CN108488082B - Electric drive torque self-balancing shaftless ducted fan or shaftless ducted blade for aircraft - Google Patents

Electric drive torque self-balancing shaftless ducted fan or shaftless ducted blade for aircraft Download PDF

Info

Publication number
CN108488082B
CN108488082B CN201810382089.0A CN201810382089A CN108488082B CN 108488082 B CN108488082 B CN 108488082B CN 201810382089 A CN201810382089 A CN 201810382089A CN 108488082 B CN108488082 B CN 108488082B
Authority
CN
China
Prior art keywords
shaftless
frame
duct
ducted
fan
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
CN201810382089.0A
Other languages
Chinese (zh)
Other versions
CN108488082A (en
Inventor
尹小林
赵海洋
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Changsha Zichen Technology Development Co Ltd
Original Assignee
Changsha Zichen Technology Development Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Changsha Zichen Technology Development Co Ltd filed Critical Changsha Zichen Technology Development Co Ltd
Priority to CN201810382089.0A priority Critical patent/CN108488082B/en
Publication of CN108488082A publication Critical patent/CN108488082A/en
Application granted granted Critical
Publication of CN108488082B publication Critical patent/CN108488082B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • F04D25/06—Units comprising pumps and their driving means the pump being electrically driven
    • F04D25/0606—Units comprising pumps and their driving means the pump being electrically driven the electric motor being specially adapted for integration in the pump
    • F04D25/066—Linear Motors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • F04D25/08—Units comprising pumps and their driving means the working fluid being air, e.g. for ventilation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K5/00—Plants including an engine, other than a gas turbine, driving a compressor or a ducted fan
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • F04D19/02—Multi-stage pumps
    • F04D19/024—Multi-stage pumps with contrarotating parts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • F04D25/06—Units comprising pumps and their driving means the pump being electrically driven
    • F04D25/0606—Units comprising pumps and their driving means the pump being electrically driven the electric motor being specially adapted for integration in the pump
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/16—Combinations of two or more pumps ; Producing two or more separate gas flows
    • F04D25/166—Combinations of two or more pumps ; Producing two or more separate gas flows using fans
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/002—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids by varying geometry within the pumps, e.g. by adjusting vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/34—Blade mountings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K7/00—Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
    • H02K7/14—Structural association with mechanical loads, e.g. with hand-held machine tools or fans

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Power Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The electric drive torque self-balancing shaftless ducted fan or shaftless ducted blade for the aircraft comprises a ducted barrel frame and at least one group of shaftless fans or shaftless blades rotating reversely, wherein the shaftless fans or shaftless blades are arranged in the ducted barrel frame to form shaftless ducted fans or shaftless ducted blades. The invention has simple structure and convenient installation and use, is suitable for aircrafts which are widely applied at present, and is especially suitable for manned aircrafts which need low noise, high lift force or thrust and self-balancing torque.

