General Purpose Propellers, How to Use Them, and Best Uses

Abstract

The present invention relates to a novel universal propeller (1), which differs from an ordinary propeller (1) in that a gear (52) is provided on each rotor blade (30), and the gear (52) is directly and operatively connected to a reference gear (51) of a timing gear (50). The timing gear (50) is operatively connected to a hub gear (12), wherein the hub gear (12) is configured to sense and process an angular velocity ω of the rotational motion of the hub (10). n , and the reference gear (51) and the gear (52) of the rotor blade (30) of the timing gear (50) are designed so that the angular velocity ω of the reference gear (51) r The angular velocity ω of the rotational motion of the hub (10) n For example: ω r / ω n =1±(1 / 2)*(S rot / S r ). Among them, S rot = the size of the gear (52) of the rotor blade (30), and S r = the size of the reference gear (51). The present invention is particularly suitable for wind power generation equipment, hydropower generation equipment, or engines of ships or aircraft.

Description

Technical Field

[0001] The invention relates to a novel universal propeller, comprising a hub rotatably mounted on a shaft, wherein on the hub are two rotor blades arranged opposite one another or at least three rotor blades arranged in a star-shaped configuration relative to one another, wherein on the hub, each rotor blade is arranged at an angle α to the central axis of the shaft at the end of its longitudinal axis so that the longitudinal axis of each rotor blade describes the outer circumferential surface of a right circular cone when rotated through 360°, and wherein the hub comprises a timing gear which enables the rotor blade to rotate about its longitudinal axis.

[0002] The invention also relates to a method for operating such a universal propeller and to advantageous uses. Background Art

[0003] A propeller (from Latin propellere 'to propel') is a machine part of an engine having blades (hereinafter called rotor blades) usually arranged radially (in a star shape) about an axis.

[0004] In fluid dynamics, or aerodynamics, a propeller is used to generate motion in a fluid, or to drive a propeller using a flowing fluid. A typical application of motion in a fluid is a propeller used as a propeller on a ship. In the context of aircraft, propellers are sometimes called air propellers; in the context of helicopters, where propulsion is primarily controlled by lift, the term "rotor" is used. Typical applications of propellers driven by flowing fluids are wind turbines or hydroelectric power plants, which operate according to the same principle, except that, instead of generating power for propulsion or lift (A), they extract power from the air or water flow. A propeller used in this way is also called a thruster.

[0005] The earliest propellers used in wind turbines date back to the 11th century, making them nearly 1,000 years old. Even in current horizontal-axis wind turbines (HAWTs), the drag component (W) of wind energy is lost, leaving only the lift component (A) to generate energy from the airflow. Specifically, to increase power, rotor diameters have become increasingly larger, as, according to the circular equation, doubling rotor blade length quadruples the rotor area. Until the late 1990s, the diameter of recently installed equipment was typically less than 50 meters; since around 2003, it has typically ranged from 60 to 90 meters. By 2018, the average rotor diameter had increased to 118 meters, and the average hub height had risen to 132 meters. A drawback of this development has been an increase in wind turbine damage caused by gusts or storms.

[0006] Compared to HAWT wind turbines, so-called Savonius rotors or vertical axis wind turbines (VAWT) have a much more pronounced design, but only use the drag component (W), thus wasting all lift components (A).

[0007] Many VAWT systems encounter the problem of being able to operate cost-effectively only above a certain wind speed, the so-called start-up speed or cut-in speed. At wind speeds below the start-up speed, the VAWT system enters an idle state, but the control electronics and actuators (e.g., for pitching the rotor blades) still need to be powered, making the system a significant electricity consumer. To address this issue, EP 1 626 176 A2 discloses a wind turbine similar to a Savonius rotor, in which solar energy converters are provided on the vertically arranged rotor blades for converting solar energy into an energy form other than solar energy, preferably into electrical energy. The energy generated by the solar energy converter can advantageously be supplied to the system at low wind speeds, thereby enabling the described system to operate independently of the power grid, even below the start-up speed.

[0008] In the context of VAWT devices, an alternative possible solution to the startup speed problem is to ensure that the rotor blades are aligned as optimally as possible with respect to the wind flow or fluid. To this end, WO 2017 / 187229 A1 discloses a VAWT device comprising a plurality of rotor blades that, on the one hand, are angled 30°-60° relative to the main vertical axis of rotation and, on the other hand, have a special aerodynamic profile designed to generate a so-called "secondary induced flow," which advantageously increases the aerodynamic efficiency of the device. In this case, the rotor blades themselves are rigidly connected to the hub of the VAWT device described therein. In contrast, US Pat. No. 4,355,956 A discloses a VAWT device that also has rotor blades angled with respect to the vertical, but is characterized not by a special profile but by their material composition. The rotor blades described are made of a flexible material and are therefore self-aligning to a certain extent, i.e., they are able to independently change their direction to a certain extent in response to wind pressure and their own restoring forces. Here, the rotor blades are also rigidly connected to the hub of the VAWT device described.

[0009] Furthermore, US 2011 / 0076144 A1 and WO 2014 / 188289 A1 disclose turbines or propellers that provide for mechanical alignment of their rotor blades relative to the wind flow or fluid, respectively. Finally, CN 105863957 A and GB 2495745 A disclose a VAWT device having rotor blades that are angled relative to the vertical axis of rotation, wherein the angle of incidence of the rotor blades can also be mechanically aligned to a certain extent with the wind flow. CN 105863957 A provides for a separate drive, such as, in particular, an electric motor or a pneumatic drive, for varying the angle of incidence of the rotor blades. Finally, GB 2495745 A provides for this purpose a planetary gear that is configured such that, during a 360° rotation of the hub together with the rotor blades arranged thereon, the rotor blades themselves are rotated by 180° relative to the hub about their longitudinal axis. However, the provided gear configuration constrains the size ratio of the gears connected to the rotor blades to the central fixed gear (sun gear) to 2 to 1, which quickly leads to very large gear expansion and, therefore, disadvantageously, to critical hub sizes as the number of rotor blades increases. In some cases, even arrangements with only three rotor blades on the hub can be problematic in prior art gear designs. Summary of the Invention

[0010] Starting from this point, the present invention is based on the object of providing a propeller which is an improvement over the prior art, in particular is more compact than conventional propellers, while allowing the provision of as many rotor blades as possible, preferably utilizing both the lift component (A) and the drag component (W), and is particularly preferably suitable for universal use both for generating energy by wind or water power and as a drive device for ships or aircraft.

