Electric high-efficiency high-pressure ducted propelling device for aviation

Abstract

The application discloses an electric high-efficiency high-pressure duct propulsion device for aviation, and particularly relates to an electric high-efficiency high-pressure duct propulsion device for aviation. In the application, the motor and the duct are integrally designed, the propeller and the duct are coaxially arranged in an up-down mode and rotate in the same direction, and the design of the middle air guide blade can make the air flow out from below the duct in a high-pressure state and form a strong thrust. In the application, the motor is in a centralized winding form, the number of stator slots is matched with the number of rotor poles to output a sine wave counter electromotive force, and the controller can realize sine wave non-inductive control. In the application, the design of the rotor magnetic isolation bridge makes the magnetic induction lines flexibly pass through, so that the tooth slot pulsation is reduced. In addition, the motor design of the application can make the high-speed and high-pressure air in the duct quickly blow away the wind noise, so that the inside of the aircraft is in front of the wind noise, and the electromagnetic noise during operation is reduced.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of ducted fan, in particular to an electric high-efficiency high-pressure ducted propulsion device for aviation. BACKGROUND

[0002] With the gradual opening of domestic airspace, the low-altitude economy is growing rapidly, and the vertical take-off and landing aircraft can be developed vigorously. The motor requirements for key components of the aircraft are very high.

[0003] In the prior art, patent application No. 202110432740.2 relates to a ducted fan device with double-layer propeller, comprising a shell, a double-layer propeller blade structure is arranged in the shell, the double-layer propeller blade structure comprises a main shaft, double-layer propeller blades are arranged on the main shaft, an end cover is arranged at one end of the main shaft, and the other end is connected with a motor through a shaft coupling. Compared with the prior art, the present application reduces the disadvantages of traditional axial flow fan no wind area, the wind volume in the center of the fan is concentrated by the first layer fan, and the compressed air is further compressed by the second layer fan. Not only the problem of no wind area is solved, but also the wind volume is increased. The guide vane is designed to improve the airflow, so that the airflow in the upper and lower two areas will not interfere with each other, and the upper airflow can continue to be transmitted to the lower layer.

[0004] The existing product also has the problems of insufficient thrust and low power density of the motor. Therefore, the present application develops a propulsion device combined with a motor and a ducted fan blade, which can improve the thrust of the propulsion device and the power density of the motor. SUMMARY

[0005] The purpose of the present application is to provide an electric high-efficiency high-pressure ducted propulsion device for aviation, which solves 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 application adopts the following technical scheme:

[0007] The present application provides an electric high-efficiency high-pressure ducted propulsion device for aviation, which comprises an outer duct, a motor shell arranged in the outer duct through a plurality of guide vanes, a stator arranged in the motor shell, a rotor arranged in the center of the motor shell and matched with the stator, a rotating shaft coaxially arranged on the rotor, and a propeller arranged on the rotating shaft. Wherein, the stator is provided with a winding.

[0008] In this embodiment, the motor shell is arranged in the middle of the outer duct through a plurality of guide vanes. The guide vanes are inclined surfaces. Thus, the motor and the duct are fixed as a whole, and the integrated design can greatly improve the service life of the device.

[0009] The propeller further comprises a hub and a blade arranged on the rotating shaft, wherein the blade is arranged oppositely to the guide vane, and the angle of the blade is smaller than that of the guide vane.

[0010] The motor further comprises an upper end cover and a lower end cover arranged on the top and bottom of the motor shell, respectively, wherein the upper and lower end covers are provided with air holes to accelerate air flow and improve heat dissipation of the motor, and the upper end cover and the lower end cover are provided with a reserved hole and a reserved hole, respectively, which are aligned with the rotor shaft hole.

[0011] The motor further comprises an upper shaft arranged on the inner top of the rotor shaft hole, a lower shaft arranged on the inner bottom of the rotor shaft hole, an upper propeller arranged on the upper shaft, and a lower propeller arranged on the lower shaft.

[0012] The upper propeller and the lower propeller are arranged with a fixed phase difference, and the angle between the blades of the upper propeller and the lower propeller is 15°.

[0013] The stator is provided with a plurality of teeth arranged on the inner circumferential wall of the stator, and the winding is arranged on the teeth.

[0014] The stator is provided with a plurality of teeth arranged on the inner circumferential wall of the stator, and the winding is arranged on the teeth.

[0015] The rotor is provided with a plurality of magnets arranged on the outer circumferential wall of the rotor, and a magnetic separation bridge is arranged between adjacent magnets.

[0016] The rotor is provided with a plurality of magnets arranged on the outer circumferential wall of the rotor, wherein the N and S poles of the magnets are arranged on the outer ring of the rotor in a positive-negative sequence, and the magnetic separation bridge is a triangular structure.

