CN107985571A - A kind of bypass system - Google Patents
A kind of bypass system Download PDFInfo
- Publication number
- CN107985571A CN107985571A CN201711256533.6A CN201711256533A CN107985571A CN 107985571 A CN107985571 A CN 107985571A CN 201711256533 A CN201711256533 A CN 201711256533A CN 107985571 A CN107985571 A CN 107985571A
- Authority
- CN
- China
- Prior art keywords
- blade
- duct
- blade ring
- bypass system
- duct wall
- 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.)
- Pending
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/20—Constructional features
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention relates to a kind of bypass system, it belongs to helicopter structure design, by varying the driving force position of blade the effective length that blade works in duct wall is increased, and add the aerodynamic force of blade offer；The incremental portion of blade reduces the air-flow mutation in duct, improves pneumatic effect, can further improve efficiency；The present invention solves the problems, such as traditional culvert channel blade and duct wall there are gap, solves the catastrophe of duct interior flow field so that evenly, aerodynamic noise reduces in flow field, and muting function is good；The blade tip fixing means that the present invention uses, the arm of force of blade lift to fixed section can reduce about half, i.e., blade institute bending moment reduces half, can greatly improve the fatigue life of blade.
Description
Technical field
The present invention relates to helicopter structure design field, more particularly to a kind of bypass system.
Background technology
Relative to high-speed rotary parts such as exposed rotor, propellers, the blade of bypass system is in duct inner working, peace
Good perfection；Meanwhile duct is obviously improved the aeroperformance of whole system effect, efficiency is higher than exposed rotor, has
Application advantage.
However, current bypass system, using the shaft-driven mode in center, blade is driven by the axis of centres to be rotated, center
It is connected between axis and duct wall by several struts, these struts have inhibition to the air-flow in duct, meanwhile, blade point
There are gap, the air-flow of gap location between portion and duct, there are flow field jumping phenomenon, to cause efficiency to drop due to lacking blade driving
The increase of low and noise；And the prevailing lift section of blade away from the big end of axis of centres linear velocity, cause blade integrally by
The bending moment force brachium arrived, bending load is larger, influences fatigue life；Also, the load impacting that flow field mutation is brought can also reduce
The service life of blade.
The content of the invention
The object of the present invention is to provide a kind of bypass system, for solving or mitigating, existing bypass system noise is big, gas
Efficiency of movement is low, the big flimsy any problem of blade tip stand under load power.
To reach above-mentioned purpose, the technical solution adopted by the present invention is：A kind of bypass system, it includes
Blade；
Blade ring, the blade ring is in circular ring shape, and the blade ring is fixedly installed on the end of multiple blades；
Duct, the duct has the duct wall identical with the blade ring-shaped, and the duct wall has a groove
To accommodate the blade ring；
Driving device, the driving device are arranged in the duct wall and conllinear with the extended line of the blade, described
Driving device is used to drive the blade ring to move the blade；
Support device, the support device are arranged between blade ring and duct wall, are used to support the blade ring.
In preferred solution of the present invention, the driving device is electromagnetic actuator device, it includes driving coil and magnetic conductance rail, institute
State driving coil and magnetic conductance rail is relatively arranged on duct wall and blade ring respectively, can be driven by the driving coil in duct wall
Magnetic conductance rail with drive blade ring move.
In preferred solution of the present invention, the support device is electromagnetic supporting device, it includes being arranged at blade ring and duct
Upper support module and lower support module between wall, upper support module and lower support module include excitation coil and are oriented to magnetic
Rail, the excitation coil and guiding track are respectively arranged on duct wall and blade ring.
In preferred solution of the present invention, there is gap between duct and the blade ring.
In preferred solution of the present invention, the groove is rectangular channel.
The bypass system of the present invention is different from traditional central axis connection blade, and blade of the invention is by duct pars intramuralis
Blade ring connects, and blade ring is supported in the groove of duct pars intramuralis, and rotation, blade rotation are driven by the driving part in duct wall
Raw air force of changing the line of production is delivered on duct wall by blade ring.Relatively traditional duct, the present invention improve the effect of bypass system
Rate, reduces noise, improves fatigue life.
Brief description of the drawings
Attached drawing herein is merged in specification and forms the part of this specification, shows the implementation for meeting the present invention
Example, and for explaining the principle of the present invention together with specification.