[0011] The universal propeller according to the present invention is different from an ordinary propeller in that a gear is provided on each rotor blade, the gear being directly operatively connected to a reference gear of a timing gear, the timing gear being operatively connected to a hub gear, wherein the hub gear is configured to sense and process the angular velocity ω of the rotational motion of the hub n , and the reference gear of the timing gear and the gear of the rotor blade are designed in the following way so that the angular velocity ω of the reference gear r The angular velocity ω of the wheel's rotational motion n The example is as follows: ω r / ω n = 1 ± (1 / 2)*( S rot / S r ), where S rot = size of the rotor blade gear, S r =The size of the base gear.

[0012] In particular in this case, the radius, the diameter and / or the number of teeth of the gear wheel can be used as parameters for determining the size of the respective gear wheel.

[0013] Furthermore, in the context of the present invention, the term "gear" is to be understood as including not only conventional gears with visible implementations of teeth of various shapes and materials, but also so-called "friction gears", i.e. non-sliding gears in contact with each other, which may be made of, for example, rubber, and which are capable of driving each other by frictional engagement.

[0014] Because the reference gear of the timing gear and the gears of the rotor blades are designed according to the formula given above, unlike the prior art, it is advantageously possible to dispense with the provision of a guide wheel between the reference gear in the timing gear and the gears of the rotor blades, thereby achieving a direct operative connection between the reference gear and the gears of the rotor blades. This results in a more compact hub design. Secondly, compared to the prior art, the interaction between the timing gear and the hub gear according to the formula given above advantageously makes it possible to dispense with dimensional specifications regarding the gears used in the timing gear (i.e., the reference gear and the gears of the rotor blades). This not only allows for the arrangement of more than three rotor blades on the hub, but also results in a compact, robust, and flexible hub design. Consequently, the number of rotor blades actually arranged on the hub of a universal propeller constructed according to the present invention can be advantageously adapted to the respective application, particularly in wind turbines, hydroelectric power plants, or engines for ships or aircraft.

[0015] Furthermore, since the longitudinal axis of each rotor blade describes the outer circumferential surface of a right circular cone when rotated through 360°, a propeller of compact design is provided in which each rotor blade can alternately utilize a lift component (A) and a drag component (W) when rotating along the outer circumferential surface of the right circular cone.

[0016] In a first refinement of the invention, the reference gear can be arranged in the center of the timing gear and surrounded by the gears of the rotor blades. In the case of this "internal configuration", the reference gear and the gears of the rotor blades can preferably be designed in such a way that the angular velocity ω of the reference gear is r The angular velocity ω of the wheel hub's rotational motion n For example: ω r / ω n = 1 + (1 / 2)*( S rot / S r ), where S rot = the size of the rotor blade gear, and S r= the size of the reference gear. This "internal configuration" advantageously provides for the selection of various gear combinations with different sizes of reference gears and rotor blade gears, and allows for the installation of multiple rotor blades on the hub. The specific size ratio of the reference gear to the gears of the selected rotor blades can be determined based on the above-described variation of the formula according to the present invention and the number of selected rotor blades. In this "internal configuration," the reference gear rotates faster than the hub.

[0017] Alternatively, in a refinement of the invention, a reference gear (preferably implemented as a planetary gear, ring gear or crown gear) can be arranged outside the center of the timing gear and thus surround the gears of the rotor blades. In the case of this "external configuration", the reference gear and the gears of the rotor blades can preferably be designed in such a way that the angular velocity ω of the reference gear is r The angular velocity ω of the wheel's rotational motion n The example is as follows: ω r / ω n = 1 - (1 / 2)*( S rot / S r ), where S rot = the size of the rotor blade gear, and S r = the size of the reference gear. This "external configuration" offers the same flexibility as the "internal configuration" in terms of the number of rotor blades and possible gear combinations, but also results in less wear or loss of the gears. According to the above-described variation of the formula according to the present invention, the reference gear in the "external configuration" rotates slower than the hub.

[0018] In a further development of the invention, the longitudinal axis of each rotor blade can be arranged at an angle α of between 30° and 60°, or between 35° and 55°, or between 40° and 50° relative to the central axis of the shaft. According to the invention, an angle of 45° has proven to be preferred, which advantageously maximizes the simultaneous utilization of the lift component (A) and the drag component (W).

[0019] In this regard, it has proven useful if, when the hub rotates about the axis, at a first transition point (T1), each rotor blade is aligned with a vertical plane (x, z) relative to a three-dimensional coordinate system (x, y, z) of the universal propeller. This alignment of the rotor blades with the vertical plane, preferably perpendicular to the air or water flow, advantageously utilizes the (theoretical) maximum value of the drag component (W).

[0020] In this case, at the first transition point (T1), the longitudinal axis of each rotor blade may have a vertical deviation of up to + / - 15° in the vertical plane (x, z).

[0021] Furthermore, it has proven useful if, when the hub rotates about the axis, at a third transition point (T3), each rotor blade is aligned with a horizontal plane (x, y) relative to the three-dimensional coordinate system (x, y, z) of the universal propeller. This alignment of the rotor blades with the horizontal plane, preferably parallel to the air or water flow, advantageously utilizes the (theoretical) maximum value of the lift component (A).

