Patent Publication Number: US-2012032447-A1

Title: Combined wing and turbine device for improved utilization of fluid flow energy

Description:
FIELD OF THE INVENTION 
     The present invention relates to a device for production of electrical, mechanical or hydraulic energy by using wind or fluid flow energy, which device includes at least one rotor, where the wind or fluid flow results in rotor rotation around its axis, at least one base profile and at least one wing. 
     BACKGROUND OF THE INVENTION 
     Prior art systems all seek to achieve focusing of flow at a kind of funnel effect against the incident flow. 
     Patent application published as WO 2008/001080 A1 (Taylor) on Mar. 1, 2008 discloses a device to increase wind power through a wind turbine located on a roof, which forms the lower boundary of each rotor, and which is equipped with a horizontally lying wing with the chord tangentially oriented relative to the rotor, which forms an upper boundary of the turbine. The document only discloses tangentially deflected wings or wing sections of concave, asymmetric nature in relation to the wing chord. The layout uses the wind&#39;s direct influence on the turbine inlet by forming a funnel in front of the turbine. This creates a limited “suction effect” on the lee side. 
     The present invention seeks to achieve greater focus on slowing down through one or more edge positioned wings, thereby achieving increased gap effect due to the increased dynamic pressure drop caused by the edge positioned wing&#39;s barring area. 
     SUMMARY OF THE INVENTION 
     The present invention provides a device for producing electrical, mechanical or hydraulic energy by using wind or other fluid flow, which device is characterized in:
         that the rotor is axially connected to a generator, and   that the wing is edge positioned so that its chord is oriented towards the rotor.       

     This allows a maximum dynamic pressure difference between front and rear of the turbine thereby increasing the “suction effect” on the lee side. 
     The edge positioned wing is made pursuant to claim  2  with a solid or hollow structure. 
     The edge positioned wing is made in accordance with claim  3 , provided with perforations in at least a portion of the wing. The edge positioned wing is made in accordance with claim  4 , equipped with edge rifles. This ensures that the device is adaptable to the landscape or a given building design and architecture, or just give a distinctive design. Moreover, they provide better flow characteristics when the wind or fluid stream passes them. 
     The edge positioned wing is in accordance with claim  5 , prism-shaped, flat, convex, concave or different flow dynamically designed. 
     In a specific embodiment, see claim  6 , the edge positioned wing chord is oriented at an angle between perpendicular to the rotor rotation axis and tangentially to the rotor outer periphery. The edge positioned wing may in accordance with claim  7  be mounted on at least a suspension item including a rotation axis around which the edge positioned wing can rotate. 
     In a preferred embodiment, see claim  8 , at least one longitudinal wing is located between the edge positioned wing and the rotor oriented with its chord essentially perpendicular to the rotor. The longitudinal wing may in accordance with claim  9 , be integrated in the edge positioned wing. The longitudinal wing may in accordance with claim  10 , be flat, convex or concave or adapted to the periphery of the rotor. This will, like perforations in the edge positioned wing design provide better flow characteristics when the wind or fluid stream passes through the turbine flow channel. 
     The rotor is in accordance with claim  11 , designed as a vertical, horizontal, propeller or screw turbine. 
     In a particularly preferred embodiment in accordance with claim  12 , at least one lamella is located in the turbine flow channel ( 8 ) bounded by the edge positioned wing and bottom profile. This ensures that the wind or fluid flow is directed towards the turbine, rather than along the turbine. 
     The bottom profile is in accordance with claim  13 , flat, curved or adapted the geometry of the rotor. 
     At least one turbine lamella is according to claim  14 , located in the turbine flow channel. This will also ensure that wind or fluid flow is directed towards the turbine. 
     In a specific embodiment, of claim  15 , two or more edge positioned wings are oriented with their chords against the rotor. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       In the following the invention will be explained with reference to the drawings, wherein: 
         FIG. 1A  shows the system in an embodiment with a simple, flat, edge positioned wing, 
         FIG. 1B  shows the system shown in  FIG. 1A  with perforations in the wing, 
         FIG. 1C  shows the system shown in  FIG. 1A  with arbitrary cuts in the edge of the wing, 
         FIG. 1D  shows the system shown in  FIG. 1A  with harmonic cuts in the edge of the wing, 
         FIG. 1E  shows the system shown in  FIG. 1A  with perforations and cuts the edge of the wing, 
         FIG. 1F  shows the system in an embodiment with a bulky edge positioned wing, 
         FIG. 2A  shows the system in a second embodiment with a flat, longitudinal wing, 
         FIG. 2B  shows a cross section of the system shown in  FIG. 2A , 
         FIG. 2C  shows the system in a second embodiment with a bulky, longitudinal wing, 
         FIG. 2D  shows a cross section of the system shown in  FIG. 2C , 
         FIG. 3A-B  shows the system in a third embodiment with turbine inlet lamellas, 
         FIG. 4A  shows a cross section of the turbine adapted arbitrary flow, 
         FIG. 4B  shows a cross section of the turbine adapted unilateral flow, 
         FIG. 5A  shows the system in a fourth embodiment with a clamped propeller-rotor, 
         FIG. 5B  shows the system in a fourth embodiment with a rotating propeller-rotor, 
         FIG. 5C  shows the system in a fifth embodiment with upright rotor, 
         FIG. 6A-C  shows the system in a cascade construction, 
         FIG. 7A-D  shows an embodiment in which the system is mounted on a ridge and a house corner, 
         FIG. 8A-C  shows an embodiment of a cascading construction mounted on a ridge and several corners of the house, 
         FIG. 9A-C  shows the system in a deflection example, 
         FIG. 10A-C  shows the system in another deflection example, 
         FIG. 11A-D  shows the system in a sixth embodiment with more than one edge positioned wing, 
         FIG. 12  shows the system in a deflection example with hanging point near the bottom profile, 
         FIG. 13A-B  shows the system in a deflection example with hanging point along the chord of the edge positioned wing, 
         FIG. 14A-J  shows various shapes of the edge positioned wing, 
         FIG. 15A-C  shows the system in a seventh embodiment in which the system is built into the roof, 
         FIG. 16A-B  shows a system similar to  FIG. 1B  built into a roof, and 
         FIG. 17  shows the cascade configurations of the system installed at all building corners. 
     
