Turbofan

Abstract

The present application relates to aircraft, and specifically provides a turbofan, aiming at solving the problem that the existing turbofan is too large in size and too heavy in weight, and is not suitable for the demand of low-altitude aircraft. To this end, the second center ring of the turbofan of the present application is sleeved outside the first center ring, the first and second support rings are correspondingly connected at both ends of the first and second center rings, the first and second spoke rings are correspondingly connected at both ends of the second center ring, the first and second spoke rings are further curved towards the height center line of the second center ring and finally form abutment, and the plurality of first blades of the first spoke ring and the plurality of second blades of the second spoke ring are mirror images. The turbofan is a mechanical full balance design, the turbofan is manufactured by using a 3D printing process, the turbofan removes the reaction force support system of the propeller, and can meet the demand of low-altitude aircraft on the light weight, high efficiency and low failure rate of the propeller.

Description

Technical Field

[0001] This invention relates to aircraft, and specifically to a turbofan. Background Technology

[0002] An aircraft is a flying machine that flies within the atmosphere and relies on air buoyancy or aerodynamics to obtain lift.

[0003] Aircraft are classified into low-altitude aircraft and high-altitude aircraft based on their flight altitude. Low-altitude aircraft generally fly at altitudes below 2,000 meters, while high-altitude aircraft typically fly at altitudes above 6,000 meters.

[0004] Low-altitude aircraft differ from high-altitude aircraft in that they require lightweight design, high efficiency, and reduced failure rates. Currently, turbofans are too large and heavy to meet the needs of low-altitude aircraft. Therefore, there is an urgent need to develop a lightweight, highly efficient turbofan with a reduced failure rate. Summary of the Invention

[0005] The present invention aims to solve the above-mentioned technical problems, namely, to solve the problem that existing turbofans are too large and heavy, making them unsuitable for the needs of low-altitude aircraft.

[0006] This invention provides a turbo fan, comprising: The first central ring has a coupling spline on its inner wall; The second central ring is fitted around the first central ring and is concentric with it; A first support ring is connected to one end of the first central ring and the second central ring; The second support ring is connected to the other end of the first central ring and the second central ring; A first spoke ring, one end of which is connected to one end of a second central ring, has multiple first blades on it; and The second spoke ring has one end connected to the other end of the second central ring, and the second spoke ring is provided with multiple second blades; The other ends of the first spoke ring and the second spoke ring are bent toward the height centerline of the second central ring and intersect to form an abutment. The plurality of first blades and the plurality of second blades are mirror images of each other on a plane, which is the plane containing the intersection line formed by the first spoke ring and the second spoke ring and the height centerline of the second central ring.

[0007] In the preferred embodiment of the above-described turbine fan, the height of the first central ring is less than the height of the second central ring.

[0008] In the preferred embodiment of the above-mentioned turbine fan, the plurality of first blades are bent clockwise relative to the first spoke ring, and the plurality of second blades are bent counterclockwise relative to the second spoke ring.

[0009] In the preferred embodiment of the above-mentioned turbine fan, both the first support ring and the second support ring are trumpet-shaped.

[0010] In the preferred embodiment of the above-mentioned turbine fan, the first support ring is provided with a plurality of first through holes, and the second support ring is provided with a plurality of second through holes, wherein the plurality of first through holes and the plurality of second through holes are matched and correspond one-to-one.

[0011] In the preferred embodiment of the above-mentioned turbine fan, the number of both the first through hole and the second through hole is five.

[0012] In the preferred embodiment of the turbo fan described above, the turbo fan further includes reinforcing ribs, which are disposed within the space enclosed by the first spoke ring and the second spoke ring.

[0013] In the preferred embodiment of the above-mentioned turbofan, there are multiple reinforcing ribs, each of which corresponds one-to-one with the multiple first blades and the multiple second blades. Each reinforcing rib is connected to the root of the corresponding first blade and the root of the corresponding second blade, and each reinforcing rib bends with the corresponding first blade. Each reinforcing rib is also connected to the second central ring.