Description

Electric drive torque self-balancing shaftless ducted fan or shaftless ducted blade for aircraft
Technical Field
The invention relates to the technical field of aircraft power, in particular to an electric drive torque self-balancing shaftless ducted fan or shaftless ducted blades for an aircraft.
Background
Today, blades or ducted fans are widely applied to various aircrafts, and various types of ducted fans or blades are endlessly designed as power of the aircrafts in order to promote the lift of the blades or reduce noise, etc. However, since the known ducted fans or blades are operated by rotating the rotor blades with the hub through the central shaft, the conventional ducted fans or blades with shafts have the following disadvantages: firstly, the existence of the hub occupies a larger air circulation space to block the flow of air flow, in order to ensure that the fan has enough flow area when in work, a mode of enlarging the outer diameter of the blade is generally adopted, but the increase of the outer diameter of the blade causes the increase of the linear speed of the blade tip, so that the noise is increased, and the blade tip is easy to deform under the pneumatic action to reduce the efficiency; secondly, boundary layer separation and secondary flow often exist at the joint of the traditional fan hub and the blades, so that the energy conversion effect is affected, and meanwhile, the work efficiency of the blades is reduced; thirdly, in order to prevent the blade tip and the duct wind barrel from being scratched, a gap, namely a blade top gap, is usually reserved between the blade tip and the duct wind barrel, and when the air conditioner runs, high-pressure air on the pressure surface of the blade can bypass the blade top gap and flow into the suction surface of the blade, so that leakage of flow is generated, volume loss is caused, the stability of a flow field is damaged, and finally the efficiency of the whole air conditioner is reduced.
In order to solve the problems, scientists have made a great deal of technical innovation and improvement, especially in the design of fans, for example, china patent application with the application number 201710914763.0 discloses a gear rack driven shaftless fan, the technical scheme is that a gear rack is driven by a motor, a rotor component which is in sliding friction is driven by the gear rack from a rim to rotate, although a central shaft and a hub are reduced, a lubricating device which is complex and difficult to maintain is required to be independently arranged in the mechanism design of the fan, meanwhile, the relative installation positions of the motor and the fan are inconvenient to use and have larger volume, the technical scheme provides a new scheme for the design of the fan, but is only a shaftless fan, and the structural characteristics of the shaftless fan determine that the shaftless fan cannot be used as a duct fan or a blade of an aircraft; the chinese patent application with the application number 201220325785.6 discloses a shaftless fan, it includes fan frame, stator component, rotor component and direction subassembly, its stator component is arranged in the fan frame, the rotor component is promoted by the magnetic ring of stator component along direction subassembly, it is mainly used computer heat dissipation, be a miniature fan device for heat dissipation, it is not adapted to the ducted fan for aircraft, still there is the following defect simultaneously, firstly, only be applicable to in the box such as computer and use, no waterproof performance, can not adapt to the environment of aircraft operation, second, it can't realize moment of torsion self-balancing, third, its frame construction is unfavorable for the control of noise.
To date, no shaftless ducted fan or shaftless ducted blade for an aircraft exists, and no shaftless ducted fan or shaftless ducted blade which has the advantages of torque self-balancing, low noise, high lift force or thrust, simple structure, convenient installation and use and suitability for the aircraft is further not seen.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provide the shaftless ducted fan or shaftless ducted blade for the aircraft, which has the advantages of simple structure, convenient installation and use, low noise, high lift force or thrust and self-balancing torque and high efficiency.
The technical scheme adopted for solving the technical problems is as follows: the utility model provides an electric drive moment of torsion self-balancing shaftless ducted fan or shaftless duct paddle for aircraft, includes duct section of thick bamboo frame and at least one set of counter-rotating shaftless fan or shaftless paddle, shaftless fan or shaftless paddle install in duct section of thick bamboo frame, form shaftless ducted fan or shaftless duct paddle.
Further, the shaftless fan or shaftless blade comprises a stator component and a rotor component, wherein the stator component is mounted on the duct barrel frame, and the rotor component is connected with the duct barrel frame through a bearing or a guide rail; the stator component comprises an armature installed in the duct barrel frame and a controller fixed on the duct barrel frame, the armature is electrically connected with the controller, and the controller is used for controlling the rotor component to be driven to rotate by forming an alternating magnetic field when the power is on; the rotor component comprises a rotor frame, permanent magnets, blades or paddles, wherein the permanent magnets are fixed on the outer wall of the rotor frame, and the blades or paddles are fixed on the inner wall of the rotor frame.