[0017] Compared with the prior art, the motor has the following beneficial technical effects:

[0018] The motor and the duct are integrated in the application, the propeller and the duct are coaxially installed, and rotate in the same direction. The design of the middle guide vane can make the air flow out of the duct under high pressure, and form a strong thrust. The concentrated winding form of the motor in the application, the number of stator slots cooperating with the number of rotor poles output a sine wave back electromotive force, so that the controller can realize sine wave non-inductive control. The design of the rotor magnetic bridge in the application makes the magnetic induction line flexible, so as to reduce the tooth slot pulsation. In addition, the motor design in the application can make the high-speed and high-pressure air in the duct blow away the wind noise quickly, so that the aircraft is in the front end of the wind noise, and the electromagnetic noise during operation is reduced. BRIEF DESCRIPTION OF DRAWINGS

[0019] The application will be further described below in combination with the drawings.

[0020] Figure 1 It is a split structure schematic diagram of the application of the electric high-efficiency high-pressure duct propulsion device for aviation.

[0021] Figure 2 It is a guide vane and motor shell overhead schematic diagram of the application of the electric high-efficiency high-pressure duct propulsion device for aviation.

[0022] Figure 3 It is an upper propeller overhead schematic diagram of the application of the electric high-efficiency high-pressure duct propulsion device for aviation.

[0023] Figure 4 It is a motor shell internal structure schematic diagram of the application of the electric high-efficiency high-pressure duct propulsion device for aviation.

[0024] Figure 5 It is a magnetic bridge enlarged structure schematic diagram of the application of the electric high-efficiency high-pressure duct propulsion device for aviation.

[0025] Explanation of reference signs:

[0026] 1, outer duct; 2, upper propeller; 21, hub; 22, blade; 3, upper shaft; 4, upper end cover; 5, guide vane; 6, motor shell; 7, lower end cover; 8, lower shaft; 9, lower propeller; 10, stator; 11, tooth; 12, winding resistance; 13, magnet; 14, rotor; 15, rotor shaft hole; 16, magnetic bridge. DETAILED DESCRIPTION

[0027] Reference Figures 1-3This embodiment discloses an electric high-efficiency high-pressure ducted propulsion device for aviation, which consists of an outer duct 1, guide vanes 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 into one unit. This integrated design can greatly improve the service life of the device.

[0028] The motor housing 6 is fitted with a stator with winding 12. The winding outputs three-phase lines UVW. The motor shaft is installed in the middle hole of the rotor. End covers are installed at both ends of the motor shaft. The upper and lower end covers have vents, allowing airflow for good heat dissipation. The end covers are fixed to the upper and lower sides of the housing. The motor shaft protrudes from the middle of the motor end cover, serving as the power output end. The output end is divided into an upper shaft and a lower shaft. The propeller is installed on the upper shaft, and the lower shaft is installed on the lower propeller.

[0029] The propeller has a 30° inclined surface design, and the guide vane 5 has a 40° inclined surface design. The direction of the propeller's inclined surface is opposite to that of the guide vane's inclined surface. The angle difference between the upper and lower propellers is 15°. When the lower point of the upper propeller's inclined surface is aligned with the upper point of the guide vane's inclined surface, the upper point of the lower propeller's inclined surface is aligned with the lower point of the guide vane's inclined surface, which compresses the air downwards and prevents the air from flowing back due to the greater pressure below and the less pressure above.

[0030] refer to Figure 4 The stator 10 has 24 slots, each with a winding. The winding is a concentrated winding method, outputting three-phase power lines UVW and three-phase star connection U1V1W1. The U-phase wire is wound clockwise onto tooth ① and counterclockwise onto tooth ② via a winding, then clockwise onto tooth ⑦ via a bridging wire, and counterclockwise onto tooth ⑧. On the teeth, wrapped counterclockwise On the teeth, clockwise through the bridge line On the teeth, wrapped counterclockwise On the tooth, output the ending U1.

[0031] The V-phase wire end passes through a winding, clockwise around tooth 4 and counterclockwise around tooth 3, then passes through a bridge wire and clockwise around... On the teeth, wrapped counterclockwise On the teeth, the bridge line is wound clockwise around... On the teeth, wrapped counterclockwise On the teeth, the bridge winds clockwise around tooth 10 and counterclockwise around tooth 9 to output the final output V1.