[0022] In this case, at the third transition point (T3), the longitudinal axis of each rotor blade may have a horizontal deviation of up to + / - 15° out of the horizontal plane (x, y).

[0023] In a further preferred development of the invention, it has proven useful if each rotor blade (at least partially) has two substantially flat upper sides.

[0024] The substantially flat upper side advantageously allows solar cells to be arranged thereon for additionally generating electricity from solar energy.

[0025] In another preferred development of the invention, it has proven useful if the side edge of each rotor blade is rounded or conical. Rounded or conical side edges have the advantage of reducing or minimizing the drag coefficient.

[0026] To prevent performance degradation due to rotor blade vibrations, it has proven useful to connect adjacent and / or opposing rotor blades to one another via cables. In this case, the cables can be attached to the rotor blades between a central location and an end location, preferably in the region of or adjacent to their rotor blade tips. Such cables advantageously provide additional stability, support, and strength to the rotor blades.

[0027] The present invention is particularly suitable for mounting arrangements in which the central axis of the shaft forms an angle ß between 0° and 360°, preferably 45°, relative to the horizontal (X) of the mounting coordinate system (X, Y, Z) associated with the universal propeller. An arrangement with an angle ß = 45° advantageously enables the universal propeller according to the present invention to be mounted on a hilltop, on a sloped or flat roof, or even on a building wall or similar vertical surface. However, even in conventional mast-mounted arrangements, the arrangement of the central axis of the shaft at an angle ß = 45° advantageously enables the universal propeller according to the present invention to be mounted away from the mast, thereby advantageously avoiding damage or breakage of the rotor blades on the mast, which can frequently occur, particularly in known HAWT installations during strong or severe winds.

[0028] The invention further relates to a method for operating a universal propeller as described above, wherein the rotation of the rotor blades about their longitudinal axis is effected synchronously with the rotation of the rotor blades through 360° along the outer circumferential surface of the cone by means of a gear mechanism.

[0029] In a refinement of this method, it has proven useful if the rotor blades rotate about their longitudinal axes at half the speed at which they rotate along the outer circumference of the cone through 360°. This allows the rotor blades to rotate along the outer circumference of the cone in sync with the rotation speed of the hub or the propeller as a whole. Conversely, the rotor blades rotate about their longitudinal axes, preferably in the opposite direction to the direction at which they rotate along the outer circumference of the cone through 360°. This has the advantage that the rotor blades are constantly aligned to utilize the maximum lift (A) or drag (W) component as they rotate along the outer circumference of the cone through 360°.

[0030] The invention is particularly suitable for advantageous applications, for example in wind power plants, hydro power plants or engines for ships or aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Additional details and further advantages of the invention are described below on the basis of preferred exemplary embodiments in conjunction with the drawings, without, however, restricting the invention thereto.

[0032] In the schematic:

[0033] Figure 1 A perspective view of a universal propeller is shown;

[0034] Figure 2 Shown Figure 1 Side view of the universal propeller;

[0035] Figure 3 The cone generated by the rotation of each rotor blade is shown, with four transition points T1 , T2 , T3 and T4 selected as an example;

[0036] Figure 4 shows a side view of a generic propeller having rounded rotor blade tips;

[0037] Figure 5An overview of conceivable rotor blade profiles is shown, wherein a) shows an example of a substantially rectangular rotor blade; b) shows an example of a rotor blade with rounded side edges; c) shows an example of a substantially rhombus-shaped rotor blade with similarly rounded side edges; d) shows an example of a rotor blade with a substantially elliptical profile with conical side edges; e) shows an example of a rotor blade with a reinforcement; f) shows another example of a rotor blade with a reinforcement; g) shows another example of a rotor blade with a reinforcement; and h) shows another example of a rotor blade with a reinforcement;

[0038] Figure 6 An exemplary installation situation and specific application of the universal propeller according to the present invention are shown;

[0039] Figure 7 Another exemplary installation situation and specific application of the universal propeller according to the present invention are shown;

[0040] Figure 8 Another exemplary installation situation and specific application of the universal propeller according to the present invention are shown;

[0041] Figure 9 Another exemplary installation situation and specific application of the universal propeller according to the present invention are shown;

[0042] Figure 9a The universal propeller according to the present invention is shown arranged transversely on the facade of a building;

[0043] Figure 9b It shows that the universal propeller according to the present invention is arranged transversely on the sloping roof of a building;

[0044] Figure 9c The universal propeller according to the present invention is shown to be arranged transversely on a flat roof of a building;

[0045] Figure 10 Another exemplary installation situation and specific application of the universal propeller according to the present invention are shown;

[0046] Figure 11 Another exemplary installation situation and specific application of the universal propeller according to the present invention are shown;

[0047] Figure 12 Another exemplary installation situation and specific application of the universal propeller according to the present invention are shown;

[0048] Figure 13 Another exemplary installation situation and specific application of the universal propeller according to the present invention are shown;

[0049] Figure 14Another exemplary installation situation and specific application of the universal propeller according to the present invention are shown;

[0050] Figure 15 Another exemplary installation situation and specific application of the universal propeller according to the present invention are shown;

[0051] Figure 16 Another exemplary installation situation and specific application of the universal propeller according to the present invention are shown;

[0052] Figure 17 Another exemplary installation situation and specific application of the universal propeller according to the present invention are shown;

[0053] Figure 18 Another exemplary installation situation and specific application of the universal propeller according to the present invention are shown;

[0054] Figure 19 An example of a timing gear in the prior art is shown;

[0055] Figure 20 shows in cross-section the improvement of the propeller according to the invention, with the timing gear in the "inner configuration"; and

[0056] Figure 21 A modification of the propeller according to the invention is shown in cross section, with the timing gear in an "external configuration". DETAILED DESCRIPTION

[0057] In the following description of preferred embodiments of the present invention, the same or comparable components are denoted by the same reference numerals.

[0058] Figure 1 A perspective view of a universal propeller 1 is shown. The universal propeller 1 shown comprises a hub 10 rotatably mounted on a shaft 20. Hub 10 is provided with either two rotor blades 30 arranged opposite one another or at least three rotor blades 30 arranged relative to one another in a star-shaped configuration. A particularly preferred exemplary embodiment is shown, which has four rotor blades 30 arranged in a star-shaped configuration. According to the invention, each rotor blade 30 is arranged on hub 10 at the end of its longitudinal axis 31 at an angle α relative to the central axis 21 of shaft 20 such that the longitudinal axis 31 of each rotor blade 30 describes the outer circumferential surface 71 of a right circular cone 70 when rotated through 360°.

[0059] Figure 2 Shown Figure 1A side view of a universal propeller 1 is shown. As can be seen, due to the fact that the longitudinal axis 31 of each rotor blade 30 describes the outer peripheral surface 71 of a right circular cone 70 when rotated through 360°, a propeller 1 of compact design is provided, wherein each rotor blade 30 can alternately utilize a lift component A and a drag component W (indicated by bold arrows) when rotating along the outer peripheral surface of the right circular cone.

[0060] In a refinement of the invention, the longitudinal axis 31 of each rotor blade 30 can be arranged at an angle α of between 30° and 60°, or between 35° and 55°, or between 40° and 50° relative to the central axis 21 of the shaft 20. According to the invention, as shown, an arrangement of 45° has proven to be preferred, which advantageously maximizes the simultaneous utilization of the lift component A and the drag component W.

[0061] In this regard, it has proven useful if, when the hub 10 rotates about the axis 20, at a first transition point T1, each rotor blade 30 is aligned with a vertical plane (x, z) of a three-dimensional coordinate system (x, y, z) associated with the universal propeller 1. The alignment of the rotor blades 30 with the vertical plane, preferably perpendicular to the air or water flow, advantageously utilizes the drag component W at its (theoretical) maximum value.

[0062] In this case, at the first transition point T1 , the longitudinal axis 31 of each rotor blade 30 may have a vertical deviation (not shown) of up to + / −15° in the vertical plane (x, z).

[0063] Furthermore, it has proven useful if, when the hub 10 rotates about the axis 20, at the third transition point T3, each rotor blade 30 is aligned with a horizontal plane (x, y) of a three-dimensional coordinate system (x, y, z) associated with the universal propeller 1. The alignment of the rotor blades 30 with the horizontal plane, preferably parallel to the air or water flow, advantageously utilizes the lift component A at its (theoretical) maximum value.

[0064] In this case, at the third transition point T3 the longitudinal axis 31 of each rotor blade 30 may have a horizontal deviation (not shown) of up to + / - 15° outside the horizontal plane (x, y).

[0065] In order to avoid performance degradation due to vibrations of the rotor blades 30, it has proven useful if rotor blades 30 that are adjacent to and / or opposite one another are connected to one another by cables 40. In this case, the cables 40 can be attached between a central position and an end position of the rotor blades 30, preferably in the region of or adjacent to the rotor blade tips 34 of the rotor blades 30. Such cables 40 advantageously provide the rotor blades 30 with additional stability, support, and strength.

[0066] Figure 3 The cone 70 generated by the rotation of each rotor blade 30 is shown, with four transition points T1, T2, T3, and T4 selected as examples. As is well known, a cone is a geometric object formed when all points of a finite, continuous surface lying in a plane are connected by straight lines to a vertex 72 outside the plane. If the surface is a circular disk 73 (as is the case here), the object is called a cone 70. If the vertex 72 is perpendicular to the disk 73 (as is the case here), the object is called a right circular cone 70. In the case of the universal propeller 1 according to the present invention, the vertex 72 is formed by the hub 10.

[0067] This improvement of the universal propeller 1 has the advantage that when the rotor blades 30 pass through the selected transition points T1 to T4, they have (not only but at least theoretically) the following drag W and lift A values:

[0068]

[0069] Figure 4 A side view of a universal propeller 1 with rounded rotor blade tips 34 is shown. It has proven useful if each rotor blade 30 (at least partially) has two substantially flat upper sides 32. The substantially flat upper sides 32 advantageously allow solar cells to be arranged thereon for additionally generating electricity from solar energy (not shown). A timing gear 50 (not shown here in a functionally accurate manner or to scale) is also provided to enable the rotor blades 30 to rotate about their longitudinal axes 31. A more detailed explanation of the timing gear 50 according to the invention, based on two improved examples, can be found in Figures 19 to 21 Found in the description.

[0070] The method for operating the universal propeller 1 as described above is characterized in that by means of the timing gear 50 (in Figure 4 and Figure 8 The rotation of the rotor blade 30 about its longitudinal axis 31 is carried out synchronously with the rotation of the rotor blade 30 through 360° along the outer circumferential surface 71 of the cone 70 ).

[0071] In a refinement of the method, it has proven useful if the speed of rotation of the rotor blade 30 about its longitudinal axis 31 is half the speed of rotation of the rotor blade along the outer circumferential surface 71 of the cone 70 over 360°. Thus, the speed of rotation of the rotor blade 30 along the outer circumferential surface 71 of the cone 70 is synchronized with the speed of rotation of the hub 10 or the propeller 1 in general as a whole. Instead, the rotor blade 30 is rotated about its longitudinal axis 31, preferably in the opposite direction to the direction of rotation of the rotor blade 30 along the outer circumferential surface 71 of the cone 70 over 360° (the direction of rotation of the rotor blade 30 and the direction of rotation of the hub 10 are determined by Figure 2 This has the advantage that the rotor blade 30 is always aligned to utilize the maximum lift component A or drag component W as it rotates through 360° along the outer circumferential surface 71 of the cone 70 .

[0072] Figure 5 An overview of a preferred rotor blade profile is shown. Figure 5 A generally rectangular rotor blade 30 is shown in FIG. Figure 5 The rotor blade shown in b) differs from this in that it has rounded side edges 33. In contrast, Figure 5 Figure c) shows a generally diamond-shaped rotor blade 30 with similarly rounded side edges 33. Finally, Figure 5 d) shows a rotor blade 30 having a substantially elliptical profile with conical side edges 33. The rounded or conical side edges 33 have the advantage of reducing or minimizing the drag coefficient. In addition, ultra-flat rotor blades 30 can also be used. Figure 5 e) to h) show different embodiments, in which reinforcements 35 can be provided in the center and / or at the ends of the rotor blade 30 for stability. Figure 5 The rotor blades 30 shown in a) to h) can be made of known composite fiber materials. Alternatively, in particular Figure 5 In the case of rotor blades 30 shown in e) to h), textile materials which are tensioned by reinforcement elements 35 are also suitable.

[0073] The invention is particularly suitable for advantageous applications, such as in wind power plants ( Figures 6 to 9 )、Hydroelectric power generation equipment( Figures 10 to 14 ) or ship ( Figure 15 ) or aircraft ( Figures 16 to 18 In this case, a suitable mounting arrangement is one in which the central axis 21 of the shaft 20 makes an angle of between 0° and 360°, preferably 45°, relative to the horizontal.

[0074] Figure 6A preferred mounting arrangement for two universal propellers 1 as part of a tandem wind turbine is shown. A mast 81 can be seen rising from the ground 80 along a vertical line Z of an installation coordinate system (X, Y, Z) associated with the universal propeller 1. The mast 81 carries two generators 60 for generating electricity, each driven by the hub 10 of the universal propeller 1 according to the invention. In this case, the central axis 21 (not shown) of the shaft 20 is positioned away from the mast 81 at a preferred angle of ß = 45° relative to the horizontal X. To synchronize the rotation of the rotor blades 30 about their longitudinal axis 31, the rotation of the rotor blades 30 through 360° along the outer circumferential surface 71 of the cone 70, and / or the drive of the generators 60, can be provided, for example, in the hub 10 itself (see FIG. 2 ). Figure 4 ) or between the hub 10 and the generator 60, one or more timing gears 50 are provided (at Figure 4 and Figure 8 are not shown in a functionally accurate manner or to scale).

[0075] Figure 7 The preferred mounting arrangement of four universal propellers 1 as part of a quattro wind turbine is shown. Obviously, the universal propellers 1 are grouped in a star configuration so that the forces acting on the mast 81 due to the lift component A and the drag component W are as balanced as possible. Further details are as follows Figure 6 shown.

[0076] Figure 8 A preferred installation arrangement of two universal propellers 1 as part of a tandem wind turbine is shown, wherein a common generator 60 is driven via a timing gear 50 and is not arranged on a mast 81 but on the ground 80 (not shown here in a functionally accurate manner or to scale).

[0077] Of course, a single universal propeller 1 according to the present invention may also be provided at the end of a mast 81, in particular a mobile phone base station mast ( Figure 9 ). In this case, the center axis 21 of the shaft 20 (not shown) is arranged at the end of the mast 81 at a preferred angle β=90° relative to the horizontal line X.

[0078] Figures 9a to 9c A further preferred mounting arrangement of individual universal propellers 1 on various buildings 82 is shown.

[0079] from Figure 9aIt can be seen that the universal propeller 1 according to the invention can be arranged transversely on the front 821 of the building 82. In this case, the central axis 21 of the shaft 20 (not shown) is arranged away from the front 821 of the building 82 and is angled relative to the horizontal line X at a preferred angle β = 45°.

[0080] Alternatively or additionally, the universal propeller 1 according to the present invention may also be arranged on the sloping roof 822 ( Figure 9b ) or flat roof 823 ( Figure 9c In this case, the center axis 21 (not shown) of the shaft 20 is arranged on the roof 822 or roof 823 of the building 82 at an angle β preferably between 45° and 90° relative to the horizontal line X.

[0081] Figure 10 A preferred installation arrangement for a universal propeller 1 as part of a hydroelectric power plant is shown. It can be seen how the universal propeller 1 according to the invention is mounted on a bearing 84 anchored in the bed 831 of a body of water 83. The arrangement can preferably be configured such that, at the transition point T1 shown, the rotor blade 30 with the highest resistance component W relative to the water flow is completely submerged in the body of water 83, while the remaining rotor blades 30 (at least partially or preferably completely) rotate outside the water level 832. The body of water 83 can be a river, a channel, or other flowing body of water, such as the outlet of a dam or the penstock of a hydroelectric power station.

[0082] Figure 11 The preferred mounting arrangement of two universal propellers 1 as part of a tandem hydroelectric power plant is shown, wherein each universal propeller 1 has a separate bearing 84. Further details are as follows Figure 10 shown.

[0083] Figure 12 A preferred mounting arrangement of two common propellers 1 as part of a tandem hydroelectric installation is shown, wherein the arrangement has a common load-bearing mast 85 anchored in the bed 831 of the body of water. Further details are again as Figure 10 shown.

[0084] Figure 13 Shown Figure 11 The tandem hydroelectric power plant is preferably arranged below the bridge 86, and the bearing 84 can be part of the bridge pier 861. Further details are again as Figure 10 shown.

[0085] Figure 14 An alternative tandem hydroelectric device is shown having bearings 84 disposed below the bridge element 862. Further details are shown in FIG. Figure 10 shown.

[0086] Figure 15 The preferred use of two universal propellers 1 as engines for a boat 87 is shown. Unlike in power generation applications, the shaft 20 of each universal propeller 1 is now driven by a motor 90 (not shown here) or similar drive device. It will be appreciated that the drive device rotates the universal propellers 1 in such a way that, when the boat is traveling straight, all forces acting on the boat 87 are balanced by the universal propellers 1.

