A new type of electric turbojet thruster with an internal rotor

Abstract

The present invention provides a novel electric turbojet thruster with an internal rotor, including a wing and a tail wing. The wing and the tail wing are connected by threads. The wing and the tail wing are respectively provided with a first spiral fin and a second spiral fin. The left end of the tail wing is provided with a plug-in mechanism, which includes a first limit groove, a first limit block, a first fixed sleeve, a first rotor, a flexible sleeve and a first screw sleeve. The left end of the tail wing is annularly provided with the first limit groove, and the first limit groove is movably connected with the first limit block. The first limit block is annularly arranged on the first fixed sleeve. The middle part of the first fixed sleeve is connected with the first rotor through a bearing, and the left end of the first fixed sleeve is provided with the first screw sleeve. This novel electric turbojet thruster with an internal rotor is easy to disassemble, install and replace the rotor, ensuring the use effect and service life of the electric turbojet thruster, and having a reasonable structural design, effectively solving the safety problem.

Description

Technical Field

[0001] The present invention relates to the technical field of thrusters, and particularly to a novel electric turbojet thruster with an internal rotor. Background Art

[0002] A thruster is a device that converts any form of energy into mechanical energy. It generates thrust by rotating blades or jetting (water). It can be used to drive a vehicle forward or as a power source for other devices such as generators. Thrusters are widely used in fields such as ships and aviation, mainly to push ships and boats forward. There are various types of thrusters, such as propeller thrusters, electric marine thrusters, aviation thrusters, water jet thrusters, etc. Each has its special uses and characteristics. And its structure is simple, and the volume is relatively small, occupying a very small area. Therefore, it is more flexible in application and also reflects the concept of green environmental protection. For existing electric turbojet thrusters, most of them have external rotors, which are prone to safety hazards, while the internal rotors are not easy to replace or disassemble, resulting in reduced service life and performance of the thruster. For this reason, we propose a novel electric turbojet thruster with an internal rotor. Summary of the Invention

[0003] The purpose of the present invention is to solve the drawbacks existing in the prior art, and to propose a novel electric turbojet thruster with an internal rotor.

[0004] To achieve the above purpose, the present invention adopts the following technical scheme: A novel electric turbojet thruster with an internal rotor, including a wing and a tail wing. The wing and the tail wing are connected by threads. The wing and the tail wing are respectively provided with a first spiral fin and a second spiral fin. The left end of the tail wing is provided with a plugging mechanism. The plugging mechanism includes a first limit groove, a first limit block, a first fixing sleeve, a first rotor, a flexible sleeve and a first screw sleeve. The left end of the tail wing is annularly provided with a first limit groove. The first limit groove is movably connected with a first limit block. The first limit block is annularly arranged on the first fixing sleeve. The middle part of the first fixing sleeve is connected with a first rotor through a bearing. The left end of the first fixing sleeve is provided with a first screw sleeve.

[0005] Preferably, the first screw sleeve is connected with the tail wing by threads, and the first screw sleeve is embedded in the left end of the tail wing.

[0006] Preferably, a flexible sleeve is arranged between the first screw sleeve and the first fixing sleeve, and the flexible sleeve is made of flexible rubber.

[0007] Preferably, the centers of the wing, the tail wing and the plugging mechanism are collinear, and the plugging mechanism is arranged inside the wing and the tail wing.

[0008] A new type of electric turbojet propeller with an internal rotor, comprising a wing and a tail wing. The wing and the tail wing are connected by threads. The wing and the tail wing are respectively provided with a first helical fin and a second helical fin. The left end of the tail wing is provided with a plug-in mechanism. The plug-in mechanism includes a fixed seat, a second limiting groove, a second limiting block, a second fixed sleeve, a second rotor and a second screw sleeve. The left end of the tail wing is provided with a fixed seat. The left end of the fixed seat is annularly provided with a second limiting block. The second limiting block is movably connected to the inside of the second limiting groove. The second limiting groove is opened on the second fixed sleeve. The second fixed sleeve is connected to the second rotor through a bearing.

[0009] Preferably, the left end of the second fixed sleeve is provided with a second screw sleeve. The second screw sleeve is connected to the tail wing by threads.

[0010] The beneficial effects of the new type of electric turbojet propeller with an internal rotor proposed by the present invention are as follows: By setting the plug-in mechanism, the wing and the tail wing structure, through the setting of the plug-in mechanism, the rotor can be quickly fixed to the tail wing, which is not only easy to disassemble, install and replace the rotor, ensuring the use effect and service life of the electric turbojet propeller, but also the unfolded part of the external rotor is very small, and the internal high-speed operation (without the risk caused by external rotation) is safer. At the same time, it replaces the original fuel method of airplanes or drones, with less energy consumption and high resource utilization rate, and is suitable for popularization and use. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 It is a left view schematic diagram of a new type of electric turbojet propeller with an internal rotor according to the present invention;

[0012] Figure 2 It is a partial main sectional view of the first embodiment of a new type of electric turbojet propeller with an internal rotor according to the present invention;

[0013] Figure 3 It is a left sectional view of the first embodiment of a new type of electric turbojet propeller with an internal rotor according to the present invention;

[0014] Figure 4 It is a right view schematic diagram of a new type of electric turbojet propeller with an internal rotor according to the present invention;

[0015] Figure 5 It is a partial main sectional view of the second embodiment of a new type of electric turbojet propeller with an internal rotor according to the present invention;

[0016] Figure 6 It is a left sectional view of the first embodiment of a new type of electric turbojet propeller with an internal rotor according to the present invention.

[0017] In the figure: 1 wing, 2 tail, 3 first spiral fin, 4 second spiral fin, 605 plug-in mechanism, 5 first limit groove, 51 first limit block, 52 first fixing sleeve, 53 first rotor, 54 flexible sleeve, 55 first screw sleeve, 6 fixing seat, 61 second limit groove, 62 second limit block, 63 second fixing sleeve, 64 second rotor, 65 second screw sleeve. Specific embodiments

[0018] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments.

[0019] Embodiment 1:

[0020] Please refer to Figure 1 、 2, 3, and 4, the present invention provides a technical solution: a novel electric turbojet thruster with an internal rotor, comprising a wing 1 and a tail wing 2. A permanent magnet energizer stator pole assembly is fixed inside the wing 1. A permanent magnet rotor unit is provided inside the permanent magnet energizer stator pole assembly. The permanent magnet rotor unit is installed between the plug-in mechanism 605 and the tail wing 2 through bearings. The electric turbojet engine can reach a maximum speed of 30,000 revolutions per minute with direct current, and the power improvement effect is remarkable. The structure is simple, the safety is strong, and it is not easily damaged. Moreover, it can replace the original fuel method of airplanes or drones. Compared with existing gliders and fuel-powered turbojet generators, the consumables are less and the resource utilization rate is high. The wing 1 and the tail wing 2 are connected by threads. The inner cavities of the wing 1 and the tail wing 2 are communicated. The wing 1 and the tail wing 2 are respectively provided with a first helical fin 3 and a second helical fin 4. The helix direction of the first helical fin 3 is opposite to the helix directions of the first rotor 53 and the second rotor 64. The left end of the tail wing 2 is provided with a plug-in mechanism 605. Through the setting of the plug-in mechanism 605, the rotor can be quickly fixed to the tail wing 2, and the disassembly, installation, and replacement of the rotor are easy, ensuring the use effect and service life of the electric turbojet thruster. The wing 1, the tail wing 2, and the center of the plug-in mechanism 605 are collinear. The setting of the plug-in mechanism 605 can improve the connection efficiency between the tail wing 2 and the rotor. The plug-in mechanism 605 is arranged inside the wing 1 and the tail wing 2. The plug-in mechanism 605 includes a first limit groove 5, a first limit block 51, a first fixing sleeve 52, a first rotor 53, a flexible sleeve 54, and a first screw sleeve 55. The left end of the tail wing 2 is annularly provided with a first limit groove 5. The left end of the tail wing 2 is provided with a groove, and the side wall of the groove is annularly provided with a first limit groove 5. The number of the first limit grooves 5 corresponds to the number of the first limit blocks 51. By setting the first limit block 51 in the first limit groove 5, the rotation of the first fixing sleeve 52 can be restricted. For the axial movement of the first fixing sleeve 52, it is restricted by the threaded connection between the first screw sleeve 55 and the tail wing 2. The flexible sleeve 54 is provided to improve the fixing stability of the first fixing sleeve 52. The material of the flexible sleeve 54 can be flexible rubber. Through the elasticity of the flexible sleeve 54, the toughness of the first fixing sleeve 52 and the first screw sleeve 55 can be increased. The first limit groove 5 is movably connected with a first limit block 51. The first limit block 51 is annularly arranged on the first fixing sleeve 52. The middle part of the first fixing sleeve 52 is connected with a first rotor 53 through a bearing. The left end of the first fixing sleeve 52 is provided with a first screw sleeve 55. The first screw sleeve 55 is threadedly connected with the tail wing 2, and the first screw sleeve 55 is embedded in the left end of the tail wing 2. A flexible sleeve 54 is arranged between the first screw sleeve 55 and the first fixing sleeve 52. The flexible sleeve 54 is flexible rubber.

[0021] When in use, for this new type of electric turbojet thruster with built-in rotors, during use, thrust is generated by the continuous rotation or jetting (of water) of the first rotor 53 to drive the vehicle forward or serve as the power for other devices such as generators. When disassembling and replacing the first rotor 53, by rotating and removing the first screw sleeve 55, due to the elastic force of the flexible sleeve 54, the first screw sleeve 55 is easier to remove. By detaching the first limit block 51 from the first limit slot 5, it can be replaced.