Fig. 1 is the bypass system top view of one embodiment of the invention.
Fig. 2 is the bypass system sectional view of one embodiment of the invention.
Fig. 3 is the bypass system sectional view of another embodiment of the present invention.
Embodiment
To make the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction with the embodiment of the present invention
Attached drawing, the technical solution in the embodiment of the present invention is further described in more detail.
It is as depicted in figs. 1 and 2 the bypass system of the present invention, it includes mainly including blade 1, blade ring 3, duct 2, drive
Dynamic device and support device.
Multiple blades 1 are uniformly fixedly installed on the axis of centres 6, and the blade ring 3 of circular ring shape is arranged at the end of blade 1, paddle
Multiple blades 1 are fixed leaf joint 3.
Duct wall of the circular duct 2 in inner side is equipped with groove, and it is identical with the extension direction of blade 1 that groove opens up direction,
Blade ring 3 gos deep into the groove that duct wall opens up.
Driving device is electromagnetic drive form, it includes driving coil 5B and magnetic conductance rail 5A, magnetic conductance rail 5A and driving coil
5B groove left surfaces on the opposite right side for being arranged at blade ring 3 and duct wall respectively, pass through the driving coil in duct wall
5B can drive magnetic conductance rail 5A to rotate, to drive blade ring 3 and blade 1 to be rotated around the axis of centres 6.In preferred solution of the present invention
In, the extended line that driving device is arranged at blade 1 is conllinear, or can set multigroup driving device, so that multigroup driving
The line of action of device is conllinear with the extended line of blade 1.It should be noted that driving coil 5B need to be arranged on duct 2, without
It can be positioned on blade ring 3, this is because blade ring 3 needs to rotate under electromagnetic driving force, and connect driving coil 5B
If cable be connected to blade ring 3, be easy to cause the winding of cable, cause the accident.
Support device is also electromagnetic drive form, and support device includes the upper support being arranged between blade ring and duct wall
Module 41 and lower support module 42, upper support module include upper excitation coil 41A and upper guiding track 41B, lower support module bag
Lower excitation coil 42A and lower guiding track 42B are included, supports excitation coil (41A/41B) in module to be arranged at duct wall groove
Top and bottom, are oriented to the top and bottom that track (41B/42B) is arranged at blade ring 3.Pass through upper support module 41 and lower support module 42
Blade ring 3 can effectively be supported, make the axis of blade 1 all the time the driving force substantially with driving device in same straight line
On.It is then preferred that a case study on implementation in, excitation coil (41A/42A) produce magnetic force be oriented to track (42A/42B) magnetic
Power is repelled each other, and repulsion type magnetic force can ensure that also the upper and lower surface of groove is not desired to contact blade ring 3 to greatest extent, reduction frictional force,
Improve the stability of blade ring 3.
In the present embodiment, the groove on duct wall is rectangular channel, and corresponding blade ring 3 is also rectangular shape.
From the figure, it can be seen that in the present invention, between duct 2 and blade ring 3 there is gap can reduce noise.Pass through
The electromagnetic drive form used in the present invention, driving part and propeller hub that traditional driving axis of centres 6 rotates etc. can be cancelled,
It is i.e. as shown in Figure 3.Due to eliminating the axis of centres 6 in bypass system, this allows for length (area) increase of blade 1 so as to increase
The lift that bypass system can be provided.
The bypass system of the present invention has the advantages that relative to conventional bypass system：
1) effective length that blade works in duct wall is added in the present invention, and increases part in linear velocity
Highest position, aerodynamic force contribution are big；The incremental portion of blade reduces the air-flow mutation in duct, improves pneumatic effect,
Efficiency can be further improved；Flight support is changed to the supporting member support by duct pars intramuralis by traditional additional strut support,
Under the conditions of same lift is born, original strut part is eliminated, aerodynamic interference of the strut to blade is eliminated, improves
Duct whole efficiency；
2) present invention solves the problems, such as traditional culvert channel blade and duct wall there are gap, solves duct interior flow field
Catastrophe so that evenly, aerodynamic noise reduces in flow field, and muting function is good；
3) the blade tip fixing means that the present invention uses, the arm of force of blade lift to fixed section can reduce about half, i.e.,
Blade institute bending moment reduces half, can greatly improve the fatigue life of blade.
