CN107264775A - Air cavity connects controller - Google Patents
Air cavity connects controller Download PDFInfo
- Publication number
- CN107264775A CN107264775A CN201710456017.1A CN201710456017A CN107264775A CN 107264775 A CN107264775 A CN 107264775A CN 201710456017 A CN201710456017 A CN 201710456017A CN 107264775 A CN107264775 A CN 107264775A
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- CN
- China
- Prior art keywords
- air
- wing
- venthole
- air cavity
- drive device
- 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.)
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/36—Structures adapted to reduce effects of aerodynamic or other external heating
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention belongs to air cavity connection controller field, air cavity connection controller is disclosed.Air cavity connection controller includes wing and the gentle body feed drive device of air admission hole, venthole, closed air chamber being arranged on wing；Air admission hole is arranged in the front edge area of upper surface of the airfoil, and air admission hole to open up direction vertical with upper surface, venthole is arranged in the trailing region of upper surface of the airfoil or/and lower surface, and the closed gentle body feed drive device of air chamber is arranged inside wing and is interconnected to form gas passage.Air cavity connection controller is applied in the aerofoil profile of independent community, while attempting the combination of groove suction and closed-loop control, resistance is reduced for providing lift, simple in construction, can realize industrialized production.
Description
Technical field
Controller is connected the present invention relates to air cavity.
Background technology
Flow separation early start was postponed in 1904 by stable suction, when Pulan Te Er (Prandtl) shows side
When interlayer is theoretical, the rotational flow in boundary layer is removed by the narrow suction tank on periphery, so that in major part
The flowing of attachment is kept on periphery.This idea is applied to Joukowski types by Ackeret, Betz＆Schrenk
Thick wing type, postpones separation by the flowing of suction to reduce its resistance, and also quoted by Lachmann.This groove suction
Method be used for different aerofoil profiles and different wing flaps, to strengthen lift, but involved soakage is too high by (1%<CQ<
3%) practical application can not, be spread to.Even if surface groove is aspirated and multiple-grooved suction is still considered as to being protected under high reynolds number
It is valuable method to hold laminar flow, but the aerofoil profile thinning for the resistance under reducing at a high speed so as to remove low pressure external fluid
The larger pipe applications in required inside are more limited.A variety of flow control methods of boundary layer separation are used for more than one
In century, in order to remedy boundary layer separation, surface groove suction method is to start from scratch to aspirate and gradually increase, until flowing is adhered to again
Surface, this blows compared to steady flow can save substantial amounts of energy, however, the succession energy inside the stream by redirecting separation
It is the failure to be related to minimize the field of energy input, Nishri proves to introduce periodic excitation (without net quality stream by groove
Amount) separation stream on the wing flap deflected attaching surface again can be forced, in his experiment, flow regime it is very sensitive
Indicator be Center of Pressure XCP, when stream is separated, XCPSwung in the position of wing flap about centre, and when stream is by again attached
Leading edge is moved closer to when.
The energy needed for this groove takes out control method is further reduced using Closed-loop Control Strategy, and experiment confirms it
Serviceability in terms of energy saving, can be in minimum possible intervention water by continuous monitoring flow and control suction parameter
The flat lower flow condition for keeping adhering to, and be safely controlled.Never in the independence as practical application before this phenomenon
Tested in the aerofoil profile of entity, surface groove suction method is also always no to test as primary method of control in this case
Cross, these are being obtained to the new discovery on the basis of surface groove suction method physical, and on the basis of many experiments, are spread out
A kind of energy-conservation, effective fluid control method have been given birth to, controller is connected the invention provides air cavity, the controller is by groove suction method
It is applied on the wing of independent community, resistance is reduced for providing lift.
The content of the invention
In view of this, controller is connected the invention provides air cavity, groove suction method is applied to independent community by the device
On wing, improve aerodynamic lift coefficient and reduce resistance coefficient simultaneously, and stream near more wings/blades can be increased
Field circular rector.
