CN220577509U - High-heat-dissipation-performance electric ducted fan propeller of aircraft - Google Patents
High-heat-dissipation-performance electric ducted fan propeller of aircraft Download PDFInfo
- Publication number
- CN220577509U CN220577509U CN202322056543.2U CN202322056543U CN220577509U CN 220577509 U CN220577509 U CN 220577509U CN 202322056543 U CN202322056543 U CN 202322056543U CN 220577509 U CN220577509 U CN 220577509U
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- Prior art keywords
- propeller
- aircraft
- annular
- pipe
- fixedly connected
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- 239000007788 liquid Substances 0.000 claims abstract description 23
- 238000001816 cooling Methods 0.000 claims abstract description 15
- 230000017525 heat dissipation Effects 0.000 claims abstract description 11
- 238000007789 sealing Methods 0.000 claims description 12
- 230000006698 induction Effects 0.000 claims description 3
- 239000006185 dispersion Substances 0.000 claims description 2
- 239000002826 coolant Substances 0.000 abstract description 13
- 239000007921 spray Substances 0.000 abstract description 5
- 230000000694 effects Effects 0.000 abstract description 3
- 238000012544 monitoring process Methods 0.000 abstract description 3
- 238000006243 chemical reaction Methods 0.000 abstract description 2
- 230000008054 signal transmission Effects 0.000 abstract description 2
- 239000000110 cooling liquid Substances 0.000 description 5
- 229920000049 Carbon (fiber) Polymers 0.000 description 2
- 239000004917 carbon fiber Substances 0.000 description 2
- 239000002131 composite material Substances 0.000 description 2
- 238000013016 damping Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 241000883990 Flabellum Species 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Cooling Or The Like Of Electrical Apparatus (AREA)
Abstract
The utility model discloses an electric ducted fan propeller of an aircraft, which has high heat dissipation performance. In the above-mentioned scheme, set up cooling module and shutoff subassembly, when the inside motor temperature of propeller main part rises to certain degree, control terminal can respond to the monitoring to the temperature, after exceeding certain threshold value, control terminal can become corresponding signal of telecommunication with temperature signal conversion, and with signal transmission to electric valve, control electric valve opens, two atomizer can spray out the coolant liquid atomizing in the second ring pipe, finally the coolant liquid gets into the propeller main part, in order to cool down the motor, consequently, not only can further dispel the heat to the motor through the coolant liquid on the basis of relying on the air current to discharge heat, still ensured the leakproofness of feed liquor pipe department to the coolant liquid, the condition that the coolant liquid was revealed is avoided appearing, thereby the effect of improving the device practicality has been reached.
Description
Technical Field
The utility model relates to the technical field of electric ducted fan propellers, in particular to an electric ducted fan propeller of an aircraft, which has high heat dissipation performance.
Background
The electric ducted fan propeller is driven by a motor, and the electric ducted fan propeller system is limited by the volume and the structure, has larger power, adopts carbon fiber composite materials for main components such as a shell and blades of the electric ducted fan at present due to the weight reduction requirement, has low heat conduction coefficient relative to the carbon fiber composite materials of metal materials, so that the heat productivity of the motor is very serious in use, but a heat dissipation device cannot be additionally arranged due to the structure and the air performance limitation, and the problem of heat dissipation of the motor is a key point which must be broken through in the electric ducted fan to improve the power density, the lifting efficiency and the operation safety.
In order to solve the above problems, patent document publication No. CN217462619U is an electric ducted fan propeller for an aircraft, comprising a ducted barrel, a motor is fixedly installed in the ducted barrel, blades of the ducted fan are connected to an output shaft of the motor, a fairing is arranged at the front ends of the blades, a plurality of centrifugal fan blades are fixedly connected to the inner wall of the fairing, an air inlet is arranged at the front ends of the fairings, and air outlets of the centrifugal fan blades flow into the motor.
It still has some drawbacks in practical use, such as: above-mentioned electronic ducted fan propeller utilizes the inner wall of paddle front end radome fairing to do centrifugal flabellum structure, and the drainage effect to the air current that gets into the motor can be played to the cooperation corresponding structure to reach the exhaust purpose of accelerating hot air, but when the motor reached certain temperature threshold value, the mode of simply relying on the air current to drive hot air exhaust can not reach effectual heat dissipation cooling effect, consequently still can lead to the motor overheated and unable normal operating.