Further, the rotating wheel frame is of a cylindrical or annular structure.
Further, the outer wall of the rotating wheel frame is provided with permanent magnet fixing grooves uniformly distributed at intervals and used for fixing the permanent magnets, the inner wall of the rotating wheel frame is provided with concave structures uniformly distributed at intervals and used for installing blades or paddles, the blades or paddles can be connected with the concave structures of the rotating wheel frame through connecting pieces, smoothness of the inner wall of the rotating wheel frame and the connected inner wall is guaranteed, and wind resistance and disturbance turbulence are reduced.
Further, the duct barrel frame comprises a duct frame and an annular end cover, wherein the duct frame is a mounting bracket of the shaftless fan or shaftless blade, and the annular end cover is connected with the end part of the duct frame through a connecting piece and used for fixing the shaftless fan or shaftless blade and preventing the shaftless fan or shaftless blade from sliding axially.
Further, two ends of the rotating wheel frame of the shaftless fan or shaftless blade are respectively connected with the duct frame and the annular end cover through bearings.
Further, the end part of the rotating wheel frame of the shaftless fan or shaftless blade is connected with the end part of the adjacent rotating wheel body through a bearing and is connected with the annular end cover through the bearing.
Further, the rotating wheel frame and the annular end cover are provided with bearing seats for fixing bearings, and the bearing seats are used for clamping the bearings and fixing the rotor component in the center of the duct.
Further, a power supply device is provided, which supplies the armature with electric energy through the controller, and generates alternating exciting magnetic fields for driving the rotor component to rotate.
Further, a swinging device is also arranged, the swinging device is connected with the duct frame and can rotate the swinging device, and the lift force direction of the electric drive torque self-balancing shaftless ducted fan or shaftless blades for the aircraft is regulated, so that the flight direction of the aircraft is controlled.
Further, the inlet and outlet of the duct barrel frame are also provided with air guide mechanisms which are fixed on the annular end covers and are flared to enlarge the air inlet area and the air dispersing area, so that the lift force is further improved, and the efficiency of the electric drive torque self-balancing shaftless duct fan or shaftless paddles for the aircraft is improved.
The electric drive torque self-balancing shaftless ducted fan or shaftless blade for the aircraft uses the power supply device as an armature of a stator component fixed on the duct barrel frame to supply power, and generates an alternating magnetic field through the control of the controller, drives a runner body on a rotor component with a permanent magnet fixed through a bearing to rotate, drives the blade fixed on the runner body to rotate, generates lifting force, and counteracts the reaction torque of rotation when a single shaftless fan flies by a group of two shaftless fans or shaftless blades rotating reversely, simultaneously provides unidirectional continuous jet type wind current, and provides high lifting force or thrust, and has simple structure, practicability and great noise reduction.
The invention has the beneficial effects that:
1. The invention adopts the power supply device to directly supply power and drives the two shaftless fans with blades fixed at the edges in a reverse rotation way by electromagnetic force, the reverse rotation not only can offset the reaction force of unidirectional rotation of a single shaftless fan to achieve torque self-balancing, but also provides wind current sprayed along the central direction of a culvert, and provides high lift force or thrust.
2. The shaftless fan has the advantages that the blade/blade fixed by the rim can greatly reduce the rotating speed of the blade tip, greatly reduce aerodynamic noise, reduce the deformation of the blade tip and improve efficiency.
3. The traditional hub is reduced, the working area of fluid can be greatly increased, the fluid flow resistance is reduced, the fluid flows more uniformly, the noise source is restrained, meanwhile, the duct is used for sound insulation, and the noise level of an aircraft can be greatly reduced.
4. Simple structure, convenient to install and use, be applicable to at present with the aircraft of gradually wide application use, be particularly useful for the manned aircraft that needs low noise, high lift or thrust and moment of torsion self-balancing.
Drawings
FIG. 1 is a schematic structural diagram of embodiment 1 of the present invention;
FIG. 2 is a cross-sectional view A-A of FIG. 1;
FIG. 3 is a schematic structural diagram of embodiment 2 of the present invention;