In order to reach foregoing invention purpose, the present invention uses following technical scheme：
Air cavity connects controller, including wing and air admission hole, venthole, the gentle body of closed air chamber being arranged on wing
Feed drive device；Air admission hole is arranged in the front edge area of upper surface of the airfoil, and air inlet opens up direction and upper surface of the airfoil
Vertically, venthole is arranged in the trailing region of upper surface of the airfoil or/and lower surface, the closed gentle body feed drive dress of air chamber
Put and be arranged inside wing and be interconnected to form gas passage, air-flow is inhaled by gas feed drive device from air admission hole
Enter, sprayed by gas passage by venthole.
The air cavity connection controller that the present invention is provided, the suction of its wings/blades leading edge fluid adds wings/blades
The circular rector in neighbouring flow field, so as to improve aerodynamic lift coefficient.When the air in wings/blades is bloated from the venthole of trailing edge
When, in certain reynolds number range, the air-flow of blowout forms negative pressure on wings/blades surface, so that airflow on surface is fitted
Area is bigger, reduces wake flow, so that aerodynamic lift coefficient is improved, while reducing resistance coefficient.
Closed air chamber can be located in leading edge of a wing region, while connecting with air admission hole and gas feed drive device
Connect.
Closed air chamber can also be located at trailing edge region in, while with venthole and gas feed drive device
Connection.
In addition, closed air chamber can also be located in leading edge of a wing region and trailing region respectively, positioned at leading edge of a wing area
Closed air chamber in domain is connected with air admission hole and gas feed drive device simultaneously, the closed air chamber in trailing region
It is connected simultaneously with venthole and gas feed drive device.
The present invention replaces the various pipeline of quantity to be communicated with venthole or/and air admission hole with closed air chamber, reduces pipe
Air drag in road so that suction and blowing force are more powerful, air force control method is more effective, while because closed air chamber is logical
Road sectional area is more much bigger than the sectional area of each pipeline, greatly reduces the probability that dirt blocks pipeline.
The body exciting bank that the present invention is provided also includes the wing flap for being arranged on trailing edge region, and venthole is arranged on wing flap
In the front edge area of upper surface.
If device is not provided with wing flap, venthole is arranged in the trailing region of upper surface of the airfoil or/and lower surface, if
Wing flap is set in trailing edge region, then venthole is arranged in the front edge area of flap upper surface.
The air cavity connection controller that the present invention is provided, the quantity of air admission hole is at least one, and specific number is not limited, many
Individual air admission hole is along spanwise array arrangement in the front edge area of upper surface of the airfoil；The quantity of venthole is at least one,
The number of venthole is not also limited, and multiple ventholes are in the trailing region of upper surface of the airfoil or/and lower surface along the span
Direction array is set.
The shape of air admission hole and venthole is not specifically limited, it is preferable that being shaped as air admission hole and venthole is circular, ellipse
Circular, square or rectangle.
Preferably, gas feed drive device is pump, and pump type is centrifugal, axial-flow type or mixed type.
The gas feed drive device that the present invention is provided is adjusted by loop system, the input signal of loop system
For pressure signal.
The outer surface side of the air admission hole for the fluid excitation system that the present invention is provided sets grid, to prevent insect, leaf
Etc. being inhaled into inside blade/wing.
Air cavity connection controller also includes being arranged on the removing dirt system inside blade/wing, and the system is by gas
The reverse drive of body feed drive device and the blowing force outside from air admission hole that produces are realized.
