .810 tilting bearing shells 812 for tilting bearings, with cross-slide connection to the windward wall of the gondola hood 820. Further training on rotor structure and tower nacelle: a) Basi; Plate 7IO of the Α frame is equipped with a lifting device, which the raceway can be lifted off the roller drive, purpose: replacing the rollers individually or the drive belt Removal of a complete drive carrier without the rotor, al nommermierden must; b) for large systems, unc the drive carriers rigid or foldable or movable Maintenance platforms provided; c) the gondola frame is equipped with cranes or hoists, which are designed so that then the rotor structure complete with the raceway can be raised or lowered using a cable-stayed or inclined rail guide.

Installation suggestion: Rotor structure is zv sammengesetzt with raceway on the floor and completely (but without blades) pulled up; Lau is secured axially with auxiliary struts. The flight starts afterwards on the tower.

Fig. 9 (a, b) shows the construction of a protective jacket for the purpose of running: First and foremost, protection on the running track against the effects of the weather, in addition to the aerodynamically favorable running ring lining. The protective jacket consists of profiled shell sections 910 which are joined together like a chain in the circumferential direction. Stabilization in relation to the circular ring is carried out by means of jacket support rollers directly on the running ring. Reels 911 are housed in reel housings 912. The ends of the protective jacket are carriers 720, 721 attached to the drive. To stabilize the protective jacket in the axial direction, obliquely directed support rollers or struts to the thrust bearing 713 can be provided.

A suitable design of the protective jacket profile can be achieved
that the center of gravity of the air resistance of the race is in
Wind direction is behind the middle of the raceway, so that a direction-stabilizing moment, a kind of wind vane effect, is generated.

Technical progress.

In the description of the technical status it was pointed out which essential problems in the utilization of the
Wind energy occur:

a) Capture a large wind cross-section with as little as possible
Cost of materials j

b) Safe control of the air and mass forces that occur in the process; ·· .-- · ■ '|

c) Concentration of the mechanical energy gained over a large area; on a single machine (only one generator) in one! machine-technically practicable form, namely with high drive '

rotational speed; '

d) economically justifiable system costs. . ::

The means of this invention can solve these problems
will: ■,

l) Compared to the known constructions with braced or ^;

wheel-like rotor systems and with more than two blades is used with
the invention a decisive improvement in the aerodynamic
Area reached: The aerodynamically effective wing area is located
outside and inside the rotor ring (here the raceway), but will
not interrupted or weakened by this. Aerodynamic
Interference does not occur on the upper side of the wing, on the
They are reduced to a negligible value on the underside of the wing.

Significant progress is achieved through the within a
Single pendulum suspension used in the stripped wing system
Wing in connection with the aerodynamic self-steering.

-27-

j. , v'vr ' ¹ .. · »·· 322200

However, this can only produce the desired effect if the change in air force on the wing can bring about an immediate change in the steady state, so there must be an elastic force support. The wing suspension according to the invention offers the advantage that the Stii force in the elastic control linkage can be smaller than the air force acting on the wing. As a result of the bracing of the wing at approx. Kü% of the wing length, the bending moment area over the wing length is significantly smaller compared to the cantilever wing. Another great advantage for the stress on the wing structure is the straight, undisturbed course of the belt fibers at the point of the greatest bending moment. There are also no massive force flux concentrations and deflections like with a hub flange. The effort for the load-bearing wing structure is therefore much lower.

The moment of inertia of the braced wing with respect to its rotary pendulum axis is reduced to a fraction insofar as the wing mass is significantly smaller and the center of gravity is close to the rotary pendulum axis. This reduction in wing inertia is the prerequisite for effective aerodynamic self-control, so that dynamic air force loads on the wing itself and the other structure are largely reduced.

2) Substantially reduced wing mass, more favorable mass distribution and, quite decisively, those strongly shortened by the wing support Free lengths result in a more favorable natural oscillation behavior of the wing.