in the figure: 1-duct cylinder frame, 101-duct frame, 102-annular end cover, 2-shaftless fan, 21-stator part, 22-rotor part, 211-armature, 212-controller, 221-rotor frame, 222-permanent magnet, 223-blade, 3-swinging device, 4-wind guiding mechanism.
Detailed Description
The invention is further described below with reference to the drawings and examples.
Example 1
Referring to fig. 1 and 2, an electric drive torque self-balancing shaftless ducted fan for an aircraft comprises a ducted barrel frame 1 and a group of shaftless fans 2 rotating reversely, wherein the shaftless fans 2 are installed in the ducted barrel frame 1 to form shaftless ducted fans. The set of counter-rotating shaftless fans 2 comprises two shaftless fans of opposite direction.
Each shaftless fan 2 comprises a stator part 21 and a rotor part 22, wherein the stator part 21 is mounted on the ducted-barrel frame 1, and the rotor part 22 is connected with the ducted-barrel frame 1 through a bearing; the stator part 21 comprises an armature 211 installed in the duct tube rack and a controller 212 fixed on the duct tube rack, wherein the armature 211 is electrically connected with the controller 212; the rotor member 22 is urged to rotate by the controller 212 controlling a magnetic field that may be alternately formed when energized; the rotor member 22 includes a rotor frame 221, permanent magnets 222, and blades 223, the permanent magnets 222 being fixed to the outer wall of the rotor frame 221, and the blades 223 being fixed to the inner wall of the rotor frame 221. The wheel frame 221 has a cylindrical structure. Permanent magnet fixed slots uniformly distributed at intervals are formed in the outer wall of the rotating wheel frame 221 and used for fixing the permanent magnets 222, concave structures uniformly distributed at intervals are formed in the inner wall of the rotating wheel frame 221 and used for installing the blades 223, the blades 223 can be connected with the concave structures of the rotating wheel frame 221 through bolts, smoothness of the inner wall of the rotating wheel frame 221 and the connected inner wall is guaranteed, and wind resistance and disturbance turbulence are reduced.
The duct barrel frame 1 comprises a duct frame 101 and an annular end cover 102, the duct frame 1 is a mounting bracket of the shaftless fan 2, and the annular end cover 102 is connected with the end part of the duct frame 101 through a connecting bolt and used for fixing the shaftless fan 2 and preventing the shaftless fan from sliding axially.
Both ends of the runner frame 221 of the shaftless fan 2 are respectively connected with the duct frame 101 and the annular end cover 102 through bearings.
The runner frame 221 and the annular end cover 102 are provided with bearing seats for fixing bearings, and are used for clamping the bearings and fixing the rotor component in the center of the duct.
The electric drive torque self-balancing shaftless ducted fan for the aircraft is further provided with a power supply device (not shown in the figure) for supplying electric energy to the armature through the controller to generate alternating excitation magnetic fields for driving the rotor components to rotate.
The electric drive torque self-balancing shaftless ducted fan for the aircraft is further provided with a swinging device 3, the swinging device 3 is connected with the ducted frame 101, and the lifting direction of the electric drive torque self-balancing shaftless ducted fan for the aircraft can be adjusted through rotating the swinging device 3, so that the control of the flight direction of the aircraft is realized.
In the working process, a power supply device is used for supplying power to an armature 211 of a stator part 21 fixed on the duct barrel frame 1, an alternating magnetic field is regulated and generated through a controller 212, a runner frame 221 fixed through a bearing and provided with a permanent magnet 222 is driven to rotate, blades 223 fixed on the runner frame 221 are driven to rotate, lift force is generated, a group of shaftless fans 2 rotating reversely counteract the reaction force of the single shaftless fan 2 during the flying process, and simultaneously, unidirectional continuous jet type wind current is provided, high lift force or thrust is provided, and the device is simple in structure, practical and greatly reduced in noise.
Example 2
Referring to fig. 3, an electric drive torque self-balancing shaftless ducted fan for an aircraft is mainly different from embodiment 1 in that: the rotating wheel frame 221 of the shaftless fan 2 is connected with the adjacent rotating wheel body through a bearing and is clamped and connected through a bearing seat.
In addition, the inlet and outlet of the duct barrel frame 1 in this embodiment are further provided with a wind guiding mechanism 4, and the wind guiding mechanism 4 is fixed on the annular end cover 102 and is flared to increase the air inlet area and the air dispersing area, further improve the lift force and improve the efficiency of the shaftless duct fan for the aircraft.
Of course, the shaftless fan 2 rotating in opposite directions can be designed into more than two groups; alternatively, the counter-rotating shaftless fan 2 may be designed as counter-rotating shaftless blades.