Disclosure of Invention
In order to overcome the defects in the prior art, the embodiment of the utility model provides the electric ducted fan propeller of the aircraft with high heat dissipation performance, so as to solve the problem that the prior art still has certain limitation in a mode of simply discharging heat by means of air flow.
In order to solve the technical problems, the utility model provides the following technical scheme: the utility model provides an electronic duct fan propeller of aircraft that heat dispersion is high, includes the propeller main part, the inside rotation of propeller main part is installed the paddle, the front end of paddle is provided with the kuppe, the inside fixed mounting of propeller main part has the kuppe, the fixed surface mounting of propeller main part has cooling module, the bottom surface fixed mounting of cooling module has the shutoff subassembly.
The cooling assembly comprises a first annular pipe, a liquid inlet pipe is fixedly communicated with the bottom surface of the first annular pipe, a control terminal is fixedly arranged in the first annular pipe, a communicating pipe is fixedly communicated with the top surface of the first annular pipe, a first sealing gasket is fixedly connected with the surface of the communicating pipe, an electric valve is fixedly connected with one end of the communicating pipe, a second annular pipe is fixedly arranged on the surface of the electric valve, and an atomizing nozzle is fixedly connected with the top surface of the second annular pipe.
The plugging assembly comprises a mounting plate, a movable plate is movably mounted in the mounting plate, a rotating shaft is rotatably mounted in the movable plate, a connecting plate is fixedly mounted at one end of the rotating shaft, a mounting plate is fixedly mounted at one side of the connecting plate, and a second sealing gasket and a plugging column are fixedly mounted on the top surface of the mounting plate respectively.
The inner walls of the first annular tube and the second annular tube are fixedly connected with the surface of the propeller main body, the number of the atomizing nozzles is two, the atomizing nozzles are fixedly communicated with the top surface of the second annular tube, the surfaces of the atomizing nozzles are fixedly connected with the surface of the propeller main body, the bottom surface of the first sealing gasket is attached to the top surface of the first annular tube, and the induction end of the control terminal is connected with the surface of the propeller main body.
The top surface of the mounting plate is fixedly connected with the bottom surface of the first annular tube, the surface of the plugging column is attached to the inner wall of the liquid inlet tube, and the surface of the second sealing gasket is attached to the bottom end of the liquid inlet tube.
The technical scheme of the utility model has the following beneficial effects:
in the above-mentioned scheme, set up cooling module and shutoff subassembly, when the inside motor temperature of propeller main part rises to certain degree, control terminal can respond to the monitoring to the temperature, after exceeding certain threshold value, control terminal can become corresponding signal of telecommunication with temperature signal conversion, and with signal transmission to electric valve, control electric valve opens, thereby coolant liquid in the first ring pipe can carry to in the second ring pipe through communicating pipe, and can spray out the coolant liquid atomizing in the second ring pipe through two atomizer, finally the coolant liquid gets into the propeller main part, in order to cool down to the motor, when needs are to the inside coolant liquid of adding of first ring pipe, at first with the fly leaf downwardly moving, make the shutoff post that the mounting disc top surface is connected can synchronous movement, and shift out from the inside of feed liquor pipe, when the shutoff post shifts out completely, rotate the connecting plate, make the shutoff post rotate to the opposite side, can add the coolant liquid afterwards, the shutoff is carried out the shutoff to the feed liquor pipe with the second sealing pad, consequently, not only can rely on the motor of air current exhaust heat, through the coolant liquid, the performance to the coolant liquid is further guaranteed to the coolant liquid, the practicality is guaranteed, the cooling device has been reached, thereby the practicality is improved.
Drawings
FIG. 1 is a schematic diagram of the overall structure of the present utility model;
FIG. 2 is a perspective assembly view of the overall device of the present utility model;
FIG. 3 is a schematic view of a cooling assembly according to the present utility model;
fig. 4 is a schematic structural view of a plugging assembly according to the present utility model.