The extensive decoupling of the wing - rotor ring as well as the rotor structure - tower, in addition the damping effect of the rotor and supporting structure in connection with the aerodynamic self-control reduce the problems of vibration stress quite considerably, which ultimately also has a cost-reducing effect. Another advantage in relation to the vibration problem arises from the fact that - based on the same height of the rotor axis - the The center of gravity of the gondola and the machine is much lower and the free turret length is smaller.

3) The raceway and rollers have a dual function: They are rotor bearings and at the same time gear elements. The rollers only have a support function and do not transmit any power. As their diameter has no influence on the speed ratio, they can be optimized with regard to ROI efficiency and service life. The wrap-around belt drive is characterized in that the Rotor power reduced on a large-area basis by frictional engagement and can be concentrated on just one work wave. Speed ratios of the order of 1 / I50 in one stage can be carried out, which can be achieved with known systems, in particular with gear drives, is not feasible.

A decisive advantage of the belt transmission according to the invention is to be seen in the fact that the speed ratio is still at the ready installed system can be varied simply by changing the output roller diameter. It is possible in this way An optimal speed adjustment to the local operating conditions only after some operating experience without significant technical Make effort.

4) The additional effort for the race is compensated by that there are savings on the wings and that no gear (usually expensive custom-made) is required. Also can the race, since it can be assembled from many identical parts, can be produced extremely inexpensively.

5) With the proposed system of the rotor structure, the rotor bearing and assembly arrangement, unhindered access to all essential assemblies and components is possible from the outside. The control, maintenance and replacement of wear parts or entire wear assemblies is made significantly easier and offers the Precondition for the fact that such important system elements can be designed for a shorter service life, what the system costs reduced to a considerable extent.

6) The force distribution brought about by the system according to the invention on a large basis results in small support and connection forces, which are decidedly easier to control. The bearing elements required e.g. for wing and rotor bearings are around the Factor 0.1 smaller compared to the system with cantilevered leaves same length. More elements are needed, these

however, they are overall more cost-effective than a few large custom-made products.

It should be noted in this context that with small Components, i.e. small cross-sections, the material utilization cheaper, the possibility of error smaller and therefore the effort is significantly lower for the safety design.

7) With the rotor system according to the invention, wind energy plant can be built with three or more large-sized wings. In connection with the favorable mass distribution and with the additional Due to the mass of the race, such a great Uralauf uniformity can be achieved that special control devices for the generator - as inevitable for single and double-bladed high-speed runners are - can be saved.

In cooperation with the other described features of the invention prerequisites are offered which the construction of wind energy rotors feasible in the power range of 10 MW.

Considered publications:

DRP 632

DE-OS 2 715 584

DE-OS 2 758 I80

DE-OS 2,817,483

Book: Status report wind energy I98O

Book: Wind energy in theory and practice, p. 26; 27 (J.P. Molly, 1978, Verlag C.F. Müller, Karlsruhe)

COPY j

Claims (1)