The above, is only the optimal embodiment of the present invention, but protection scope of the present invention is not limited thereto,
Any one skilled in the art the invention discloses technical scope in, the change or replacement that can readily occur in,
It should be covered by the protection scope of the present invention.Therefore, protection scope of the present invention should be with the protection model of the claim
Subject to enclosing.
Claims (5)
1. a kind of bypass system, it is characterised in that the bypass system includes
Blade；
Blade ring, the blade ring is in circular ring shape, and the blade ring is fixedly installed on the end of multiple blades；
Duct, the duct has the duct wall identical with the blade ring-shaped, and there is the duct wall groove to hold
Receive the blade ring；
Driving device, the driving device is arranged in the duct wall and, the driving conllinear with the extended line of the blade
Device is used to drive the blade ring to move the blade；
Support device, the support device are arranged between blade ring and duct wall, are used to support the blade ring.
2. bypass system according to claim 1, it is characterised in that the driving device is electromagnetic actuator device, it is wrapped
Driving coil and magnetic conductance rail are included, driving coil and the magnetic conductance rail is relatively arranged on duct wall and blade ring, passes through duct respectively
Driving coil in wall can drive magnetic conductance rail to drive blade ring to move.
3. bypass system according to claim 1, it is characterised in that the support device is electromagnetic supporting device, it is wrapped
The upper support module being arranged between blade ring and duct wall and lower support module are included, upper support module and lower support module wrap
Include excitation coil and be oriented to track, the excitation coil and guiding track are respectively arranged on duct wall and blade ring.
4. according to any bypass system of Claims 2 or 3, it is characterised in that have between duct and the blade ring
Gap.
5. bypass system according to claim 1, it is characterised in that the groove is rectangular channel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711256533.6A CN107985571A (en) | 2017-12-03 | 2017-12-03 | A kind of bypass system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711256533.6A CN107985571A (en) | 2017-12-03 | 2017-12-03 | A kind of bypass system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107985571A true CN107985571A (en) | 2018-05-04 |
Family
ID=62035362
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711256533.6A Pending CN107985571A (en) | 2017-12-03 | 2017-12-03 | A kind of bypass system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107985571A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA971150A (en) * | 1971-09-29 | 1975-07-15 | Alberto Kling | Precessor flying craft |
| WO2004065208A2 (en) * | 2003-01-23 | 2004-08-05 | Ufoz Llc | Quiet vertical takeoff and landing aircraft using ducted, magnetic induction air-impeller rotors |
| US20110147511A1 (en) * | 2004-03-10 | 2011-06-23 | Poltorak Alexander I | Rotating wing aircraft with tip-driven rotor and rotor-guide ring |
| CN106516127A (en) * | 2016-11-30 | 2017-03-22 | 中国直升机设计研究所 | Magnetic levitation rotor wing system and helicopter with same |
| CN106516128A (en) * | 2016-09-28 | 2017-03-22 | 南京航空航天大学 | Novel electromagnetic multi-rotor aircraft based on turbine engine and control method thereof |
| CN107089323A (en) * | 2016-02-17 | 2017-08-25 | 徐丛逸 | A kind of aircraft rotor driver and aircraft |
-
2017
- 2017-12-03 CN CN201711256533.6A patent/CN107985571A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA971150A (en) * | 1971-09-29 | 1975-07-15 | Alberto Kling | Precessor flying craft |
| WO2004065208A2 (en) * | 2003-01-23 | 2004-08-05 | Ufoz Llc | Quiet vertical takeoff and landing aircraft using ducted, magnetic induction air-impeller rotors |
| US20110147511A1 (en) * | 2004-03-10 | 2011-06-23 | Poltorak Alexander I | Rotating wing aircraft with tip-driven rotor and rotor-guide ring |
| CN107089323A (en) * | 2016-02-17 | 2017-08-25 | 徐丛逸 | A kind of aircraft rotor driver and aircraft |
| CN106516128A (en) * | 2016-09-28 | 2017-03-22 | 南京航空航天大学 | Novel electromagnetic multi-rotor aircraft based on turbine engine and control method thereof |
| CN106516127A (en) * | 2016-11-30 | 2017-03-22 | 中国直升机设计研究所 | Magnetic levitation rotor wing system and helicopter with same |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20180504 |
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| RJ01 | Rejection of invention patent application after publication |