[ reference numerals ]
1. A pusher body; 2. a paddle; 3. a fairing; 4. a guide cover; 5. a cooling assembly; 6. a plugging assembly; 51. a first annular tube; 52. a liquid inlet pipe; 53. a control terminal; 54. a communicating pipe; 55. a first gasket; 56. an electric valve; 57. a second annular tube; 58. an atomizing nozzle; 61. a mounting plate; 62. a movable plate; 63. a rotating shaft; 64. a connecting plate; 65. a mounting plate; 66. a second gasket; 67. and plugging the column.
Detailed Description
In order to make the technical problems, technical solutions and advantages to be solved more apparent, the following detailed description will be given with reference to the accompanying drawings and specific embodiments.
The embodiment of the utility model provides an electric ducted fan propeller of an aircraft with high heat dissipation performance, as shown in fig. 1 to 4, comprising a propeller main body 1, wherein a blade 2 is rotatably arranged in the propeller main body 1, a fairing 3 is arranged at the front end of the blade 2, a fairing 4 is fixedly arranged in the propeller main body 1, a cooling component 5 is fixedly arranged on the surface of the propeller main body 1, and a plugging component 6 is fixedly arranged on the bottom surface of the cooling component 5.
The cooling assembly 5 includes a first annular tube 51, the bottom surface of the first annular tube 51 is fixedly connected with a liquid inlet tube 52, the inside of the first annular tube 51 is fixedly connected with a control terminal 53, the top surface of the first annular tube 51 is fixedly connected with a communicating tube 54, the surface of the communicating tube 54 is fixedly connected with a first sealing pad 55, one end of the communicating tube 54 is fixedly connected with an electric valve 56, the surface of the electric valve 56 is fixedly connected with a second annular tube 57, the top surface of the second annular tube 57 is fixedly connected with an atomizing spray head 58, the inner walls of the first annular tube 51 and the second annular tube 57 are fixedly connected with the surface of the propeller main body 1, the number of the atomizing spray heads 58 is two, the surfaces of the atomizing spray heads 58 are fixedly connected with the surface of the propeller main body 1, the bottom surface of the first sealing pad 55 is attached to the top surface of the first annular tube 51, the surface of the control terminal 53 is fixedly connected with the surface of the electric motor main body 1, the electric motor is connected with the surface of the electric motor main body 53, and the electric motor main body 1 is connected with the electric motor main body 1 through the temperature sensor, and the electric motor is connected with the electric motor main body 1, and the electric motor main body 1 is cooled, the temperature sensor is connected with the electric motor main body 1, and the temperature sensor is connected with the electric motor main body through the electric motor and the electric motor, the electric motor and the electric motor is connected with the electric motor and the electric motor.
Wherein, as shown in fig. 4, the plugging assembly 6 comprises a mounting plate 61, the inside movable mounting of mounting plate 61 has fly leaf 62, the inside rotation of fly leaf 62 is installed and is rotated shaft 63, the one end fixed mounting of shaft 63 has connecting plate 64, one side fixed mounting of connecting plate 64 has mounting plate 65, the top surface of mounting plate 65 is fixed mounting respectively has second sealed 66 and shutoff post 67, the top surface of mounting plate 61 and the bottom surface fixed connection of first ring pipe 51, the surface of shutoff post 67 is laminated with the inner wall of feed liquor pipe 52, the surface of second sealed 66 is laminated with the bottom of feed liquor pipe 52, through the fly leaf 62 and the shaft 63 structure that set up, both surfaces are damping material, consequently the damping material can play certain fixed action to fix the position of fly leaf 62 and connecting plate 64.
The working process of the utility model is as follows: when the temperature of the motor inside the propeller main body 1 rises to a certain extent, the control terminal 53 can perform induction monitoring on the temperature, after a certain threshold value is exceeded, the control terminal 53 can convert a temperature signal into a corresponding electric signal, the signal is transmitted to the electric valve 56, the electric valve 56 is controlled to be opened, cooling liquid in the first annular tube 51 can be conveyed into the second annular tube 57 through the communicating tube 54, cooling liquid in the second annular tube 57 can be atomized and sprayed out through the two atomizing nozzles 58, finally the cooling liquid enters the propeller main body 1 to cool the motor, when the cooling liquid needs to be added into the first annular tube 51, the movable plate 62 is firstly moved downwards, so that the plugging column 67 connected to the top surface of the mounting plate 65 can be synchronously moved and moved out of the inside of the liquid inlet tube 52, when the plugging column 67 is completely moved out, the connecting plate 64 is rotated, the plugging column 67 can be rotated to the other side, the cooling liquid can be added at this time, and then the plugging column 67 is reset in cooperation with the second sealing pad 66 to plug the liquid inlet tube 52.