    
    
     DETAILED DESCRIPTION OF THE INVENTION 
     The invention uses wind and fluid flow energy in a new way by using static structures&#39; ability to generate pressure differences and velocity changes in fluid flow when the flow is forced around obstructive objects or through the narrow passages. 
     The present invention relates to a system for utilization of flow energy in wind or other flowing fluids. The invention uses a new method for utilization of flow energy, characterized by one or more static wings to block a portion of the flow, while another part passes through a turbine or directly above the turbine. The wing system is characterized by allowing maximum air flow passes through the turbine, in addition to allowing a portion of flow passing between the turbine and the vertical wing, either through slits or through perforations or by allowing the lower edge or lower edge profile of the wing to form an upper boundary of the turbine. 
     The edge positioned wing(s) ( 1 ) can be completely flat or aerodynamically designed with their wing chords directed to the rotational axis of the turbine. Moreover, the edge positioned wing ( 1 ) generally has a symmetrical structure relative to its chord. A bottom profile ( 4 ) located opposite the edge at the wing ( 1 ) defines the lower boundary of turbine flow channel ( 8 ) in which the rotor ( 5 ) is located. 
     The edge positioned wing ( 1 ) may be combined with one or more wings/profiles ( 2 ) located so that their bottom represents the upper boundary of the turbine chamber ( 8 ). The top of the wing/profile ( 2 ), forms together with the lower edge of the edge positioned wing ( 1 ) one or more slits ( 7 ) or perforations ( 10 ) immediately above or near the top of the wing/profile ( 2 ). Perforations ( 10 ) can be located on the edge positioned wing ( 1 ) if the wing/profile ( 2 ) is omitted. 
     The system may also have one or more lamella ( 3 ), which serve to deflect the longitudinal wind or flow fields, so as to force the flow through the turbine chamber ( 8 ), split ( 7 ) or perforations ( 10 ) and over the edge positioned wing ( 1 ) rather than parallel to the edge positioned wing ( 1 ). The lamella ( 3 ) also strength the construction and may be designed as straight, concave, convex or any combination in between. 
     The system is ridge based and uses wind and other fluid currents&#39; ability to generate pressure and velocity changes when the flow must pass around static structures. In contrast to known similar systems the invention uses a simple, static barring wing/wings to generate a lower pressure which sucks the flow through the turbine, caused by the increased dynamic pressure difference between the inlet side and lee side, whereby the “suction effect” on the lee side increases. 
     The effects achieved are higher pressure differential across the turbine. The split ( 7 ) between the wing and turbine, and/or perforations ( 10 ) in the wing, serves to create a quick and steady flow through and immediately around of the turbine ( 5 ). 
     The system is characterised by being able to be combined with any known rotor types and in a simple and aesthetic manner to increase the efficacy of these. The system is particularly suited to static location on ridges, skyscrapers, landscape protrusions, etc. 
     The invention comprises at least the edge positioned wing ( 1 ), rotor ( 5 ) and lamella ( 3 ) attached to the wall, roof, house corner, landscape projection as well as under water ridges, river bottom, waterfall or similar flow-intensive sites. 
     The system can be designed so it is double-acting and works by currents from both sides. 
     The system is designed so it can be built into buildings, landscapes, soil or similar, or designed for placement on such structures. 
     In the following description a horizontal rotor type is defined as a rotor with rotor wings and a rotating shaft where the flow moves longitudinally along the rotating shaft. A vertical rotor type is defined as a rotor with rotor wings and a rotating shaft where the flow is moving at right angles onto the rotating shaft along its length. The chord is defined as the line between the wing front and rear edge (the upper and lower edge of the edge positioned wing). 
     System Components: 
     With reference to the above description and subsequent figure description and embodiments the components of the invention reference numbers as indicated in brackets in front of the title. 
     (1) The Edge Positioned Wing: 
     