[0014] When adopting the above technical solution, the turbofan of the present invention includes a first central ring, a second central ring, a first support ring, a second support ring, a first spoke ring, and a second spoke ring. The inner wall of the first central ring is provided with a coupling spline. The second central ring is fitted outside the first central ring and is concentric with it. The first support ring and the second support ring are correspondingly connected to the two ends of the first central ring and the second central ring. The first central ring, the second central ring, the first support ring, and the second support ring constitute the support structure of the turbofan. The first spoke ring and the second spoke ring are correspondingly connected to the two ends of the second central ring. The first spoke ring and the second spoke ring also bend towards the height centerline of the second central ring and intersect to finally form an abutment. The intersection line formed by the plurality of first blades of the first spoke ring and the plurality of second blades of the second spoke ring relative to the first spoke ring and the second spoke ring is a mirror image of the plane where the height centerline of the second central ring is located. The aforementioned turbofan employs a mechanically balanced design, achieving mechanical balance by offsetting the tangential component of the centrifugal force on the blades against the bending stress of the airflow, balancing the axial reaction forces on both sides of the axial flow section blades, and balancing the reaction forces on the blades from the flow deflection region. This results in high efficiency, lightweight construction, and a low failure rate. The turbofan of this invention is manufactured using 3D printing technology, further contributing to its lightweight and low failure rate. Furthermore, the turbofan eliminates the propeller's reaction force support system, thus achieving high efficiency, lightweight construction, and a reduced failure rate. Therefore, the turbofan of this invention meets the requirements of low-altitude aircraft for lightweight, high-efficiency propellers and the elimination of the propeller's reaction force support system to reduce failure rates. Attached Figure Description

[0015] The preferred embodiments of the present invention are described below with reference to the accompanying drawings, in which: Figure 1 This is a schematic perspective view of the turbine fan of the present invention at one angle; Figure 2 This is a schematic perspective view of the turbine fan of the present invention from another angle; Figure 3 This is a schematic perspective view of the turbine fan of the present invention from another angle; Figure 4 yes Figure 1 A schematic main sectional view of the turbine fan; Figure 5 yes Figure 1 A schematic top view of a turbine fan; Figure 6 It is along Figure 5 A schematic cross-sectional view after being cut along line AA; Figure 7 It is along Figure 5 A schematic cross-sectional view after reverse sectioning along line AA.

[0016] The symbols in the diagram represent the following meanings: 100 turbo fan, 10. First central ring, 11. Spline 20 Second central ring, 30 First support ring, 31 First through hole, 40 Second support ring, 41 Second through hole, 50 First ring spokes, 51 First blade, 60 Second ring spokes, 61 Second blade, 70 reinforcing ribs. Detailed Implementation

[0017] Preferred embodiments of the present invention will now be described with reference to the accompanying drawings. Those skilled in the art should understand that these embodiments are merely illustrative of the technical principles of the invention and are not intended to limit the scope of protection of the invention. Those skilled in the art can make adjustments as needed to adapt to specific applications.

[0018] It should be noted that in the description of this invention, terms such as "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," indicating directional or positional relationships, are based on the directional or positional relationships shown in the accompanying drawings. These are merely for ease of description and do not indicate or imply that the device or element must have a specific orientation, or be constructed and operated in a specific orientation; therefore, they should not be construed as limitations on the invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0019] Furthermore, it should be noted that, in the description of this invention, unless otherwise explicitly specified and limited, the terms "connected" and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0020] Figure 1 This is a schematic perspective view of the turbine fan of the present invention at one angle. Figure 1 The diagram shows the specific structure of the first central ring, second central ring, second support ring, and second spoke ring of the turbine fan. Figure 2 This is a schematic perspective view of the turbine fan of the present invention from another angle. Figure 2 The specific structures of the first central ring, the second central ring, the first support ring, and the first spoke ring are shown. Figure 3 This is a schematic perspective view of the turbine fan of the present invention from another angle. Figure 3 The specific structures of the first and second spoke rings are shown. Figure 4 yes Figure 1 A schematic main sectional view of the turbine fan. Figure 4 The specific connection structure of the first central ring, the second central ring, the first support ring, the second support ring, the first spoke ring, and the second spoke ring is shown. Figure 5 yes Figure 1 A schematic top view of the turbine fan. Figure 5 The specific structures of the first and second spoke rings are shown. Figure 6 It is along Figure 5 A schematic cross-sectional view after being cut along line AA. Figure 6 The specific structure of the reinforcing rib is shown. Figure 7 It is along Figure 5 A schematic cross-sectional view after reverse sectioning along line AA. Figure 7 The specific structure of the reinforcing rib is shown.

