Electric efficient high-pressure duct propelling device for aviation

Abstract

The invention discloses an electric efficient high-pressure duct propelling device for aviation, and particularly relates to an electric efficient high-pressure duct propelling device for aviation. According to the invention, the motor and the duct are integrally designed, the propeller duct is internally and coaxially mounted up and down and operates in the same direction, and the middle air guide blade is designed, so that air can quickly flow out of the lower part of the duct in a high-pressure state to form strong thrust. According to the invention, a motor centralized winding mode is adopted, and the number of stator slots is matched with the number of rotor poles to output sine wave back electromotive force, so that a controller realizes sine wave non-inductive control. By means of the design of the rotor magnetic isolation bridge, magnetic induction lines can flexibly pass through the rotor magnetic isolation bridge, and tooth groove pulsation is reduced. In addition, due to the design of the motor, wind noise can be quickly blown away by high speed and high pressure of air in the duct, the interior of the aircraft is located at the front end of the wind noise, and electromagnetic noise generated during operation is reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of ducted fans, and in particular to an electric high-efficiency high-pressure ducted propulsion device for aviation. Background Art

[0002] With the gradual liberalization of domestic airspace and the rapid growth of the low-altitude economy, vertical takeoff and landing aircraft can be vigorously developed, and the requirements for motors in key components of aircraft are very high.

[0003] In the prior art, the patent application number 202110432740.2 relates to a ducted fan device with a double-layer propeller, including a housing. A double-layer propeller blade structure is provided inside the housing. The double-layer propeller blade structure includes a main shaft. Double-layer propeller blades are provided on the main shaft. One end of the main shaft is provided with an end cover, and the other end is connected to a motor through a coupling. Compared with the prior art, the present invention reduces the disadvantages of the windless area of traditional axial fans, uses the first-layer fan to concentrate the air volume in the center of the fan, and then further compresses the compressed air by the second-layer fan, not only solving the windless area problem, but also increasing the air volume. Guide vanes are designed to improve the air flow so that the air flows in the upper and lower regions do not interfere with each other, and the upper-layer air flow can continue to be transmitted to the lower layer, etc.

[0004] Existing products still have problems such as insufficient thrust and low power density of the motor. Based on this, the present invention develops a propulsion device combining a motor with a ducted fan and a wind blade, which can improve the thrust of the propulsion device and the power density of the motor. Summary of the Invention

[0005] The purpose of the present invention is to provide an electric high-efficiency high-pressure ducted propulsion device for aviation, and solve the problem of how to improve the thrust of the propulsion device and the power density of the motor.

[0006] To solve the above technical problems, the present invention adopts the following technical solutions:

[0007] The present invention provides an electric high-efficiency high-pressure ducted propulsion device for aviation, including an outer duct, a motor housing arranged in the outer duct through a plurality of guide vanes, a stator arranged in the motor housing, a rotor arranged at the center of the motor housing and adapted to the stator, a rotating shaft coaxially arranged on the rotor, and a propeller arranged on the rotating shaft; wherein windings are arranged on the stator.

[0008] Further in this embodiment, the motor housing is arranged in the middle of the outer duct through the plurality of guide vanes; wherein the guide vanes are of an inclined surface structure; thereby fixing the motor and the duct into an integral body, and such an integrated design can greatly improve the service life of the device.

[0009] In a further aspect of this embodiment, the propeller includes a hub and blades disposed on the rotating shaft; wherein the inclined direction of the inclined surface of the blade is opposite to that of the inclined surface of the air guiding blade; and the inclination angle of the blade is smaller than the inclined surface angle of the air guiding blade.

[0010] In a further aspect of this embodiment, an upper end cover and a lower end cover are respectively provided at the top and bottom of the motor housing; air holes are provided in the upper and lower end covers to accelerate air flow and enable good heat dissipation of the motor; reserved holes aligned with the rotor shaft holes are respectively provided at the centers of the upper end cover and the lower end cover.

[0011] In a further aspect of this embodiment, a rotor shaft hole for installing the rotating shaft is axially provided in the rotor; an upper shaft is provided at the inner top of the rotor shaft hole, a lower shaft is provided at the inner bottom of the rotor shaft hole, an upper propeller is provided on the upper shaft, and a lower propeller is provided on the lower shaft.