Erich a thousand 7913 Send Description: Wind energy system with wheel rotor and horizontal axis. Patent claims: 1. Wind energy plant with wheel rotor and Horizonzalacb.se and with more than two wings, the wheel from a radially braced Ring and the wing circle diameter is larger than the wheel diameter and the center of gravity of the air force of the wing outside of the wheel diameter, with the wings strutted and single are attached rotatably about their longitudinal axis and the wing angle of attack is automatically controlled by the aerodynamic effect and where the power is transmitted directly from the wheel ring by frictional connection, characterized by the following features a) the wheel ring is designed as a raceway (4o) with an outer cylindrical Running surface formed, the blades are arranged with an axial spacing on the leeward side of the raceway and as a means for rotor mounting is an axial thrust bearing (71) only on the windward pole of the central rotor hub (1O) and a roller bearing only radially (20, 21) with cylindrical rollers on the lower circle segment: of the raceway provided within an angular range of approx. 90 and the azimuth bearing (8l) is arranged at the level of the roller drive (20, 21), b) a belt drive is provided in the circular section of a roller drive as a means for the power take-off from the running surface of the running ring (k0) , which consists of an endless drive belt (210) with at least two running rollers (21 ^), a driven roller (211) and a deflection roller (213) are included, a frictional connection between the race and the drive belt being provided in such a way that a strand of the looping path is arranged between the taking race and the enclosed rollers, c) to support the air force and the wing weight on the raceway (4o) a thrust bracket (50) is provided for each wing, which on the raceway has a connection base in the circumferential direction only for axial and tangential loading direction (with respect to the rotor axis) and on the wing a connection base in the direction of the Has the wing longitudinal axis for axial, tangential and radial loading direction and the wing strut (55) is connected on the one hand to this thrust bracket and on the other hand to the thrust bearing pole (71) of the rotor hub, d) a statically determined three-point bearing is provided on the rotor system for each wing, namely on the outside of the race the thrust bracket (pO) the strut pivot bearing (A) and inside on the rotor hub the hub pivot bearing (B) and that axially in the direction of the rotor axis '. Movable adjusting bearings (C), with regard to the wing the strut pivot bearing (A) is as close as possible to the ac line, the hub pivot bearing (B) with the distance r. behind the ac-line and the positioner (C) with the distance r in front of the ac-line, where Laeer (A) and bearing (B) have a common axis of rotation, which is offset by a small angle V ³ in the direction of rotor rotation leading against the wing a.c. line: e) as a basis for receiving the axial thrust bearing and the roller drive a rotor structure (70) is provided, which consists of a central A-frame and lateral drive girders and is in is statically closed and with which the rotor is mounted in the azimuth bearing on the tower. ' 2. Wind power plant according to claim 1, characterized in that the belt drive with respect to the rotor center on the Side is arranged on which the rotor raceway (4o) on Roller drive starts up. 3. Wind power plant according to claim 1 and 2, characterized in that the driven roller (211) of the belt drive is mounted on a rocker (215) and that a j ^ ecrnn 1 Hu Fi χ η for the driven roller on the outside of the Umschlin ^ ungsbahn S heating roller (212) is arranged, with a power supply from the output roller via a cardan shaft to a generator (G) being provided. COPY J k. Wind energy installation according to Claims 1 to 3 », characterized in that the number of rollers is greater on the upstream side (21) of the rotor than on the downstream side (20). 5. Wind energy plant according to claim 1 to Ί, characterized in that the rollers (2lA) individually on one Carrier system are cantilevered on the leeward side with roller axis parallel to the rotor axis, that the roller bearing is centered to A roller is arranged and a pendulum hub is provided for this purpose, so that the bearing housing (310) is suspended from a pendulum joint (3H). this hinge axis being aligned tangentially to the raceway and arranged above the bearing center point that the axle body (320), on which the roller is suspended, in connection with its support (322) has a spring property and dai an adjusting device (323) is provided, with which the rollers be adjusted to an exact circular path and track to the raceway can. 6. Wind power plant according to claim 1 to 5i characterized in that a tube bracket (518) is provided on the carrier system for each roller, the projection of which is in the dei extending cylindrical cavity of the roller, the axle body (320) formed as a fork-shaped pendulum axle and inside the pipe bracket is mounted and resiliently supported. 