The last points to be described are: first, in the description of the present application, it should be noted that, unless otherwise specified and defined, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be mechanical or electrical, or may be a direct connection between two elements, and "upper," "lower," "left," "right," etc. are merely used to indicate relative positional relationships, which may be changed when the absolute position of the object being described is changed;
secondly: in the drawings of the disclosed embodiments, only the structures related to the embodiments of the present disclosure are referred to, and other structures can refer to the common design, so that the same embodiment and different embodiments of the present disclosure can be combined with each other under the condition of no conflict;
finally: the foregoing description of the preferred embodiments of the utility model is not intended to limit the utility model to the precise form disclosed, and any such modifications, equivalents, and alternatives falling within the spirit and principles of the utility model are intended to be included within the scope of the utility model.
Claims (5)
1. The utility model provides an electronic duct fan propeller of aircraft that heat dispersion is high, includes the propeller main part, the inside rotation of propeller main part is installed the paddle, the front end of paddle is provided with the kuppe, the inside fixed mounting of propeller main part has the kuppe, a serial communication port, the fixed surface of propeller main part installs cooling module, the bottom surface fixed mounting of cooling module has the shutoff subassembly.
2. The electric ducted fan propeller of an aircraft with high heat dissipation performance according to claim 1, wherein the cooling assembly comprises a first annular pipe, a liquid inlet pipe is fixedly communicated with the bottom surface of the first annular pipe, a control terminal is fixedly installed in the first annular pipe, a communicating pipe is fixedly communicated with the top surface of the first annular pipe, a first sealing gasket is fixedly connected with the surface of the communicating pipe, an electric valve is fixedly connected with one end of the communicating pipe, a second annular pipe is fixedly installed on the surface of the electric valve, and an atomizing nozzle is fixedly connected with the top surface of the second annular pipe.
3. The electric ducted fan propeller of an aircraft with high heat dissipation performance according to claim 1, wherein the plugging assembly comprises a mounting plate, a movable plate is movably mounted in the mounting plate, a rotating shaft is rotatably mounted in the movable plate, a connecting plate is fixedly mounted at one end of the rotating shaft, a mounting plate is fixedly mounted at one side of the connecting plate, and a second sealing gasket and a plugging column are fixedly mounted on the top surface of the mounting plate respectively.
4. The electric ducted fan propeller of the aircraft with high heat dissipation performance according to claim 2, wherein the inner walls of the first annular tube and the second annular tube are fixedly connected with the surface of the propeller main body, the number of the atomizing nozzles is two, the two atomizing nozzles are fixedly communicated with the top surface of the second annular tube, the surfaces of the two atomizing nozzles are fixedly connected with the surface of the propeller main body, the bottom surface of the first sealing gasket is attached to the top surface of the first annular tube, and the induction end of the control terminal is connected with the surface of the propeller main body.
5. The electric ducted fan propeller of an aircraft with high heat dissipation performance according to claim 3, wherein the top surface of the mounting plate is fixedly connected with the bottom surface of the first annular tube, the surface of the plugging column is attached to the inner wall of the liquid inlet tube, and the surface of the second sealing gasket is attached to the bottom end of the liquid inlet tube.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322056543.2U CN220577509U (en) | 2023-08-02 | 2023-08-02 | High-heat-dissipation-performance electric ducted fan propeller of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322056543.2U CN220577509U (en) | 2023-08-02 | 2023-08-02 | High-heat-dissipation-performance electric ducted fan propeller of aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220577509U true CN220577509U (en) | 2024-03-12 |
Family
ID=90108201
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322056543.2U Active CN220577509U (en) | 2023-08-02 | 2023-08-02 | High-heat-dissipation-performance electric ducted fan propeller of aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220577509U (en) |
-
2023
- 2023-08-02 CN CN202322056543.2U patent/CN220577509U/en active Active
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