[0012] In a further aspect of this embodiment, there is a fixed phase difference between the blades of the upper propeller and the lower propeller; the angle between the blades of the upper propeller and the lower propeller is 15°.

[0013] In a further aspect of this embodiment, a plurality of teeth are evenly spaced on the inner peripheral wall of the stator, and windings are provided on the teeth, and the windings output three-phase lines U, V, and W.

[0014] In a further aspect of this embodiment, a plurality of teeth are evenly spaced on the inner peripheral wall of the stator, windings are provided on the teeth, the windings are in a concentrated winding method, and three-phase power supply lines U, V, W and three-phase star connection lines U1, V1, W1 are output.

[0015] In a further aspect of this embodiment, a plurality of magnets are evenly spaced on the outer peripheral wall of the rotor, and a magnetic isolation bridge is provided between adjacent magnets.

[0016] In a further aspect of this embodiment, a plurality of magnets are evenly spaced on the outer peripheral wall of the rotor, wherein the N poles and S poles of the magnets are respectively installed on the outer ring of the rotor in a positive-negative sequence, and the magnetic isolation bridge is composed of two opposite triangular structures; the magnetic isolation bridge is made of silicon steel sheet; this can reduce cogging torque and increase mechanical strength. With this winding design and rotor design of the invention, the output is a sine wave back electromotive force, and the AC utilization rate of the controller can be improved by cooperating with sensorless control.

[0017] Compared with the prior art, the beneficial technical effects of the present invention are:

[0018] In the present invention, the motor and the duct are integrally designed. The propellers are coaxially installed vertically inside the duct and rotate in the same direction. The design of the intermediate air guide vanes enables air to flow out rapidly from below the duct under high pressure, generating a strong thrust. In the present invention, the motor adopts a centralized winding form, and the number of stator slots is coordinated with the number of rotor poles to output a sine wave back electromotive force, enabling the controller to achieve sine wave sensorless control. In the present invention, the design of the rotor magnetic isolation bridge allows magnetic induction lines to pass through flexibly, reducing cogging pulsation. In addition, the motor design of the present invention can blow away the wind noise rapidly with the high-speed and high-pressure air inside the duct, placing the interior of the aircraft at the front end of the wind noise and reducing the electromagnetic noise during operation. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The present invention will be further described below in conjunction with the drawings.

[0020] Figure 1 It is a schematic exploded view of the electric high-efficiency high-pressure duct propulsion device for aircraft of the present invention;

[0021] Figure 2 It is a top view schematic diagram of the air guide vanes and the motor housing of the electric high-efficiency high-pressure duct propulsion device for aircraft of the present invention;

[0022] Figure 3 It is a top view schematic diagram of the upper propeller of the electric high-efficiency high-pressure duct propulsion device for aircraft of the present invention;

[0023] Figure 4 It is a schematic diagram of the internal structure of the motor housing of the electric high-efficiency high-pressure duct propulsion device for aircraft of the present invention;

[0024] Figure 5 It is a schematic enlarged view of the magnetic isolation bridge of the electric high-efficiency high-pressure duct propulsion device for aircraft of the present invention.

[0025] DESCRIPTION OF THE REFERENCE NUMERALS:

[0026] 1. Outer duct; 2. Upper propeller; 21. Propeller hub; 22. Propeller blade; 3. Upper shaft; 4. Upper end cover; 5. Air guide vane; 6. Motor housing; 7. Lower end cover; 8. Lower shaft; 9. Lower propeller; 10. Stator; 11. Tooth; 12. Winding; 13. Magnet; 14. Rotor; 15. Rotor shaft hole; 16. Magnetic isolation bridge. DETAILED DESCRIPTION OF THE INVENTION

[0027] Reference Figures 1 - 3, in this embodiment, an electric high-efficiency high-pressure ducted propulsion device for aviation is disclosed, which is composed of an outer duct 1, a guide vane 5, upper and lower propellers (2 / 9), a motor shaft, end caps (4 / 7), a motor housing 6, a stator 10, a rotor 14, windings 12, and magnets 13. One end of the guide vane 5 is connected to the middle of the inner wall of the outer duct 1, and the other end is connected to the motor housing 6, fixing the motor and the duct together as one body. This integrated design can greatly improve the service life of the device.