7. Wind energy plant according to claim 1 to 5 »alternative to claim 6, characterized in that the axle body for each roller is designed as a three-hinged frame (3 ² 5, 328) in the manner of an oscillating axis. 8. Wind energy plant according to claim 1 to 7 » characterized in that the rollers are designed as hollow cylinders are and a fully elastic, rubber-like tread (317) have. 9. Wind power plant according to claim 1 to 8, with a race, which is composed of ring sections and radial spokes i characterized in that joint joints (-'ill) are provided on the end faces of the ring sections to connect the ring sections a tangential bracing system is provided by such that compressive stress is present in the joint joints (^ 11) which is greater than the largest due to external operating forces caused tensile stress. 10. Wind energy plant according to claim 1 to 9, characterized in that in each case above the butt joint CtIl) of two ring sections (410) a radially aligned spoke (Ί12) is connected that to connect the spoke to both ring | Sections two spoke tabs (413) are provided that these j spoke tabs spread in the circumferential direction of the race; are at an angle of spread l80> ^ ^> ^> 120 and in each case am; Push bar (422) of the Hingsektion close to the center of gravity of the ring profile ι files are connected, that the butt joints are each Ha at the j career corner points of the ring profile and that all connections (spoke head tabs, tabs-push bar) are articulated by means of shear bolts . 11. Wind energy plant according to claim 1 to 10, ■ characterized in that as a means for tan.arential tension ' The radial tension of the spokes is used in the ring sections. 12. Wind energy plant according to claim 1 to 11, characterized in that the mounting base for the sliding bracket (50) of a wing each in the area of an annular joint (4ll) is provided. 13. Wind energy plant according to claim 1 to 12, characterized in that the raceway profile has the shape of a triangle, the base line of which lies radially on the outside and is provided for generating the ring raceway, that two raceway belts (Ίΐ5) ι a roof belt (il6 ^{) and push walls (z} l27, ^ 28) and push webs (^ 22) are provided and that the track plate (kjO) is designed as a composite plate or made of a fiber composite material. l4. Windenrgieanlage according to claim 1 to .. 13, wherein for support A thrust bracket is provided for the wing forces on the raceway, characterized by the following features, a) the push console comprises a push plate (501), a strut tie rod (510), a compression rod (515), two strut pivot bearings (A, A) and a strut bow.e; elenk (505), "copy b) the thrust plate (501) is shear and flexurally rigid in the tangential plane (with respect to the raceway) and is flexible and elastic perpendicular to it; aligned approximately under k5 to the direction of rotation c) the pressure rod (515) is aligned radially with respect to the rotor at the junction of the thrust plate (501) and the pressure rod is a at Bearing axis axially and radially bearing pressure pivot bearing A angec and at the junction of the compression rod (515) and the strut tension rod (5IC is a related Bearing axis only radially supporting thrust-pivot position arranged, with the position of the rod node! calibrated nal provided at the storage center point within the drawer A j d) the strut pull rod (510) is bent with respect to the rotor radius towards hir (against the direction of rotation), the strut-joint (505) is arranged in a recess (5C of the thrust plate) - although it is supported on all sides in the plane of the plate and can be displaced perpendicularly to it by a small amount, and The strut tie rod (510) is attached to this flexion joint radially outwards and the wing strut (550) is attached radially inwards against the rotor thrust bearing (71) 15. Wind energy plant according to claim 1 to Ik, characterized in that the strut pivot bearing (Ä, A) something 3C Z are installed sunk in the wing towards the middle of the bearing, for which purpose on the Flüj a bearing recess (570) adapted to the shape of the bearing housing is provided and the screw connection is within the wing profile contour takes place by means of the screw segments (521). 16. Wind energy plant according to claim 1 to 15, characterized in that the shaft journal (517) to the thrust pivot bearing (A) has a cavity with a spherical pressure socket (I and an inclined bore for this purpose, that the strut tension rod> is stored in this pressure socket by means of a clamping ring (512), the tension rod and clamping ring having a releasable positive connection. 17- wind power plant according to claims 1 to l6, characterized in that the strut tension rod (510) consists of a spherical head, Hollow shaft and joint eye is assembled and pressure braced by means of a clamping bolt. l8. Wind energy installation according to Claims 1 to 17 »characterized in that the wing strut (55) is aerodynamically has effective profile cladding, which around the strut axis is rotatable, a mechanical coupling with the adjustment system of the wing for the purpose of angle of attack control is provided. 