DE102019007452B3 - Bidirectional flow machine - Google Patents

Abstract

The invention relates to a bidirectional flow machine (1) which is designed either as a working machine or as a power machine (10, 11) and has a diffuser for a flow (F) that changes diametrically in direction. The diffuser of the turbomachine (1) acts either as a diffuser (14) or as a cone (15) and is supported by a wing staircase (2) with at least three levels of action (Q1-Qn) on an axis of rotation (x) and by a housing (12) formed for at least one electrical machine (13). The wing staircase (2) has an apex (S) and a plane of symmetry in the plane of action (Q2-Qn) of a middle ring wing (B), which middle ring wing (B) is preceded by at least one ring wing (A) in the direction of the flow (F) and at least one ring wing (C) continues to run. The ring blades (A, B, C) have convex suction sides and concave pressure sides and are connected to the electrical machine (13) by means of radial rotor blades (R) and overlap each other along their length (y) and with a radial gradient (z) in such a way that the ring wing (A) of the wing staircase (2) which precedes the middle ring wing (B) has a guide ring (20) and, together with the middle ring wing (B), an annular guide nozzle (21) for a resulting flow (c) of the middle ring wing (B) forms with a cone angle (51,52).

Description

The invention relates to a bidirectional flow machine which is designed either as a working machine or as a power machine and has a diffuser for a flow that changes diametrically in direction. The diffuser of the turbomachine acts either as a diffuser or a confuser and is formed by a wing staircase with at least three levels of action on an axis of rotation and by a housing for at least one electrical machine. The wing staircase has an apex and a plane of symmetry in the plane of action of a middle ring wing, which middle ring wing is preceded by at least one ring wing in the direction of the flow and at least one ring wing is following. The ring blades have convex suction sides and concave pressure sides and are connected to the electrical machine by means of radial rotor blades and overlap each other lengthways and with a radial slope in such a way that the ring blade of the wing staircase leading to the middle ring blade has a guide ring and together with the middle ring blade forms an annular guide nozzle with a cone angle for a resulting flow onto the central annular wing. In the case of the diffuser, the air flowing towards the staircase is with the divergent cone angle, the outer sides of the ring blades being designed as convex suction sides, while in the case of the cone the air flowing towards the wing stairs is with a convergent cone angle, the insides of the ring blades being designed as convex suction sides, so that In each case, in the planes of action, a lift force is generated from the resulting flow, which is inclined towards the flow and in the respective direction of rotation of the ring blades. A periodically and diametrically changing direction occurs as a natural tidal current on coasts, straits and estuaries, so that a preferred embodiment of the bidirectional flow machine relates to a power machine that is driven as a water turbine by the currents caused by ebb and flow. A preferred application for the prime mover relates to an air turbine that generates electrical energy from an oscillating water column at a so-called OWC (Oscillating Water Column) that is connected either to the mainland or to a floating body anchored in the water. A new type of application for an air-powered, bidirectionally effective engine relates to a hydraulic lifting mechanism that is driven by the excess headwater of a river and can be installed on existing or yet to be built transverse structures in the inland waterway network. An airtight housing of the two separate chambers of the hydraulic elevator enables the installation of jacketed air turbines in the airtight shell construction of the elevator, which are driven by a regularly changing overpressure and underpressure in the air chambers of the elevator. In a particularly preferred embodiment, the bidirectional turbomachine has a working machine. A bidirectionally effective fan can e.g. can be integrated into a building envelope construction and enables controlled room ventilation with an air intake and exhaust function. A larger bi-directional fan can be used to ventilate a tunnel. A particularly advantageous embodiment of the working machine relates to rudder propellers and, in particular, transverse thrusters for watercraft.

State of the art

On the occasion of a survey on the use of hydropower in Baden-Württemberg, 17,500 locations were validated. There are currently only 1,700 run-of-river power plants in operation, each with an output of 1000 kW or more. 400 locations have been closed, while 665 existing transverse structures in the state's water network are not in use. This hydropower potential determination for Baden-Württemberg, carried out by Büro am Fluss eV in Wendlingen am Neckar, clearly shows the further expansion of hydropower in connection with the energy transition. The operators of small hydropower plants always come into conflict with nature conservation when the migratory movements of the fish lead through the turbine channel without an alternative. So-called OWC power plants consist of a wave chamber open to the surf and an air chamber above the water level with an opening for pressure equalization. A surging wave raises the water level in the wave chamber and causes an overpressure in the air mass above and a current for pressure equalization. As the wave passes, the water level drops again and the air flow changes direction. In this way, a periodically changing direction of air flow at high speed is used to generate electrical energy with a power machine designed as an air turbine, which maintains its direction of rotation when the direction of flow changes. The so-called Wells turbine has a plurality of rotor blades arranged radially around an axis of rotation, each with a symmetrical wing profile. The disadvantage here is that the rotational speed increasing in the rotor circle from the inside to the outside cannot be taken into account when designing the rotor blade with a symmetrical blade profile, as is the case with a turbomachine with an asymmetrical blade profile. Therefore the efficiency of a Wells turbine is not optimal. Measures to improve the efficiency concern adaptive blade profiles, which react to the changed flow conditions with a reversible blade adjustment. Well-known rudder propellers and transverse thrusters are only optimally effective as thrusters in one direction. So-called controllable pitch propellers, with which a thrust reversal is made possible, are complex to manufacture and maintenance-intensive in operation. In 1889, R. Gaertner's publishing house in Berlin published a book entitled “The flight of birds as the basis of the art of flying”. Otto Lilienthal publishes test results on air resistance and lift of different wing profiles with a suction and a pressure side. Based on mirror-symmetrical shapes, he recognizes the aerodynamic function of the wing nose by an asymmetrical wing profile, although, as he writes, the in 40-43 The symmetrical and asymmetrical cross-sections shown gave almost equally good results.

From the DE 32 13 810 A1 a turbine emerges that is designed for two flow directions, in which guide vanes and radial rotor blades are each arranged mirror-symmetrically to a plane of rotation. In each case one guide vane and one rotor blade of a pair are provided for one flow direction. A rotor blade has a uniform, asymmetrical airfoil that cannot be adapted to the different rotational speeds of the rotor, so that in the case of an air turbine there is an undesirable loss of performance and associated noise development due to the air vortex being broken.

From the US 2010/0 259 048 A1 a water turbine emerges in which three impellers with radial rotor blades rotate around a common axis of rotation at a distance from one another and are connected to a ballastable float. The radial rotor blades of an impeller are mounted both on the hub and on an outer ring.

From the U.S. 5,096,382 A an annular propeller emerges in which several radial rotor blades are each connected at their blade tips with an arcuate ring segment. Between the blade tips, the arcuate ring segment regularly changes its inclination to the axis of rotation and its wing curvature, so that there is an abrupt interruption of the closed ring shape in the area of the blade tip. The asymmetrical ring shape of the propeller leads to an uneven distribution of mass, which causes an undesirable imbalance in a high-speed propeller, so that the hub and bearing are exposed to extreme loads.

From the GB 2 026 620 A discloses a water turbine in which a plurality of radial rotor blades are connected to a peripheral ring. The surrounding ring carrier of the turbine anchored in a flow by means of several ropes is designed to accommodate secondary turbines, which are driven by the centrifugal force of the wheel rotating in the flow. From the US 9 926 906 B2 different designs for wind turbines emerge, which are designed to use the kinetic and thermal energy contained in a wind flow. Several radial rotor blades are connected to an outer ring wing, which has an asymmetrical wing profile and the suction side of which is on the outside of the ring. The task of the ring wing is to direct air into the downstream area of the wind turbine and in this way to counteract the lee-side widening of the flow tube. Another task of the annular wing is to avoid flow losses at the tips of the radial rotor blades.

From the JP H01-130 067 A the result is a bidirectional turbine through which the flow is deflected perpendicular to the direction of flow. A plurality of rotor blades are arranged at a radial distance and parallel to an axis of rotation and run through an annular orbit. From the WO 2016/145 477 A1 a water turbine emerges with a central flow guide body and several rotor blades arranged radially to the axis of rotation.

From the WO 2013/021 205 A2 is the result of a gearless, synchronously excited ring generator for a water turbine.

From the WO 2006/029 496 A1 shows a bidirectional through-flow jacket turbine which is symmetrical to a plane of rotation. Radial rotor blades arranged in pairs for one direction of flow are connected at their outer end to a ring which has an elliptical profile in its cross section and, together with a slot-shaped interruption in the turbine shell, is designed to improve the flow through the turbine.

From the WO 2003/025 385 A2 shows a shell turbine with a stator and an impeller. The casing of the turbine acts as a diffuser. As a water turbine, the jacket is designed as a flow guide device mirror-symmetrically to the plane of rotation of the rotor, so that the turbine can be designed for a flow that changes direction regularly and periodically. The rotor ring of a gearless, synchronously excited ring generator is connected to the rotor blade ends and interacts with a stator ring embedded in a duct wall.

Task

Proceeding from the prior art presented, the invention is based on the object of specifying a new type of bidirectionally effective flow machine with a staircase formed by at least three ring blades. According to a first object of the invention, the turbo machine is designed as a prime mover to convert the energy contained in a flow that changes periodically diametrically in direction into a rotary motion and into an electric current. According to a second task, the turbomachine is designed as a working machine to convert a rotary movement into a flow and into a thrust force. In particular, the object of the invention is to find a mirror-symmetrical arrangement for at least three ring blades of a wing staircase which, in combination with radial rotor blades, act as a buoyant rotor and cause a lift force inclined in the respective direction of rotation of a ring blade and towards the flow.

• - Angabe einer Flügeltreppe für eine Strömungsmaschine mit mehr als drei Ringflügeln, deren Flügelprofile sich der Länge nach zwischen 5 und 50 Prozent ihrer Profiltiefe übergreifen
• - Volle Leistungsentfaltung der Strömungsmaschine bereits bei niedrigen Auslegungsschnelllaufzahlen λ von 2,5-3,5
• - Passiv wirkende Drehzahlbegrenzung der Strömungsmaschine über die Auslegungsschnelllaufzahl X der Ringflügel
• - Angabe einer leisen Strömungsmaschine, bei der die Flügeltreppe eine schalltechnisch wirksame Abschirmung bildet
• - Angabe einer Kraftmaschine als Luft- oder Wasserturbine
• - Erzeugung einer luvseitigen Schubkraft, die dem leeseitigen Schub einer Kraftmaschine entgegenwirkt, sodass die Tragkonstruktion einer Luft- oder Wasserturbine wesentlich entlastet wird.
• - Angabe einer frei angeströmten Wasserturbine für ein Gezeitenströmungskraftwerk
• - Angabe einer ummantelten Kraftmaschine als eine Luftturbine für ein Wellenkraftwerk mit oszillierender Wassersäule
• - Angabe einer ummantelten Kraftmaschine als eine Luftturbine an einem neuartigen hydraulischen Hebewerk an Staustufen
• - Angabe einer Kraftmaschine für ein Auf- und Abwindkraftwerk
• - Angabe robuster und wartungsarmer Wind- und Wasserturbinen
• - Angabe einer Arbeitsmaschine als Ventilator für die kontrollierte Be- und Entlüftung eines Gebäudes
• - Angabe einer Arbeitsmaschine als Ventilator für die kontrollierte Be- und Entlüftung eines Tunnels
• - Angabe einer Arbeitsmaschine als Querstrahlruder für ein Wasserfahrzeug

These objects are achieved with the features of the invention mentioned in the main claim. Further objects and advantageous properties of the invention emerge from the subclaims. In detail, the following objects are achieved by the invention:

• - Specification of a wing staircase for a flow machine with more than three ring wings, the wing profiles of which overlap between 5 and 50 percent of their profile depth
• - Full power delivery of the turbomachine already at low design speed ratios λ of 2.5-3.5
• - Passively acting speed limitation of the turbomachine via the design high speed number X of the ring blades
• - Specification of a quiet turbomachine in which the wing staircase forms an effective acoustic shield
• - Specification of a prime mover as an air or water turbine
• - Generation of a thrust on the windward side, which counteracts the leeward thrust of an engine, so that the load on the supporting structure of an air or water turbine is significantly relieved.
• - Specification of a free flow water turbine for a tidal current power plant
• - Specification of a jacketed engine as an air turbine for a wave power plant with an oscillating water column
• - Specification of a jacketed engine as an air turbine on a new type of hydraulic hoist at barrages
• - Specification of a prime mover for an updraft and downdraft power plant
• - Specification of robust and low-maintenance wind and water turbines
• - Specification of a working machine as a fan for the controlled ventilation of a building
• - Specification of a working machine as a fan for the controlled ventilation of a tunnel
• - Specification of a working machine as a transverse thruster for a watercraft

Structure and function of the bidirectional flow machine

The bidirectional flow machine can be designed either as a power machine or as a flow converter to convert the kinetic energy contained in a flow periodically diametrically changing direction into a rotary movement, or as a work machine or as a thrust generator to convert the kinetic energy into a rotary motion to walk a current. The flow machine has a diffuser that acts either as a diffuser or as a cone in an air or water flow and is formed by a flow-through winged staircase with planes of action on an axis of rotation as well as by at least one housing for an electrical machine with a motor and a generator function. The wing staircase has an apex and a plane of symmetry in the plane of action of the central ring wing, which is preceded by at least one ring wing and at least one ring wing follows in the respective direction of the flow. The ring blades each have suction and pressure sides and are connected to the electrical machine by means of radial rotor blades and overlap one another lengthwise with a radial gradient in such a way that the leading ring blade has a guide ring and, together with the middle ring blade, an annular guide nozzle for the Forms approach flow to the middle ring wing with a cone angle. In the case of a diffuser, a divergent cone angle flows onto the wing staircase, the outer sides of the ring blades being designed as suction sides. In the case of a confusor, a convergent cone angle flows towards the wing staircase, the inner sides of the ring wings being designed as suction sides. From a resulting flow, the ring blades in the planes of action each generate a lift force that acts over the entire circumference of the ring blades and is inclined towards the flow and in the direction of rotation of the respective ring blade. If the wing staircase consists of more than three ring wings, the ring wings overlap each other in such a way that, in the case of the diffuser, a plurality of leading ring wings have an ascending run of the wing staircase that rises to the vertex of the central ring wing arranged in the plane of symmetry and a plurality of trailing ring wings one from the apex of the middle ring wing descending course of the wing staircase forms, with the ring wing of both flights of stairs with a divergent cone angle flow towards. If the diffuser of the turbomachine acts as a confuser, the flight of stairs of the wing staircase, formed by a plurality of leading ring wings, descends to the apex of the central ring wing arranged in the plane of symmetry, while the majority of trailing ring wings, starting from the apex of the wing stairs, have an ascending course and both Staircases with a convergent cone angle are flown against and the convex suction sides and the concave pressure sides of the ring blades overlap each other lengthways and with a radial gradient in such a way that a ring blade leading in the flow forms a guide ring for the next ring blade in the flow and successive ones Ring blades form ring-shaped guide nozzles with one another for the resulting flow of the next ring blade with a cone angle and which the profile chords of the blade profiles overlap between 5 and 50 percent of their profile depth to form the annular guide nozzle. The diffuser of the turbomachine formed by the housing of the turbomachine is designed in such a way that the resulting flow onto a plurality of trailing annular blades with a divergent or convergent cone angle also takes place.

Arrangement and layout of the double staircase

The ratio of the rotational speed of an annular wing to the undisturbed flow speed is the so-called design speed factor X, the decisive parameter for the flow dynamic design of the wing profile. The ring blades each have in a cutting plane inclined at an angle of inclination of 20-140 degrees with respect to the relevant plane of action through their center a lift-generating wing profile, which in the case of a diffuser eg as a convex-concave profile and in the case of a confuser eg as a concave-convex Profile or as a plano-convex profile, each with a profile chord extending from the wing nose to the wing trailing edge and with a curvature height measured between a skeleton line and the profile chord. The profile chords of the ring wings are each set at an angle of incidence compared to the cone angle of the resulting flow, which is e.g. 1-6 degrees on the leading ring wing, for example 9-15 degrees and on the trailing ring wing of the wing staircase, for example 6-12 degrees . The profile chord of the middle ring wing is aligned parallel to the axis of rotation and longer than the profile chord of the leading ring wing with a profile chord inclined towards the flow and the trailing ring wing of the same size with a profile chord inclined against the flow. The radii measured in the planes of action of the ring blades at the vertices of the convex suction sides differ in the difference between a smaller and a larger radius and thus define the radial gradient of the wing staircase. In the case of a diffuser, the radius of the central ring wing is larger than the equal radius of the leading and trailing ring wing. In the case of a confusor, the radius of the central ring wing is smaller than the equal radius of the leading and trailing ring wing. The ring blades rotate either with a direction of rotation in the same direction or with an opposite direction of rotation around the axis of rotation, the lift-generating wing profile being overflowed diagonally to the axis of rotation with a flow resulting from the flow velocity and the respective circumferential speed of the ring blades and at an angle of inclination of Cutting plane inclined at 20-140 degrees with respect to the planes of action through the respective center point causes the least resistance, so that the lift force in the cutting planes is offset from the axis of rotation. If the lift force were to run through the respective center point of a ring wing, the current would have to cover a further path, which would result in more resistance. Because the flow always takes the path of least resistance, the lift force caused by a ring wing is inclined in the direction of rotation and towards the flow, so that in the planes of action of the ring wings a tangential drive force and a thrust force acting perpendicular to it result from the lift force. The wing nose and the wing trailing edge of the wing profile are each designed identically and have either a nose radius or a flat circular ring surface on the windward and leeward sides. The wing profile of the ring wing is designed for a defined high speed of 2.5-3.5, for example. The design of the airfoil is based on the resulting flow as a vector sum of the flow velocity, the rotational speed and the cone angle of the resulting flow. The inclination angle of the cutting plane and the cone angle thus define the resulting flow. The following applies to the leading ring wing: the flatter the angle of inclination, the higher the speed. If the leading and the middle ring vanes rotate in opposite directions, the angle of inclination is between 70 and 110 degrees. In the case of a diffuser, the suction sides of the wing profiles are on the Outer sides of the ring wings and, in the case of a confuser, on the inner sides of the ring wings. The three ring blades of a turbomachine are part of the diffuser, whereby the convex suction sides and the concave pressure sides of the airfoils, which act as lift rotors in terms of flow dynamics, act as guide surfaces for the resulting inflow in the cutting planes inclined at angles of inclination of 20-140 degrees compared to the planes of action. The ring blades are each designed for a given design speed limit X, so that passive speed limitation of the turbomachine is made possible by the fact that the resulting flow breaks off on the wing profile of the ring blades when the design speed number A is exceeded and causes increased rotational resistance.

The diffuser as a diffuser

An annular wing, in which the outside of the wing profile is designed as a suction side, requires a diffuser that acts as a diffuser, so that the flow against the annular wing is at a divergent cone angle in order to generate a torque on the axis of rotation. A preferred embodiment of the diffuser relates to a bidirectionally effective diffuser, which consists of a rotary body with a spindle, disc or torus shape and with a collar in the plane of symmetry of the central ring wing, which is arranged coaxially and concentrically to the axis of rotation and mirror-symmetrically to the plane of action of the central ring wing, is formed by the radial rotor blades and the wing staircase itself, so that the flow flows towards the three ring blades with the divergent cone angle. In a particularly advantageous embodiment of the diffuser, the spindle-shaped rotating body with the collar, the wing staircase and the rotor blades are arranged within an outer jacket, which is formed by a tube open on two sides or by a toroidal ring body, each with an inflow-side inlet, with a nozzle constriction and, in the case of a Water turbine is formed with a downstream suction pipe, so that the flow on the inside of the shell is deflected away from the axis of rotation and the flow is against the ring blades with the divergent cone angle. The rotor blades are each connected at their hub-side end to a rotor ring of the electrical machine that is integrated into the rotating body and at their outer end to the ring blades and act as a diffuser by converting the flow into a rotary motion, with the flow slowing down and the accompanying increased pressure causes the flow tube to widen, so that the flow against the ring blades is at a cone angle. The flow can only be slowed down to a certain extent by the energy drawn from the rotor blades and the ring blades. If too much energy is withdrawn from it, the blockage of the flow tube causes a back pressure, which leads to a decrease in the performance of the flow machine. In this sense, Betz's law also applies to a bidirectional flow machine. However, the flow dynamic effectiveness of the ring wing is based on its suction side, so that in the case of a diffuser the flow is also recorded outside the structural radius and Betz's law in this case can be applied to a flow tube with a significantly larger radius than the one that is given by the constructive radius of the ring wing. In addition, the ring wing prevents the formation of undesirable turbulence at the rotor blade tips thanks to its closed contour at the nose and trailing edge, which improves the efficiency of the radial rotor blades. Annular blades and rotor blades taken together enable a power coefficient significantly greater than 16/27 in relation to the structural diameter of the turbomachine.

The diffuser as a confuser

An annular wing, in which the inside of the wing profile is designed as a suction side, requires a diffuser that acts as a cone so that the flow against the annular wing is at a convergent cone angle in order to generate a torque on the axis of rotation. In the case of a turbomachine with a jacket, the cone is formed by a Venturi nozzle that has a maximum nozzle constriction on the inside of the jacket, mirror-symmetrical to the plane of rotation of the central ring vane. The Venturi nozzle directs the flow towards the axis of rotation with a cone angle. In the area of the maximum nozzle constriction, the middle ring vane rotates at a radial distance from the jacket. The connection of the ring blade to a rotor ring of the ring generator embedded in the jacket at the nozzle constriction is established by radial rotor blades with a symmetrical blade profile. Downstream, a diffuser is connected to the confuser and the nozzle constriction. Since a bidirectionally effective engine is mirror-symmetrical to the plane of rotation of the central ring wing, the diffuser acts analogously in both directions of flow.

