Patent Document

CROSS-REFERENCE TO RELATED APPLICATIONS 
       [0001]    This application claims priority pursuant to 35 U.S.C. 119(e) to co-pending U.S. Provisional Patent Application Ser. No. 60/952,261, filed Jul. 27, 2007, the entire disclosure of which is incorporated herein by reference. 
     
    
     FIELD OF THE INVENTION 
       [0002]    The invention relates generally to a rotor for helicopters and autogiros, a propeller for aircraft propulsion or a propeller for power generation in a turbine or windmill, and relates specifically to a propeller with delta-shaped blades, capable of having pitch adjusted by torsion bars, and optionally of variable sweep and aspect ratio. 
       BACKGROUND OF THE INVENTION 
       [0003]    Rhomboid-shaped wings are known in the art (see Ref (1-4)). The rhomboid wing gets its name from the diamond shape formed by the wings on both sides of an aircraft fuselage. These are excellent examples of designs with unique aero-structural features that have the ability to match mission requirements, and provide superior flight performance. These studies show some unique capabilities of the rhomboid wing, specifically superior aeroelastic properties. 
         [0004]    Many efforts have been made with good results to support these thoughts, Ref (5-26). Efforts began at Saint Louis University—Parks College with water tunnel studies of a rhomboid wing to acquire flow visualization data for a proposal to AFRL. The Parks data showed interesting results suggesting that a flow reversal might occur at high angles of attack, Ref (27-29). A MS Thesis followed to study the flows more closely. That work, Ref (30), showed no flow reversal, and indicated no stall to a much higher angle of attack than did the prior work. Another MS thesis, Ref (31), evaluated the buffet properties of a more complete model where the rhomboid wing was mated to a stylized fighter type of fuselage. That study showed no stall to 55 degrees, and a much more muted vortex flow than found on the F-15 and F/A-18 fighters. While the thesis was still pending, a paper, Ref (32), was published. Next, the applicant embarked on work with Variable Geometry Rhomboid Wings, Ref (33-34). 
         [0005]    In addition to the Rhomboid wing design, the Applicant worked in parallel with the use of torsion bars in straight wings for control of wing twist. This provided a means to alter the loads on the wings, thus controlling maneuvering. The applicant made the surprising discovery that the torsion bar wing-warping technique enhanced the ability to control aeroelasticity to adjust lift to drag ratio, control flutter and gust and buffet response, Ref (35-37). Because of the synergism of the rhomboid wings and wings with torsion bars, the applicant merged those two ideas, and was issued a US patent, Ref (40) (see also Ref (38-39)). The aeroelastic and flutter properties of the rhomboid wing design were extensively studied, Ref (41-43). 
         [0006]    The applicant also has extensive experience with windmills and propellers (see Ref (44-48)). The applicant concluded that current wind turbine and aircraft propulsion propeller blade models often have some serious disadvantages. For example, in helicopters and propeller aircraft, the rotors and propellers must rotate at a very high rotational speed in order to produce sufficient lift and thrust. These high rotational speeds result in greater vibrational forces. Wind turbines have similar problems with vibrational forces because of the high wind speeds needed to turn the blades. These high rotational speeds also result in a great amount of noise. A second problem with the current propeller blade models is the fragile nature of the blade designs. Current blades are long and slender and vulnerable to damage from foreign objects (e.g. gunfire). 
         [0007]    The applicant made the surprising discovery that the rhomboid wing design could be employed as a propeller blade to fill a long-felt and unmet need in the art of propellers and rotors. 
       SUMMARY OF THE INVENTION 
       [0008]    The present invention relates to a concept for using the rhomboid wing as a propeller or rotor. The invention can be employed in (a) conventional propeller aircraft, (b) helicopters and autogiros, and (c) wind turbines and windmills. A rhomboid wing, as used in a propeller application, actually requires only one half (one side of the fuselage) of the traditional rhomboid wing design. Therefore, throughout this application, the applicant refers to the unique blade configuration of this invention as a delta blade system. 
         [0009]    The invention combines use of torsion bars to achieve desirable control of wing twist, with the delta blade system, in a propeller application. It uses wing twist to control the air loading on the craft; hence better control of maneuvering is achieved. It also provides all of the advantages of variable geometry wings. Compared to traditional propeller blade configurations, the invention boasts improved performance and enhanced aeroelastic properties. The invention is a far more efficient system providing economic advantages, higher speeds, and more durable designs. 
         [0010]    The foregoing and other objects are intended to be illustrative of the invention and are not meant in a limiting sense. Many possible embodiments of the invention may be made and will be readily evident upon a study of the following specification and accompanying drawings comprising a part thereof. Various features and subcombinations of invention may be employed without reference to other features and subcombinations. Other objects and advantages of this invention will become apparent from the following description taken in connection with the accompanying drawings, wherein is set forth by way of illustration and example, an embodiment of this invention and various features thereof. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWING 
         [0011]    A preferred embodiment of the invention, illustrative of the best mode in which the applicant has contemplated applying the principles, is set forth in the following description and is shown in the drawings and is particularly and distinctly pointed out and set forth in the appended claims. 
           [0012]      FIG. 1  depicts one side of a two delta blade system propeller of the instant invention. This drawing shows a single torsion bar extending from the hub at the root to the spherical joint at the tip. 
           [0013]      FIG. 2  depicts one side of a two delta blade system propeller of the instant invention. This drawing shows a torsion bar in each of the leading blade and the trailing blade. 
           [0014]      FIG. 3  depicts one side of a two delta blade system propeller of the instant invention. The torsion bar or bars are not visible in this drawing. 
           [0015]      FIG. 4  depicts one manner of connecting the torsion bar system to the hub, utilizing a crown gear, a bevel gear and a bevel gear support. 
           [0016]      FIG. 5  depicts an alternative manner of connecting the torsion bar system to the hub, utilizing a gear and bearing. 
           [0017]      FIG. 6  depicts a two delta blade system propeller of the instant invention as used on a helicopter. 
           [0018]      FIG. 7  depicts the two delta blade system of  FIG. 6  with the helicopter vehicle removed. 
           [0019]      FIG. 8  depicts a three delta blade system propeller of the instant invention as used in a wind turbine, electricity generation, application. 
           [0020]      FIG. 9  depicts a control loop for a propeller of the instant invention. The control loop shows how blade angle and orientation with respect to fluid flow direction should be modified based on various inputs such as wind speed and rotational frequency. 
           [0021]      FIG. 10  concentric torsion bars with servo-motors within a blade. 
           [0022]      FIG. 11  depicts a spherical bearing as used in a variable geometry delta blade with leading blade, trailing blade, torsion bars, ribs and ribs with a spherical joint at the blade tip. 
       
    
    
     DETAILED DESCRIPTION OF THE INVENTION 
       [0023]    As required, a detailed embodiment of the present invention is disclosed herein; however, it is to be understood that the disclosed embodiment is merely exemplary of the principles of the invention, which may be embodied in various forms. Therefore, specific structural and functional details disclosed herein are not to be interpreted as limiting, but merely as a basis for the claims and as a representative basis for teaching one skilled in the art to variously employ the present invention in virtually any appropriately detailed structure. 
         [0024]    The invention is an improved propeller blade design. It is comprised of a central hub and a plurality of delta blade systems. The hub rotates about an axis. The delta blade systems extend outward radially away from the hub in a plane perpendicular to the hub&#39;s axis of rotation. The invention can incorporate any number of delta blade systems, preferably two or three. Each delta blade system is spaced equidistant from the adjacent delta blade systems. 
         [0025]    Each delta blade system is comprised of a leading blade, a trailing blade, a spherical joint and a torsion bar system. The tip of the leading blade is connected to the tip of the trailing blade via the spherical joint. The spherical joint is connected to the hub via a torsion bar system. 
         [0026]    The roots of the leading blade and the trailing blade are connected to the hub. Throughout this specification and claims, the terms “root” and “proximal end” are used interchangeably. The root of each blade is connected to the hub by any means now known or hereinafter discovered. For example, and not by way of limitation, in one embodiment the root is connected to the hub with a ball joint or universal joint.  FIGS. 4 and 5  show two other alternative embodiments.  FIG. 4  shows a torsion bar ( 46 ) within either the leading blade or the trailing blade connected to the hub via a crown gear ( 40 ), a bevel gear ( 42 ), and bevel gear support ( 44 ). In  FIG. 5 , the torsion bar ( 50 ) is connected to the hub ( 56 ) with a gear ( 52 ) and bearing ( 54 ). One skilled in the art will appreciate that the roots of the blades can be connected to the hub in many different configurations. 
         [0027]    The torsion bar system comprises a minimum of one torsion bar, preferably a plurality of torsion bars.  FIG. 1  depicts the invention with a single torsion bar system with the torsion bar ( 10 ) extending from the hub ( 12 ) to the spherical joint ( 18 ). Although  FIG. 1  depicts the single torsion bar system with the torsion bar ( 10 ) external to both the leading blade ( 14 ) and the trailing blade ( 16 ), the single torsion bar ( 10 ) could alternatively be located within either the leading blade ( 14 ) or the trailing blade ( 16 ). 
         [0028]    The torsion bar system may comprise several torsion bars.  FIG. 2  shows a torsion bar system with two torsion bars ( 20 ). In  FIG. 2 , the two torsion bars ( 20 ) extend from the hub ( 22 ) to the spherical joint ( 28 ); one along the leading blade ( 24 ) and the other along the trailing blade ( 26 ). In  FIG. 3 , the torsion bar system is not visible from the exterior of the delta blade system, although the hub ( 30 ), leading blade ( 32 ), trailing blade ( 34 ) and spherical joint ( 36 ) are shown. 
         [0029]    In one embodiment of the invention, shown in  FIG. 10 , a plurality of torsion bars ( 100 ) of the torsion bar system are configured concentrically. The concentrically configured torsion bars ( 100 ) run along a blade ( 140 ) from tip ( 120 ) to root ( 150 ). In various embodiments of this concentrically configured torsion bar system, the torsion bars ( 100 ) run along the leading blade, along the trailing blade, along both, or along neither (e.g. external to both the leading blade and the trailing blade as in  FIG. 1 ). A servo motor ( 110 ( n )) applies a torque to each torsion bar ( 100 ( n )). The blade ( 140 ) includes a rib ( 130 ) at any point along the length of the blade where additional or differential torque is desired. 
         [0030]    In another embodiment of the invention, shown in  FIG. 11 , the torsion bar system further comprises a spherical bearing ( 250 ).  FIG. 11  shows the spherical bearing ( 250 ) from the side ( 250 ( i )) and front ( 250 ( ii )). The spherical bearing ( 250 ) is mounted in a rib ( 270 ) via a bearing mount ( 260 ). In some cases, the invention includes long torsion bars ( 220 ) that extend from the hub to the spherical joint ( 200 ). A spherical bearing ( 250 ) (or multiple spherical bearings) located along the length of the long torsion bar ( 220 ) reduces binding of the torsion bar system. A torsion bar ( 220 ) with a spherical bearing ( 250 ) can extend in a non-linear path from hub to spherical joint ( 200 ). Because of this, a torsion bar ( 220 ) with a spherical bearing ( 250 ) (or multiple spherical bearings) is used in situations where a linear torsion bar is impractical or impossible. 
         [0031]    The delta blade system of  FIG. 11  includes a leading blade ( 230 ) and a trailing blade ( 240 ) connected to the hub at the root and to each other at the tip, via a spherical joint ( 200 ). Each blade further includes several ribs ( 270 ) and two additional spars ( 210 ) that run parallel to the torsion bar ( 220 ). Each rib ( 270 ) includes a spherical bearing ( 250 ) to prevent binding and aid in torsion rigidity. 
         [0032]    When the spars ( 210 ) deflect together, blade-bending results. When the spars ( 210 ) deflect differentially, torsion results. The torsion bar ( 220 ) is a third spar. Together, the torsion bars, spars and ribs can selectively provide torsion or bending of the blade. 
         [0033]    A torque is applied to one end of the torsion bar system. In a single torsion bar system, a single torque is applied to the root end of the torsion bar. The torque applied at the root of the torsion bar twists the spherical joint at the tip. As the spherical joint twists, the tip of the leading blade (or the tip of the trailing blade or both) twists. As the tip of the leading blade (or the tip of the trailing blade or both) twists, the angle of attack varies. Thus, by controlling torque applied at the root of the torsion bar system, one can control the angle of attack of the leading blade (or the trailing blade or both). In a torsion bar system with more than one torsion bar, a torque is applied at the root of each torsion bar. The torque or each torque is applied by a servo motor, a hydraulic actuator, any other means for applying a torque to a torsion bar, or some combination thereof. As shown in  FIG. 10 , a servo motor ( 110 ( n )) is located at the root of each torsion bar ( 100 ( n )). 
         [0034]    For example and not by way of limitation, a torsion bar system of one embodiment includes multiple torsion bars configured concentrically in both the leading blade and the trailing blade. A torque is applied at the root of each of the torsion bars. In this embodiment, the leading blade and the trailing blade further include a plurality of ribs located at specific points along their respective lengths, as shown in  FIG. 11 . Each of the ribs is connected to a respective one of the concentrically configured torsion bars as shown in  FIG. 10 . Each torque applied at the root of a different torsion bar controls the angle of attack of one of the leading blade or the trailing blade at a specific point along its length, where the torsion bar connects to a rib. By varying the angles of attack of the two blades at different points along the length, one can experience significantly improved performance, efficiency, and flight control compared to currently employed propeller models. 
         [0035]      FIG. 6  shows a delta blade configuration of an embodiment of the instant invention. In one embodiment of the configuration shown in  FIG. 6 , two delta blades ( 60 ) are used as rotors on a helicopter vehicle ( 64 ). As shown in  FIG. 6 , the helicopter vehicle ( 64 ) includes two delta blades ( 60 ) arrayed opposite each other and connected to a central rotating hub ( 65 ). Each delta blade ( 60 ) includes a leading blade ( 62 ) and a trailing blade ( 68 ) connected to the hub ( 65 ) at the root and to each other at the tip, via a spherical joint ( 63 ). The helicopter vehicle ( 64 ) includes Jet-Thrust for anti-torque control ( 66 ). 
         [0036]    In  FIG. 7 , the blades of the helicopter vehicle are shown removed from the vehicle. Each delta blade includes a leading blade ( 72 ) and a trailing blade ( 74 ) connected to the hub ( 70 ) at the root and to each other at the tip, via a spherical joint ( 76 ). The delta blades may also be used on Autogiros and, in a smaller version, as a propeller or propellers on a propeller aircraft. 
         [0037]      FIG. 8  depicts the delta blade configuration of an embodiment of the instant invention as used in a wind turbine (or windmill) application. In  FIG. 8 , the invention employs three delta blade systems ( 84 ) connected to a central hub ( 82 ). Each of the three delta blades ( 84 ) are equidistant from the other two. Each of the three delta blades includes a leading blade ( 83 ) and a trailing blade ( 85 ) connected to the hub ( 82 ) at the root and to the other at the tip, via a spherical joint ( 81 ). The wind mill shown in  FIG. 8  is erected on a four-legged tower ( 86 ) with a top plate ( 98 ) of the tower. The wind mill includes a transmission ( 90 ), generator ( 92 ), pivot ( 94 ), weather vane ( 96 ) and a lightening rod ( 80 ). 
         [0038]      FIG. 9  depicts a control loop for the wind turbine of  FIG. 8 . The angles of attack of the blades (leading or trailing or both) are controlled by torsion bar systems. The angles of attack are varied depending on a number of factors including wind speed and direction with respect to the axis of rotation of the hub and rotational frequency of the hub and blades. The transmission shown in  FIG. 9  is optional, but preferred. The control loop shown in  FIG. 9  is applicable to wind turbines and is shown to illustrate an example of a preferred control loop. A similar control loop would be applicable for aircraft propeller and helicopter or autogiro rotor applications of this invention, with the generator replaced with an engine. 
         [0039]    In another embodiment of the instant invention, also not shown in the figures, the angle between the leading blade and the trailing blade is variable. The root end of the leading blade (or the trailing blade or both) can be moved to any position along an arc that is concentric with the perimeter of the hub. The arc of possible movement may be located within or external to the hub. An angle may be measured of the leading blade and a line tangential to the arc at the intersection of the leading blade and the arc. That angle is variable between 90 degrees and 180 degrees. In other embodiments, the same is true of the trailing blade and both the leading trailing blade and trailing blade. By controlling the variance of the location of the root of the leading blade (or the trailing blade or both), the sweep and aspect ratio of the delta blade system can be controlled and varied to improve performance, flight control and efficiency in different fluid dynamic conditions. 
         [0040]    In another embodiment, the instant invention is a method of controlling the apparatus described herein. The method comprises the steps of applying a torque to the root end of each of the torsion bars of the torsion bar systems. The torque, or each torque, is applied as described above to control the angle of attack of the leading blade, the trailing blade or both. Each torque is preferably applied to control the angle of attack at a plurality of locations along each of the leading blade and the trailing blade, as described above. In another embodiment, a method of the instant invention further comprises the additional step of applying a lateral force to the root end of the leading blade (or trailing blade or both) such that the sweep and aspect ratio of the delta blade is controllably varied as described above. 
         [0041]    In the foregoing description, certain terms have been used for brevity, clearness and understanding; but no unnecessary limitations are to be implied therefrom beyond the requirements of the prior art, because such terms are used for descriptive purposes and are intended to be broadly construed. Moreover, the description and illustration of the inventions is by way of example, and the scope of the inventions is not limited to the exact details shown or described. 
         [0042]    Although the foregoing detailed description of the present invention has been described by reference to an exemplary embodiment, and the best mode contemplated for carrying out the present invention has been shown and described, it will be understood that certain changes, modification or variations may be made in embodying the above invention, and in the construction thereof, other than those specifically set forth herein, may be achieved by those skilled in the art without departing from the spirit and scope of the invention, and that such changes, modification or variations are to be considered as being within the overall scope of the present invention. Therefore, it is contemplated to cover the present invention and any and all changes, modifications, variations, or equivalents that fall with in the true spirit and scope of the underlying principles disclosed and claimed herein. Consequently, the scope of the present invention is intended to be limited only by the attached claims, all matter contained in the above description and shown in the accompanying drawings shall be interpreted as illustrative and not in a limiting sense. 
         [0043]    Having now described the features, discoveries and principles of the invention, the manner in which the invention is constructed and used, the characteristics of the construction, and advantageous, new and useful results obtained; the new and useful structures, devices, elements, arrangements, parts and combinations, are set forth in the appended claims. 
         [0044]    It is also to be understood that the following claims are intended to cover all of the generic and specific features of the invention herein described, and all statements of the scope of the invention which, as a matter of language, might be said to fall therebetween. 
       REFERENCES 
       [0045]    The following references are cited by number throughout this disclosure. Applicant makes no statement, inferred or direct, regarding the status of these references as prior art. Applicant reserves the right to challenge the veracity of statements made in these references, all of which are incorporated herein by reference in their entireties.
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A., “Use of Torsion Bars for Twist, Air Loads, and Control of Fixed and Variable Geometry Rhomboid Wings,” EAA Air Venture 2004, Oshkosh, Wis., 27 Jul.-2 Aug., 2004   39. Ferman, M. A., “Use of Torsion Bars for Control of Twist, Air Loads, and Aeroelasticity of Fixed and Variable Geometry Rhomboid Wings,” 9th International Conference on Recent Advances in Structural Dynamics, University of Southampton, ISVR, Southampton, UK, 17-19 Jul. 2006   40. Ferman, M. A., “Device and Method of Control of Fixed and Variable Geometry Rhomboid Wings,” U.S. Pat. No. 7,131,611, November 2006.   41. Aguilar, E., “Aeroelastic Analyses and Wind Tunnel Tests of A Rhomboid Joined Wing Model,” M.S. Thesis, Parks College, Saint Louis University, St. Louis, Mo., May 2004   42. Aguilar, E. and Ferman, M. A., “Experimental and Analytical Studies of a Rhomboid Wing Flutter Model,” EAA Air Venture 2004, Oshkosh, Wis., 27 Jul.-2 Aug., 2004   43. Ferman, M. 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Technology Category: 2