[0021] like Figure 1 As shown, see also Figures 2-7 To address the issue that existing turbofans are too large and heavy to meet the needs of low-altitude aircraft, such as... Figure 1 As shown, the present invention provides a turbine fan 100 comprising: a first central ring 10, a second central ring 20, a first support ring 30, a second support ring 40, a first spoke ring 50, and a second spoke ring 60 (see...). Figure 2 The inner wall of the first central ring 10 is provided with a coupling spline 11. The second central ring 20 is fitted around the first central ring 10 and is concentric with the first central ring 10. Figure 2 As shown, the first support ring 30 is connected to one end of the first central ring 10 and the second central ring 20, as follows: Figure 4 As shown, the first support ring 30 is connected to the outer right end of the first central ring 10 and the inner right end of the second central ring 20. Figure 1 As shown, the second support ring 40 is connected to the other end of the first central ring 10 and the second central ring 20, as... Figure 4 As shown, the second support ring 40 is connected to the outer left end of the first central ring 10 and the inner left end of the second central ring 20. Figure 2 As shown, one end of the first spoke ring 50 is connected to one end of the second central ring 20, and the first spoke ring 50 is provided with multiple first blades 51, such as... Figure 4 As shown, one end of the first spoke ring 50 is connected to the right end of the second central ring 20. (As indicated...) Figure 1 As shown, one end of the second spoke ring 60 is connected to the other end of the second central ring 20, and the second spoke ring 60 is provided with multiple second blades 61, such as... Figure 4 As shown, one end of the second spoke ring 60 is connected to the left end of the second central ring 20. (As indicated...) Figure 4 As shown, see also Figure 6In this configuration, the other ends of the first spoke ring 50 and the second spoke ring 60 are both bent toward the height centerline of the second central ring 20 and intersect to form an abutment. Multiple first blades 51 and multiple second blades 61 are mirror images of each other on a plane, which is the plane containing the intersection line formed by the first spoke ring 50 and the second spoke ring 60 and the height centerline of the second central ring 20.

[0022] When the above technical solution is adopted, such as Figure 4 As shown, the turbine fan 100 of the present invention includes a first central ring 10, a second central ring 20, a first support ring 30, a second support ring 40, a first spoke ring 50, and a second spoke ring 60. The first central ring 10, the second central ring 20, the first support ring 30, and the second support ring 40 constitute the support structure of the turbine fan 100. The first spoke ring 50 and the second spoke ring 60 are correspondingly connected to the two ends of the second central ring 20. The first spoke ring 50 and the second spoke ring 60 also bend towards the height centerline of the second central ring 20 and intersect to finally form an abutment. The intersection line formed by the plurality of first blades 51 of the first spoke ring 50 and the plurality of second blades 61 of the second spoke ring 60 relative to the first spoke ring 50 and the second spoke ring 60 is a mirror image of the plane containing the height centerline of the second central ring 20. The aforementioned turbofan 100 features a mechanically balanced design, achieving mechanical balance by offsetting the tangential component of the centrifugal force on the blades (referring to the first blade 51 and the second blade 61) against the bending stress of the airflow on the blades (referring to the first blade and the second blade), achieving mechanical balance of the axial reaction forces on both sides of the axial flow section blades (referring to the first blade and the second blade), and achieving mechanical balance of the reaction forces of the flow deflection region on the blades (referring to the first blade and the second blade). Therefore, it achieves high efficiency, lightweight design, and low failure rate. The turbofan 100 of this invention is manufactured using 3D printing technology, thus achieving lightweight design and low failure rate. Furthermore, the turbofan 100 of this invention eliminates the propeller reaction force support system, thus achieving high efficiency, lightweight design, and reduced failure rate. Therefore, the turbofan 100 of this invention can meet the requirements of low-altitude aircraft for lightweight propellers, high efficiency, and reduced failure rate by eliminating the propeller reaction force support system.

[0023] As one possible implementation method, such as Figure 4 As shown, the height of the first central ring 10 is less than the height of the second central ring 20.

