Lifting body duct and stratosphere high-altitude power generation device

Abstract

The invention discloses a lifting body duct and a high-altitude power generation device comprising the same, the lifting body duct comprises a duct body, the duct body is a revolving body, the section contour of the duct body is defined by four curves L1, L2, L3 and L4, the revolving axis of the duct body coincides with a straight line y = 0, the curve L1 and the curve L2 are elliptic curves, and the curve L2 and the curve L3 are elliptic curves. The curve L3 and the curve L4 are represented by a Bezier curve, by applying the high-altitude power generation device comprising the lifting body duct, the stability of the high-altitude power generation device can be effectively improved, and the length of a mooring assembly of the high-altitude power generation device is reduced.

Description

Technical Field

[0001] This invention relates to the field of wind power, and in particular to lifting ducts and stratospheric high-altitude power generation devices. Background Technology

[0002] With economic development, modern society's demand for energy, especially clean energy, is increasing, and the wind power industry, as a clean energy source, is also booming. Currently, most wind power installations are located on land or sea surfaces with relatively high wind energy reserves, but due to complex climate environments and frequent airflow changes, their power generation efficiency is not high enough.

[0003] On the other hand, in order to make full use of high-altitude wind energy, a scheme to generate electricity through high-altitude tethered wind power devices has emerged; however, the existing high-altitude tethered floating devices have a low lift-to-drag ratio, resulting in a small angle between the tether rope and the ground, which not only increases the length of the tether rope, but also makes it difficult to ensure the aerodynamic stability of the floating device. Summary of the Invention

[0004] The present invention aims to at least solve one of the technical problems existing in the prior art. To this end, the present invention proposes a lifting duct that can effectively improve the lift-to-drag ratio of the duct.

[0005] The first aspect of the present invention provides a lifting duct, comprising a duct body, wherein the duct body is a body of revolution, and the cross-sectional profile of the duct body is formed by four curve segments L1, L2, L3, and L4. The axis of rotation of the duct body coincides with the straight line y = 0, wherein:

[0006] Curve L1 is an elliptic curve with endpoints (x0, y0) and (x3, y3) respectively. The equation of curve L1 is:

[0007] y=y0+(y3-y0)√(1-(x-x3)^2 / (x3)^2);

[0008] Curve L2 is an elliptic curve with endpoints (x0, y0) and (x1, y1) respectively. The equation of curve L2 is:

[0009] y=y0+(y1-y0)√(1-(x-x1)^2 / (x1)^2);

[0010] Curve L3 is a curve with two endpoints (x1, y1) and (x2, y2) respectively. Curve L3 is represented by a Bezier curve. The characteristic polygon of curve L3 has four vertices: P0, P1, P2 and P3. The coordinates of point P0 are (x1, y1), the coordinates of point P1 are ((2x1+x2) / 3, y1), the coordinates of point P2 are ((x1+2x2) / 3, y2), and the coordinates of point P3 are (x2, y2).

[0011] Curve L4 is a curve with two endpoints (x3, y3) and (x2, y2) respectively. Curve L4 is represented by a Bezier curve. The characteristic polygon of curve L4 has three vertices: Q0, Q1 and Q2. The coordinates of point Q0 are (x3, y3), the coordinates of point Q1 are ((x2+x3) / 2, y3), and the coordinates of point Q2 are (x2, y2).

[0012] in:

[0013] x0=0,y0=16,x1=49.0763938207692,y1=12.65,x2=19.999329488951, y2=19.6741370238314, x3=40.1355074566128, y3=27.0092559933703.

[0014] According to some embodiments of the present invention, curve L1 and curve L3 have a rounded transition section.

[0015] The high-altitude power generation device of the second aspect of the present invention includes: the aforementioned lifting body duct; a generator disposed within the lifting body duct; a drive fan disposed within the lifting body duct, the drive fan being used to drive the generator to rotate; and a mooring assembly connecting the lifting body duct to the ground.

[0016] According to some embodiments of the present invention, the high-altitude power generation device further includes a tail fin assembly disposed on the outside of the duct body.

[0017] According to some embodiments of the present invention, there are multiple tail wing assemblies, and the multiple tail wing assemblies are evenly distributed along the circumference of the duct body.

[0018] According to some embodiments of the present invention, the tail assembly includes: a stabilizer assembly disposed on the outside of the duct body; a control surface assembly rotatably disposed on the stabilizer; and a winglet disposed at the end of the control surface assembly.

[0019] According to some embodiments of the present invention, the high-altitude power generation device further includes an eddy current generator disposed outside the duct body and located in front of the tail fin assembly.

[0020] According to some embodiments of the present invention, the high-altitude power generation device further includes a power turbine disposed at the end of the vortex generator.

[0021] According to some embodiments of the present invention, the drive fan is coaxial with the duct body and the drive fan is located in the throat of the lifting body duct.

[0022] According to some embodiments of the present invention, the culvert body is composed of multiple segments, and the multiple segments are distributed circumferentially along the culvert body.

[0023] According to some embodiments of the present invention, the segment includes: a truss; a rigid shell disposed on the truss, the rigid shell being located on the inner side and / or front side of the truss; and a soft airbag disposed on the truss, the soft airbag being disposed on the outer side of the truss.

[0024] According to some embodiments of the present invention, the rigid shell is located on the inner side and / or front side of the truss, and the soft airbag is located on the outer side of the truss.

[0025] By applying the above-mentioned lifting duct, the lift-to-drag ratio can be effectively improved compared to existing duct configurations.

[0026] Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. Attached Figure Description

[0027] The above and / or additional aspects and advantages of the present invention will become apparent and readily understood from the description of the embodiments taken in conjunction with the following drawings, in which:

[0028] Figure 1 This is a cross-sectional view of the lifting body duct in an embodiment of the present invention;

[0029] Figure 2 This is a schematic diagram of the cross-sectional shape of the lifting body duct in an embodiment of the present invention;

[0030] Figures 3 to 8 This is a schematic diagram of the lift-drag ratio-elevation angle (K-α) curve of the lifting body duct under different wind speeds in an embodiment of the present invention.

[0031] Figure 9 This is an isometric view of the high-altitude power generation device in an embodiment of the present invention;

[0032] Figure 10 This is an isometric view of a portion of the high-altitude power generation device in an embodiment of the present invention;

[0033] Figure 11 for Figure 10 Enlarged view of point A in the middle;

[0034] Figure 12 for Figure 10 Enlarged view of point B in the middle;

[0035] Figure 13 for Figure 12 Enlarged view of point C in the middle;

[0036] Figure 14This is a schematic diagram of the forces acting on the high-altitude power generation device according to an embodiment of the present invention;

[0037] The above figures include the following reference numerals.

[0038] label name 100 duct body 110 Segmentation 200 Power components 210 Eddy current generator 220 Power Turbo 300 Tail wing assembly 310 Stabilizer Module 320 rudder assembly 321 Winglet 400 Tethering components 500 ground Detailed Implementation

[0039] Embodiments of the present invention are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention.

[0040] In the description of this invention, it should be understood that the orientation descriptions, such as up, down, front, back, left, right, etc., are based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting this invention.

[0041] In the description of this invention, "several" means one or more, "multiple" means two or more, "greater than," "less than," and "exceeding" are understood to exclude the stated number, while "above," "below," and "within" are understood to include the stated number. The use of "first" and "second" in the description is merely for distinguishing technical features and should not be construed as indicating or implying relative importance, or implicitly indicating the number of indicated technical features, or implicitly indicating the order of the indicated technical features.

[0042] In the description of this invention, unless otherwise explicitly defined, terms such as "set up," "install," and "connect" should be interpreted broadly, and those skilled in the art can reasonably determine the specific meaning of the above terms in this invention in conjunction with the specific content of the technical solution.

[0043] Reference Figure 1 The lifting duct of this embodiment includes a duct body 100, which is a body of revolution. The cross-sectional profile of the duct body 100 is formed by four curves: L1, L2, L3, and L4. The axis of rotation of the duct body 100 coincides with the straight line y = 0.

[0044] Curve L1 is an elliptic curve with endpoints (x0, y0) and (x3, y3) respectively. The equation of curve L1 is:

[0045] y=y0+(y3-y0)√(1-(x-x3)^2 / (x3)^2);

[0046] Curve L2 is an elliptic curve with endpoints (x0, y0) and (x1, y1) respectively. The equation of curve L2 is:

[0047] y=y0+(y1-y0)√(1-(x-x1)^2 / (x1)^2);

[0048] Curve L3 is a curve with two endpoints (x1, y1) and (x2, y2) respectively. Curve L3 is represented by a Bezier curve. The characteristic polygon of curve L3 has four vertices: P0, P1, P2 and P3. The coordinates of point P0 are (x1, y1), the coordinates of point P1 are ((2x1+x2) / 3, y1), the coordinates of point P2 are ((x1+2x2) / 3, y2), and the coordinates of point P3 are (x2, y2).