Claims (2)

1. The utility model provides an electric drive moment of torsion self-balancing shaftless ducted fan or shaftless ducted paddle for aircraft which characterized in that: the system comprises a ducted barrel frame and at least one group of shaftless fans or shaftless paddles rotating reversely, wherein the shaftless fans or shaftless paddles are arranged in the ducted barrel frame to form shaftless ducted fans or shaftless ducted paddles; the shaftless fan or shaftless blade comprises a stator component and a rotor component, wherein the stator component is installed on the duct barrel frame, and the rotor component is connected with the duct barrel frame through a bearing or a guide rail; the stator component comprises an armature installed in the duct barrel frame and a controller fixed on the duct barrel frame, the armature is electrically connected with the controller, and the controller is used for controlling the rotor component to be driven to rotate by forming an alternating magnetic field when the power is on; the rotor component comprises a rotor frame, permanent magnets, blades or paddles, wherein the permanent magnets are fixed on the outer wall of the rotor frame, and the blades or paddles are fixed on the inner wall of the rotor frame; permanent magnet fixing grooves which are uniformly distributed at intervals are formed in the outer wall of the rotating wheel frame and used for fixing permanent magnets, concave structures which are uniformly distributed at intervals are formed in the inner wall of the rotating wheel frame and used for installing blades or paddles, the blades or paddles are connected with the concave structures of the rotating wheel frame through connecting pieces, smoothness of the inner wall of the rotating wheel frame and the connected inner wall is guaranteed, and wind resistance and disturbance turbulence are reduced; the duct barrel frame comprises a duct frame and an annular end cover, the duct frame is a mounting bracket of a shaftless fan or shaftless blade, and the annular end cover is connected with the end part of the duct frame through a connecting piece; the two ends of the rotating wheel frame of the shaftless fan or shaftless blade are respectively connected with the duct frame and the annular end cover through bearings; the end part of the rotating wheel frame of the shaftless fan or shaftless blade is connected with the end part of the adjacent rotating wheel body through a bearing and is connected with the annular end cover through a bearing; the power supply device is used for providing electric energy for the armature through the controller, generating an alternating excitation magnetic field and driving the rotor component to rotate; the swing device is connected with the duct frame, and the lift force direction of the electric drive torque self-balancing shaftless duct fan or shaftless blade for the aircraft is adjusted through rotating the swing device, so that the flight direction of the aircraft is controlled; the inlet and outlet of the duct barrel frame are also provided with air guide mechanisms which are fixed on the annular end covers and are expanded in a horn shape.
2. The electric drive torque self-balancing shaftless ducted fan or shaftless ducted blade for an aircraft of claim 1, wherein: the rotating wheel frame is of a cylindrical or annular structure.
CN201810382089.0A 2018-04-26 2018-04-26 Electric drive torque self-balancing shaftless ducted fan or shaftless ducted blade for aircraft Active CN108488082B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201810382089.0A CN108488082B (en) 2018-04-26 2018-04-26 Electric drive torque self-balancing shaftless ducted fan or shaftless ducted blade for aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201810382089.0A CN108488082B (en) 2018-04-26 2018-04-26 Electric drive torque self-balancing shaftless ducted fan or shaftless ducted blade for aircraft

Publications (2)

Publication Number Publication Date
CN108488082A CN108488082A (en) 2018-09-04
CN108488082B true CN108488082B (en) 2024-09-10

Family

ID=63314154

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201810382089.0A Active CN108488082B (en) 2018-04-26 2018-04-26 Electric drive torque self-balancing shaftless ducted fan or shaftless ducted blade for aircraft

Country Status (1)