[0087] Figure 16 The preferred use of four universal propellers 1 as part of an energy kite 88 is shown. Figure 7 In the exemplary embodiment of FIG, universal propellers 1 are also grouped in a star configuration, so that the forces acting on energy kite 88 due to lift component A and drag component W are balanced as much as possible. It can be seen how the hub 10 of each universal propeller 1 drives a corresponding generator 60, which is grouped in a star configuration around a central bearing 84, so that the forces of universal propeller 1 are balanced. In other respects, reference can be made to the explanations given above.

[0088] Figure 17 and 18 The preferred use of two universal propellers 1 as engines for an aircraft 89 (a transport drone) is shown. In contrast to the application for power generation, the shaft 20 of each universal propeller 1 is now driven by a motor 90 or similar drive device. It will be understood that the drive device causes the universal propellers 1 to rotate in such a way that when the aircraft is flying straight ahead, all forces acting on the aircraft 89 are balanced by the universal propellers 1. Advantageously, in this case, Figure 17 The aircraft 89 shown does not require additional wings. Instead, the universal propeller 1 can be arranged directly on the outer shell of the aircraft, which has the advantage of making the aircraft 89 very easy to maneuver. Figure 18 In the case of the aircraft 89 shown, short stub wings can be provided for connecting the universal propeller 1 to the outer shell of the aircraft 89 , which advantageously increases the flight stability of the aircraft 89 .

[0089] In the following Figure 19 - 21, the operating principle of the universal propeller 1 according to the present invention is shown based on various improvements and configuration examples, in particular the interaction between the timing gear 50 and the hub gear 12.

[0090] to this end, Figure 19 An example of a timing gear 50 in the related art is shown.

[0091] The example shown here shows a timing gear 50 for controlling five rotor blades 30. For this purpose, in addition to the reference gear 51 and the five gears 52 of the rotor blades 30, five further directional wheels 53 located between the reference gear 51 and the gears 52 must be provided, the directional wheels 53 being used in particular for transmitting power and adjusting the direction of rotation of the gears 52 of the rotor blades 30. It is also necessary to maintain S between the reference gear 51 and the gears 52 of the rotor blades 30. rot / S r = 2 / 1 dimensional relationship, where S rot = size of the gear 52 of the rotor blade 30, S r = the size of the reference gear 51, thereby ensuring that the rotation of the rotor blade 30 about its longitudinal axis 31 is synchronized with the rotation of the rotor blade 30 through 360° along the outer circumferential surface 71 of the cone 70. In the prior art, the above-mentioned design requirements disadvantageously result in a relatively large structure for the hub 10 including such a timing gear 50. Furthermore, arranging multiple large gears 51, 52, 53 in a relatively small hub 10 is often economically unfeasible and technically demanding, and in some configurations, is even technically impossible.

[0092] on the contrary, Figure 20 A cross-section of a modification of the propeller 1 according to the invention is shown, wherein the timing gear 50 is in the so-called "inner configuration".

[0093] As can be seen, the hub 10 includes a timing gear 50 that enables the rotor blades 30 to rotate about their longitudinal axis 31. Provided on each rotor blade 30 is a gear 52 that is directly operatively connected to a reference gear 51 of the timing gear 50. Advantageously, compared to the prior art, a directional wheel 53 is not necessary here. The timing gear 50 is operatively connected to the hub gear 12, which is configured to sense and process the angular velocity ω of the rotational movement of the hub 10. n The operative connection between the timing gear 50 and the hub gear 12 can be achieved in various ways. In this example, the reference gear 51 of the timing gear 50 is operatively connected to the hub gear 12, in particular to one of the gears of the hub gear 12, via a connecting element 511. The hub gear 12 can preferably be designed as a planetary gear or a simple gear.

[0094] In the “inner structure” of the timing gear 50 shown here, a reference gear 51 is arranged in the center of the timing gear 50 and is surrounded by gears 52 of the rotor blade 30 .

[0095] According to the invention, the reference gear 51 and the gear 52 of the rotor blade 30 are designed in such a way that the angular velocity ω of the reference gear 51 is rThe angular velocity ω of the rotational motion of the hub 10 n For example:

[0096] ω r / ω n = 1± (1 / 2)*( S rot / S r ),

[0097] Among them, S rot = size of the gear 52 of the rotor blade 30, S r =The size of the reference gear 51.

[0098] In the case of the “internal construction” of the timing gear 50 shown here, the reference gear 51 and the gear 52 of the rotor blade 30 are preferably designed in such a way that the angular velocity ω of the reference gear 51 is r The angular velocity ω of the rotational motion of the hub 10 n For example:

[0099] ω r / ω n = 1 + (1 / 2)*( S rot / S r ),

[0100] Among them, S rot = size of the gear 52 of the rotor blade 30, S r =The size of the reference gear 51.

[0101] The following table shows the angular velocity ω of the reference gear 51 calculated using the aforementioned modified formula according to the present invention for various gear size combinations: r , and an example of the maximum possible number of rotor blades 30 that can be arranged in corresponding combinations on the hub 10. The angular velocity ω of the rotational movement of the hub 10 n In this case it is set to the value 1 (so ω r The value represents the value relative to ω n relative speed).

[0102]

[0103] According to the table, for example, a size ratio S of 1:1 rot / S r The angular velocity ω of the reference gear 51 is caused by r Angular velocity ω relative to the rotational motion of the hub 10 n=1.5, which can be technically accommodated by selecting a correspondingly designed hub gear 12. In the case of the aforementioned design of the timing gear 50 and hub gear 12 in an "internal configuration" and their interaction, this can be calculated using the formula according to the present invention, for example, a maximum of 4 to 5 rotor blades 30 can be arranged on the hub 10.

[0104] In this case, the above table only represents some theoretically possible combinations, so that advantageously, the design of the timing gear 50 can be freely selected depending on the application.

[0105] at last, Figure 21 A cross-sectional view of a modification of the propeller 1 according to the invention is shown, wherein the timing gear 50 is in an "external configuration".

[0106] and Figure 20 Compared with the "internal structure" shown in FIG, the difference is that here the reference gear 51 (preferably realized as a planetary gear, ring gear or crown gear) is arranged outside the center of the timing gear 50 and then surrounds the gear 52 of the rotor blade 30. Figure 20 The description also applies to this modification accordingly. In this case, the reference gear 51 and the gear 52 of the rotor blade 30 are preferably designed so that the angular velocity ω of the reference gear 51 is r The angular velocity ω of the rotational motion of the hub 10 n For example:

[0107] ω r / ω n = 1 - (1 / 2)*( S rot / S r ),

[0108] Among them, S rot = size of the gear 52 of the rotor blade 30, S r =The size of the reference gear 51.

[0109] The following table shows the angular velocity ω of the reference gear 51 calculated using the aforementioned modified formula according to the present invention for different gear size combinations: r , and an example of the maximum possible number of rotor blades 30 that can be arranged in corresponding combinations on the hub 10. The angular velocity ω of the rotational movement of the hub 10 n In this case it is set to the value 1 (so ω r The value represents the value relative to ω n relative speed).

[0110]

[0111] According to the table, for example, a size ratio S of 1:4 rot / S r The angular velocity ω of the reference gear 51 is caused by r Angular velocity ω relative to the rotational motion of the hub 10 n =0.875, which can be technically accommodated by selecting a correspondingly designed hub gear 12. With the aforementioned design of the timing gear 50 and hub gear 12 in an "external configuration" and their interaction, this can be calculated using the formula according to the present invention, for example, that a maximum of 4 to 6 rotor blades 30 can be arranged on the hub 10.

[0112] In the case of the timing gear 50 of the prior art (see Figure 19 ), the combination of the gear 52 of the rotor blade 30 listed in the last row of the above table is the size S of the reference gear 51 r A combination twice as large is simply not physically (technically) feasible and can at best be achieved with a chain drive or toothed belt drive.

[0113] In this case, the above table again represents only some theoretically possible combinations, so that, advantageously, also in the case of “external configuration”, the design of the timing gear 50 can be freely selected depending on the application.

[0114] The present invention relates to a novel universal propeller 1, which differs from an ordinary propeller 1 in that a gear 52 is provided on each rotor blade 30. The gear 52 is directly operatively connected to the reference gear 51 of the timing gear 50. The timing gear 50 is operatively connected to the hub gear 12. The hub gear 12 is configured to sense and process the angular velocity ω of the rotational motion of the hub 10. n And the reference gear 51 of the timing gear 50 and the gear 52 of the rotor blade 30 are designed so that the angular velocity ω of the reference gear 51 r The angular velocity ω of the rotational motion of the hub 10 n The example is as follows: ω r / ω n = 1 ± (1 / 2)*(S rot / S r ), where S rot = size of the gear 52 of the rotor blade 30, S r =The size of the reference gear 51.

[0115] The present invention is particularly suitable for wind power generation equipment, hydropower generation equipment, or engines of ships or aircraft.

[0116] Reference Signs List

[0117] 1 general propeller

[0118] 10 wheels

[0119] 11 Central axis of wheel hub 10

[0120] 12 hub gears

[0121] 20-axis

[0122] 21 Central axis of shaft 20

[0123] 30 rotor blades

[0124] 31 Longitudinal axis of the rotor blade 30

[0125] 32 Upper side of rotor blade 30

[0126] 33 Side edge of rotor blade 30

[0127] 34 rotor blade tips

[0128] 35 reinforcement

[0129] 40 cable

[0130] 50 timing gear

[0131] 51 reference gear

[0132] 511 connection element

[0133] 52 rotor blade (30) gear

[0134] 53 directional wheels (only in the prior art)

[0135] 60 generators

[0136] 70 cone

[0137] 71 Outer peripheral surface of cone 70

[0138] 72 The vertex of cone 70

[0139] 73 cone 70 disk

[0140] 80 ground

[0141] 81 masts

[0142] 82 buildings

[0143] 821 front

[0144] 822 pitched roof

[0145] 823 flat roof

[0146] 83 water bodies

[0147] 831 Riverbed of water body

[0148] 832 water surface

[0149] 84 bearings

[0150] 85 load-bearing mast

[0151] 86 Bridge

[0152] 861 bridge pier

[0153] 862 bridge element

[0154] 87 ships

[0155] 88 Energy Kite

[0156] 89 aircraft

[0157] 90 engine

[0158] A lift component

[0159] W resistance component

[0160] T1, T2, T3, T4 transition points

[0161] α is the angle between the longitudinal axis 31 and the central axis 21 in the three-dimensional coordinate system of the universal propeller 1

[0162] The angle between the central axis 21 of the β-axis 20 and the horizontal line X in the installation coordinate system of the universal propeller 1 is

[0163] xyz three-dimensional coordinate system of universal propeller 1

[0164] x The first direction of the horizontal plane

[0165] y The second direction of the horizontal or vertical plane

[0166] zThe first direction of the vertical plane

[0167] X, Y, Z universal propeller 1 installation coordinates

[0168] X-horizontal line

[0169] Y horizontal line (perpendicular to X)