[0032] The W-phase wire is wound clockwise around tooth 5 and counterclockwise around tooth 6 via the winding, and then wound clockwise through the bridge wire. On the teeth, wrapped counterclockwise On the teeth, clockwise around the bridge line On the teeth, clockwise around the bridge line On the teeth, clockwise around the bridge line On the teeth, clockwise around the bridge line On the teeth, clockwise around the bridge line

[0033] The rotor is designed with 20 poles, and 20 magnets are arranged on the outer circle of the rotor, with N poles and S poles arranged in sequence, and a magnetic bridge is designed between two magnets. The magnetic bridge is designed as two opposite triangles, which can reduce cogging torque, increase mechanical strength, and help reduce noise.

[0034] The output is a sine wave back electromotive type, and the inductive control can improve the utilization rate of AC power of the controller.

[0035] Working principle

[0036] The motor UVW three-phase line is connected to AC power, the stator forms a rotating magnetic field, which drives the rotor to rotate, and the rotor drives the propeller to rotate through the motor shaft. The design of the propeller makes the air flow quickly downward, and the air flows to the middle guide vane. The design of the inclined surface of the guide vane increases the speed of the air flowing downward, prevents the high-pressure air below the guide vane from flowing upward, and increases the air pressure below the guide vane. Then, the lower propeller also operates simultaneously. The high-pressure air guided by the guide vane is further pressurized by the lower propeller, so that the air flows quickly out of the duct below in a high-pressure state, forming a strong thrust.

[0037] The noise of the propeller at the end of the duct is greatly reduced. The design of the motor makes the electromagnetic noise during operation reach the minimum, and the high-speed and high-pressure air quickly blows away the wind noise, so that the inside of the aircraft is at the front end of the wind noise, and is isolated from the noise.

[0038] The number of stator and rotor slots can be changed with the number of rotors, which can be 18 slots or 12 slots. The number of blades can be changed according to actual needs, which can be more than 2. The number of upper and lower propellers and guide vanes is the same, such as the design of 2 upper propellers, and the lower propeller and guide vane are also 2.

[0039] The above embodiments only describe the preferred mode 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 modifications and improvements of the technical solutions of the present invention made by those skilled in the art shall fall within the protection scope determined by the claims of the present invention.

Claims

1. An electrically powered high-efficiency high-pressure ducted propulsive device for aviation, characterized in that: The motor shell (6) is arranged in the middle of the outer duct (1) through a plurality of guide vanes (5); the guide vane (5) is a slope structure; the propeller includes a hub and a blade arranged on the shaft; the slope inclination direction of the blade is opposite to the slope inclination direction of the guide vane (5); the inclination angle of the blade is smaller than the slope inclination angle of the guide vane (5). A rotor shaft hole (15) for mounting the shaft is arranged on the axial direction of the rotor (14); an upper shaft (3) is arranged on the inner top of the rotor shaft hole (15), a lower shaft (8) is arranged on the inner bottom of the rotor shaft hole (15), an upper propeller (2) is arranged on the upper shaft (3), and a lower propeller (9) is arranged on the lower shaft (8). The upper propeller (2) and the lower propeller (9) have a fixed phase difference; a plurality of magnets (13) are uniformly and interval arranged on the outer peripheral wall of the rotor (14), and a magnetic separation bridge (16) is arranged between adjacent magnets (13). The top and bottom of the motor shell (6) are respectively provided with an upper end cover (4) and a lower end cover (7); a reserved hole aligned with the rotor shaft hole (15) is arranged in the center of the upper end cover (4) and the center of the lower end cover (7). The angle between the blades of the upper propeller (2) and the lower propeller (9) is 15°.

2. The electrically efficient high pressure ducted propulsive apparatus for aircraft as defined in Claim 1, wherein: A plurality of teeth (11) are uniformly and interval arranged on the inner peripheral wall of the stator (10), and the winding (12) is arranged on the teeth (11).

3. The electrically efficient high pressure ducted propulsive apparatus for aircraft as defined in Claim 1, wherein: There are 24 teeth (11) uniformly and interval arranged on the inner peripheral wall of the stator (10), the winding (12) is arranged on the teeth (11), the winding (12) is a concentrated winding method, and three-phase power lines U, V, W and three-phase star connection U1, V1, W1 are output.

4. The electrically efficient high pressure ducted propulsive apparatus for aircraft as defined in Claim 1, wherein: There are 20 magnets (13) uniformly and interval arranged on the outer peripheral wall of the rotor (14), the N and S poles of the 20 magnets are arranged on the outer ring of the rotor (14) in turn with one positive and one negative, the magnetic separation bridge (16) is a triangular structure opposite to each other; the magnetic separation bridge (16) is a silicon steel sheet.

5. The electrically efficient high pressure ducted propulsive apparatus for aircraft as claimed in claim 4 wherein: ​ 6. The electrically efficient high pressure ducted propulsive apparatus for aircraft as defined in Claim 1, wherein: ​

Images