Country Link
CN (1) CN108488082B (en)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111852687A (en) * 2019-04-29 2020-10-30 贯月航空技术(杭州)有限公司 Electric contra-rotating ducted fan
CN110654190A (en) * 2019-10-31 2020-01-07 南京航空航天大学 Tilting shaftless ducted rotor aerocar and working method thereof
CN110949658A (en) * 2019-12-13 2020-04-03 南京华航翼飞行器技术有限公司 Miniature shaftless ducted rotor craft and flight control method thereof
CN113404712B (en) * 2020-03-16 2024-07-16 广东美的白色家电技术创新中心有限公司 Fan, air conditioner outdoor unit and air conditioner
CN111891337A (en) * 2020-07-15 2020-11-06 浙江安浮航空科技有限公司 High-speed shaftless duct type rotor wing
CN114087123B (en) * 2021-12-02 2024-04-26 华北水利水电大学 Shaftless wind driven generator, maximum power tracking power generation and grid-connected decoupling control method

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN206503738U (en) * 2016-12-29 2017-09-19 深圳光启合众科技有限公司 Ducted fan
CN107461354A (en) * 2017-09-23 2017-12-12 西北工业大学 A kind of shaftless blower fan of wheel rim drive-type
CN208203623U (en) * 2018-04-26 2018-12-07 长沙紫宸科技开发有限公司 The shaftless ducted fan of torque self-balancing or shaftless culvert channel blade are driven in aircraft electricity consumption

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7032861B2 (en) * 2002-01-07 2006-04-25 Sanders Jr John K Quiet vertical takeoff and landing aircraft using ducted, magnetic induction air-impeller rotors
CN102052339A (en) * 2011-01-20 2011-05-11 浙江理工大学 Double-layer reverse axial fan
CN205952317U (en) * 2016-08-27 2017-02-15 翟正 Disk -type unmanned vehicles
CN207145293U (en) * 2017-07-13 2018-03-27 浙江双阳风机有限公司 A kind of convection rotary type axial flow fan with adjustable moving blades

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN206503738U (en) * 2016-12-29 2017-09-19 深圳光启合众科技有限公司 Ducted fan
CN107461354A (en) * 2017-09-23 2017-12-12 西北工业大学 A kind of shaftless blower fan of wheel rim drive-type
CN208203623U (en) * 2018-04-26 2018-12-07 长沙紫宸科技开发有限公司 The shaftless ducted fan of torque self-balancing or shaftless culvert channel blade are driven in aircraft electricity consumption

Also Published As

Publication number Publication date
CN108488082A (en) 2018-09-04

Similar Documents

Publication Publication Date Title
CN108488082B (en) Electric drive torque self-balancing shaftless ducted fan or shaftless ducted blade for aircraft
EP3625123B1 (en) Combined fan and motor
CN208203623U (en) The shaftless ducted fan of torque self-balancing or shaftless culvert channel blade are driven in aircraft electricity consumption
GB2565886B (en) Electric engine
EP3626611B1 (en) Aircraft propulsion system
KR20130076781A (en) Electrical powered tail rotor of a helicopter
CN111152907B (en) Propulsion system and control method thereof
US11884386B2 (en) System, assemblies and methods for mechanical-thrust power conversion multifans
WO2020121671A1 (en) Motor-integrated fluid machine and vertical take-off and landing aircraft
CN103944313A (en) Direct-coupled magnetic suspension fan
CN112874746A (en) Birotor pump spouts propeller and adopts instrument of marcing of this propeller
US20230415903A1 (en) Electically powered engine
CN210985876U (en) Novel electric culvert power device
CN113978740B (en) Double-rotor rim-driven inner and outer duct type propeller for aviation
CN114726177A (en) Permanent magnet contra-rotating propulsion motor and aircraft
CN112678138A (en) Tandem motor pump jet propeller
CN217125119U (en) Magnetic suspension propeller and turbojet engine applying same
CN214617056U (en) Shaftless fluid jet equipment
CN115123539B (en) Magnetic suspension electric tail rotor of helicopter
CN215860876U (en) Magnetic suspension axial flow fan with impeller as thrust disc
CN114368472A (en) Magnetic suspension propeller and turbojet engine applying same
CN113978703A (en) Rim drive formula duct propeller of aviation usefulness
US20240158073A1 (en) System, assemblies and methods for mechanical-thrust power conversion multifans
CN213783105U (en) Permanent magnet contra-rotating propulsion motor and aircraft
CN116495158B (en) Ducted shaftless water jet propeller

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant