CN208203623U - The shaftless ducted fan of torque self-balancing or shaftless culvert channel blade are driven in aircraft electricity consumption - Google Patents
The shaftless ducted fan of torque self-balancing or shaftless culvert channel blade are driven in aircraft electricity consumption Download PDFInfo
- Publication number
- CN208203623U CN208203623U CN201820603045.1U CN201820603045U CN208203623U CN 208203623 U CN208203623 U CN 208203623U CN 201820603045 U CN201820603045 U CN 201820603045U CN 208203623 U CN208203623 U CN 208203623U
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- Prior art keywords
- shaftless
- blade
- duct
- fan
- balancing
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Classifications
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- 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
- 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
- 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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The shaftless ducted fan of torque self-balancing or shaftless culvert channel blade are driven in aircraft electricity consumption, including duct tub and at least one set of shaftless fan or shaftless blade reversely rotated, the shaftless fan or shaftless blade are mounted in duct tub, form shaftless ducted fan or shaftless culvert channel blade.The utility model structure is simple, and is easily installed use, is suitable for using at present with increasingly widely applied aircraft, is particularly suitable for needing the manned vehicle of low noise, high-lift or thrust and torque self-balancing.
Description
Technical field
The utility model relates to aircraft power technical fields, and in particular to a kind of aircraft electricity consumption drive torque self-balancing without
Axis ducted fan or shaftless culvert channel blade.
Background technique
Today, blade or ducted fan are widely used to all kinds of aircraft, in order to promote blade lift or reduce noise
Deng various forms of ducted fans or blade etc. emerge one after another as the design scheme of aircraft power.But because of well known duct
Fan or blade are worked in such a way that central axis drive hub is with movable vane piece rotation, existing to have axis ducted fan
Or blade have the disadvantage that first is that, the presence of wheel hub occupies biggish air passing space, hinders the flowing of air-flow, is
There is enough circulation areas when the work of guarantee blower, be commonly designed by the way of increasing outer blade diameter, but outer blade diameter
Increase cause the increase of blade tip linear velocity, will lead to the increase of noise, and be easily deformed and lead at blade tip under pneumatic action
Efficiency is caused to reduce;Second is that the junction of conventional fan wheel hub and blade is usually present boundary layer separation and Secondary Flow, energy is affected
The conversion effect of amount, while reducing blade work doing efficiency;Third is that blade tip is scratched with duct air duct in order to prevent,
Between the two would generally be there are gap, i.e. blade tip clearance, when operation, the high pressure gas of blade pressure surface can bypass blade tip clearance stream
Enter blade suction surface, not only create the leakage of flow in this way, cause volumetric loss, and destroy the stability in flow field, most
Lead to the reduction of overall efficiency eventually.
To solve the above-mentioned problems, scientific worker has carried out a large amount of technological innovation and improvement, especially setting in blower
On meter, such as application No. is 201710914763.0 Chinese patent applications to disclose a kind of shaftless blower of gear-rack drive formula,
Its technical solution is to be revolved by rack-and-pinion from the rotor part of wheel rim driving sliding friction by motor driven gear rack gear
Turn, although reducing central axis and wheel hub, needs individually to add complicated and maintenance difficult profit in the mechanism design of the blower
Sliding device, at the same its motor and blower relative mounting location inconvenience use and volume it is larger, though the technical solution is blower
Design provides a kind of new departure, but only a kind of technical solution of shaftless blower, structure feature determine that it cannot function as
The ducted fan or blade of aircraft;Application No. is 201220325785.6 Chinese patent applications to disclose a kind of shaftless wind
Fan comprising fan frame, stator component, rotor component and guidance set, stator component are placed in fan frame, and rotor component is along guiding
Component is pushed by the magnet ring of stator component, is mainly used for computer heat dissipation, is a kind of heat transmission mini-fan device, is not suitable with
In aircraft ducted fan, while there is also following deficiencies, first is that, it is only applicable to use in the cabinets such as computer, no waterproofness
Can, do not adapt to aircraft operation environment, second, cannot achieve torque self-balancing, third, frame structure is unfavorable for making an uproar
The control of sound.
So far, there has been no the shaftless ducted fan of aircraft or shaftless culvert channel blade, more having no can torque self-balancing, low noise
Sound, high-lift or thrust and structure is simple, easy to install and use, the shaftless ducted fan or shaftless that uses suitable for aircraft
Culvert channel blade.
Utility model content
Technical problem to be solved in the utility model is for overcome the deficiencies in the prior art, to provide a kind of structure letter
List is easily installed use, the shaftless ducted fan of efficient aircraft of low noise, high-lift or thrust and torque self-balancing
Or shaftless culvert channel blade.
The technical scheme adopted by the utility model to solve the technical problem is as follows: torque self-balancing is driven in a kind of aircraft electricity consumption
Shaftless ducted fan or shaftless culvert channel blade, including duct tub and at least one set of shaftless fan or shaftless paddle reversely rotated
Leaf, the shaftless fan or shaftless blade are mounted in duct tub, form shaftless ducted fan or shaftless culvert channel blade.
Further, the shaftless fan or shaftless blade include stator component and rotor part, the stator component installation
In duct tub, the rotor part is connect by bearing or guide rail with duct tub;The stator component includes being mounted on
Armature in duct tub and the controller being fixed in duct tub, the armature, to be electrically connected, pass through control with controller
Device control can form alternate magnetic field drive rotor component rotation when being powered;The rotor part include rotary wheel frame, permanent magnet,
Blade or blade, the permanent magnet are fixed on rotary wheel frame outer wall, and the blade or blade are fixed on rotary wheel frame inner wall.
Further, the rotary wheel frame is tubular or ring structure.
Further, the rotary wheel frame outer wall is equipped with permanent magnet fixing groove uniformly at intervals, is used for fixed permanent magnet, and described turn
Wheel carrier inner wall is equipped with concave architecture uniformly at intervals, and for installing blade or blade, the blade or blade can pass through connector
It is connect with rotary wheel frame concave architecture, while guaranteeing smooth, reduction windage and the disturbance turbulent flow of rotary wheel frame inner wall and interconnecting interior wall.
Further, the duct tub includes duct frame and annular end cap, and the duct frame is shaftless fan or shaftless paddle
The mounting bracket of leaf, the annular end cap is connect with duct frame end portion by connector, for fixing shaftless fan or shaftless paddle
Leaf prevents it from sliding axially.
Further, the both ends of the rotary wheel frame of the shaftless fan or shaftless blade pass through bearing and duct frame and annular respectively
End cap connection.
Further, the end of the rotary wheel frame of the shaftless fan or shaftless blade is connected by bearing and adjacent web end
It connects, and is connect by bearing with annular end cap.
Further, the rotary wheel frame and annular end cap are equipped with the bearing block of fixing bearing, for being clamped bearing and will turn
Subassembly is fixed on duct center.
Further, it is additionally provided with power supply device, the power supply device provides electric energy by controller for armature, generates alternate
Excitation field, for driving rotor part to rotate.
Further, it is additionally provided with pendulous device, the pendulous device is connect with duct frame, can be adjusted by rotary swing device
The lift direction that the shaftless ducted fan of torque self-balancing or shaftless blade are driven in aircraft electricity consumption is saved, realizes aircraft flight direction
Control.
Further, the inlet and outlet of the duct tub are additionally provided with wind guiding mechanism, and the wind guiding mechanism is fixed on annular end cap
On, and flare expands, and increases incoming air area and relieve heat area, further increases lift, improves aircraft electricity consumption and drives torque
The shaftless ducted fan of self-balancing or shaftless blade efficiency.
The aircraft electricity consumption of the utility model drives the shaftless ducted fan of torque self-balancing or shaftless blade with power supply device
It is fixed on the armature supply of the stator component in duct tub, and is controlled by controller and generates alternating fields, is driven through axis
The web rotation on the fixed rotor part with permanent magnet is held, drive is fixed on the rotation of web blade, generates lift,
And with one group of two shaftless fan of reverse rotation or shaftless blade, the reaction of rotation when single shaftless fan flight is offset
Torsion, while providing the distinguished and admirable of unidirectional sustained firing formula, provides high-lift or thrust, and structure is simple, practical and can be greatly reduced
Noise.
The utility model has the beneficial effects that
1. the utility model uses power supply device directly to power and consolidate with two of the reverse rotation of electromagnetism power drive with edge
The shaftless fan of fixed blade, the reaction force that reverse rotation can not only offset single shaftless fan single direction rotation reach torque certainly
Balance, and provide along the distinguished and admirable of duct center position injecting type, high-lift or thrust are provided.
2. the shaftless fan blade/blade fixed with wheel rim, can be greatly reduced blade tip revolving speed, gas can be greatly reduced
Dynamic noise, and reduce blade tip deformation and improve efficiency.
3. reduce traditional wheel hub, can greatly lifting fluid can work done area, while reducing fluid flow resistance, make to flow
The noise grade of aircraft can be greatly reduced with duct sound insulation while inhibiting noise source in the more uniform flowing of body.
4. structure is simple, and is easily installed use, it is suitable for using at present with increasingly widely applied aircraft, it is especially suitable
For needing the manned vehicle of low noise, high-lift or thrust and torque self-balancing.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of the utility model embodiment 1;
Fig. 2 is the A-A cross-sectional view of Fig. 1;
Fig. 3 is the structural schematic diagram of the utility model embodiment 2;
In figure: 1- duct tub, 101- duct frame, 102- annular end cap, the shaftless fan of 2-, 21- stator component, 22- turn
Subassembly, 211- armature, 212- controller, 221- rotary wheel frame, 222- permanent magnet, 223- blade, 3- pendulous device, 4- induced draft fan
Structure.
Specific embodiment
The following is a further explanation of the present invention with reference to the accompanying drawings and embodiments.
Embodiment 1
Referring to Figures 1 and 2, the shaftless ducted fan of torque self-balancing, including duct tub 1 and one are driven in a kind of aircraft electricity consumption
The shaftless fan 2 that group reversely rotates, the shaftless fan 2 are mounted in duct tub 1, form shaftless ducted fan.Described one
The shaftless fan 2 that group reversely rotates includes two and turns to opposite shaftless fan.
Each shaftless fan 2 includes stator component 21 and rotor part 22, and the stator component 21 is mounted on duct
In tub 1, the rotor part 22 is connect by bearing with duct tub 1;The stator component 21 includes being mounted on duct cylinder
Armature 211 in frame and the controller 212 being fixed in duct tub, the armature 211 is with controller 212 to be electrically connected;It is logical
The alternate rotation of magnetic field drive rotor component 22 can be formed when being powered by crossing the control of controller 212;The rotor part 22 includes
Rotary wheel frame 221, permanent magnet 222 and blade 223, the permanent magnet 222 are fixed on 221 outer wall of rotary wheel frame, and the blade 223 is fixed
In 221 inner wall of rotary wheel frame.The rotary wheel frame 221 is tubular construction.221 outer wall of rotary wheel frame is equipped with permanent magnet uniformly at intervals
Fixing groove is used for fixed permanent magnet 222, and 221 inner wall of rotary wheel frame is equipped with concave architecture uniformly at intervals, for installing blade
223, the blade 223 can be connect by bolt with 221 concave architecture of rotary wheel frame, at the same guarantee 221 inner wall of rotary wheel frame be connected
Smooth, reduction windage and the disturbance turbulent flow of inner wall.
The duct tub 1 includes duct frame 101 and annular end cap 102, and the duct frame 1 is the installation of shaftless fan 2
Bracket, the annular end cap 102 are bolted with 101 end of duct frame by connection, for fixing shaftless fan 2, prevent it
It slides axially.
The both ends of the rotary wheel frame 221 of the shaftless fan 2 pass through bearing and duct frame 101 respectively and annular end cap 102 connects
It connects.
The rotary wheel frame 221 and annular end cap 102 are equipped with the bearing block of fixing bearing, for being clamped bearing and by rotor
Component is fixed on duct center.
The aircraft electricity consumption drives the shaftless ducted fan of torque self-balancing and is additionally provided with power supply device (not shown), for electricity
Pivot provides electric energy by controller, alternate excitation field is generated, for driving rotor part to rotate.