Controller is connected the invention provides air cavity, the device can realize air-flow by gas feed drive device from entering
The upstream end suction of stomata, is sprayed into gas passage by venthole.Compared with prior art, there is advantages below in the present invention：
(1) surface groove suction method is a kind of conventional control method in hydrodynamic calculations, but never in the independence as practical application
Attempted simultaneously in the aerofoil profile of entity groove inhale and closed-loop control combination, the present invention is using closing in independent wings/blades leading edge
The Active Control Method of surface groove suction under ring control.The pressure inductor of closed-loop control is the Center of Pressure of wings/blades；
(2) suction of its wings/blades leading edge fluid, adds the circular rector in flow field near wings/blades, so as to improve air force
Lift coefficient.When venthole bulging of the air in wings/blades from trailing edge, in certain reynolds number range, blowout
Air-flow forms negative pressure on wings/blades surface, so that airflow on surface fitting area is bigger, wake flow is reduced, so as to improve air
Powered lift coefficient, while reducing resistance coefficient；(3) present invention replaces quantity various pipeline and outlet with closed air chamber
Hole or/and air admission hole are communicated, and reduce the air drag in pipeline so that suction and blowing force are more powerful, air force controlling party
Method is more effective, while because closed air chamber channel cross-sectional area is more much bigger than the sectional area of each pipeline, greatly reducing dirt resistance
Fill in the probability of pipeline.(4) the air force Active Control Method of prior art is used primarily on wing flap, to change trailing edge
Neighbouring flow field, and the suction of the wings/blades leading edge of the present invention and the combination of advertising of trailing edge are unprecedented, leading edge is taken out
Inhale each independent on the flow to aerofoil surface with advertising for trailing edge, the suction purpose of leading edge is in control wings/blades
The circular rector in peripheral flow field, so that increase lift coefficient, and the table for advertising the mainly control latter half of fluid of wings/blades of trailing edge
Face degree of adhesion, reduces wake flow width, so that reduce resistance coefficient, while the raising to lift coefficient is contributed, and two kinds of controls
The combination of method not only doubles the control benefit aspirated and advertised, more solve the airflow exits that are faced when both are used alone and
The problem of source.
Brief description of the drawings
Fig. 1 is the sectional view that air cavity provided by the present invention connects controller；
Fig. 2 connects the sectional view of controller for the air cavity of the wing provided by the present invention with wing flap；
Fig. 3 is located at the three-dimensional knot of the air cavity connection controller in leading edge of a wing region for the closed air chamber that the present invention is provided
Structure schematic diagram；
Fig. 4 is located at the three-dimensional knot of the air cavity connection controller in trailing edge region for the closed air chamber that the present invention is provided
Structure schematic diagram；
Fig. 5 is located at the air cavity connection controller in the leading edge of a wing and trailing region for the closed air chamber that the present invention is provided
Dimensional structure diagram.
Embodiment
Controller is connected the invention discloses air cavity, those skilled in the art can use for reference present disclosure, be suitably modified dress
Zero setting part is realized.In particular, all similar replacements and change be aobvious for a person skilled in the art
And be clear to, they are considered as being included among the present invention.The method of the present invention and application are entered by preferred embodiment
Description is gone, related personnel substantially can be not departing from present invention, in spirit and scope to method described herein and application
It is modified or suitably change is with combining, realizes and apply the technology of the present invention.
Air cavity connects controller, including wing Y and air admission hole 1, venthole 5, the closed air chamber being arranged on wing Y
(21,22) and gas feed drive device 3；Air admission hole 1 is arranged in the front edge area of upper surface of the airfoil, and air inlet 1 is opened up
Direction is vertical with upper surface of the airfoil, and venthole 5 is arranged in the trailing region of upper surface of the airfoil or/and lower surface, closed air
Room (21,22) and gas feed drive device 3 are arranged inside wing and are interconnected to form gas passage, and air-flow passes through
Gas feed drive device 3 is sucked from air admission hole 1, is sprayed by gas passage by venthole 5.
As shown in figure 3, in one embodiment, closed air chamber 21 can be located in leading edge of a wing region, and together
When be connected with air admission hole 1 and gas feed drive device 3.
As shown in figure 4, in another embodiment, closed air chamber 22 can also be located in trailing edge region,
While being connected with venthole 5 and gas feed drive device 3.
In addition, as shown in figure 5, closed air chamber can also be located at respectively in leading edge of a wing region and trailing region
Closed air chamber 21 in leading edge of a wing region is connected with air admission hole 1 and gas feed drive device 3 simultaneously, positioned at trailing region
Interior closed air chamber 22 is connected with venthole 5 and gas feed drive device 3 simultaneously.
The air cavity connection controller that the present invention is provided also includes the wing flap 6 for being arranged on trailing edge region, and venthole 5 is set
In the front edge area of the upper surface of wing flap 6.
If device is not provided with wing flap 6, venthole 5 is arranged on wing Y upper surface or/and the trailing region of lower surface
It is interior, if setting wing flap 6 in wing Y trailing regions, then venthole 5 is arranged in the front edge area of the upper surface of wing flap 6.
The air cavity connection controller that the present invention is provided, the quantity of air admission hole 1 is at least one, and specific number is not limited,
Multiple air admission holes 1 are along spanwise (Y-K) array arrangement in the front edge area of upper surface of the airfoil；The number of venthole 5 is extremely
It it is less one, the number of venthole is not also limited, multiple ventholes 5 edge on wing or/and in the trailing region of lower surface
The setting of spanwise (Y-K) array.
In a kind of specific embodiment, air admission hole 1 and venthole 5 are shaped to circular, ellipse, square
Or rectangle；The outer surface side of air admission hole sets grid.
Another preferred embodiment in, gas feed drive device 3 is pump, and the type of pump is centrifugal, axle
Streaming or mixed type；Gas feed drive device is adjusted by loop system, and the input signal of loop system is pressure
Signal.
Operationally, the pressure sensor signal in wings/blades is through closed circuit for the air cavity connection controller that the present invention is provided
Control system outputs signals to pump control system, and pump 3 exports suitable horsepower, and the air outside wings/blades is passed through wing
The air admission hole 1 of front edge area is sucked, by the closed air chamber 21 of wings/blades leading edge, is then aggregated into pump 3, and pump 3 is connected to
The closed air chamber 22 of wings/blades trailing edge, is bloated finally by trailing edge or the venthole of wing flap front edge area 5.
According to the actual requirements, air-flow can be sucked from venthole, via gas with reverse drive gas feed drive device
Passage is last from suction hole bulging.
The reverse drive of gas feed drive device and the blowing force outside from air admission hole that produces can realize blade/wing
The removing of internal dirt.
Described above is only the preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, under the premise without departing from the principles of the invention, some improvements and modifications can also be made, these improvements and modifications also should
It is considered as protection scope of the present invention.
Claims (10)
1. air cavity connects controller, it is characterised in that：Including wing and the air admission hole, venthole, the confined air that are arranged on wing
Air chamber and gas feed drive device；Air admission hole is arranged in the front edge area of upper surface of the airfoil, air inlet open up direction with
Upper surface of the airfoil is vertical, and venthole is arranged in the trailing region of upper surface of the airfoil or/and lower surface, the closed gentle body of air chamber
Feed drive device is arranged inside wing and is interconnected to form gas passage.
2. air cavity as claimed in claim 1 connects controller, it is characterised in that：Closed air chamber is located at leading edge of a wing region
It is interior, while being connected with air admission hole and gas feed drive device.
3. air cavity as claimed in claim 1 connects controller, it is characterised in that：Closed air chamber is located at trailing edge region
It is interior, while being connected with venthole and gas feed drive device.
4. air cavity as claimed in claim 1 connects controller, it is characterised in that：Closed air chamber is located at leading edge of a wing area respectively
In domain and trailing region, the closed air chamber in leading edge of a wing region connects with air admission hole and gas feed drive device simultaneously
Connect, the closed air chamber in trailing region is connected with venthole and gas feed drive device simultaneously.
5. air cavity as claimed in claim 1 connects controller, it is characterised in that：Air cavity connection controller also includes being arranged on machine
The wing flap of wing trailing region, venthole is arranged in the front edge area of flap upper surface.
6. air cavity as claimed in claim 1 connects controller, it is characterised in that：The quantity of air admission hole is at least one, and
Set along spanwise array；The quantity of venthole is at least one, and is set along spanwise array.
7. the air cavity connection controller as described in claim 1 or 6, it is characterised in that：Air admission hole and venthole are shaped as circle
Shape, ellipse, square or rectangle.
8. air cavity as claimed in claim 1 connects controller, it is characterised in that：Gas feed drive device is pump, pump type
For centrifugal, axial-flow type or mixed type.
9. air cavity as claimed in claim 1 connects controller, it is characterised in that：Gas feed drive device is by closed circuit control system
System regulation, the input signal of loop system is pressure signal.
10. air cavity as claimed in claim 1 connects controller, it is characterised in that：The outer surface side of air admission hole sets grid.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710456017.1A CN107264775A (en) | 2017-06-16 | 2017-06-16 | Air cavity connects controller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710456017.1A CN107264775A (en) | 2017-06-16 | 2017-06-16 | Air cavity connects controller |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107264775A true CN107264775A (en) | 2017-10-20 |
Family
ID=60066369
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710456017.1A Pending CN107264775A (en) | 2017-06-16 | 2017-06-16 | Air cavity connects controller |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107264775A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111017192A (en) * | 2019-12-24 | 2020-04-17 | 中国航空工业集团公司西安飞机设计研究所 | Mixed laminar flow wing suitable for double-fuselage layout verification machine |
| CN111452954A (en) * | 2020-04-20 | 2020-07-28 | 中国民用航空飞行学院 | Broken vortex structure of wing, wing and aircraft |
| CN113942630A (en) * | 2021-10-09 | 2022-01-18 | 中国直升机设计研究所 | Airfoil surface for generating lift force and thrust force based on airflow ejection effect and aircraft |
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| CN101323371A (en) * | 2008-06-24 | 2008-12-17 | 北京航空航天大学 | Lift augmenter with united jet flow structure on wing flap |
| CN201436385U (en) * | 2009-05-11 | 2010-04-07 | 上海神飞能源科技有限公司 | Wind motor blade |
| DE102013226935A1 (en) * | 2013-12-20 | 2015-06-25 | Airbus Operations Gmbh | Flow body, wing, aircraft and method for balancing aerodynamic loads |
| CN104890858A (en) * | 2015-06-12 | 2015-09-09 | 北京象限空间科技有限公司 | Wing structure with active flow control mechanism |
| CN207045693U (en) * | 2017-06-16 | 2018-02-27 | 青岛华创风能有限公司 | Air cavity connects controller |
-
2017
- 2017-06-16 CN CN201710456017.1A patent/CN107264775A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101323371A (en) * | 2008-06-24 | 2008-12-17 | 北京航空航天大学 | Lift augmenter with united jet flow structure on wing flap |
| CN201436385U (en) * | 2009-05-11 | 2010-04-07 | 上海神飞能源科技有限公司 | Wind motor blade |
| DE102013226935A1 (en) * | 2013-12-20 | 2015-06-25 | Airbus Operations Gmbh | Flow body, wing, aircraft and method for balancing aerodynamic loads |
| CN104890858A (en) * | 2015-06-12 | 2015-09-09 | 北京象限空间科技有限公司 | Wing structure with active flow control mechanism |
| CN207045693U (en) * | 2017-06-16 | 2018-02-27 | 青岛华创风能有限公司 | Air cavity connects controller |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111017192A (en) * | 2019-12-24 | 2020-04-17 | 中国航空工业集团公司西安飞机设计研究所 | Mixed laminar flow wing suitable for double-fuselage layout verification machine |
| CN111452954A (en) * | 2020-04-20 | 2020-07-28 | 中国民用航空飞行学院 | Broken vortex structure of wing, wing and aircraft |
| CN113942630A (en) * | 2021-10-09 | 2022-01-18 | 中国直升机设计研究所 | Airfoil surface for generating lift force and thrust force based on airflow ejection effect and aircraft |
| CN113942630B (en) * | 2021-10-09 | 2023-04-28 | 中国直升机设计研究所 | Airfoil and aircraft capable of generating lift force and thrust force based on airflow injection effect |
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Application publication date: 20171020 |