Training for prime movers

In a prime mover, the radial rotor blades have a stationary, bidirectionally effective blade profile arranged mirror-symmetrically to the planes of action of the ring blades with a teardrop-shaped cross-section aligned in the direction of rotation and connect the ring blades to the hub-side rotor ring of an electrical machine. A wind or water turbine retains in one periodically diametrically the direction changing flow the respective direction of rotation of the ring blades. In an existing flow, the prime mover is driven by the radial rotor blades and the ring blades. On a prime mover, each of the three ring blades can be connected to its own electrical machine by means of the rotor blades, so that the leading, middle and trailing ring blades can each be accelerated to different design speed numbers X and the electrical machines when the respective design speed numbers reach λ are, as synchronously excited ring generators, each with a stator and rotor ring and a frequency converter to generate electricity on an air or water turbine. A bidirectional flow machine through which a flow machine can flow can advantageously be used for different designs of tidal turbines and flowing water turbines. A water turbine anchored on the seabed is either exposed to a free flow or is designed as a jacket turbine with a bidirectional flow-through housing with an inlet, a nozzle constriction and a suction pipe. As an alternative to anchoring at the bottom of a body of water, a prime mover can be connected to the underside of a floating body anchored in the current or to a ship. The engine can also be integrated into a bridge construction in which the flow openings are designed as a guide apparatus. Water turbines have an anchor plate, which is connected, for example, to the bottom of a ship or to a river or sea floor in order to anchor the engine in a stationary manner in a current that changes direction regularly. An air turbine according to the invention gains energy from an oscillating water column within a so-called OWC power plant, which is either connected to a coast or to a floating body anchored off a coast. If the direction of flow changes rapidly, the ring blades of an air turbine maintain their respective direction of rotation and, as a flywheel, overcome the temporary standstill during the load change due to the stored angular momentum. The principle of the oscillating water column can also be used on existing and previously unused transverse structures within an inland waterway network. For this purpose, a new type of hydraulic lifting mechanism is proposed, which is driven by any excess headwater from a river course at existing barrages and barrages that are still to be built. At a barrage, gravity continuously transports water-filled containers, which can also be used as a fish lift, from the upper water to the lower water and from the lower water to the upper water. A roof or a housing of the hydraulic lift creates an airtight lockable air chamber from the atmosphere so that jacketed air turbines can be installed in the roof or in the housing, which when lowering one container from the suction of the air flowing into the air chamber and are driven by the air escaping from the air chamber in the simultaneous lifting process of the second container. With every fully automatically controlled discharge of the upper water into the lower water by flaps with a subsequent refilling of the container, fish can safely follow their natural urge to migrate both upstream and downstream. The frequency of the locks depends on the amount of water present, so that the flow of a river can mainly be regulated by a large number of corresponding lock chambers independently of shipping traffic, with an unused overshooting of the dammed water is only provided for in extreme weather events. The hydraulic elevator uses the positional energy of the headwater to generate a periodically changing air pressure in the air chambers connected to the lock chambers, from which electrical power is obtained by means of the electric machine of an air turbine. A coherent roof over a plurality of lock chambers arranged parallel to one another can be designed as a green bridge over a river that is harmoniously integrated into the landscape and thus serves to network the biotopes separated by the river. Several modularly arranged air turbines can be provided for pressure equalization in the air chambers. The hydraulic elevator can move a large amount of air for energy generation with a comparatively small amount of water, which is required for each lock. Finally, an air turbine according to the invention can also be used in an updraft / downdraft power plant in order to generate electricity. On the one hand, an updraft / downdraft power plant uses the chimney effect for the ascent of solar-heated air, which is collected over a large area by a canopy of the updraft power plant, while the downdraft function uses the weight of cool air masses that cause a downwind within the chimney.

Training for work machines

In the case of a working machine, at least the rotor blades of the middle ring wing are set at a uniform angle of attack of 45 degrees with respect to the plane of action of the middle ring wing. In an outer end section, the rotor blades of the central ring vane are rigidly connected to the leading, central and trailing ring vane and, at their hub-side end, to the rotor ring of the electrical machine. The electrical machine of a work machine is designed as an asynchronously excited induction motor with a stator and rotor ring and with a frequency converter, so that the three ring blades are steplessly adjusted to the specified design speed X can be accelerated. The induction motor has a frequency converter, which enables the control of the speed and the change of the direction of rotation of the electrical machine and thus a thrust reversal, so that the working machine, for example, as a two-way fan in a building envelope structure for the air exchange with supply and exhaust air or as a bidirectionally effective transverse thruster can be formed at the bow and stern of a watercraft.

The figures show different embodiments and applications for bidirectional flow machines. The sections A-A, B-B, C-C, D-D each show the aerodynamically effective wing profiles in the section plane inclined at an angle of inclination with respect to the respective plane of action.