         
         
           
             i. Oriented with the chord against the rotor 
             ii. For so-called vertical turbines (Savonius, Darrieus, Banki, Ossberger or similar) the edge positioned wing chord is pointing towards the rotary shaft or can bend to an angle so that the chord is tangential to the outer radius of the rotor. 
             iii. For horizontal turbines (“normally” known as propellers on e.g. Vestas Wind Turbines) the edge positioned wing chord is parallel to the plane which is perpendicular to the axis of rotation, or angled relative to this level, if the turbine is rotating. 
             iv. The purpose of the edge positioned wing is to provide maximum dynamic pressure difference between front and rear of turbine by blocking a larger area of the flow over the turbine. 
             v. In order to achieve better flow characteristics the wing may be perforated or riffled in different ways, so a portion of flow can pass through them. The edge positioned wing ( 1 ) may have a hollow or solid structure. 
           
         
       
    
     (2) The Longitudinal Wing/the Upper Turbine Flow-Delimiting Wing: 
     
         
         
           
             i. May be integrated into the edge positioned wing ( 1 ). 
             ii. For vertical turbines the chord is perpendicular or nearly perpendicular on the axis of rotation. 
             iii. May be flat, convex, concave or aerodynamically adapted the periphery of the rotor. 
             iv. May as the edge positioned wing ( 1 ) be perforated, riffled, hollow or solid in structure. 
           
         
       
    
     (3) Lamellas and Gable Profile: 
     
         
         
           
             i. Divide the system into at least one and up to an infinite number of turbine flow channels ( 8 ) by consisting of at least two and up to an infinite number of lamellas/gable profiles. 
             ii. Bearings for vertical turbine rotor shafts or open for through going rotor. 
             iii. Serves as flow lamella and prop and carries the edge positioned wing ( 1 ), the longitudinal wing ( 2 ) and the rotor ( 5 ). May also bear the edge positioned wing ( 1 ) alone or the longitudinal wing ( 2 ) alone. 
             iv. Lamellas in the gables may be designed with an opening which forms the bearings for the rotor shaft. The intermediate strips can be designed with an opening for a continuous rotor ( 5 ) or an opening which forms the bearings for one through going rotor shaft or two associated rotor shafts. 
             v. Serve as attachment points on terrain, roof, wall or similar. 
             vi. May as the edge positioned wing ( 1 ) be perforated, riffled, hollow or solid structure. 
           
         
       
    
     (4) Bottom Profile/the Lower Turbine Inlet-Delimiting Profile: 
     
         
         
           
             i. Forms the bottom of the turbine. The bottom need not be oriented horizontally, but may be placed vertically or in any other direction depending on local conditions. 
             ii. Bottom profile may consist of the present surface on which the system is fastened, such as wall, roof, soil or rock. 
             iii. Bottom profile may be similar to the longitudinal wing ( 2 ), be completely flat, curved or adapted the turbine periphery. 
           
         
       
    
     (5) Rotor: 
     
         
         
           
             i. May be combined with any known turbine types. 
             ii. The rotor produces in vertical rotor types (“Cross Wind turbines”) the rotational energy in the transmission housing ( 6 ), where it is converted into either electrical, mechanical or hydraulic energy. 
             iii. For horizontal turbine types (propeller) the energy is produced in the centrally located turbine in response to the rotor shaft. Here rotational energy is converted into electrical, mechanical or hydraulic energy. 
           
         
       
    
     (6) Transmission Housing: 
     
         
         
           
             i. For types with vertical rotor the transmission takes place in the transmission housing ( 6 ) located in the system&#39;s end gables. 
             ii. There may, for long transmission systems be houses built in the lamellas ( 3 ) with appropriate adaptation of the geometry of the lamellas. 
             iii. Inserted in the roof the transmission house may be built entirely or partially into the roof, whereby the generator, gearbox or similar energy input mechanism will be serviced from the inside of the roof. 
           
         
       
    
     (7) Gaps: 
     
         
         
           
             i. Gaps are established between wing ( 1 ) and wing ( 2 ) and between gable wing ( 9 ) and transmission housing ( 6 ), ridge or other support. This is similar to slots on a conventional wing. 
             ii. The gap can be in full length from lamella ( 3 ) to lamella ( 3 ) or be divided into smaller sections. The gap may in the gable wing ( 9 ) be full length or divided into smaller sections. 
           
         
       
    
     (8) Turbine Flow Channel: 
     
         
         
           
             i. The turbine flow channel consists of an arrangement of the edge positioned wing ( 1 ) or the longitudinal wing ( 2 ), bottom profile ( 4 ) and lamellas ( 3 ). 
             ii. The interior of the turbine flow channel may be provided with lamellas ( 12 ) to deflect incoming and outgoing fluid flow. 
           
         
       
    
     (9) Gable Wing 
     
         
         
           
             i. The gable wing has a stiffening effect on the construction laterally. 
             ii. The gable wing increases the obstructive area so large pressure differential occurs between the front and back of the turbine flow channel ( 8 ). 
             iii. May as the edge positioned wing ( 1 ) consists of several other wings placed above each other and/or be perforated ( 10 ) and/or be provided with rifled edges ( 11 ). 
             iv. May be formed so as to follow contours on the edge positioned wing ( 1 ) and the longitudinal wing ( 2 ), or have contour, slit/gap and perforations of artistic or decorative character. 
           
         
       
    
     (10) Perforation in the Wings 
     
         
         
           
             i. Serves the purpose of creating vortices in the lee side, thus creating a more laminar flow. Does the same principle as slots on a conventional wing. 
             ii. Can be round, squared or of arbitrary geometry, including artistic or decorative design. 
           
         
       
    
     (11) Jagged Wing Edges 
     
         
         
           
             i. Edges of wings may be jagged or riffled like perforations ( 10 ), creating small flow vortices near the edge positioned wing ( 1 ) surface in the lee side, with the same effect as vortex generators. 
             ii. May be arbitrarily designed, including having decorative or artistic nature. 
           
         
       
    
     (12) Turbine Flow Channel Lamellas: 
     
         
         
           
             i. The interior of the turbine flow channel ( 8 ) may be provided with lamellas ( 12 ) to deflect incoming and outgoing fluid flow. 
           
         
       
    
     The invention is explained in more detail below with reference to examples where; 
       FIGS. 1A to 1F  show the invention in its simplest embodiment, consisting of the edge positioned wing ( 1 ) with the chord oriented towards the rotor ( 5 ) and where the gable profiles ( 3 ) maintain the edge positioned wing ( 1 ) and the rotor ( 5 ) at the rotor shaft. The lower boundary of the turbine flow channel ( 8 ) is defined by the bottom profile ( 4 ) onto which the gable profiles ( 3 ) are attached. The upper boundary of the turbine flow channel ( 8 ) is defined by the edge positioned wing ( 1 ). The rotor ( 5 ) may be designed as a vertical rotor, for example a Banki, Ossberger or Cross Wind Turbine. 
       FIG. 1A  shows the invention with a simple, flat, edge positioned wing ( 1 ) with a chord oriented towards the rotor ( 5 ). 
       FIG. 1B  shows the same as  FIG. 1A  in an embodiment with perforations ( 10 ) in the edge positioned wing ( 1 ). 
       FIGS. 1C and 1D  show the same as  FIG. 1A  in an embodiment in which the edge positioned wing ( 1 ) is riffled. 
       FIG. 1C  shows the edge rifles ( 11 ) in the form of serrations at the edge of the edge positioned wing ( 1 ). 
       FIG. 1D  shows the harmonic edge rifles ( 11 ) in the form of cuts in the edge positioned wing ( 1 ). 
       FIG. 1E  shows riffles ( 11 ) in the form of quaint edge cutting into the edge positioned wing ( 1 ) combined with perforations ( 10 ) in the edge positioned wing ( 1 ). This appears to the system in a simple and aesthetic manner. 
       FIG. 1F  shows the invention with a bulky, edge positioned wing ( 1 ) with different surface profile geometry with the chord oriented towards the rotor ( 5 ). 
       FIG. 2A to 2D  show the invention in a specific embodiment with the introduction of a longitudinal wing ( 2 ) between the edge positioned wing ( 1 ) and the rotor ( 5 ). 
       FIG. 2A  shows the invention in a specific embodiment with the introduction of a flat, longitudinal wing ( 2 ) between the edge positioned wing ( 1 ) and the rotor ( 5 ). This creates a gap ( 7 ) with the same function as the perforations ( 10 ), of earlier descriptions. The lower edge of the longitudinal wing ( 2 ) represents here the upper boundary of the turbine flow channel ( 8 ). 
       FIG. 2B  shows the same as  FIG. 2A  in cross section. 
       FIG. 2C  shows the invention with bulky, long voluminous wing ( 2 ) combined with the edge positioned wing ( 1 ) in a manner resulting in perforations ( 10 ). 
       FIG. 2D  shows the same as  FIG. 2C  in cross section. 
       FIG. 3A  shows the invention in a specific embodiment with the introduction of turbine flow channel lamellas ( 12 ). 
       FIG. 3B  shows the invention in a specific embodiment with the introduction of a longitudinal wing ( 2 ) and turbine flow channel lamellas ( 12 ). 
       FIGS. 4A and 4B  show a cross-sectional view of the turbine flow channel ( 8 ) adapted to the rotor ( 5 ) geometry by special geometric shape of the longitudinal wing ( 2 ) and bottom profile ( 4 ). 
       FIG. 4A  shows the symmetrical structure of the turbine flow channel ( 8 ) adapted arbitrary flow from both sides. 
       FIG. 4B  shows the symmetrical structure of the turbine flow channel ( 8 ) adapted unilateral flow from a predominant direction. 
       FIGS. 5A-5B  show the invention in a specific embodiment with propeller-rotor. 
       FIG. 5A  shows the invention in a specific embodiment with a horizontal rotor, for example a propeller rotor, which rotor is fixed with the rotor plane parallel to the edge positioned wing ( 1 ). 
       FIG. 5B  shows the invention in a specific embodiment with propeller rotor, which rotor is pivoted with center point between the edge positioned wing ( 1 ) and flow lamella ( 3 ). 
       FIG. 5C  shows the invention in an embodiment in which the rotor ( 5 ) orients the axis of rotation along the intersection of the edge positioned wing ( 1 ) and flow lamella ( 3 ). The rotor ( 5 ) can be designed as a vertical turbine, for example a Savonius or Darrieus turbine with propeller-shaped wings. 
       FIGS. 6A-6C  show the invention in the cascade style, where the invention in relation to  FIGS. 1A-1F ,  2 A- 2 D,  3 ,  4 A- 4 B and  5 A- 5 C and all the forms, multiplied into any number. 
       FIGS. 7A-7D  show the invention in a preferred form where the bottom profile ( 4 ) is formed by the local surface, angled arbitrarily between 0° and 180°, illustrated by mounting on any roof and house corner. In the example there is shown a gable wing ( 9 ) and transmission housing ( 6 ). The gable wing ( 9 ) can be omitted, but would mean a loss of power. The transmission house ( 6 ) can be omitted if the rotational energy turnover occurs by direct interaction between the gable lamellas ( 3 ) and rotor ( 5 ). 
       FIGS. 8A-8B  shows the invention in a preferred embodiment where a long voluminous wing ( 2 ) has been introduced between the edge shaped wing ( 1 ) and rotor ( 5 ). 
       FIG. 8B  shows a cascade installation of the invention, which generates three turbine flow channels ( 8 ). The rotors ( 5 ) is embedded in the gable profiles ( 3 ) and internally connected via a common rotor shaft that delivers rotational energy in transmission housings ( 6 ), where it is transformed into electrical, mechanical or hydraulic energy. In the ends, the invention further equipped with gabled wings ( 9 ) to the lateral stiffening and for aesthetic reasons. 
       FIG. 8C  shows the embodiment of  FIG. 8B  mounted on a building in multiplied numbers and at all edges and ridges. 
       FIGS. 9A and 9B  show the invention in an example, where the angle β divides the bottom profile into two equal halves marked with the center line C L . The arbitrary angle α marks the edge positioned wing ( 1 ) deflection from the center line intersection of bottom profiles ( 4 ) peak. 
       FIG. 9C  shows  FIG. 9B  in an embodiment mounted on a corner, for example a building with flat roof. The  FIG. 9C  is shown with walls and roof as bottom profile ( 4 ). 
       FIGS. 10A and 10B  show the invention in a bending example, where the angle β divides the bottom profile into two equal halves marked with the center line C L . The arbitrary angle α marks the edge positioned wing ( 1 ) deflection from the center line of intersection of the rotor ( 5 ) hub. 
       FIG. 100  shows  FIG. 10B  of the example located on the corner, for example building with flat roof. The  FIG. 100  is shown with walls and roof as bottom profile ( 4 ). 
     The edge positioned wing ( 1 ) shown both in  FIG. 9A-C  and  FIGS. 10A-C  is clamped by means of the lamellas ( 3 ) in an angle corresponding to the arbitrary bending angle α. 
       FIG. 11A-11D  show examples with more than one edge positioned wing ( 1 ). The invention can in principle be provided with an infinite number of edge positioned wings in accordance with the bending principles indicated in  FIGS. 10A and 10B . 
       FIGS. 11A and 11B  show the execution example, where there are two edge positioned wings ( 1 ) with chord oriented to the rotor ( 5 ). 
       FIG. 11A  shows in cross section the invention with double edge positioned wing ( 1 ). 
       FIG. 11B  shows the invention with double wing ( 1 ) in perspective. 
       FIGS. 110 and 10D  shows the execution example, where there are three edge positioned wings ( 1 ,  1 ′,  1 ″) with chord oriented to the rotor ( 5 ). Alternatively, wings ( 1 ′,  1 ″) are designed like turbine inlet lamellas ( 12 ). 
       FIG. 11C  shows the invention with three feathered wings ( 1 ) in cross section. The angles a, q, s and y represent arbitrary angles relative to the bottom profile ( 4 ). 
       FIG. 11D  shows the embodiment with three edge positioned wings in perspective. 
       FIG. 12  shows examples of the invention with respect to the flow affected mechanical deflection of the edge positioned wing ( 1 ) around a suspension point located near the top of bottom profiles ( 4 ), wherein the edge at the wing ( 1 ) in the unaffected state will be oriented with the chord against the rotor ( 5 ). The deflection angle of the chord is marked with α. This deflection can occur in the embodiments, where lamellas ( 3 ) are omitted or are located below the longitudinal wing ( 2 ). Hereby the edge positioned wing ( 1 ), the gable wing ( 9 ) and possibly the longitudinal wing ( 2 ) are formed in a single unit. 
       FIGS. 13A and 13B  show examples of the invention in relation to any previously described embodiment, wherein the edge positioned wing ( 1 ) may be deflected around a suspension point located along the edge positioned wing chord from the wing edge nearest the rotor ( 5 ) to an arbitrary point along the edge positioned wing chord behind the rotor ( 5 ). The deflection can be fixed or loosely hung and thus made dependent on the flow&#39;s effect on the edge positioned wing ( 1 ), in which this chord have a tangential characteristic in relation to the rotor ( 5 ). 
       FIG. 14  shows examples of a number of possible shapes of the edge positioned wing ( 1 ). The chord is indicated by dotted line. 
       FIG. 14A  shows a completely flat wing. 
       FIG. 14B  shows an oval wing. 
       FIG. 14C  shows a prism-shaped wing. 
       FIG. 14D  shows a teardrop-shaped wing. 
       FIG. 14E  shows a hybrid between round and sharp edged wing. 
       FIG. 14F  shows an oblong, rounded wings. 
       FIG. 14G  shows an oval, teardrop-shaped wing. 
       FIG. 14H  shows a wing with broad, flat base integral of the longitudinal wing ( 2 ) of the edge positioned wing ( 1 ). 
       FIG. 14   i  shows a wing with broad, rounded, convex base integral the longitudinal wing ( 2 ) of the edge positioned wing ( 1 ). 
       FIG. 14   j  shows a wing with a broad concave base integral of the longitudinal wing ( 2 ) of the edge positioned wing ( 1 ). 
     FIGS.  14 A 1  to  14 J 4  show further embodiments of the aforementioned designs. Notation  1  indicates massive embodiments. Notation  2  indicates perforated embodiments. Notation  3  indicates edge riffled embodiments. Notation  4  shows square, perforated performance forms. 
       FIGS. 15A to 15C  show the invention fully embedded in the roof, where only the edge positioned wing ( 1 ) is above the ridge. The longitudinal wing ( 2 ) is shown in a preferred embodiment in which it is designed to follow the shape of the remaining roof structure. The embodiment is designed in such a way that the transmission housing ( 6 ) is made part of the roof, by which transmission can be serviced from below the ceiling. The turbine flow channel ( 8 ) is asymmetrically adapted to the rotor of the Banki/Ossberger or similar vertical rotor type. The Geometry of the upper side of the longitudinal wing ( 2 ) is adapted the ridge of the roof and is both concave and convex. The edges of the lamellas/gable profiles ( 3 ) follow the contours of the wings ( 1 ) and ( 2 ). 
     The number of turbines flow channels ( 8 ) is here multiplied up to four, but can in principle be reduced to one or increased in infinite numbers. In each turbine flow channel ( 8 ) a separate rotor is located. The rotors ( 5 ) are mutually connected via a common shaft with bearing in gable profiles ( 3 ). Rotational energy is transferred through the shaft in the transmission housings ( 6 ), where it converted to electrical, mechanical or hydraulic energy. The turbines flow channels ( 8 ) can be equipped with turbine inlet lamellas ( 12 ) as shown in  FIGS. 3A and 3B . 
       FIG. 15A  shows the embodiment in cross section. 
       FIG. 15B  shows the embodiment in perspective. 
       FIG. 15C  shows the embodiment integrated into a building. 
       FIGS. 16A and 16B  show the invention in an embodiment similar to the principles in  FIG. 1B . 
       FIG. 16A  shows the invention in cross section. 
       FIG. 16B  shows the invention integrated into the roof of a building. 
       FIG. 17  shows the invention in cascading style similar to  FIG. 8C , where the invention in relation to  FIGS. 1A-1F ,  2 A- 2 D,  3 ,  4 A- 4 B and all the intermediate forms, is mounted on a high-rise building. The invention is suitable for mounting on all building corners.