[0028] The motor housing 6 is equipped with a stator with windings 12. The windings output three-phase lines UVW. The middle hole of the rotor is fitted with the motor shaft, and end caps are installed at both ends of the motor shaft. Wind holes are opened on the upper and lower end caps, and the air flow enables good heat dissipation of the motor. The end caps are fixed on the upper and lower surfaces of the housing. The motor shaft protrudes from the middle of the motor end cap as the power output end. The output end is divided into an upper shaft and a lower shaft. The upper shaft is fitted with a propeller, and the lower shaft is fitted with a lower propeller.

[0029] The propellers are designed with a 30° inclined plane, and the guide vane 5 is designed with a 40° inclined plane. The inclined plane directions of the propellers are opposite to those of the guide vane. The angle between the upper propeller and the lower propeller is 15°. When the lower point of the inclined plane of the upper propeller aligns with the upper point of the inclined plane of the guide vane, the upper point of the inclined plane of the lower propeller aligns with the lower point of the inclined plane of the guide vane, compressing the air downward and preventing the air from flowing back due to the large pressure below and the small pressure above.

[0030] Reference Figure 4 , the stator 10 has 24 slots, and each tooth slot has windings. The windings are wound in a concentrated winding method, outputting three-phase power lines UVW and three-phase star connection U1V1W1. The lead of phase U is wound around tooth ① in a clockwise direction and around tooth ② in a counterclockwise direction through the winding, then wound around tooth ⑦ in a clockwise direction through the jumper wire and around tooth ⑧ in a counterclockwise direction, and through the jumper wire clockwise on tooth, and counterclockwise around tooth, and through the jumper wire clockwise on tooth, and counterclockwise around tooth, and the output end is U1.

[0031] The lead of phase V is wound around tooth ④ in a clockwise direction and around tooth ③ in a counterclockwise direction through the winding, then wound around tooth in a clockwise direction through the jumper wire and around tooth in a counterclockwise direction, and through the jumper wire wound around tooth in a clockwise direction and around tooth in a counterclockwise direction, and through the jumper wire wound clockwise around tooth ⑩ and counterclockwise around tooth ⑨ to output the end V1.

[0032] The lead of phase W is wound around tooth ⑤ in a clockwise direction and around tooth ⑥ in a counterclockwise direction through the winding, and then wound around tooth in a clockwise direction through the jumper wire and counterclockwise around On the tooth, clockwise through the crossover line at On the tooth, counterclockwise wound around On the tooth, clockwise through the crossover line at On the tooth, counterclockwise wound around On the tooth, the output ends with W1.

[0033] The rotor is designed with 20 poles and is equipped with 20 magnets. The N and S poles are installed on the outer ring of the rotor in a positive-negative sequence. A magnetic isolation bridge is designed between two magnets. The magnetic isolation bridge is designed as two opposite triangles, which can reduce the cogging torque, increase the mechanical strength, and at the same time help reduce the noise.

[0034] With this invention's winding design plus the rotor design, the output is a sine wave back electromotive force, which can improve the AC utilization rate of the controller when combined with sensorless control.

[0035] Principle of operation

[0036] The three-phase lines UVW of the motor are connected to alternating current, and a rotating magnetic field is formed in the stator, driving the rotor to rotate. The rotor drives the propeller to rotate through the motor shaft. The design of the propeller enables the air to flow rapidly downward and reach the middle air guide vane. The inclined surface design of the air guide vane increases the speed of the downward air flow, preventing the high-pressure air below the air guide vane from flowing upward, increasing the air pressure below the air guide vane. Then, there is also the lower propeller operating simultaneously. The high-pressure air guided by the air guide vane is further pressurized by the lower propeller, enabling the air to flow out rapidly below the duct under high-pressure conditions, forming a powerful thrust.

[0037] The wind noise at the end of the propeller inside the duct is reduced a lot. The design of the motor minimizes the electromagnetic noise during operation. The high-speed and high-pressure air quickly blows away the wind noise, placing the interior of the aircraft at the front end of the wind noise and isolating it from the noise.

[0038] The number of stator and rotor slots can be changed according to the number of rotors, and can be 18 slots or 12 slots. The number of air guide vanes can be changed according to actual needs and can be more than 2. The number of upper and lower propellers is the same as that of the air guide vanes. For example, if the design of the upper propeller is 2, then the lower propeller and the air guide vanes are also 2.

[0039] The above embodiments only describe the preferred embodiments of the present invention, and do not limit the scope of the present invention. Without departing from the design spirit of the present invention, various deformations and improvements made by those of ordinary skill in the art to the technical solutions of the present invention shall fall within the protection scope determined by the claims of the present invention.

Claims

1. An electric high-efficiency high-pressure ducted propulsion device for aviation, characterized in that: It comprises an outer duct (1), a motor housing (6) arranged in the outer duct (1) via a plurality of air guide vanes (5), a stator (10) arranged in the motor housing (6), a rotor (14) arranged at the center of the motor housing (6) and adapted to the stator (10), a rotating shaft coaxially arranged on the rotor (14), and a propeller arranged on the rotating shaft; A winding (12) is arranged on the stator (10).

2. The electric high-efficiency high-pressure ducted propulsion device for aviation according to claim 1, characterized in that: The motor housing (6) is arranged in the middle of the outer duct (1) via a plurality of the air guide vanes (5); wherein the air guide vanes (5) are inclined structures.

3. The electric high-efficiency high-pressure ducted propulsion device for aviation according to claim 2, characterized in that: The propeller comprises a hub and a blade arranged on the rotating shaft; wherein the inclination direction of the inclined surface of the blade is opposite to the inclination direction of the inclined surface of the wind guide blade (5); and the inclination angle of the blade is smaller than the inclination angle of the inclined surface of the wind guide blade (5).

4. The electric high-efficiency high-pressure ducted propulsion device for aviation according to claim 1, characterized in that: An upper end cover (4) and a lower end cover (5) are respectively provided at the top and bottom of the motor housing (6); a reserved hole aligned with the rotor shaft hole (15) is respectively opened at the center of the upper end cover (4) and the center of the lower end cover (5).

5. The electric high-efficiency high-pressure ducted propulsion device for aviation according to claim 4, characterized in that: A rotor shaft hole (15) for mounting the rotating shaft is provided in the axial direction of the rotor (14); an upper shaft (3) is provided at the inner top of the rotor shaft hole (15); a lower shaft (8) is provided at the inner bottom of the rotor shaft hole (15); an upper propeller (2) is provided on the upper shaft (3); and a lower propeller (9) is provided on the lower shaft (8).

6. The electric high-efficiency high-pressure ducted propulsion device for aviation according to claim 5, characterized in that: There is a fixed phase difference between the blades of the upper propeller (2) and the lower propeller (9); the angle difference between the blades of the upper propeller (2) and the lower propeller (9) is 15°.

7. The electric high-efficiency high-pressure ducted propulsion device for aviation according to claim 6, characterized in that: A plurality of teeth (11) are evenly spaced apart on the inner peripheral wall of the stator (10), and the winding (12) is arranged on the teeth (11).

8. The electric high-efficiency high-pressure ducted propulsion device for aviation according to claim 6, characterized in that: 24 teeth (11) are evenly spaced apart on the inner circumferential wall of the stator (10), and the winding (12) is arranged on the teeth (11). The winding (12) is a centralized winding method, and outputs three-phase power lines U, V, W and three-phase star connections U1, V1, W1.

9. The electric high-efficiency high-pressure ducted propulsion device for aviation according to claim 1, characterized in that: A plurality of magnets (13) are evenly spaced apart on the outer peripheral wall of the rotor (14), and a magnetic isolation bridge (16) is provided between adjacent magnets (13).

10. The electric high-efficiency high-pressure ducted propulsion device for aviation according to claim 9, characterized in that: Twenty magnets (13) are evenly spaced apart on the outer peripheral wall of the rotor (14), wherein the N poles and S poles of the 20 magnets are respectively mounted on the outer ring of the rotor (14) in sequence, one positive and one negative, and the magnetic isolation bridge (16) is two opposite triangular structures; the magnetic isolation bridge (16) is a silicon steel sheet.

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