• 1 eine Strömungsmaschine als Kraftmaschine mit Diffusor und mit vektorieller Darstellung der strömungsdynamisch bewirkten Kräfte in der perspektivischen Ausschnittsdarstellung,
• 2 die Kraftmaschine nach 1, oben mit Anströmung von rechts und unten mit Anströmung von links, in einem Längsschnitt entlang der Rotationsachse,
• 3 die Kraftmaschine nach 1-2 mit vektorieller Darstellung der von den Ringflügeln bewirkten Kräfte in einer anströmungsseitigen Ansicht und mit Schnitten B-B und B'-B' des mittleren Ringflügels,
• 4 das strömungsdynamisch wirksame konvex-konkave Fügelprofil des mittleren Ringflügels der Kraftmaschine nach 1-3 in zwei Querschnitten A-A und A'-A',
• 5 ein altenatives strömungsdynamisch wirksames polygonales Fügelprofil für den mittleren Ringflügels der Kraftmaschine nach 1-3 in zwei Querschnitten B-B und B'-B',
• 6 eine Strömungsmaschine als eine Arbeitsmaschine mit Diffusor in der perspektivischen Ausschnittsdarstellung,
• 7 die Arbeitsmaschine nach 6, oben mit Anströmung von rechts und unten mit Anströmung von links, in einem Längsschnitt entlang der Rotationsachse,
• 8 die Arbeitsmaschine nach 6-7, in der anströmugsseitigen Ansicht,
• 9 eine Strömungsmaschine als eine Kraftmaschine mit einem Diffusor, der von einem Rotationskörper und von einem Mantel mit einer Aufweitung gebildet wird, in der perspektivischen Ausschnittsdarstellung,
• 10 die Kraftmaschine nach 9, oben mit Anströmung von rechts und unten mit Anströmung von links, in einem Längsschnitt entlang der Rotationsachse,
• 11 die Kraftmaschine nach 9-10 mit vektorieller Darstellung der von den Ringflügeln bewirkten Kräfte in einer anströmungsseitigen Ansicht,
• 12 eine Strömungsmaschine als eine Arbeitsmaschine, die als ein Querstrahlruder in den Bug eines Schiffs integriert ist, in der perspektivischen Ausschnittsdarstellung,
• 13 das Querstrahlruder nach 12 in einem Längsschnitt entlang der Rotationsachse,
• 14 eine Strömungsmaschine als eine Arbeitsmaschine, die als ein Ventilator ausgebildet ist, in der perspektivischen Ausschnittsdarstellung,
• 15 den Ventilator nach 14 in einem Längsschnitt entlang der Rotationsachse,
• 16 eine Strömungsmaschine als eine Kraftmaschine mit Konfusor in der perspektivischen Ausschnittsdarstellung,
• 17 die Kraftmaschine nach 16, oben mit Anströmung von rechts und unten mit Anströmung von links, in einem Längsschnitt entlang der Rotationsachse,
• 18 die Kraftmaschine nach 16-17 mit vektorieller Darstellung der von den Ringflügeln bewirkten Kräfte in einer anströmungsseitigen Ansicht,
• 19 das strömungsdynamisch wirksame konkav-konvexe Fügelprofil des mittleren Ringflügels der Kraftmaschine nach 16-18 in zwei Querschnitten C-C und C'-C',
• 20 ein altenatives strömungsdynamisch wirksames plankonvexes Fügelprofil für den mittleren Ringflügel der Kraftmaschine nach 16-18 in zwei Querschnitten D-D und D'-D',
• 21 eine Variante der Kraftmaschine nach 16-20 mit einer von fünf Ringflügeln gebildeten Flügeltreppe in einem schematischen Längsschnitt entlang der Rotationsachse
• 1 zeigt eine bidirektionale Strömungsmaschine 1, die als eine Kraftmaschine 11 dazu ausgebildet ist, die in einer Luft- oder Wasserströmung F enthaltene kinetische Energie in eine Drehbewegung zu wandeln. Die Kraftmaschine 11 besteht aus einem konzentrisch und koaxial zu der Rotationsachse x angeordneten Rotationskörper 120, der in der Strömung F als ein Diffusor 14 wirkt und ein Gehäuse 12 für eine elektrische Maschine 13 bildet.
• Insgesamt neun radiale Rotorblätter R verbinden eine nicht näher bezeichnete Nabe des Rotationskörpers 120 mit drei Ringflügeln A,B,C, die in Richtung der Strömung F jeweils in drei hintereinander angeordneten Wirkungsebenen Q1-Q3 rotieren. Die Rotorblätter R weisen ein in Drehrichtung ausgerichtetes tropfenförmiges Blattprofil 16 auf und verbinden die drei Ringflügel A,B,C mit einer elektrischen Maschine 13, die in das von einem Rotationskörper 120 gebildete Gehäuse 12 der elektrischen Maschine 13 integriert ist. Die Ringflügel A,B,C rotieren mit eine gemeinsamen Drehrichtung um die Rotationsachse x und
• übergreifen sich der Länge y und der Höhe z nach so, dass die Flügeltreppe 2 gebildet wird. Jeweils in Schnittebenen N1-N3, die mit Neigungswinkeln β gegenüber den Wirkungsebenen Q1-Q3 geneigt sind, weisen die Ringflügel A,B,C das strömungsdynamisch wirksame Flügelprofil 24 eines Auftriebsläufers auf. Der Rotationskörper 120 weist einen Kragen 123 auf, sodass der von den Rotorblättern R und von der Flügeltreppe 2 gebildete Leitapparat der Kraftmaschine 11 als Diffusor 14 wirkt und die aus der Strömungsgeschwindigkeit a und der Umlaufgeschwindigkeit b resultierende Anströmung c einer Luft- oder Wasserströmung die Ringflügel A,B,C jeweils in den Schnittebenen N1-N3 mit einem divergenten Konuswinkel 51 anströmt. Die resultierende Anströmung c bewirkt an den drei Ringflügeln A,B,C jeweils eine in Drehrichtung und zur Strömung F hin geneigte Auftriebskraft d, die in den Schnittebenen N1-N3 in eine Vortriebskraft e und in eine Sogkraft h aufgeteilt wird. Aus der Vortriebskraft e und dem Widerstand j leiten sich in den Wirkungsebenen Q der Ringflügel A,B,C die tangentiale Antriebskraft g und der Rotationswiderstand k sowie die gegen die Richtung der Strömung F wirkende Schubkraft F und die Druckkraft 1 ab. Eine Halterung 125 verbindet das Gehäuse 12 der elektrischen Maschine 13 mit einer nicht näher bezeichneten Ankerplatte, die im Fall einer Wasserturbine in dem Grund eines Gewässers verankert oder mit dem Boden eines Schiffs verbunden werden kann.
• 2 zeigt einen schematischen Längsschnitt der als Kraftmaschine 11 ausgebildeten Strömungsmaschine 1 mit Darstellung des bidirektional wirksamen Leitapparats, der in der oberen Hälfte der Zeichnung von rechts und in der unteren Hälfte der Zeichnung von links angeströmt wird und in der Strömung F jeweils als Diffusor 14 wirkt. Der Leitapparat besteht aus einem koaxial und konzentrisch zu der Rotationsachse x angeordneten spindelförmigen Rotationskörper 120 in Form eines doppelseitigen Rotationsparaboloids mit einem Kragen 123, aus den Rotorblättern R und aus den Ringflügeln A,B,C, deren Saug- und Druckseiten in der Strömung F als Leitflächen 22 wirken. Die Kraftmaschine 11 ist spiegelsymmetrisch zu der Wirkungsebene Q des mittleren Ringflügels B angeordnet und kann z.B. als eine Wasserturbine zur Nutzung einer periodisch die Richtung wechselnden Gezeitenströmung ausgebildet werden. Die bidirektionale Wirkung der Kraftmaschine 11 wird durch den Kragen 123 in der Wirkungsebene Q des mittleren Ringflügels B unterstützt, in dessen Leeseite sich die Strömung F derart verwirbelt, dass auch der nachlaufende Ringflügel C mit einem divergenten Konuswinkel δ1 angeströmt wird. Relativ zu dem divergenten Konuswinkel 51 der Strömung F weisen die Profilsehnen p der Ringflügel A,B,C jeweils einen Anstellwinkel α auf, der bei dem vorauslaufenden Ringflügel A z.B. 6 Grad, bei dem mittleren Ringflügel B z.B. 15 Grad und bei dem nachlaufenden Ringflügel C z.B. 11 Grad beträgt.
• 3 zeigt die Kraftmaschine 11 nach 1-2 mit Darstellung der von der Strömung F bewirkten Auftriebskräfte d, die an dem vorauslaufenden Ringflügel A mit einem Versatz m1, an dem mittleren Ringflügel B mit einem Versatz m2 und an dem nachlaufenden Ringflügel C mit einem Versatz m3 zu der Rotationsachse x angreifen. Das in dem Querschnitt A-A, oben und in 4 im Detail dargestellte, strömungsdynamisch wirksame, konvex-konkave Flügelprofil 24 des mittleren Ringflügels B unterscheidet sich von dem in dem Querschnitt A'-A' unten dargestellten Flügelprofil, bei dem eine Auftriebskraft d angenommen wurde, die ohne Versatz durch die Rotationsachse x verläuft. Die anströmungsseitige Ansicht der Kraftmaschine 11 zeigt die in Drehrichtung und nach Luv geneigte Auftriebskraft d, aus der an den Ringflügeln A,B,C jeweils eine Sogkraft h und eine tangentiale Antriebskraft g abgeleitet werden. Die radialen Rotorblätter R1-R3 haben wie in 1 gezeigt ein in Drehrichtung ausgerichtetes, tropfenförmiges Blattprofil 16 und sind jeweils an ihrem äußeren Ende mit den Ringflügeln A,B,C und an ihrem nabenseitigen Ende mit einer elektrische Maschine 13 verbunden, die in das von dem Rotationskörper 120 gebildete Gehäuse 12 integriert ist.
• 4 zeigt das strömungsdynamisch wirksame Flügelprofil 24 des mittleren Ringflügels B der Kraftmaschine 11 nach 1-3 mit einer sich zwischen der Flügelnase n und der Flügelhinterkante o erstreckenden Profilsehne p sowie mit einer zwischen der Profilsehne p und der Skelettlinie t gemessenen Wölbungshöhe q. Der mit einem Neigungswinkel β gegenüber der Wirkungsebene Q2 durch den Mittelpunkt M geführte Querschnitt A-A zeigt das strömungsdynamisch wirksame Flügelprofil 24 des mittleren Ringflügels B, während der ebenfalls mit dem Neigungswinkel β gegenüber der Wirkungsebene Q2 des mittleren Ringflügels B geführte Querschnitt A'-A' nicht durch den Mittelpunkt M verläuft und ein Profil zeigt, welches die Strömung F zu überwinden hätte, wenn sie, wie in 3 in dem Schnitt A'-A' gezeigt, ohne Versatz m2 die Rotationsachse x schneiden würde. Das in dem Schnitt A'-A' dargestellte Profil des mittleren Ringflügels B ist länger und hat eine größere Querschnittfläche als das in dem Querschnitt A-A dargestellte strömungsdynamisch wirksame Flügelprofil 24 des mittleren Ringflügels B. Da die Strömung F stets den Weg des geringsten Widerstands nimmt, dienen die in 4 dargestellten Querschnitte A-A und A'-A' der geometrischen Beweisführung für die in 1 und 3 dargestellte tangentiale Antriebskraft g der Ringflügel A,B,C.
• 5 zeigt ein alternatives, polygonales Flügelprofil 24 für die Ringflügel A,B,C der in 1-3 dargestellten Kraftmaschine 11. Das polygonale Flügelprofil 24 weist eine sich zwischen der Flügelnase n und der Flügelhinterkante o erstreckende Profilsehne p sowie eine zwischen der Profilsehne p und der Skelettlinie t gemessenen Wölbungshöhe q auf. Der Querschnitt B-B zeigt das von der Strömung F genutzte Flügelprofil 24. Der Querschnitt B'-B' zeigt ein angenommenes Flügelprofil 24, das die Strömung F zu überwinden hätte, wenn die Auftriebskraft d wie in 3 gezeigt ohne Versatz m1-m3 an der Rotationsachse x angreifen würde.
• 6 zeigt eine bidirektionale Strömungsmaschine 1, die als eine Arbeitsmaschine 10 in Form eines Ventilators 17 dazu ausgebildet ist, Luft in einem schaltbaren Wechsel in zwei einander entgegengesetzte Richtungen zu beschleunigen. Im Unterschied zu der in 1 gezeigten Kraftmaschine 11 sind bei der Arbeitsmaschine 10 die Rotorblätter R mit einem Anstellwinkel α von einheitlich 45 Grad gegenüber den Wirkungsebenen Q der Ringflügel A,B,C angestellt, sodass sie eine Strömung F generieren. Für den Wechsel der Strömungsrichtung ist es notwendig die Drehrichtung der Ringflügel A,B,C umzukehren. Der Ventilator 17 hat ein äußeres Gehäuse 12 dessen Innenwand konkav gewölbt ist. Die Anordnung der Ringflügel A,B,C entspricht im wesentlichen dem in 1-4 gezeigten Ausführungsbeispiel. Jeweils in Schnittebenen N1-N3, die mit Neigungswinkeln β gegenüber den Wirkungsebenen Q1-Q3 geneigt sind, weisen die Ringflügel A,B,C das strömungsdynamisch wirksame Flügelprofil 24 eines Auftriebsläufers auf. Der Leitapparat der Arbeitsmaschine 10 wirkt als Diffusor 14, sodass, wie in 1 gezeigt, die aus der Strömungsgeschwindigkeit a und der Umlaufgeschwindigkeit b resultierende Anströmung c die Ringflügel A,B,C in den Schnittebenen N1-N3 jeweils mit einem divergenten Konuswinkel 51 anströmt. Die resultierende Anströmung c des Flügelprofils 24 bewirkt über den gesamten Umfang der drei Ringflügel A,B,C eine in Drehrichtung und zur Strömung F hin geneigte Auftriebskraft d, die jeweils in den Schnittebenen N1-N3 in eine Vortriebskraft e und in eine Sogkraft h aufgeteilt wird. Aus der Vortriebskraft e und dem Widerstand j leiten sich in den Wirkungsebenen Q die tangentiale Antriebskraft g und der Rotationswiderstand k sowie die gegen die Richtung der Strömung F wirkende Schubkraft F und die Druckkraft 1 ab. Eine Halterung 125 verbindet die elektrische Maschine 13 der Arbeitsmaschine 10 mit einem äußeren Mantel 121, der in den Aufbau der Außenwand eines Gebäudes integriert werden kann um einen kontrollierten Luftwechsel in dem Gebäude sicherzustellen.
• 7 zeigt einen Längsschnitt der Arbeitsmaschine 10 nach 6 mit Darstellung des bidirektional wirksamen Leitapparats, der in der oberen Hälfte der Zeichnung von rechts und in der unteren Hälfte der Zeichnung von links angeströmt wird und in der Strömung F jeweils als Diffusor 14 wirkt. Der Leitapparat besteht aus einem koaxial und konzentrisch zu der Rotationsachse x angeordneten Rotationskörper 120 in Form eines doppelseitigen Rotationsparaboloids mit einem Kragen 123 und aus den Ringflügeln A,B,C, deren Saug- und Druckseiten in der Strömung F als Leitflächen 22 wirken. Die Kraftmaschine 11 ist spiegelsymmetrisch zu der Wirkungsebene Q des mittleren Ringflügels B angeordnet und kann z.B. als eine Wasserturbine zur Nutzung einer periodisch die Richtung wechselnden Gezeitenströmung ausgebildet werden. Die bidirektionale Wirkung der Kraftmaschine 11 wird durch den Kragen 123 in der Wirkungsebene Q des mittleren Ringflügels B unterstützt, in dessen Leeseite sich die Strömung F derart verwirbelt, dass auch der nachlaufende Ringflügel C mit einem divergenten Konuswinkel 51 angeströmt wird. Wie in 1 gezeigt weisen die Profilsehnen p der Ringflügel A,B,C relativ dem divergenten Konuswinkel 51 der Strömung F einen Anstellwinkel α auf, der bei dem vorauslaufenden Ringflügel A z.B. 6 Grad, bei dem mittleren Ringflügel B z.B. 15 Grad und bei dem nachlaufenden Ringflügel C z.B. 11 Grad beträgt. Im Unterschied zu der in 1 gezeigten Kraftmaschine 11 weisen die Rotorblätter R bei der hier gezeigten Arbeitsmaschine 10 einen einheitlichen Anstellwinkel von 45 Grad gegenüber den Wirkungsebenen Q der Ringflügel A,B,C auf.
• 8 zeigt die Arbeitsmaschine 10 nach 6-7 in einer anströmungsseitigen Ansicht mit.Darstellung der jeweils in Drehrichtung und nach Luv geneigten Auftriebskraft d, aus der jeweils in den Wirkungsebenen Q der Ringflügel A,B,C eine tangentiale Antriebskraft g abgeleitet wird.
• 9 zeigt eine bidirektionale Strömungsmaschine 1, die als eine Kraftmaschine 11 dazu ausgebildet ist, die in einer Strömung F aus Luft oder Wasser enthaltene kinetische Energie in eine Drehbewegung zu wandeln. Die Kraftmaschine 11 besteht aus einem konzentrisch und koaxial zu der Rotationsachse x angeordneten Rotationskörper 120, der mittels einer Halterung 125 an einem äußeren Mantel 121 verankert ist, aus der Flügeltreppe 2 und aus den Rotorblättern R, die jeweils die Ringflügel A,B,C mit einer elektrischen Maschine 13 verbinden. Die Ringflügel A,C sind mittels von Rotorblättern R mit einem im Bereich der Düsenverengung 122 in den Mantel 121 integrierten elektrischen Maschine 13 verbunden, während der mittlere Ringflügel B über das nabenseitige Ende der Rotorblätter R mit der in den Rotationskörper 120 integrierten elektrischen Maschine 13 verbunden ist. Der Leitapparat der Kraftmaschine 11 wird von einem Mantel 121 mit einem Zulauf, mit einer Düsenverengung 122 in der Wirkungsebene Q des mittleren Ringflügels B und von einem abstromseitigen Saugrohr 124, sowie von der Flügeltreppe 2 gebildet. Der zentrale Rotationskörper 120 wirkt zusammen mit der Erweiterung des Mantels 121 als ein Diffusor 14, sodass die Ringflügel A,B,C, wie in 9 gezeigt, jeweils mit einem divergenten Konuswinkel 51 angeströmt werden.
• 10 zeigt die Kraftmaschine 11 nach 9 in einem schematischen Längsschnitt, die in der oberen Hälfte der Zeichnung von rechts und in der unteren Hälfte der Zeichnung von links angeströmt wird und in der Strömung F jeweils als Diffusor 14 wirkt. Der Leitapparat der Kraftmaschine 11 besteht aus einem koaxial und konzentrisch zu der Rotationsachse x angeordneten spindelförmigen Rotationskörper 120 mit einem Kragen 123 und aus der von den Ringflügeln A,B,C gebildeten Flügeltreppe 2, deren Saug- und Druckseiten in der Strömung F als Leitflächen 22 wirken. Die Kraftmaschine 11 ist spiegelsymmetrisch zu der Wirkungsebene Q des mittleren Ringflügels B angeordnet und kann z.B. als eine Wasserturbine zur Nutzung einer periodisch die Richtung wechselnden Gezeitenströmung ausgebildet werden. Die bidirektionale Wirkung der Kraftmaschine 11 wird durch den Kragen 123 in der Wirkungsebene Q des mittleren Ringflügels B unterstützt, in dessen Leeseite sich die Strömung F derart verwirbelt, dass auch der nachlaufende Ringflügel C mit einem divergenten Konuswinkel 51 angeströmt wird. Relativ zu dem divergenten Konuswinkel 51 der der resultierenden Anströmung weisen die Profilsehnen p der Ringflügel A,B,C, wie in 2 dargestellt einen Anstellwinkel α auf.
• 11 zeigt die Kraftmaschine 11 nach 9-10 in einer anströmungsseitigen Ansicht mit Darstellung der jeweils in Drehrichtung und nach Luv geneigten Auftriebskraft d, aus der jeweils in den Wirkungsebenen Q der Ringflügel A,B,C eine Sogkraft h und eine tangentiale Antriebskraft g abgeleitbar sind.
• 12 zeigt eine Strömungsmaschine 1 als eine Arbeitsmaschine 10, die als ein bidirektional wirksames Querstrahlruder 18 in den Bug eines nicht näher bezeichneten Schiffs integriert ist. Der Leitapparat des Querstrahlruders 18 besteht aus einem spindelförmigen Rotationskörper 120, der eine elektrische Maschine 13 aufnimmt und mittels von sechs lösbaren radialen Halterungen 125 derart in einen äußeren Mantel 121 mit einer Erweiterung eingesetzt ist, dass für die Strömung F ein Zulauf, eine Düsenverengung 122 und ein Saugrohr 124 gebildet werden. Die Rotorblätter R des mittleren Ringflügels B sind an ihrem äußeren Ende starr mit den Ringflügeln A,B,C und nabenseitig mit der in den Rotationskörper 120 integrierten elektrischen Maschine 13 verbunden. Die Rotorblätter R2 weisen einen einheitlichen Anstellwinkel α von 45 Grad gegenüber der Wirkungsebene Q des mittleren Ringflügels B auf. Die elektrische Maschine 13 ist als ein Induktionsmotor mit einem Frequenzumrichter ausgebildet, der eine stufenlose Regelung der Drehzahl und eine Umkehr der Schubrichtung ermöglicht.
• 13 zeigt das Querstrahlruder 18 nach 12 in einem Längsschnitt entlang der Rotationsachse x mit Darstellung der von dem Querstrahlruder 18 bewirkten Schubkraft f, oben von rechts nach links und unten von links nach rechts. Der Längsschnitt zeigt den als Diffusor 14 wirkenden Leitapparat des Querstrahlruders 18, der von dem konzentrisch und koaxial zu der Rotationsachse x ausgebildeten Rotationskörper 120 mit einem Kragen 123 in der Wirkungsebene Q des mittleren Ringflügels B, von der Flügeltreppe 2 sowie von einem äußeren Mantel 121, einem Zulauf und einem Saugrohr 124 gebildet wird. Die konvexen Saugseiten und die konkaven Druckseiten der Ringflügel A,B,C sind jeweils als Leitflächen 22 für die Strömung F ausgebildet. Der Kragen 123 ist ebenfalls Teil des Leitapparats und bewirkt, dass in der jeweiligen Richtung der Strömung F die drei Ringflügel A,B,C mit einem divergenten Konuswinkel δ1 angeströmt werden. Dabei ist der vorauslaufende Ringflügel A als ein Leitring 20 für die Anströmung des mittleren Ringflügels B ausgebildet. Durch eine horizontale Länge y und durch eine vertikale Höhe z übergreifen sich die Ringflügel A,B,C so, dass zwischen dem vorauslaufenden Ringflügel A und dem mittleren Ringflügel B eine Leitdüse 21 gebildet wird.
• 14 zeigt eine Strömungsmaschine 1 als Arbeitsmaschine 10, die als ein Ventilator 17 ausgebildet ist. Das Gehäuse 12 des Ventilators 17 besteht aus einem torusförmigen Rotationskörper 120, der zusammen mit einem äußeren Mantel 121 einen Ringtorus bildet. Die elektrische Maschine 13 arbeitet als asynchron erregte Induktionsmaschine und weist einen Statorring 130 und einen Läuferring 131 auf. Radiale Rotorblätter R, die mit einem Anstellwinkel von 45 Grad gegenüber der Wirkungsebene Q des mittleren Ringflügels B angestellt sind, sind mit den drei Ringflügeln A,B,C und an ihrem nabenseitigen Ende mit dem Läuferring 131 des Ringgenerators starr verbunden. Die Rotorblätter R weisen gegenüber der Innenseite des Ringtorus eine Haarfuge auf.
• 15 zeigt den Ventilator 17 nach 14 in einem Längsschnitt entlang der Rotationsachse x. Die Ringflügel A,B,C übergreifen einander der Länge y und der Höhe z nach derart, dass eine Flügeltreppe 2 gebildet wird, wobei die konvexen Saugseiten und die konkaven Druckseiten der Ringflügel A,B,C als Leitflächen 22 für die von den Rotorblättern R induzierte Strömung F wirken.
• In Richtung der Strömung F, die die Ringflügel A,B,C oben von rechts und unten von links anströmt, wirkt jeweils der vorauslaufende Ringflügel A als ein Leitring 20 für die Anströmung des mittleren Ringflügels B mit dem divergenten Konuswinkel 51. Ein Leitgitter 23 ist Teil des Leitapparats des Ventilators 17.
• Abstromseitig ist das Leitgitter 23 verstellbar ausgebildet. Die von der Strömungsmaschine 1 erzeugte, entgegen der Strömungsrichtung wirkende Schubkraft f führt dazu, dass die anströmende Luft angesaugt wird. Die Rotorblätter R weisen einen einheitlichen Anstellwinkel von 45 Grad gegenüber den Wirkungsebenen Q der Ringflügel A,B,C auf und erzeugen die Strömung F. Ein Wechsel der Drehrichtung des Ventilators 17 bewirkt eine Schubumkehr mit einer diametral entgegengesetzten Richtung der Strömung F.
• 16 zeigt eine Strömungsmaschine 1, die als eine Kraftmaschine 11 mit einem von einem äußeren Mantel 121 gebildeten Gehäuse 12 ausgebildet ist. Der Leitapparat der Kraftmaschine 11 wirkt in der jeweiligen Richtung der Strömung F als Konfusor 15, sodass die Ringflügel A,B,C, wie in 17 gezeigt mit einem konvergenten Konuswinkel 52 angeströmt werden. Der Leitapparat weist für die Strömung F einen sich verjüngenden Zulauf, eine Düsenverengung 122 in Form einer Venturi-Düse und einen sich abstromseitig erweiternden Auslauf auf, der im Fall einer Wasserturbine als Saugrohr 124 wirkt. Radiale Rotorblätter R verbinden die Ringflügel A,B,C jeweils mit einer in das Gehäuse 12 eingelassenen elektrischen Maschine 13. Die Ringflügel A und C sind jeweils rechtsdrehend, während der mittlere Ringflügel B linksdrehend ausgebildet ist. Die Kraftmaschine 11 kann entweder als Wasser- oder als Windturbine ausgebildet werden.
• 17 zeigt einen Längsschnitt durch die Kraftmaschine 11 nach
• 16 entlang der Rotationsachse x, oben mit der Strömung F von rechts und unten mit der Strömung F von links. Die Ringflügel A,B,C bilden untereinander eine Flügeltreppe 2, wobei sie sich der Länge y nach und mit der Höhe z derart übergreifen, dass zwischen dem vorauslaufenden Ringflügel A und dem mittleren Ringflügel B eine Leitdüse 21 gebildet wird. Innerhalb der Strömung F wirken die außenliegenden Druckseiten und die innenliegenden konvexen Saugseiten der Ringflügel A,B,C jeweils als Leitflächen 22, die in der Strömung F einerseits einen möglichst geringen Widerstand hervorrufen und andererseits, wie in 18 gezeigt, in den Wirkungsebenen Q eine tangentiale Antriebskraft g in der jeweiligen Drehrichtung der Ringflügel A,B,C bewirken. Die Rotorblätter R sind jeweils spiegelsymmetrisch zu den Wirkungsebenen Q ausgebildet und weisen, wie in 18 gezeigt, jeweils ein tropfenförmiges Blattprofil 16 mit einer in Drehrichtung ausgerichteten Flügelnase n auf.
• 18 zeigt die Kraftmaschine 11 nach 16-17 mit Darstellung der von der Strömung F bewirkten Auftriebskraft d, die an dem vorauslaufenden Ringflügel A einen Versatz m1, an dem mittleren Ringflügel B einen Versatz m2 und an dem nachlaufenden Ringflügel C einen Versatz m3 aufweist. Das in dem Querschnitt D-D und in 20 im Detail dargestellte, plankonvexe und strömungsdynamisch wirksame Flügelprofil 24 des mittleren Ringflügels B unterscheidet sich von dem in dem Querschnitt D'-D' dargestellten Flügelprofil, bei dem eine Auftriebskraft d angenommen wurde, die ohne Versatz durch die Rotationsachse x der in 16,17 dargestellten Flügeltreppe 2 verläuft. Die gegensinnige Drehrichtung der Ringflügel A,C und des Ringflügels B werden in einer schematischen Schnittdarstellung der Blattprofile 16 der radialen Rotorblätter R deutlich.
• 19 zeigt das strömungsdynamisch wirksame konkav-konvexe Flügelprofil 24 des vorauslaufenden und des nachlaufenden Ringflügels A,B der Kraftmaschine 11 nach 16-18 mit einer sich zwischen der Flügelnase n und der Flügelhinterkante o erstreckenden Profilsehne p sowie mit einer zwischen der Profilsehne p und der Skelettlinie t gemessenen Wölbungshöhe q. Der mit einem Neigungswinkel β gegenüber den Wirkungsebenen Q1,Q3 durch die Mittelpunkte M des vorauslaufenden und des nachlaufenden Ringflügels A,B geführte Querschnitt C-C zeigt das strömungsdynamisch wirksame konkav-konvexe Flügelprofil 24, während der ebenfalls mit dem Neigungswinkel β gegenüber den Wirkungsebenen Q1,Q3 geführte Querschnitt C'-C' nicht durch die Mittelpunkte M des vorauslaufenden und des nachlaufenden Ringflügels A,B geführt ist und ein Profil zeigt, welches die Strömung F zu überwinden hätte, wenn sie die Rotationsachse x ohne den in 18 an den Ringflügeln A,B,C gezeigten Versatz m1,m2,m3 schneiden würde. Das in dem Schnitt C'-C' dargestellte Profil des vorauslaufenden und des nachlaufenden Ringflügels A,B ist länger und hat eine größere Querschnittfläche als das in dem Querschnitt C-C dargestellte strömungsdynamisch wirksame, konkav-konvexe Flügelprofil 24 der Ringflügel A,C. Da die Strömung F stets den Weg des geringsten Widerstands nimmt, dienen die in 19 dargestellten Querschnitte auch der geometrischen Beweisführung für die in 18 dargestellte tangentiale Antriebskraft g der Ringflügel A,B,C.
• 20 zeigt das plankonvexe Flügelprofil 24 des mittleren Ringflügels B der Kraftsmaschine 11 nach 16-19. Das plankonvexe Flügelprofil 24 weist eine sich zwischen der Flügelnase n und der Flügelhinterkante o erstreckende Profilsehne p sowie eine zwischen der Profilsehne p und der Skelettlinie t gemessenen Wölbungshöhe q auf. Der Querschnitt D-D zeigt das strömungsdynamisch wirksame Flügelprofil 24, während der Querschnitt D'-D' dasjenige Flügelprofil zeigt, welches die Strömung F zu überwinden hätte, wenn die Auftriebskraft d, wie in 18 am Beispiel des mittleren Ringflügels B gezeigt, keinen Versatz zu der Rotationsachse x aufweisen würde.
• 21 zeigt einen Längsschnitt durch eine Kraftmaschine 11, die sich von dem in 16-20 gezeigten Ausführungsbeispiel durch die Anzahl der Ringflügel A,B,C unterscheidet. Die Flügeltreppe 2 wird von insgesamt fünf Ringflügeln A,B,C gebildet, wobei neben dem mittleren Ringflügel B zwei vorauslaufende Ringflügel A und zwei nachlaufende Ringflügel C dargestellt sind. Die Flügeltreppe 2 ist spiegelsymmetrisch zu der Wirkungsebene Q3 des mittleren Ringflügels B mit dem Scheitelpunkt S aufgebaut und ist oberhalb der Rotationsachse x mit einer Strömungsrichtung von rechts und unterhalb der Rotationsachse x mit einer Strömungsrichtung von links dargestellt. Das Gehäuse 12 der als Kraftmaschine 11 ausgebildeten Strömungsmaschine weist einen Mantel 121 mit einem einströmungsseitigen Zulauf, einer als Venturi-Düse ausgebildeten Düsenverengung 122 mit einem Kragen 123 sowie einem Auslauf, der im Fall einer Wasserturbine als Saugrohr 124 ausgebildet ist, auf. In den Mantel 121 der Kraftmaschine 11 ist eine elektrische Maschine 13 eingelassen, die aus fünf in Reihe angeordneten Statorringen 130 und Läuferringen 131 aufgebaut ist, sodass diefünf Ringflügel A,B,C unabhängig voneinander um die Rotationsachse x rotieren können. Sowohl die beiden vorauslaufenden Ringflügel A als auch die beiden nachlaufenden Ringflügel C übergreifen einander der Länge y nach zwischen den Mittelpunkten M auf der Rotationsachse x und der Höhe z nach zwischen den Scheitelpunkten S, sodass zwischen den vorauslaufenden Ringflügeln A und dem mittleren Ringflügel B sowie zwischen dem mittleren Ringflügel B und den nachlaufenden Ringflügeln C jeweils eine ringförmige Leitdüse 21 gebildet wird. Wie in 16 dargestellt, sind die Ringflügel A,B,C der Flügeltreppe 2 jeweils mittels von drei radialen Rotorblättern mit symmetrischen Blattprofilen 16 mit den Läuferringen 131 der elektrischen Maschine 13 verbunden. Dabei kann die Drehrichtung von einem zum nächsten Ringflügel A,B,C jeweils wechseln.