The aircraft electricity consumption drives the shaftless ducted fan of torque self-balancing and is additionally provided with pendulous device 3, the pendulous device 3 with
Duct frame 101 connects, and can adjust the liter that the shaftless ducted fan of torque self-balancing is driven in aircraft electricity consumption by rotary swing device 3
The control in aircraft flight direction is realized in power direction.
The course of work is powered with the armature 211 that power supply device is the stator component 21 being fixed in duct tub 1, and led to
It crosses controller 212 and adjusts generation alternating fields, the runner being driven through on the fixed rotor part 22 with permanent magnet 222 of bearing
Frame 221 rotate, and then drive be fixed on 221 blade 223 of rotary wheel frame rotation, generate lift, and with one group of reverse rotation without
Axis fan 2 offsets reaction force when single shaftless 2 flight of fan, while providing the distinguished and admirable of unidirectional sustained firing formula, provides height
Lift or thrust, structure is simple, practical and noise can be greatly reduced.
Embodiment 2
Referring to Fig. 3, a kind of aircraft electricity consumption drive shaftless ducted fan of torque self-balancing exists with the main distinction of embodiment 1
In: the rotary wheel frame 221 of the shaftless fan 2 is connect by bearing with adjacent web, and is clamped by bearing block.
In addition, the inlet and outlet of duct tub 1 described in the present embodiment are additionally provided with wind guiding mechanism 4, the wind guiding mechanism 4 is fixed on
On annular end cap 102, flare expands, and increases incoming air area and relieve heat area, further increases lift, improves aircraft and uses
Shaftless ducted fan efficiency.
Certainly, the shaftless fan 2 of the reverse rotation may be designed as more than two;Alternatively, the nothing of the reverse rotation
Axis fan 2 may be designed as the shaftless blade reversely rotated.
Claims (10)
1. the shaftless ducted fan of torque self-balancing or shaftless culvert channel blade are driven in aircraft electricity consumption, it is characterised in that: including duct cylinder
Frame and at least one set of shaftless fan or shaftless blade reversely rotated, the shaftless fan or shaftless blade are mounted on duct tub
It is interior, form shaftless ducted fan or shaftless culvert channel blade.
2. the shaftless ducted fan of torque self-balancing or shaftless culvert channel blade are driven in aircraft electricity consumption according to claim 1,
Be characterized in that: the shaftless fan or shaftless blade include stator component and rotor part, and the stator component is mounted on duct
In tub, the rotor part is connect by bearing or guide rail with duct tub;The stator component includes being mounted on duct cylinder
Armature in frame and the controller being fixed in duct tub, the armature, to be electrically connected, are controlled with controller by controller
Alternate magnetic field drive rotor component rotation can be formed when being powered;The rotor part include rotary wheel frame, permanent magnet, blade or
Blade, the permanent magnet are fixed on rotary wheel frame outer wall, and the blade or blade are fixed on rotary wheel frame inner wall.
3. the shaftless ducted fan of torque self-balancing or shaftless culvert channel blade are driven in aircraft electricity consumption according to claim 2,
Be characterized in that: the rotary wheel frame is tubular or ring structure.
4. the shaftless ducted fan of torque self-balancing or shaftless culvert channel blade are driven in aircraft electricity consumption according to claim 2,
Be characterized in that: the rotary wheel frame outer wall is equipped with permanent magnet fixing groove uniformly at intervals, is used for fixed permanent magnet, in the rotary wheel frame
Wall is equipped with concave architecture uniformly at intervals, and for installing blade or blade, the blade or blade pass through connector and rotary wheel frame
Concave architecture connection, while guaranteeing smooth, reduction windage and the disturbance turbulent flow of rotary wheel frame inner wall and interconnecting interior wall.
5. the shaftless ducted fan of torque self-balancing or nothing are driven in aircraft electricity consumption described in -4 any claims according to claim 1
Axis culvert channel blade, it is characterised in that: the duct tub includes duct frame and annular end cap, the duct frame be shaftless fan or
The mounting bracket of shaftless blade, the annular end cap are connect with duct frame end portion by connector.