[0024] As one possible implementation method, such as Figure 2 As shown, multiple first blades 51 are bent clockwise relative to the first spoke ring 50, as... Figure 1 As shown, multiple second blades 61 are bent counterclockwise relative to the second spoke ring 60.

[0025] As one possible implementation method, such as Figure 4As shown, both the first support ring 30 and the second support ring 40 are trumpet-shaped.

[0026] As one possible implementation method, such as Figure 2 As shown, the first support ring 30 is provided with a plurality of first through holes 31, such as Figure 1 As shown, the second support ring 40 is provided with a plurality of second through holes 41, and the plurality of first through holes 31 are matched with the plurality of second through holes 41 and correspond one to one.

[0027] As one possible implementation method, such as Figure 2 As shown, see also Figure 1 The number of first through holes 31 and second through holes 41 is five each. Specifically, the plurality of first through holes 31 and the plurality of second through holes 41 can be evenly distributed along the circumference. Of course, in other embodiments, the number of the plurality of first through holes 31 and the plurality of second through holes 41 can be three, four, six, or other numbers, depending on the working conditions.

[0028] As one possible implementation method, such as Figure 4 As shown, see also Figures 6-7 The turbine fan 100 also includes a reinforcing rib 70, which is disposed within the space enclosed by the first spoke ring 50 and the second spoke ring 60.

[0029] As one possible implementation method, such as Figure 4 As shown, see also Figure 6 , Figure 7 The structure comprises multiple reinforcing ribs 70, each corresponding to one of the first blades 51 and the second blades 61. Each reinforcing rib 70 connects to the root of the corresponding first blade 51 and the root of the corresponding second blade 61, and each reinforcing rib 70 bends with the corresponding first blade 51. Each reinforcing rib 70 is also connected to the second central ring 20. This structure achieves minimal material usage, the lightest structure, and the highest strength.

[0030] The technical solution of the present invention has been described above with reference to the preferred embodiments shown in the accompanying drawings. However, it will be readily understood by those skilled in the art that the scope of protection of the present invention is obviously not limited to these specific embodiments. Without departing from the principles of the present invention, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after such changes or substitutions will all fall within the scope of protection of the present invention.

Claims

1. A turbine fan, characterized in that, include: The first central ring has a coupling spline on its inner wall; The second central ring is fitted around the first central ring and is concentric with it; A first support ring is connected to one end of the first central ring and the second central ring; The second support ring is connected to the other end of the first central ring and the second central ring; The first spoke ring has one end connected to one end of the second central ring, and the first spoke ring is provided with a plurality of first blades; and The second spoke ring has one end connected to the other end of the second central ring, and the second spoke ring is provided with multiple second blades; The other ends of the first spoke ring and the second spoke ring are bent toward the height centerline of the second central ring and intersect to form an abutment. The plurality of first blades and the plurality of second blades are mirror images of each other on a plane, which is the plane containing the intersection line formed by the first spoke ring and the second spoke ring and the height centerline of the second central ring.

2. The turbine fan according to claim 1, characterized in that, The height of the first central ring is less than the height of the second central ring.

3. The turbine fan according to claim 1, characterized in that, The plurality of first blades bend clockwise relative to the first spoke ring, and the plurality of second blades bend counterclockwise relative to the second spoke ring.

4. The turbine fan according to claim 1, characterized in that, Both the first support ring and the second support ring are trumpet-shaped.

5. The turbine fan according to claim 1, characterized in that, The first support ring is provided with a plurality of first through holes, and the second support ring is provided with a plurality of second through holes, wherein the plurality of first through holes and the plurality of second through holes are matched and correspond one-to-one.

6. The turbine fan according to claim 5, characterized in that, The number of the first through hole and the number of the second through hole are both five.

7. The turbine fan according to any one of claims 1-6, characterized in that, The turbine fan also includes reinforcing ribs, which are disposed within the space enclosed by the first spoke ring and the second spoke ring.

8. The turbine fan according to claim 7, characterized in that, The number of reinforcing ribs is multiple, and each reinforcing rib corresponds one-to-one with the multiple first blades and the multiple second blades. Each reinforcing rib is connected to the root of the corresponding first blade and the root of the corresponding second blade, and each reinforcing rib bends with the corresponding first blade. Each reinforcing rib is also connected to the second central ring.

Images