Show it:

• 1 a flow machine as a prime mover with a diffuser and with a vector representation of the forces caused by the fluid dynamics in the perspective detail representation,
• 2 the engine after 1 , above with flow from the right and below with flow from the left, in a longitudinal section along the axis of rotation,
• 3 the engine after 1-2 with vector representation of the forces caused by the ring blades in an upstream view and with sections BB and B'-B 'of the middle ring blade,
• 4th the fluid dynamically effective convex-concave wing profile of the middle ring wing of the engine 1-3 in two cross-sections AA and A'-A ',
• 5 an alternative, flow dynamically effective polygonal wing profile for the middle ring wing of the engine 1-3 in two cross-sections BB and B'-B ',
• 6 a flow machine as a working machine with diffuser in the perspective detail view,
• 7th the working machine after 6 , above with flow from the right and below with flow from the left, in a longitudinal section along the axis of rotation,
• 8th the working machine after 6-7 , in the upstream view,
• 9 a flow machine as a prime mover with a diffuser, which is formed by a body of revolution and a jacket with a widening, in the perspective detail view,
• 10 the engine after 9 , above with flow from the right and below with flow from the left, in a longitudinal section along the axis of rotation,
• 11 the engine after 9-10 with vector representation of the forces caused by the ring blades in an upstream view,
• 12 a turbomachine as a working machine, which is integrated as a transverse thruster in the bow of a ship, in the perspective detail view,
• 13 the transverse thruster after 12 in a longitudinal section along the axis of rotation,
• 14th a flow machine as a working machine, which is designed as a fan, in the perspective detail view,
• 15th the fan 14th in a longitudinal section along the axis of rotation,
• 16 a flow machine as a prime mover with a confuser in the perspective detail view,
• 17th the engine after 16 , above with flow from the right and below with flow from the left, in a longitudinal section along the axis of rotation,
• 18th the engine after 16-17 with vector representation of the forces caused by the ring blades in an upstream view,
• 19th the fluid dynamically effective concave-convex wing profile of the middle ring wing of the engine 16-18 in two cross-sections CC and C'-C ',
• 20th an alternative, plano-convex wing profile that is effective in terms of flow dynamics for the middle ring wing of the engine 16-18 in two cross-sections DD and D'-D ',
• 21st a variant of the prime mover 16-20 with a wing staircase formed by five ring wings in a schematic longitudinal section along the axis of rotation
• 1 shows a bidirectional flow machine 1 that act as a prime mover 11 is designed to convert the kinetic energy contained in an air or water flow F into a rotary motion. The power machine 11 consists of a rotating body arranged concentrically and coaxially with respect to the axis of rotation x 120 that in the flow F as a diffuser 14th acts and a housing 12 for an electric machine 13 forms.
• A total of nine radial rotor blades R. connect an unspecified hub of the rotating body 120 with three ring wings A. , B. , C. , which in the direction of flow F each in three successive planes of action Q1-Q3 rotate. The rotor blades R. have a teardrop-shaped leaf profile aligned in the direction of rotation 16 and connect the three ring wings A. , B. , C. with an electric machine 13 going into that of a solid of revolution 120 formed housing 12 the electric machine 13 is integrated. The ring wings A. , B. , C. rotate with a common direction of rotation around the axis of rotation x and
• overlap the length y and the height z so that the wing staircase 2 is formed. Each in cutting planes N1-N3 that with tilt angles β compared to the effect levels Q1-Q3 are inclined, have the ring wings A. , B. , C. the aerodynamically effective wing profile 24 a lift rotor. The solid of revolution 120 has a collar 123 so that the one from the rotor blades R. and from the double staircase 2 formed guide apparatus of the engine 11 as a diffuser 14th acts and that from the flow velocity a and the speed of rotation b resulting flow c an air or water flow, the ring blades A. , B. , C. each in the cutting planes N1-N3 with a divergent cone angle 51 flows towards. The resulting flow c causes on the three ring wings A. , B. , C. in each case a lift force inclined in the direction of rotation and towards the flow F. d that are in the cutting planes N1-N3 into a propulsive force e and into a suction force H is divided. From the propulsive force e and the resistance j are guided in the effect levels Q of the ring wings A. , B. , C. the tangential driving force G and the resistance to rotation k as well as the thrust F acting against the direction of the flow F and the pressure force 1 from. A bracket 125 connects the housing 12 the electric machine 13 with an unspecified anchor plate which, in the case of a water turbine, can be anchored in the bottom of a body of water or connected to the bottom of a ship.
• 2 shows a schematic longitudinal section as a prime mover 11 trained flow machine 1 with representation of the bidirectionally effective diffuser, which is flown against in the upper half of the drawing from the right and in the lower half of the drawing from the left and in the flow F each as a diffuser 14th works. The diffuser consists of a spindle-shaped body of revolution arranged coaxially and concentrically with respect to the axis of rotation x 120 in the form of a double-sided paraboloid of revolution with a collar 123 , from the rotor blades R. and from the ring wings A. , B. , C. , their suction and pressure sides in the flow F as guide surfaces 22nd Act. The power machine 11 is mirror symmetrical to the plane of action Q of the middle ring wing B. arranged and can be designed, for example, as a water turbine for the use of a tidal current which periodically changes direction. The bidirectional action of the prime mover 11 is through the collar 123 in the plane of action Q of the middle ring wing B. supported, in whose leeward side the flow F swirls in such a way that the trailing ring wing C. with a divergent cone angle δ1 is flowed against. Relative to the divergent cone angle 51 the profile chords show the flow F p the ring wing A. , B. , C. each one angle of attack α on, the one at the leading ring wing A. e.g. 6 degrees, with the middle ring wing B. eg 15 degrees and with the trailing ring wing C. Eg 11 degrees.
• 3 shows the prime mover 11 after 1-2 with representation of the lift forces caused by the flow F. d on the leading ring wing A. with an offset m1, on the middle ring wing B. with an offset m2 and on the trailing ring wing C. attack with an offset m3 to the axis of rotation x. That in the cross section AA, above and in 4th Convex-concave wing profile shown in detail, effective in terms of flow dynamics 24 of the middle ring wing B. differs from the wing profile shown in the cross-section A'-A 'below, in which a lift force d was assumed that runs through the axis of rotation x without offset. The upstream view of the engine 11 shows the lift force inclined in the direction of rotation and to windward d , from the on the ring wings A. , B. , C. a suction force each H and a tangential driving force G be derived. The radial rotor blades R1-R3 have as in 1 a teardrop-shaped leaf profile oriented in the direction of rotation is shown 16 and are each at their outer end with the ring wings A. , B. , C. and at its end on the hub side with an electric machine 13 connected to that of the rotating body 120 formed housing 12 is integrated.
• 4th shows that aerodynamically effective wing profile 24 of the middle ring wing B. the prime mover 11 after 1-3 with one between the wing nose n and the trailing edge of the wing O extending profile tendon p as well as one between the profile chord p and the skeleton line t measured arch height q . The one with an angle of inclination β compared to the impact level Q2 through the center M. guided cross section AA shows the aerodynamically effective wing profile 24 of the middle ring wing B. , while the also with the angle of inclination β compared to the impact level Q2 of the middle ring wing B. guided cross-section A'-A 'not through the center M. runs and shows a profile which the flow F would have to overcome if it, as in 3 shown in the section A'-A 'would intersect the axis of rotation x without offset m2. The profile of the central ring wing shown in section A'-A ' B. is longer and has a larger cross-sectional area than the aerodynamically effective airfoil shown in cross-section AA 24 of the middle ring wing B. . Since the flow F always takes the path of least resistance, the in 4th shown cross-sections AA and A'-A 'of the geometrical evidence for the in 1 and 3 shown tangential driving force G the ring wing A. , B. , C. .
• 5 shows an alternative, polygonal wing profile 24 for the ring wings A. , B. , C. the in 1-3 illustrated engine 11 . The polygonal wing profile 24 shows one between the wing nose n and the trailing edge of the wing O extending profile tendon p and one between the profile chord p and the skeleton line t measured arch height q on. The cross section BB shows the wing profile used by the flow F. 24 . The cross-section B'-B 'shows an assumed wing profile 24 that the flow F would have to overcome if the buoyancy force were d as in 3 shown would attack the axis of rotation x without an offset m1-m3.
• 6 shows a bidirectional flow machine 1 that as a work machine 10 in the form of a fan 17th is designed to accelerate air in a switchable alternation in two opposite directions. In contrast to the in 1 shown prime mover 11 are at the machine 10 the rotor blades R. with an angle of attack α of uniform 45 degrees compared to the planes of action Q of the ring wings A. , B. , C. employed so that they generate a flow F. To change the direction of flow, it is necessary to change the direction of rotation of the ring blades A. , B. , C. to reverse. The ventilator 17th has an outer casing 12 whose inner wall is concave. The arrangement of the ring wings A. , B. , C. essentially corresponds to that in 1-4 embodiment shown. Each in cutting planes N1-N3 that with tilt angles β compared to the effect levels Q1-Q3 are inclined, have the ring wings A. , B. , C. the aerodynamically effective wing profile 24 a lift rotor. The distributor of the working machine 10 acts as a diffuser 14th so, as in 1 shown from the flow velocity a and the speed of rotation b resulting flow c the ring wings A. , B. , C. in the cutting planes N1-N3 each with a divergent cone angle 51 flows towards. The resulting flow c of the wing profile 24 effects over the entire circumference of the three ring wings A. , B. , C. a lifting force inclined in the direction of rotation and towards the flow F. d , each in the cutting planes N1-N3 into a propulsive force e and into a suction force H is divided. From the propulsive force e and the resistance j the tangential driving force is directed in the planes of action Q. G and the resistance to rotation k as well as the thrust F acting against the direction of the flow F and the pressure force 1 from. A bracket 125 connects the electric machine 13 the working machine 10 with an outer coat 121 , which can be integrated into the structure of the outer wall of a building in order to ensure a controlled exchange of air in the building.
• 7th shows a longitudinal section of the work machine 10 after 6 with representation of the bidirectionally effective diffuser, which is flown against in the upper half of the drawing from the right and in the lower half of the drawing from the left and in the flow F each as a diffuser 14th works. The diffuser consists of a rotating body arranged coaxially and concentrically to the axis of rotation x 120 in the form of a double-sided paraboloid of revolution with a collar 123 and from the ring wings A. , B. , C. , their suction and pressure sides in the flow F as guide surfaces 22nd Act. The power machine 11 is mirror symmetrical to the plane of action Q of the middle ring wing B. arranged and can be designed, for example, as a water turbine for the use of a tidal current which periodically changes direction. The bidirectional action of the prime mover 11 is through the collar 123 in the impact level Q of the middle ring wing B. supported, in whose leeward side the flow F swirls in such a way that the trailing ring wing C. with a divergent cone angle 51 is flowed against. As in 1 shown have the profile tendons p the ring wing A. , B. , C. relative to the divergent cone angle 51 the flow F has an angle of attack α on, the one at the leading ring wing A. e.g. 6 degrees, with the middle ring wing B. eg 15 degrees and with the trailing ring wing C. Eg 11 degrees. In contrast to the in 1 shown prime mover 11 point the rotor blades R. in the machine shown here 10 a uniform angle of attack of 45 degrees compared to the planes of action Q of the ring blades A. , B. , C. on.
• 8th shows the working machine 10 after 6-7 in an upstream view with representation of the lift force inclined in the direction of rotation and to windward d , from which each in the action levels Q of the ring wing A. , B. , C. a tangential driving force G is derived.
• 9 shows a bidirectional flow machine 1 that act as a prime mover 11 is designed to convert the kinetic energy contained in a flow F of air or water into a rotary motion. The power machine 11 consists of a rotating body arranged concentrically and coaxially with respect to the axis of rotation x 120 that by means of a bracket 125 on an outer coat 121 is anchored from the double staircase 2 and from the rotor blades R. each of the ring wings A. , B. , C. with an electric machine 13 connect. The ring wings A. , C. are by means of rotor blades R. with one in the area of the nozzle constriction 122 in the coat 121 integrated electric machine 13 connected, while the middle ring wing B. over the hub-side end of the rotor blades R. with that in the solid of revolution 120 integrated electric machine 13 connected is. The control apparatus of the engine 11 is covered by a coat 121 with an inlet, with a nozzle constriction 122 in the plane of action Q of the middle ring wing B. and from a downstream suction pipe 124 , as well as from the double staircase 2 educated. The central body of revolution 120 works together with the expansion of the mantle 121 as a diffuser 14th so that the ring wings A. , B. , C. , as in 9 shown, each with a divergent cone angle 51 are flowed against.
• 10 shows the prime mover 11 after 9 in a schematic longitudinal section, which is flown against in the upper half of the drawing from the right and in the lower half of the drawing from the left and in the flow F each as a diffuser 14th works. The control apparatus of the engine 11 consists of a spindle-shaped body of revolution arranged coaxially and concentrically with respect to the axis of rotation x 120 with a collar 123 and from that of the ring wings A. , B. , C. formed winged staircase 2 , their suction and pressure sides in the flow F as guide surfaces 22nd Act. The power machine 11 is mirror symmetrical to the plane of action Q of the middle ring wing B. arranged and can be designed, for example, as a water turbine for the use of a tidal current which periodically changes direction. The bidirectional action of the prime mover 11 is through the collar 123 in the plane of action Q of the middle ring wing B. supported, in whose leeward side the flow F swirls in such a way that the trailing ring wing C. with a divergent cone angle 51 is flowed against. Relative to the divergent cone angle 51 The profile chords show that of the resulting flow p the ring wing A. , B. , C. , as in 2 shown an angle of attack α on.
• 11 shows the prime mover 11 after 9-10 in an upstream view showing the lift force inclined in the direction of rotation and to windward d , from each of the action levels Q the ring wing A. , B. , C. a suction force H and a tangential driving force G are derivable.
• 12 shows a turbomachine 1 as a work machine 10 acting as a bidirectional transverse thruster 18th is integrated into the bow of an unspecified ship. The nozzle of the transverse thruster 18th consists of a spindle-shaped body of revolution 120 who is an electric machine 13 and by means of six detachable radial brackets 125 so in an outer coat 121 with an extension is used that for the flow F an inlet, a nozzle constriction 122 and a suction pipe 124 are formed. The rotor blades R. of the middle ring wing B. are rigid at their outer end with the ring wings A. , B. , C. and on the hub side with that in the body of revolution 120 integrated electric machine 13 connected. The rotor blades R2 have a uniform angle of attack α of 45 degrees compared to the plane of action Q of the middle ring wing B. on. The electric machine 13 is designed as an induction motor with a frequency converter, which enables stepless control of the speed and a reversal of the thrust direction.
• 13 shows the transverse thruster 18th after 12 in a longitudinal section along the axis of rotation x showing that of the transverse thruster 18th caused thrust f , up from right to left and down from left to right. The longitudinal section shows the as a diffuser 14th acting diffuser of the transverse thruster 18th , the body of revolution formed concentrically and coaxially to the axis of rotation x 120 with a collar 123 in the plane of action Q of the middle ring wing B. , from the double staircase 2 as well as from an outer coat 121 , an inlet and a suction pipe 124 is formed. The convex suction sides and the concave pressure sides of the ring blades A. , B. , C. are each used as guide surfaces 22nd designed for the flow F. The collar 123 is also part of the diffuser and causes the three ring blades in the respective direction of the flow F A. , B. , C. with a divergent cone angle δ1 are flowed against. The leading ring vane A acts as a guide ring 20th for the Approach to the middle ring wing B. educated. The ring wings overlap with a horizontal length y and a vertical height z A. , B. , C. so that between the leading ring wing A and the middle ring wing B. a guide nozzle 21st is formed.
• 14th shows a turbomachine 1 as a work machine 10 that act as a fan 17th is trained. The case 12 of the fan 17th consists of a toroidal body of revolution 120 that along with an outer coat 121 forms a ring torus. The electric machine 13 works as an asynchronously excited induction machine and has a stator ring 130 and a runner ring 131 on. Radial rotor blades R. with an angle of attack of 45 degrees with respect to the plane of action Q of the central ring wing B. are employed are with the three ring wings A. , B. , C. and at its end on the hub side with the rotor ring 131 of the ring generator rigidly connected. The rotor blades R. have a hairline opposite the inside of the ring torus.
• 15th shows the fan 17th after 14th in a longitudinal section along the axis of rotation x. The ring wings A. , B. , C. overlap the length y and the height z in such a way that a wing staircase 2 is formed, the convex suction sides and the concave pressure sides of the ring blades A. , B. , C. as guide surfaces 22nd for those of the rotor blades R. induced flow F act.
• In the direction of the flow F, which the ring vanes A. , B. , C. When it flows in from the right at the top and from the left at the bottom, the leading ring wing acts A. as a guide ring 20th for the flow towards the middle ring wing B. with the divergent cone angle 51 . A guide grille 23 is part of the fan control system 17th .
• The guide grille is on the downstream side 23 adjustable. The one from the turbo engine 1 generated thrust acting against the direction of flow f causes the incoming air to be sucked in. The rotor blades R. have a uniform angle of attack of 45 degrees compared to the planes of action Q of the ring blades A. , B. , C. and generate the flow F. A change in the direction of rotation of the fan 17th causes a thrust reversal with a diametrically opposite direction of the flow F.
• 16 shows a turbomachine 1 that act as a prime mover 11 with one of an outer coat 121 formed housing 12 is trained. The control apparatus of the engine 11 acts as a confuser in the respective direction of the flow F. 15th so that the ring wings A. , B. , C. , as in 17th shown with a convergent cone angle 52 are flowed against. The diffuser has a tapering inlet for the flow F, a nozzle constriction 122 in the form of a Venturi nozzle and an outlet widening on the downstream side, which in the case of a water turbine acts as a suction pipe 124 works. Radial rotor blades R. connect the ring wings A. , B. , C. each with one in the housing 12 recessed electric machine 13 . The ring wings A. and C. are clockwise, while the middle ring wing B. is designed to rotate left. The power machine 11 can be designed as either a water or a wind turbine.
• 17th shows a longitudinal section through the engine 11 after
• 16 along the axis of rotation x, above with the flow F from the right and below with the flow F from the left. The ring wings A. , B. , C. form a double staircase below each other 2 , where they overlap the length y and with the height z in such a way that between the leading ring wing A. and the middle ring wing B. a guide nozzle 21st is formed. The outer pressure sides and the inner convex suction sides of the ring vanes act within the flow F A. , B. , C. each as guide surfaces 22nd that are in the flow F. on the one hand cause the lowest possible resistance and on the other hand, as in 18th shown in the effect levels Q a tangential driving force G in the respective direction of rotation of the ring blades A. , B. , C. effect. The rotor blades R. are each mirror-symmetrical to the action levels Q trained and have, as in 18th shown, each a teardrop-shaped leaf profile 16 with a wing nose aligned in the direction of rotation n on.
• 18th shows the prime mover 11 after 16-17 showing the lift force caused by the flow F. d on the leading ring wing A. an offset m1, on the middle ring wing B. an offset m2 and on the trailing ring wing C. has an offset m3. That in the cross-section DD and in 20th Plano-convex and aerodynamically effective wing profile shown in detail 24 of the middle ring wing B. differs from the airfoil shown in the cross section D'-D ', in which a lift force d it was assumed that the axis of rotation x of the in 16 , 17th illustrated double staircase 2 runs. The opposite direction of rotation of the ring blades A. , C. and the ring wing B. are shown in a schematic sectional view of the leaf profiles 16 of the radial rotor blades R. clear.
• 19th shows the aerodynamically effective concave-convex airfoil 24 of the leading and trailing circular wing A. , B. the prime mover 11 after 16-18 with one between the wing nose n and the trailing edge of the wing O extending profile tendon p as well as one between the profile chord p and the skeleton line t measured arch height q . The one with an angle of inclination β compared to the effect levels Q1 , Q3 through the midpoints M. of the leading and trailing circular wing A. , B. guided cross-section CC shows the flow dynamically effective concave-convex wing profile 24 , while the also with the angle of inclination β compared to the effect levels Q1 , Q3 guided cross-section C'-C 'not through the center points M. of the leading and trailing circular wing A. , B. and shows a profile that the flow F would have to overcome if it had the axis of rotation x without the in 18th on the ring wings A. , B. , C. offset shown would cut m1, m2, m3. The profile of the leading and trailing annular wing shown in the section C'-C ' A. , B. is longer and has a larger cross-sectional area than the flow-dynamically effective, concavo-convex airfoil shown in the cross section CC 24 the ring wing A. , C. . Since the flow F always takes the path of least resistance, the in 19th The cross-sections shown also provide the geometrical evidence for the in 18th shown tangential driving force G the ring wing A. , B. , C. .
• 20th shows the plano-convex wing profile 24 of the middle ring wing B. the prime mover 11 after 16-19 . The plano-convex wing profile 24 shows one between the wing nose n and the trailing edge of the wing O extending profile tendon p and one between the profile chord p and the skeleton line t measured arch height q on. The cross section DD shows the aerodynamically effective wing profile 24 , while the cross-section D'-D 'shows that airfoil which the flow F would have to overcome if the lift force were to d , as in 18th using the example of the middle ring wing B. shown would have no offset from the axis of rotation x.
• 21st shows a longitudinal section through an engine 11 that differ from the in 16-20 shown embodiment by the number of ring wings A. , B. , C. differs. The double staircase 2 is made up of a total of five ring wings A. , B. , C. formed, being next to the middle ring wing B. two leading ring wings A. and two trailing ring wings C. are shown. The double staircase 2 is mirror symmetrical to the plane of action Q3 of the middle ring wing B. with the vertex S. and is shown above the axis of rotation x with a direction of flow from the right and below the axis of rotation x with a direction of flow from the left. The case 12 as a power machine 11 trained fluid flow machine has a jacket 121 with an inlet on the inflow side, a nozzle constriction designed as a Venturi nozzle 122 with a collar 123 as well as an outlet, which in the case of a water turbine acts as a suction pipe 124 is trained on. In the coat 121 the prime mover 11 is an electrical machine 13 embedded, consisting of five stator rings arranged in series 130 and runner rings 131 is constructed so that the five ring wings A. , B. , C. can rotate independently of one another around the axis of rotation x. Both the two leading ring wings A. as well as the two trailing ring wings C. overlap each other in length y between the centers M. on the axis of rotation x and the height z between the vertices S. so that between the leading ring wings A. and the middle ring wing B. as well as between the middle ring wing B. and the trailing ring wings C. one ring-shaped guide nozzle each 21st is formed. As in 16 shown are the ring wings A. , B. , C. the double staircase 2 each by means of three radial rotor blades with symmetrical blade profiles 16 with the runner rings 131 the electric machine 13 connected. The direction of rotation can be from one to the next ring vane A. , B. , C. change each time.