19- wind power plant according to claim 1 to 18, with a aerodynamically automatic individual control of the wings, characterized by the following features, a) the adjusting bearing (C) is supported by the adjustment device on the rotor hub (10), b) the entire adjustment path - corresponding to a wing rotation from the smallest to the largest angle of attack - comprises a single adjustment path S ₁ , which is related to the air force acting on the individual _{wing, and a collective adjustment path s Q} which is with the collective servomotor and with a Control system is related, c) the adjusting device consists of a control rod for each wing (6l2), a suspension element (613) as a means for the elastic support of the wing force, and a non-elastic one Servomotor (61A), with the spring element and servomotor connected in series and the servomotors of all wings are connected to one another and to a common control device are. 20. Wind power plant according to claim 1 to 19 »wherein the raceway rotor is cantilevered on a rotor structure on the leeward side, characterized by the following features, a) the rotor structure comprises a Α-frame (710, 711, 712) and two drive carriers (720, 72l) with drive struts (722, 723) and A-frame strut (71A), b) the Α-frame is arranged centrally and symmetrically to the rotor circle and extends diagonally from the lower circumferential edge of the barrel ring COPY j up to the engine axle, it consists of two rigid side bars (ZU, 7I-) and base plate (710) and shows at its tip Housing (715) for the thrust bearing on, c) the drive carriers (720, 721) are each in the circumferential direction of the raceway on the Α-frame in the raceway plane pivotably arranged one on the base plate (710) for each drive carrier Bearing base (J) is provided and the drive struts (722, 723 are attached to the Α-frame, d) as a means for a detachable and downwind tiltable; The rotor structure is attached to the tower nacelle on the door side Edge of the base plate (710) a tilting shaft (715) vorgesc the associated tilting bearings (Ö12) are on the outside of the gondola frame (810) arranged leeward with respect to the azimuth axis and the A-Hahmenstrebc (71 ^ 0 is attached to the gondola frame, which is lengthened to the windward side. 21. Wind energy plant according to claim 1 to 20, characterized in that the connecting device between the A-frame strut (71 ^) and the gondola frame (8IO) is a suspension element and a damping element. 22. Wind energy plant according to claim 1 to 21, characterized in that a crank arm (7th is provided, on whose short lever arm the A-frame strut is hinged and on whose long lever arm a ballast weight (751 is attached. 23. Wind energy plant according to claim 1 to 22, characterized in that the tilting bearing of the rotor ¹ supporting structure and the existing relative movement on the connecting device between A-frame and gondola frame is seen as a means for actuating a ballast control device that a horizontally movable ballast weight is suspended from an extension of the gondola frame whose drive is connected to the ballast I control device. 2k. Windener.cie plant according to claim 1 to 23, wherein the Azitnutla.eer is designed as a journal bearing, characterized in that the tower head above the tower strut ring as part of the Azimuth pin is formed that a main bearing pin on the tower head (84o) (84l) is inserted or flanged, which consists of electrically insulating material, with at the top this main bearing journal a radial roller bearing (843) and a thrust roller bearing (844) is arranged and a free shaft of the main bearing journal is designed as a slip ring carrier (842), and a support bearing ring (846) being provided at the base of the azimuth pin. 25 wind energy installation according to claims 1 to 24, characterized in that the tower gondola consists essentially of the gondola frame (8IO) and the gondola hood (820) and the gondola strut (& 30) consists, wherein the nacelle cover has a main plate (821) with a spherical shell (822), and that the tower nacelle on the main bearing (843, 844) is mounted hanging on the azimuth pin, the support bearing shells (847) being provided on the gondola frame (8IO). 26. Wind energy plant according to claim 1 to 25, characterized in that to protect the ring running surface against Weather conditions a protective jacket (910) is provided, which is composed of individual profiled ring sections in a chain-like manner and in the circumferential direction on the drive carriers (720, 721) that is attached to the circular stabilization of the protective jacket Roller supports (912) are provided and that a strut for additional axial fixation of the protective jacket, against the thrust bearing (7I) is provided. j 27. Wind power plant according to claim 1 to 26, with a belt drive according to claim 1, 2 and 3 »characterized in that a roller sequence in the direction of rotation of the running ring: deflection roller (213), rollers (214) and driven roller (211) is provided. 28. Windenergio installation according to claim 1 to 26, as an alternative to Claim 27 »characterized in that in the direction of rotation of the running ring a roller sequence: output roller (211), rollers (2l4) and deflection roller (213) is provided and that between the output roller (211) and generator (G) a conversion gear and a cardan shaft / is arranged. Q