[0170] Z vertical line

Claims

1. A universal propeller (1) comprising a hub (10) rotatably mounted on a shaft (20), wherein: On the wheel hub (10), Two rotor blades (30) are provided, and the two rotor blades (30) are arranged opposite to each other; or At least three rotor blades (30) are provided, the at least three rotor blades (30) being arranged in a star-shaped configuration relative to one another, wherein, on the hub (10), each rotor blade (30) is arranged at an angle α relative to the central axis (21) of the shaft (20) at the end of the longitudinal axis (31) of the rotor blade (30) so that the longitudinal axis (31) of each rotor blade (30) describes the outer peripheral surface (71) of a right circular cone (70) when rotated through 360°, wherein the hub (10) comprises a timing gear (50), the timing gear (50) enabling the rotor blade (30) to rotate about the longitudinal axis (31) of the rotor blade (30); Wherein, a gear (52) is provided on each rotor blade (30), and the gear (52) is directly operatively connected to the reference gear (51) of the timing gear (50); And, wherein the timing gear (50) is operatively connected to the hub gear (12), wherein the hub gear (12) is configured to sense and process the angular velocity ω of the rotational motion of the hub (10) n ; It is characterized in that The reference gear (51) is provided at the center of the timing gear (50) and is surrounded by the gear (52) of the rotor blade (30), and The reference gear (51) of the timing gear (50) and the gear (52) of the rotor blade are designed so that the angular velocity ω of the reference gear (51) is r The angular velocity ω of the rotational motion of the hub (10) n The example is as follows: r / ω n = 1 + (1 / 2)*(S rot / S r ), where S rot = the size of the gear (52) of the rotor blade (30), and S r = size of the reference gear (51); or Characterized in that the reference gear (51) is arranged outside the center of the timing gear (50) and further surrounds the gear (52) of the rotor blade (30), and The reference gear (51) of the timing gear (50) and the gear (52) of the rotor blade (30) are designed so that the angular velocity ω of the reference gear (51) is r The angular velocity ω of the rotational motion of the hub (10) n The example is as follows: ω r / ω n = 1 - (1 / 2)*( S rot / S r ), where S rot = the size of the gear (52) of the rotor blade (30), S r = the size of the reference gear (51).

2. The universal propeller (1) according to claim 1, characterized in that The reference gear (51) is arranged outside the center of the timing gear (50) and further surrounds the gear (52) of the rotor blade (30). The reference gear (51) is realized as a planetary gear, a ring gear or a crown gear.

3. The universal propeller (1) according to claim 1 or 2, characterized in that: The longitudinal axis (31) of each rotor blade is arranged at an angle α relative to the central axis (21) of the shaft (20) within the following angular range: Between 30° and 60°.

4. The universal propeller (1) according to claim 1, characterized in that When the hub (10) rotates about the axis (20), at a first transition point (T1), each rotor blade (30) is aligned with a vertical plane (x, z) of a three-dimensional coordinate system (x, y, z) associated with the universal propeller (1).

5. The universal propeller (1) according to claim 4, characterized in that At the first transition point (T1), the longitudinal axis (31) of each rotor blade (30) has a vertical deviation of up to + / - 15° in the vertical plane (x, z).

6. The universal propeller (1) according to claim 1, characterized in that When the hub (10) rotates about the axis (20), at a third transition point (T3), each rotor blade is aligned with a horizontal plane (x, y) of a three-dimensional coordinate system (x, y, z) associated with the universal propeller (1).

7. The universal propeller (1) according to claim 6, characterized in that At the third transition point (T3), the longitudinal axis (31) of each rotor blade (30) has a horizontal deviation of up to + / - 15° out of the horizontal plane (x, y).

8. The universal propeller (1) according to claim 1, characterized in that Each rotor blade (30) has at least partially two substantially planar upper sides (32), wherein solar cells are arranged on the planar upper sides (32) of each rotor blade (30).

9. The universal propeller (1) according to claim 1, characterized in that The side edge (33) of each rotor blade (30) is in the shape of an inverted rounded or conical shape.

10. The universal propeller (1) according to claim 1, characterized in that Mutually adjacent and / or mutually opposite rotor blades (30) are connected to each other by means of cables (40), which are attached to the rotor blades (30) between a center position and an end position.

11. The universal propeller (1) according to claim 1, characterized in that The central axis (21) of the shaft (20) forms an angle between 0° and 360° relative to a horizontal line (X) of an installation coordinate system (X, Y, Z) associated with the universal propeller (1).

12. The universal propeller (1) according to claim 10, characterized in that The cable (40) is attached to the rotor blade (30) in the region of or adjacent to the rotor blade tip (34) of the rotor blade (30).

13. The universal propeller (1) according to claim 11, characterized in that The central axis (21) of the shaft (20) is at 45° relative to a horizontal line (X) of the installation coordinate system (X, Y, Z).

14. The universal propeller (1) according to claim 1, characterized in that The longitudinal axis (31) of each rotor blade is arranged at an angle α relative to the central axis (21) of the shaft (20) within the following angular range: between 35° and 55°.

15. The universal propeller (1) according to claim 1, characterized in that The longitudinal axis (31) of each rotor blade is arranged at an angle α relative to the central axis (21) of the shaft (20) within the following angular range: between 40° and 50°.

16. The universal propeller (1) according to claim 1, characterized in that The angle α between the longitudinal axis (31) of each rotor blade and the central axis (21) of the shaft (20) is set at 45°.

17. A method for operating a universal propeller (1) as claimed in claim 1, wherein: By means of the timing gear (50), the rotation of the rotor blade (30) about the longitudinal axis (31) of the rotor blade (30) is achieved synchronously with the rotation of the rotor blade (30) along the outer peripheral surface (71) of the cone (70) through 360°.

18. The method according to claim 17, wherein The rotational speed of the rotor blade (30) around the longitudinal axis (31) of the rotor blade (30) is half the rotational speed of the rotor blade (30) when rotating along the outer peripheral surface (71) of the cone (70) through 360°.

19. Use of the universal propeller (1) according to claim 1 in a wind power plant, a hydropower plant, or an engine of a ship or an aircraft.

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