[0049] Curve L4 is a curve with two endpoints (x3, y3) and (x2, y2) respectively. Curve L4 is represented by a Bezier curve. The characteristic polygon of curve L4 has three vertices: Q0, Q1 and Q2. The coordinates of point Q0 are (x3, y3), the coordinates of point Q1 are ((x2+x3) / 2, y3), and the coordinates of point Q2 are (x2, y2).

[0050] in:

[0051] x0=0,y0=16,x1=49.0763938207692,y1=12.65,x2=19.999329488951, y2=19.6741370238314, x3=40.1355074566128, y3=27.0092559933703.

[0052] By applying the above-mentioned lifting duct, the lift-to-drag ratio can be effectively improved compared to existing duct configurations.

[0053] Figure 2 The cross-section shown is the body of revolution that constitutes the duct body 100. The yellow part is curve L1, the blue part is curve L2, the red part is curve L3, and the green part is curve L4. Curves L3 and L4 are represented in the form of Bezier curves. According to the relevant content in Chapter 3 of the textbook "Computer-Aided Geometric Modeling Technology", the shape of the Bezier curve can be determined by giving each vertex of the characteristic polygon of the Bezier curve.

[0054] It can be seen that the four curves that constitute the profile of the body of revolution can all be shaped, so the cross-sectional profile can be uniquely determined. By rotating the cross-sectional profile around y=0, that is, the X-axis, the duct body 100 can be formed. At this time, the axis is also the axis of the duct body 100.

[0055] In this embodiment, "inside the duct" refers to the air passage of the duct, and "inside the duct body 100" refers to the interior of the rotating body.

[0056] In this embodiment, in order to better demonstrate the high lift-to-drag ratio effect of the above-mentioned lifting duct configuration, the applicant conducted a simulation experiment on the above-mentioned lifting duct. The table below shows the simulation results when the drag coefficient Cd in the duct is 0.5.

[0057]

[0058]

[0059]

[0060] Figures 2 to 8 The above table shows the K-α curves for speeds of 20m / s, 30m / s, 40m / s, 50m / s, 60m / s, and 75m / s, respectively. It can be seen that when the drag coefficient Cd is 0.5, the lift-to-drag ratio can reach 3.16 at a wind speed of 40m / s and an angle of attack of 6°.

[0061] In addition, the applicant also used a simulation system to simulate the K-α variation relationship when the drag coefficient Cd is 0.3 and 0.1, as shown in the two tables below.

[0062]

[0063]

[0064]

[0065]

[0066]

[0067] like Figure 2 As shown, a rounded transition section can be set between the yellow and green curves as needed to reduce abrupt changes in the airfoil surface.

[0068] like Figure 9 As shown, the high-altitude power generation device of this embodiment includes: the aforementioned lifting body duct; a generator disposed within the lifting body duct; a drive fan disposed within the lifting body duct, the drive fan being used to drive the generator to rotate; and a mooring assembly 400 connecting the lifting body duct to the ground 500.

[0069] like Figure 14The diagram shown is a simplified schematic of the force situation of the entire high-altitude power generation device. The mooring rope of the mooring component 400 is approximated as a straight line segment. When the entire high-altitude power generation device is in a static state, the ratio of lift L to drag D, i.e., the lift-to-drag ratio K, and the angle β between the mooring rope of the mooring component 400 and the ground 500 satisfy K = tan(β). At this time, it is also true that when the height of the duct body 100 is constant, the larger the lift-to-drag ratio, the larger β, and the shorter the length of the mooring rope of the mooring component 400.

[0070] Therefore, the application of high-altitude power generation devices including the aforementioned lifting body duct can effectively improve the stability of high-altitude power generation devices and reduce the length of the mooring parts of high-altitude power generation devices.

[0071] It is worth noting that the drag coefficient Cd is actually the drag coefficient of the drive fan inside the duct, which is related to the wind energy utilization rate of the entire high-altitude power generation device.

[0072] In this embodiment, the high-altitude power generation device is preferably arranged in the lower stratosphere region at an altitude of 9000m-11000m. Since the airflow in the stratosphere is stable throughout the year and is almost unaffected by seasonal and climate changes, the power generation efficiency of the high-altitude power generation device can be effectively improved and its position can be kept relatively stable. For the relevant structure of the high-altitude power generation device and the tethering component 400, please refer to the relevant content disclosed in CN113931797A.

[0073] like Figures 9 to 12 As shown, it also includes a tail fin assembly 300, which is disposed on the outside of the duct body 100.

[0074] The tail fin assembly 300 is provided in multiples and is evenly distributed along the circumference of the duct body 100. Preferably, six tail fin assemblies 300 are arranged. They can be used to adjust the attitude of the duct body 100. At the same time, the tail fin assembly 300 can also increase the lift to a certain extent and further increase the angle β between the tether rope and the ground 500. In addition, the tail fin assembly 300 can also be used to ensure the balance of the entire lifting body duct in the pitch, roll and yaw directions.

[0075] It is worth noting that in actual use, the airflow along Figure 2 As shown, the flow passes through the duct in the positive x-axis direction, therefore Figure 2From the perspective shown, the left side is the inlet and the right side is the outlet. The cross-sectional area at the inlet is smaller than that at the outlet. At this time, the entire lifting duct is also equivalent to a diffuser duct. The driving fan is coaxial with the duct body 100 and is located in the throat of the lifting duct. The throat refers to the position with the smallest cross-sectional area in the duct. In the actual power generation process, after the airflow enters the duct inlet, it is accelerated and the wind speed is the greatest at the throat. After flowing through the driving fan, it is blown out from the outlet, effectively improving the wind energy utilization rate.

[0076] It is worth noting that the drag coefficient Cd in the duct mentioned above is actually the drag coefficient of the drive fan set at the throat of the duct. During the power generation process, a pitch control mechanism can be set on the drive fan to change the drag coefficient Cd by adjusting the pitch of the blades on the drive fan, thereby improving the adaptability to environmental changes (including wind speed, wind shear, etc.).

[0077] It is understandable that the tail assembly 300 can adopt an existing all-moving tail fin or a traditional stabilizer plus control surfaces, such as... Figure 10 , Figure 12 As shown, the tail assembly 300 includes: a stabilizer assembly 310 disposed on the outside of the duct body 100; a control surface assembly 320 rotatably disposed on the stabilizer; and a winglet 321 disposed at the end of the control surface assembly 320. Specifically, the control surface assembly 320 encompasses the wingtip of the tail assembly 300, so in order to reduce wingtip vortices, a winglet 321 is disposed at the end of the control surface assembly 320, i.e., the wingtip.

[0078] like Figure 10 , Figure 11 As shown, the high-altitude power generation device also includes an eddy current generator 210, which is disposed on the outside of the duct body 100 and located in front of the tail fin assembly 300; wherein, the eddy current generator 210 can generate eddy current ratio and transmit it to the displacement assembly to delay boundary layer separation.

[0079] Specifically, the high-altitude power generation device also includes a power turbine 220, which is located at the end of the eddy current generator 210. The power turbine 220 and the eddy current generator 210 together constitute the power assembly 200. Specifically, the structure of the power turbine 220 is similar to that of the duct body 100, the drive fan and the generator. It also includes a small duct located at the end of the eddy current generator 210. The duct includes a drive fan and a motor connected to the drive fan.

[0080] In some embodiments, each tail fin assembly 300 is provided with a vortex generator 210 at its front end, and each vortex generator 210 is provided with a power turbine 220 at its end. During normal power generation, the power turbine 220 can also generate wind power. In case of emergencies such as the tether rope breaking, the attitude of the entire high-altitude power generation device can be adjusted by controlling multiple power turbines 220, so that the high-altitude power generation device can land smoothly in a safe area in an emergency, reducing personal and property losses caused by the fall.

[0081] like Figure 10 As shown, the duct body 100 is composed of multiple segments 110, which are distributed circumferentially along the duct body 100. Specifically, the duct body 100 includes 6 segments 110, which are distributed circumferentially along the duct body 100 and mounted on the truss assembly, while the tail fin assembly 300 and the vortex generator 210 are both mounted on the truss assembly.

[0082] In some embodiments, the segment 110 includes: a truss; a rigid shell disposed on the truss, the rigid shell being located on the inner side and / or front side of the truss; and a soft airbag disposed on the truss, the soft airbag being disposed on the outer side of the truss; wherein, the soft airbag is filled with high-pressure nitrogen, and after inflation, it can better maintain the aerodynamic configuration of the outer side of the duct body 100, while providing a certain lift, further increasing the angle β between the mooring rope and the bottom surface; while the inner surface of the duct serves as an airflow channel, and in order to ensure airflow stability, a rigid shell is required.

[0083] The embodiments of the present invention have been described in detail above with reference to the accompanying drawings. However, the present invention is not limited to the above embodiments. Within the scope of knowledge possessed by those skilled in the art, various changes can be made without departing from the spirit of the present invention.

Claims

1. A lifting duct, characterized in that, Includes a duct body (100), which is a body of revolution. The cross-sectional profile of the duct body (100) is formed by four curves: L1, L2, L3, and L4. The axis of rotation of the duct body (100) coincides with the straight line y = 0. Curve L1 is an elliptic curve with endpoints (x0, y0) and (x3, y3) respectively. The equation of curve L1 is: y=y0+(y3-y0)√(1-(x-x3)^2 / (x3)^2); Curve L2 is an elliptic curve with endpoints (x0, y0) and (x1, y1) respectively. The equation of curve L2 is: y=y0+(y1-y0)√(1-(x-x1)^2 / (x1)^2); Curve L3 is a curve with two endpoints (x1, y1) and (x2, y2) respectively. Curve L3 is represented by a Bezier curve. The characteristic polygon of curve L3 has four vertices: P0, P1, P2 and P3. The coordinates of point P0 are (x1, y1), the coordinates of point P1 are ((2x1+x2) / 3, y1), the coordinates of point P2 are ((x1+2x2) / 3, y2), and the coordinates of point P3 are (x2, y2). Curve L4 is a curve with two endpoints (x3, y3) and (x2, y2) respectively. Curve L4 is represented by a Bezier curve. The characteristic polygon of curve L4 has three vertices: Q0, Q1 and Q2. The coordinates of point Q0 are (x3, y3), the coordinates of point Q1 are ((x2+x3) / 2, y3), and the coordinates of point Q2 are (x2, y2). in: x0=0,y0=16,x1=49.0763938207692,y1=12.65,x2=119.999329488951, y2=19.6741370238314, x3=40.1355074566128, y3=27.0092559933703.

2. The lifting body duct according to claim 1, characterized in that... There is a rounded transition section between curve L1 and curve L3.

3. A high-altitude power generation device, characterized in that, include: The lifting body duct as described in claim 1; The generator is installed inside the lifting body duct. A drive fan is disposed in the lifting body duct, and the drive fan is used to drive the generator to rotate. A mooring assembly (400) connects the lifting body duct to the ground.

4. The high-altitude power generation device according to claim 3, characterized in that, It also includes a tail fin assembly (300) disposed on the outside of the duct body (100).

5. The high-altitude power generation device according to claim 4, characterized in that, There are multiple tail wing assemblies (300), and the multiple tail wing assemblies (300) are evenly distributed along the circumference of the duct body (100).

6. The high-altitude power generation device according to claim 5, characterized in that, The tail fin assembly (300) includes: Stabilizer assembly (310) is disposed on the outside of the duct body (100); The rudder surface assembly (320) is rotatably mounted on the stabilizer surface; A winglet (321) is disposed at the end of the control surface assembly (320).

7. The high-altitude power generation device according to claim 5, characterized in that, It also includes a vortex generator (210) disposed on the outside of the duct body (100) and located in front of the tail fin assembly (300).

8. The high-altitude power generation device according to claim 7, characterized in that, It also includes a power turbine (220) disposed at the end of the vortex generator (210).

9. The high-altitude power generation device according to claim 4, characterized in that, The drive fan is coaxial with the duct body (100) and is located in the throat of the lifting body duct.

10. The high-altitude power generation device according to claim 4, characterized in that, The culvert body (100) is composed of multiple segments (110), which are distributed circumferentially along the culvert body (100).

11. The high-altitude power generation device according to claim 10, characterized in that, The segment (110) includes: truss; A rigid housing is disposed on the truss, the rigid housing being located on the inner side and / or front side of the truss; A soft airbag is disposed on the truss, and the soft airbag is disposed on the outside of the truss.

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