[0022] Embodiment 2:

[0023] Please refer to Figure 1 、 2 Figures 5 and 6. A solution different from Embodiment 1 provided by the present invention is that the plugging mechanism 605 includes a fixed seat 6, a second limit slot 61, a second limit block 62, a second fixed sleeve 63, a second rotor 64, and a second screw sleeve 65. A fixed seat 6 is provided at the left end of the tail fin 2. The fixed seat 6 can be fixedly welded to the tail fin 2. A groove is provided at the left end of the tail fin 2. The cross-section of the groove is circular. The outer diameter of the fixed seat 6 is equal to the groove width of the groove. The second limit block 62 is fixedly welded to the second limit block 62. The number of the second limit blocks 62 corresponds to that of the second limit slots 61. The second limit blocks 62 are annularly provided at the left end of the fixed seat 6. The second limit blocks 62 are movably connected to the inside of the second limit slots 61. The second limit slots 61 are opened on the second fixed sleeve 63. The second fixed sleeve 63 is connected to the second rotor 64 through a bearing. A second screw sleeve 65 is provided at the left end of the second fixed sleeve 63. The second screw sleeve 65 is connected to the tail fin 2 through a thread.

[0024] When in use, for this new type of electric turbojet thruster with built-in rotors, during use, thrust is generated by the continuous rotation or jetting (of water) of the second rotor 64 to drive the vehicle forward or serve as the power for other devices such as generators. When disassembling and replacing the second rotor 64, by rotating and removing the second screw sleeve 65, detaching the second limit block 62 from the second limit slot 61, and pulling the second rotor 64 from right to left, it can be disassembled and replaced, with simple operation and convenient use.

[0025] The above is only the preferred specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention, according to the technical solution and inventive concept of the present invention, with equivalent substitution or change, should be covered within the protection scope of the present invention.

Claims

1. A new type of electric turbojet propeller with an internal rotor, comprising a wing (1) and a tail fin (2), characterized in that: The wing (1) and the tail wing (2) are connected by threads. The wing (1) and the tail wing (2) are respectively provided with a first spiral fin (3) and a second spiral fin (4). The left end of the tail wing (2) is provided with a plugging mechanism (605). The plugging mechanism (605) includes a first limiting groove (5), a first limiting block (51), a first fixing sleeve (52), a first rotor (53), a flexible sleeve (54) and a first screw sleeve (55). The left end of the tail wing (2) is annularly provided with the first limiting groove (5). The first limiting block (51) is movably connected in the first limiting groove (5). The first limiting block (51) is annularly arranged on the first fixing sleeve (52). The middle of the first fixing sleeve (52) is connected to the first rotor (53) through a bearing. The left end of the first fixing sleeve (52) is provided with the first screw sleeve (55).

2. A novel electric turbojet thruster with an internal rotor according to claim 1, characterized in that: The first screw sleeve (55) is connected to the tail wing (2) by threads, and the first screw sleeve (55) is embedded in the left end of the tail wing (2).

3. A novel electric turbojet propeller with an internal rotor according to claim 1, characterized in that: A flexible sleeve (54) is arranged between the first screw sleeve (55) and the first fixing sleeve (52). The flexible sleeve (54) is made of flexible rubber.

4. A novel electric turbojet thruster with an internal rotor, characterized in that: The centers of the wing (1), the tail wing (2) and the plugging mechanism (605) are collinear. The plugging mechanism (605) is arranged inside the wing (1) and the tail wing (2).

5. A novel electric turbojet thruster with an internal rotor, comprising a wing (1) and a tail fin (2), characterized in that: The wing (1) and the tail wing (2) are connected by threads. The wing (1) and the tail wing (2) are respectively provided with a first spiral fin (3) and a second spiral fin (4). The left end of the tail wing (2) is provided with a plugging mechanism (605). The plugging mechanism (605) includes a fixing seat (6), a second limiting groove (61), a second limiting block (62), a second fixing sleeve (63), a second rotor (64) and a second screw sleeve (65). The left end of the tail wing (2) is provided with the fixing seat (6). The left end of the fixing seat (6) is annularly provided with the second limiting block (62). The second limiting block (62) is movably connected in the second limiting groove (61). The second limiting groove (61) is opened on the second fixing sleeve (63). The second fixing sleeve (63) is connected to the second rotor (64) through a bearing.

6. A novel electric turbojet thruster with an internal rotor according to claim 5, characterized in that: The left end of the second fixing sleeve (63) is provided with the second screw sleeve (65). The second screw sleeve (65) is connected to the tail wing (2) by threads.

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