List of reference symbols

1

Turbo machine

x

Axis of rotation

y

length

z

pitch

ABC

Ring wing

M.

Focus

S.

Vertex

R.

Rotor blade

Q1-Qn

Impact level

Nl-Nn

Cutting plane

β

Inclination angle

10

Working machine

11

Power machine

12

casing

120

Body of revolution

121

coat

122

Nozzle constriction

123

collar

124

Suction pipe

125

bracket

13th

Electric machine

130

Stator ring

131

Runner ring

14th

Diffuser

15th

Confuser

16

Leaf profile

17th

fan

18th

Transverse thruster

2

Double staircase

F.

flow

α

Angle of attack

δ1

Divergent cone angle

δ2

Convergent cone angle

20th

Guide ring

21st

Guide nozzle

22nd

Guide surface

23

Baffle

24

Wing profile

a

Flow velocity

b

Speed of rotation

c

Resulting flow

d

Buoyancy

e

Propulsive force

f

Thrust

G

Tangential driving force

H

Suction force

j

resistance

k

Rotational resistance

1

Compressive force

m1-mm

Offset

n

Wing nose

O

Trailing edge of the wing

p

Profile tendon

q

Camber height

r1, r2

radius

t

Skeleton line

Claims (10)

Bidirectional flow machine (1), which is designed either as a working machine or as a power machine (10, 11) and has a diffuser for a diametrically direction-changing flow (F), which is either a diffuser (14) or a confuser ( 15) acts and is formed by a wing staircase (2) with at least three levels of action (Q1-Qn) on an axis of rotation (x) and by a housing (12) for at least one electrical machine (13), which wing staircase (2) has a vertex (S) and a plane of symmetry in the plane of action (Q2-Qn) of a central ring wing (B), which middle ring wing (B) is preceded by at least one ring wing (A) and at least one ring wing (C) follows and which ring blades (A, B, C) have convex suction sides and concave pressure sides which are connected to the electrical machine (13) by means of radial rotor blades (R) and which extend along the length (y) and with a radial slope (z) overlap each other in such a way that the ring wing (A) of the wing staircase (2) which precedes the middle ring wing (B) has a guide ring (20) and, together with the middle ring wing (B), an annular guide nozzle (21) for a resulting flow (c) of the middle ring wing (B) with a cone angle (51,52), whereby in the case of the diffuser (14) the staircase (2) with a divergent cone angle (51) is flown against and the outer sides of the ring wings (A, B, C) as convex suction sides are formed and in the case of the confusor (15) the staircase (2) with a convergent cone angle (52) is flown against and the inner sides of the annular wings (A, B, C) are designed as convex suction sides, so that in each of the action levels ( Q1-Qn) a lift force (d) is generated from the resulting flow (c), which is inclined towards the flow (F) and in the respective direction of rotation of the annular blades (A, B, C). Turbo machine (1) after Claim 1 , in which the ring wings (A, B, C) overlap each other in such a way that the at least one leading ring wing (A) in the case of the diffuser (14) has an ascending course of the wing staircase towards the apex (S) of the middle ring wing (B) (2) and the at least one trailing ring wing (C) form a run of the wing staircase (2) descending from the apex (S) of the middle ring wing (B) and in the case of the confuser (15) the leading ring wing (A) one to the Vertex (S) of the middle ring wing (B) descending course of the wing staircase (2) and the trailing ring wing (C) form a course of the wing staircase (2) rising from the apex (S) of the middle ring wing (B), whereby the convex Suction sides and the concave pressure sides of the annular vanes (A) of length (y) and with a radial slope (z) overlap each other in such a way that one leading Ring wing (A) forms a guide ring (20) for the next ring wing (A) in the direction of flow (F) and two successive ring wings (A) form an annular guide nozzle (21) for the resulting flow (c) of the next ring wing (A) ) with a cone angle (51,52), the diffuser of the turbomachine (1) formed by the housing (12) causing the resulting inflow (c) of the trailing annular blades (C) with a cone angle (51,52). Turbo machine (1) after Claim 1 , in which the annular wings (A, B, C) each in a cutting plane (N1-Nn) inclined at an angle of inclination (β) of 20-140 degrees compared to one of the planes of action (Q1-Qn) through their center (M) on the Axis of rotation (x) have a lift-generating, bidirectionally effective wing profile (24), which in the case of a diffuser (14) either as a convex-concave profile or as a polygonal profile and in the case of a confuser (15) either as a concavo-convex profile or as Plano-convex profile, each with a profile chord (p) extending from the wing nose (n) to the wing trailing edge (o) and with a camber height (q) measured between a skeleton line (t) and the profile chord (p) and the profile chords (p) the ring blades (A, B, C) each have an angle of attack (α) relative to the cone angle (51,52) of the resulting flow (c), which is eg 1-6 degrees on a leading ring blade (A) the middle ring wing (B) e.g. 9-15 degrees and on a nac running ring wing (C) is 6-12 degrees, for example. Turbo machine (1) after Claim 3 , in which the ring blades (A, B, C) either rotate in the same direction around the axis of rotation (x), or each rotate with an opposite direction of rotation around the axis of rotation (x), the aerofoil profile (24) generating lift with the a flow velocity (a) and the flow (c) resulting from a rotational speed (b) of the ring blades (A, B, C) transversely to the axis of rotation (x) and at an angle of inclination (β) of 20-140 degrees opposite the planes of action (Q1-Qn) inclined section planes (N1-Nn) through the center (M) of the respective ring wing (A, B, C) causes the least resistance (j), so that the lift force (d) in the section planes (N1- Nn) each with an offset (m1-mn) acts on the axis of rotation (x) and in the planes of action (Q1-Qn) the ring wing (A, B, C) from the lift force (d) a tangential drive force (g) and a against the flow (F) and parallel to the axis of rotation (x) acting Sch ubkraft (f) can be derived. Turbo machine (1) after Claim 3 or 4th , in which the profile chords (p) of the wing profiles (24) extend between identically designed noses (n) and trailing edges (o) of the ring wings (A, B, C), with one of three ring wings (A, B, C) formed wing staircase (2) the profile chord (p) of the middle ring wing (B) with the radius (r2) is longer than the profile chord (p) of the ring wing (A) leading in the direction of the flow (F) with a radius (r1) and of the equally large trailing ring wing (C1) with the radius (r1) and the radii (r1, r2) measured at the apexes (S) of the convex suction sides of the ring wings (A, B, C) by the radial slope (z) than the difference between the radii (r1, r2) such that the radius (r2) of the central ring wing (B) in the case of a diffuser (14) is greater than the radius (r1) of the leading and trailing ring wings (A , C) and the radius (r2) of the middle ring wing (B) in the case of a confuser (15) is smaller than the radius (r1) of the above us and the trailing annular wing (A, C), the profile chords (p) of the wing profiles (24) overlapping between 5 and 50 percent of their profile depth to form the annular guide nozzle (21) and the annular wings (A, B, C ) generate a buoyancy force (d) dynamically and are each designed for a given design speed factor λ, so that passive speed limitation of the turbomachine (1) is made possible by the resulting inflow (c) when the design speed factor X is exceeded on the wing profile (24) of the Ring wing (A, B, C) tears off and causes increased resistance to rotation (k). Turbo machine (1) after Claim 1 , in which the electrical machine (13) accelerates the radial rotor blades (R) and each individual ring blade (A, B, C) of a prime mover (11) individually to the respective design speed number λ, so that when the design speed number X is reached, as a synchronously excited ring generator with stator and rotor ring (130, 131) and with a frequency converter to generate electricity, e.g. on an air or water turbine, or in which the electric machine (13) of a working machine (10) is connected to the radial rotor blades (R) connected ring vane (A, B, C) is accelerated to a design speed number λ, the electrical machine (13) being designed as an induction motor with stator and rotor rings (130, 131) and with a frequency converter and the working machine (10), for example, as a bidirectional more effective Fan (17) or as a bidirectionally effective transverse thruster (18) works. Turbo machine (1) after Claim 1 , the housing (12) of which acts as a diffuser (14) in the direction of the flow (F), so that the resulting flow (c) of the annular blades (A, B, C) has a divergent cone angle (51), the diffuser (14 ) either by a mirror-symmetrical to the plane of action (Q1-Qn) of the central ring wing (B) and coaxially and concentrically to the axis of rotation (x) arranged rotational body (120) with a Spindle, disc or torus shape and is formed with a collar (123), or that the diffuser (14) is formed by the body of revolution (120) with collar (123) and by a jacket (121), which is one with respect to the body of revolution (120) has complementary expansion and the jacket (121) as a tube open in both directions of the flow (F) or as a toroidal ring body, each with an inflow-side inlet, with a nozzle constriction (122) and, in the case of a water turbine, with a downstream one Suction pipe (124) is formed. Turbo machine (1) after Claim 1 , the housing (12) of which acts as a confuser (15) in the respective direction of the flow (F) and of a jacket (121) with an inlet, a nozzle constriction (122) with a collar (123) and, in the case of a water turbine, with a suction pipe (124) is formed, the flow (F) flowing towards the ring blades (A, B, C) with the convergent cone angle (δ2) and the apex (S) of the middle ring blade (B) and the maximum nozzle constriction (122) of the jacket (121) are arranged in the plane of action (Q2-Qn) of the central ring wing (B). Turbo machine (1) after Claim 1 , which is designed as a work machine (10), in which the rotor blades (R) of the central ring vane (B) at their hub-side end with the rotor ring (131) of the electrical machine (13) and in one end section rigidly with the ring blades (A , B, C) are connected and have a uniform angle of attack (α) of 45 degrees with respect to the plane of action (Q2-Qn) of the central annular wing (B), the reversal of the direction of rotation of the electrical machine (13) by means of an inverter changes the direction of the Thrust force (f) causes the working machine (11) to be designed as a two-way fan (17) in a building envelope structure for the exchange of air with supply and exhaust air or as a bidirectional transverse thruster (18) at the bow and stern of a watercraft can. Turbo machine (1) after Claim 1 , which is designed as a power machine (11), the rotor blades (R) each having a fixed, bidirectionally effective and mirror-symmetrical to the planes of action (Q1-Qn) of the ring blades (A, B, C) arranged blade profile (16) with a teardrop-shaped Have cross-section, so that the engine (11) maintains the respective direction of rotation of the annular blades (A, B, C) in the flow (F), which changes periodically diametrically in direction, and the electric machine (13) generates electricity as a generator of an air or water turbine .

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