6. the shaftless ducted fan of torque self-balancing or shaftless culvert channel blade are driven in aircraft electricity consumption according to claim 5,
Be characterized in that: the both ends of the rotary wheel frame of the shaftless fan or shaftless blade pass through bearing and duct frame respectively and annular end cap connects
It connects.
7. the shaftless ducted fan of torque self-balancing or shaftless culvert channel blade are driven in aircraft electricity consumption according to claim 5,
Be characterized in that: the end of the rotary wheel frame of the shaftless fan or shaftless blade is connect by bearing with adjacent web end, and
It is connect by bearing with annular end cap.
8. driving the shaftless ducted fan of torque self-balancing or nothing according to aircraft electricity consumption described in claim 2-4 any claim
Axis culvert channel blade, it is characterised in that: be additionally provided with power supply device, the power supply device provides electric energy by controller for armature, produces
Raw alternate excitation field, for driving rotor part to rotate.
9. the shaftless ducted fan of torque self-balancing or shaftless culvert channel blade are driven in aircraft electricity consumption according to claim 5,
It is characterized in that: being additionally provided with pendulous device, the pendulous device is connect with duct frame, by rotary swing device, adjusts aircraft
The lift direction of the shaftless ducted fan of torque self-balancing or shaftless blade is driven in electricity consumption, realizes the control in aircraft flight direction.
10. the shaftless ducted fan of torque self-balancing or shaftless culvert channel blade are driven in aircraft electricity consumption according to claim 5,
Be characterized in that: the inlet and outlet of the duct tub are additionally provided with wind guiding mechanism, and the wind guiding mechanism is fixed on annular end cap, are in loudspeaker
Shape expands.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
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CN201820603045.1U CN208203623U (en) | 2018-04-26 | 2018-04-26 | The shaftless ducted fan of torque self-balancing or shaftless culvert channel blade are driven in aircraft electricity consumption |
Applications Claiming Priority (1)
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CN201820603045.1U CN208203623U (en) | 2018-04-26 | 2018-04-26 | The shaftless ducted fan of torque self-balancing or shaftless culvert channel blade are driven in aircraft electricity consumption |
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Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN108488082A (en) * | 2018-04-26 | 2018-09-04 | 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 |
CN110185637A (en) * | 2019-06-03 | 2019-08-30 | 深圳国氢新能源科技有限公司 | Fuel cell compressor |
CN110395388A (en) * | 2019-06-06 | 2019-11-01 | 王镇辉 | The driving fan in edge, double status switching mechanisms and wing, VTOL aircraft |
CN111140520A (en) * | 2019-12-30 | 2020-05-12 | 浙江欧盾风机有限公司 | Low-noise axial flow fan |
CN111828391A (en) * | 2020-06-22 | 2020-10-27 | 江苏大学 | Shaftless inducer with adjustable blades for pump |
CN112607002A (en) * | 2020-12-18 | 2021-04-06 | 南京航空航天大学 | Double-rotor ducted aircraft based on annular motor drive and control method thereof |
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2018
- 2018-04-26 CN CN201820603045.1U patent/CN208203623U/en active Active
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN108488082A (en) * | 2018-04-26 | 2018-09-04 | 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 |
CN110185637A (en) * | 2019-06-03 | 2019-08-30 | 深圳国氢新能源科技有限公司 | Fuel cell compressor |
CN110395388A (en) * | 2019-06-06 | 2019-11-01 | 王镇辉 | The driving fan in edge, double status switching mechanisms and wing, VTOL aircraft |
CN111140520A (en) * | 2019-12-30 | 2020-05-12 | 浙江欧盾风机有限公司 | Low-noise axial flow fan |
CN111140520B (en) * | 2019-12-30 | 2021-01-08 | 浙江欧盾风机有限公司 | Low-noise axial flow fan |
CN111828391A (en) * | 2020-06-22 | 2020-10-27 | 江苏大学 | Shaftless inducer with adjustable blades for pump |
CN111828391B (en) * | 2020-06-22 | 2021-09-21 | 江苏瑞阳环保有限公司 | Shaftless inducer with adjustable blades for pump |
CN112607002A (en) * | 2020-12-18 | 2021-04-06 | 南京航空航天大学 | Double-rotor ducted aircraft based on annular motor drive and control method thereof |
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