CN109896027A - A kind of bump inlet and Boundary layer flow method based on plasma synthesis jet stream - Google Patents
A kind of bump inlet and Boundary layer flow method based on plasma synthesis jet stream Download PDFInfo
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- CN109896027A CN109896027A CN201910284481.6A CN201910284481A CN109896027A CN 109896027 A CN109896027 A CN 109896027A CN 201910284481 A CN201910284481 A CN 201910284481A CN 109896027 A CN109896027 A CN 109896027A
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Abstract
The invention discloses a kind of bump inlet based on plasma synthesis jet stream and Boundary layer flow methods.The poly- low energy stream supplement energy of the Shock/Boundary-Layer interference section inner product that the bump inlet is induced by the momentum effect of the high-speed jet generated using jet-flow excitor to bulge promotes it attached again, the row that jet stream drives the up-front low energy of bulge to flow to bulge two sides row's shift-in and enhances bump inlet simultaneously moves boundary layer ability, realizes the active control to bump inlet.Driver is arranged in below bulge or is arranged in below body, and jet exit direction exports molded line along bulge molded line, or along driver.The present invention solves the problems, such as that traditional bump inlet Active Control Method effluxvelocity is low, control force is not strong and needs additional gas source, provides general, passive active Flow Control method for efficient, the wide envelope curve work of such air intake duct.
Description
Technical field
The invention belongs to supersonic flows control field, in particular to a kind of supersonic speed based on plasma synthesis jet stream
Bump inlet and entrance boundary coating control method.
Background technique
Bump air intake duct is a kind of novel air inlet path, and Bump air intake duct can not use boundary layer diverter, blowing/suction to arrange
It applies and also can get superperformance.The critical component of Bump air intake duct is its bulge compressing surface, type face usually pass through supersonic speed without
Glutinous single-stage circular cone flow field is using streamlined impeller design gained.Although Bump air intake duct has many compared with traditional air intake duct
Advantage, but in practical work process, shock wave/body boundary layer that air intake duct leading edge inevitably has bulge induction is dry
It disturbs, the presence of the interference will lead to a large amount of low energy stream and be piled up in bulge leading edge, changes the air-driven type face of bulge, bulge is caused to lure
Guided wave system deviates design point, weakens bulge and moves ability to the row in boundary layer, reduces inlet characteristic.Therefore bulge is induced and is flowed
The research of curvature of field face Shock/Boundary-Layer interference characteristic control method is very necessary.
For the performance for further increasing bump inlet, the research of bump inlet control method is mainly concentrated at present
In terms of the optimization to bulge wall surface type face, by using performance more preferably bulge benchmark flow field and design method in this research
Bulge type face is generated so as to improve air intake duct leading edge shock boundary layer interference bring adverse effect, and then improves air intake duct
Energy.But when this method works under High Mach number state there is no avoidance produced by the shock wave boundary layer interaction of air intake duct induction
Complicated flow field structure the problem of changing bulge air-driven type face, bulge is made to deviate design point.Because to guarantee air intake duct
The work of energy efficient stable, is deflated for the air intake duct of High Mach number design using based on boundary layer in entire envelope
Shock-boundary control measure be very necessary.After the bump inlet using processing of deflating with boundary layer, FC-1 is brave
The maximum flight Mach number of imperial fighter plane is up to 1.8.However since boundary layer air bleed technique is a kind of Active control technology, will disappear
The capture flow of air intake duct is consumed, and complicated deflation structure is set and will increase the weight of bulge and generate deflation resistance and then cut
Advantage in weak bulge bring weight and structure.
Flow control technique based on synthesizing jet-flow is one of active Flow Control technology, can be defeated in massless
Periodically outside leaving momentum under the premise of out, therefore the zero-net-mass-flux jet technology that is otherwise known as.Wherein spark discharge plasma swashs
Encourage device only and need consumption electric energy, no mechanical movable part belongs to zero-net-mass-flux jet technology, spark discharge plasma excitation device it is rapid
Development provides strong means for flow at high speed control.It is also embodied in Shock/Boundary-Layer controlling party wall jet driver
Outstanding control ability.Therefore, it is realized using plasma synthesis fluidics and shock wave boundary is induced to bump inlet
Disengagement zone Boundary layer flow caused by layer interference effect, is able to solve conventional ultrasound speed air intake duct Active Control Method effluxvelocity
Low, control force is not strong and the problem of needing additional gas source, has in terms of eliminating additional mass optimization huge excellent
Gesture.
Summary of the invention
Goal of the invention: to promote bump inlet row to move boundary layer, bump inlet performance is improved, the invention proposes one
Bump inlet of the kind based on plasma synthesis jet stream.
Invention also provides the Boundary layer flow methods for using bump inlet of the present invention.
Technical solution: following technical scheme can be used in the present invention:
A kind of bump inlet based on plasma synthesis jet stream, including internal surface, lip cover, bulge type face, machine
Body plane；The lip cover is located on the outside of internal surface, and lip cover surface and internal surface form the internal channel of air intake duct；Institute
State bulge type face as connection internal surface and body plane between joint face, and bulge type face relative to body plane to
Outer formation bulge；It is characterized in that, being additionally provided at least one jet-flow excitor, the jet-flow excitor is arranged in bulge type face
Below lower section and body plane；
Jet-flow excitor is arranged in below bulge type face, then the jet exit of jet-flow excitor be arranged in bulge surface and/
Or edge in face of bulge type；If jet exit is arranged in bulge surface, jet exit direction is arranged along bulge molded line；If jet exit
It is arranged in edge in face of bulge type, jet direction is along driver outlet molded line setting；
Jet-flow excitor is arranged in below body plane, then jet-flow excitor should be arranged in the curved surface shock wave of bulge induction/
Boundary layer is interfered in section, and the jet exit of jet-flow excitor is arranged in body plane, and jet exit direction is along jet excitation
Device exports the setting of molded line direction.
Further, jet-flow excitor arranged direction and Supersonic Stream angular separation are 0~90 °.
Further, the jet-flow excitor is two electrode horizontal plasma synthesis jet-flow excitors.
Further, jet-flow excitor, which is opened up to position, is no more than lip cover edge.
In addition, following technical scheme also can be used in bump inlet of the invention:
A kind of bump inlet based on plasma synthesis jet stream, including internal surface, lip cover, bulge type face, machine
Body plane；The lip cover is located on the outside of internal surface, and the internal channel of air intake duct is formed between lip cover and internal surface；Institute
State bulge type face as connection internal surface and body plane between joint face, and bulge type face relative to body plane to
Outer formation bulge；It is additionally provided at least one jet-flow excitor, the jet-flow excitor is arranged in below bulge type face or body
Below plane；
If jet-flow excitor is arranged in below bulge type face, the jet exit of jet-flow excitor is arranged in bulge surface
And/or edge in face of bulge type；If jet exit is arranged in bulge surface, jet exit direction is arranged along bulge molded line, and jet stream
Driver, which is opened up to position, is no more than lip cover edge；If jet exit is arranged in edge in face of bulge type, jet direction goes out along driver
The setting of shape of the mouth as one speaks line, and jet-flow excitor is opened up to position and is no more than lip cover edge；
If jet-flow excitor is arranged in below body plane, the curved surface that jet-flow excitor should be arranged in bulge induction swashs
In wave/boundary layer interference section, the jet exit of jet-flow excitor is arranged in body plane, and jet exit direction is swashed along jet stream
Device outlet molded line direction setting is encouraged, and jet-flow excitor is opened up to position and is no more than lip cover edge.
Further, the jet-flow excitor is two electrode horizontal jet-flow excitors；Jet-flow excitor is opened up to position not
More than lip cover edge.
It is provided by the invention that following technical scheme can be used using the Boundary layer flow method of above-mentioned bump inlet, including
Following steps:
(1) jet-flow excitor position and angle are arranged according to bump inlet flow field；
(2) when air intake duct is when designing Mach number work, jet-flow excitor is connected, gas expansion and is sprayed in driver cavity
Out high-speed jet so as to bulge induction shock wave boundary layer interaction section in inject momentum；
(3) high-speed jet to bulge leading edge low energy stream apply flow direction and open up to disturbance, so that low energy is flowed to bulge two sides
Row moves.
The utility model has the advantages that compared with prior art, present invention utilizes the Plasma synthesis jet streams with the high momentum of high-temperature
To bulge leading edge low energy stream apply transverse direction and open up to disturbance, by the momentum effect of plasma jet to curved surface shock wave side
The low energy stream gathered in interlayer interference range supplements momentum, make low energy stream periodically and have certain flow direction and open up to speed and to
Bulge two sides row moves, and enhances bulge row and moves boundary layer ability, it is suppressed that the interference induction of bulge leading edge curved surface Shock/Boundary-Layer produces
The scale of raw Disengagement zone, reduce boundary layer pitot loss and flow losses and reduce bulge pressure drag and rub
Resistance is wiped, the performance of bump inlet is improved.Due to this method can massless export under the premise of periodically outward
Therefore leaving momentum is realized using plasma synthesis fluidics and is made to bump inlet induction shock wave boundary layer interaction
With caused Disengagement zone Boundary layer flow, there is big advantage in terms of eliminating additional mass optimization.
Detailed description of the invention
Fig. 1 is the top view of one bump inlet of the embodiment of the present invention.
Fig. 2 is the diagrammatic cross-section of one bump inlet of the embodiment of the present invention.
Fig. 3 is the top view of two bump inlet of the embodiment of the present invention.
Fig. 4 is the diagrammatic cross-section of two bump inlet of the embodiment of the present invention.
Fig. 5 is the top view of three bump inlet of the embodiment of the present invention.
Fig. 6 is the diagrammatic cross-section of three bump inlet of the embodiment of the present invention.
Bulge wall surface section is in when having no added jet stream under the different moments that Fig. 7 is bump inlet of the present invention work
Plane of symmetry boundary layer velocity profile situation of change.
Specific embodiment
The following further describes the present invention in detail with reference to the accompanying drawings and specific embodiments.
Embodiment one
It is a kind of bump inlet based on plasma synthesis jet stream provided by the invention incorporated by reference to shown in Fig. 1 and Fig. 2
A kind of embodiment.The bump inlet includes internal surface 4, lip cover 3, bulge type face 2, body plane 5.The lip cover 3
Positioned at 4 outside of internal surface, and the internal channel of air intake duct is formed between lip cover 3 and internal surface 4.Bulge type face 2
As the joint face between connection internal surface 4 and body plane 5, and bulge type face 2 is outwardly formed relative to body plane 5
Bulge.In this embodiment, several jet-flow excitors 1 are additionally provided with, the jet-flow excitor 1 is arranged in below bulge type face
Below body plane.Wherein:
Jet-flow excitor 1 is arranged in 2 lower section of bulge type face, then the jet exit of jet-flow excitor 1 is arranged in bulge surface
And/or edge in face of bulge type；If jet exit is arranged in bulge surface, jet exit direction is arranged along bulge molded line, and jet stream
Driver, which is opened up to position, is no more than lip cover edge；If jet exit is arranged in edge in face of bulge type, jet direction goes out along driver
The setting of shape of the mouth as one speaks line；
Jet-flow excitor 1 is arranged in 5 lower section of body plane, then the curved surface that jet-flow excitor 1 should be arranged in bulge induction swashs
In wave/boundary layer interference section, the jet exit of jet-flow excitor is arranged in body plane 5, and jet exit direction is along jet stream
Driver exports the setting of molded line direction.
As shown in Figure 1,1 arranged direction of jet-flow excitor and Supersonic Stream angular separation θ are 0~90 °.Jet-flow excitor
Open up to position (i.e. in Fig. 1 overlook visual angle under the direction arrow A for exhibition to) be no more than lip cover edge B.
The plasma synthesis jet-flow excitor is the excitation of two electrode horizontal momentum injection type plasma body synthesizing jet-flows
Device, the plasma synthesis jet-flow excitor or be one or be one group of plasma synthesis jet-flow excitor array, excitation
Device is made of the outlet of DC power supply, discharge capacity, driver anode, driver cathode, driver cavity and driver.Each arteries and veins
Impulse electricity is acquired to the energy that driver injects according to formula:
Wherein ts is the electric discharge time started, and te is electric discharge deadline, and U (t) is the discharge voltage changed over time, I (t)
For the discharge current changed over time.
And use the Boundary layer flow method of the bump inlet of above-described embodiment are as follows:
(1) jet-flow excitor position and angle are arranged according to bump inlet flow field.
(2) when air intake duct is when designing Mach number work, jet-flow excitor is connected, gas expansion and is sprayed in driver cavity
Out high-speed jet so as to bulge induction shock wave boundary layer interaction section in inject momentum.Wherein, for air intake duct in difference
It is selectable to make to be arranged in the jet-flow excitor work below bulge type face or below body plane in the case where designing Mach number
Make, rather than all jet-flow excitors are worked.
(3) high-speed jet to bulge leading edge low energy stream apply flow direction and open up to disturbance, so that low energy is flowed to bulge two sides
Row moves.
Embodiment two
It is real for the present invention is based on second of the bump inlet of plasma synthesis jet stream incorporated by reference to shown in Fig. 3 and Fig. 4
Example is applied, the embodiment is roughly the same with the structure of embodiment one, equally includes internal surface 4, lip cover 3, bulge type face 2, machine
Body plane 5, and be provided with several jet-flow excitors 1, and with embodiment one the difference is that, 1 cloth of the jet-flow excitor
It sets below bulge type face.The jet exit of jet-flow excitor 1 is arranged in edge in face of bulge surface and/or bulge type；If jet stream
Outlet is arranged in bulge surface, and jet exit direction is arranged along bulge molded line, and jet-flow excitor 1 is opened up to position and is no more than lip cover
3 edges；If jet exit is arranged in edge in face of bulge type, jet direction is along driver outlet molded line setting.
Use the Boundary layer flow method of the bump inlet of above-described embodiment are as follows:
(1) jet-flow excitor position and angle are arranged according to bump inlet flow field.
(2) when air intake duct is when designing Mach number work, jet-flow excitor is connected, gas expansion and is sprayed in driver cavity
Out high-speed jet so as to bulge induction shock wave boundary layer interaction section in inject momentum.
(3) high-speed jet to bulge leading edge low energy stream apply flow direction and open up to disturbance, so that low energy is flowed to bulge two sides
Row moves.
Embodiment three
Incorporated by reference to shown in Fig. 5 and Fig. 6, for the present invention is based on the third realities of the bump inlet of plasma synthesis jet stream
Example is applied, the embodiment is roughly the same with the structure of embodiment one, equally includes internal surface 4, lip cover 3, bulge type face 2, machine
Body plane 5, and be provided with several jet-flow excitors 1, and with embodiment one and embodiment two the difference is that, the jet stream swashs
Device 1 is encouraged to be only placed at below body plane.And jet exit direction and stream air angle are 90 °, 1 Zhan Xiangwei of jet-flow excitor
It sets and is no more than 3 edge of lip cover
Use the Boundary layer flow method of the bump inlet of above-described embodiment are as follows:
(1) jet-flow excitor position and angle are arranged according to bump inlet flow field.
(2) when air intake duct is when designing Mach number work, jet-flow excitor is connected, gas expansion and is sprayed in driver cavity
Out high-speed jet so as to bulge induction shock wave boundary layer interaction section in inject momentum.
(3) high-speed jet to bulge leading edge low energy stream apply flow direction and open up to disturbance, so that low energy is flowed to bulge two sides
Row moves.
Verification experimental verification example
Make low energy below by way of a specific verification experimental verification to illustrate that bump inlet provided by the invention can be realized
Flow to the technical effect that bulge two sides row moves.
In certain design Mach number Md=2, benchmark circular cone semiapex angle α=28 °, leading edge molded line height h0The bulge wall of=10mm
Face uses Boundary layer flow method of the present invention, free stream Mach number M∞=2.0.Plasma synthesis jet-flow excitor is arranged in
Bulge lower face and Supersonic Stream angular separation are 90 °.Driver apart from bulge leading edge 2.5mm, driver slit width 2mm,
Jet exit is arranged in edge in face of bulge type, and jet exit direction and stream air angle are 90 °.Each pulsed discharge is to excitation
The energy 33.27mJ of device injection.It compared the section bulge wall surface z=15mm under different moments in Fig. 7 and be in have no added jet stream
When plane of symmetry boundary layer velocity profile situation of change, compared wall surface resistance and resistance coefficient variation in table 1.As can be seen that
After jet stream air blowing is added in the position, velocity profile is fuller under the bulge position, the decline of bulge wall surface resistance.To confirm to be somebody's turn to do
Can make low energy stream periodically in experiment has certain transverse direction and opens up to speed and arrange shifting to bulge two sides, has reached expection
Effect.
| Time | Bulge wall surface resistance | Bulge wall surface resistance coefficient |
| 0us | 6.9269 | 11.3092 |
| 50us | 6.8811 | 11.2344 |
| 150us | 6.8731 | 11.2214 |
Invention implement the technical solution method and approach it is very much, the above be only embodiments of the present invention it
One.It should be pointed out that for those skilled in the art, without departing from the principle of the present invention, may be used also
To make several improvements and modifications, these modifications and embellishments should also be considered as the scope of protection of the present invention.It is not known in the present embodiment
The available prior art of each component part realized.
Claims (7)
1. a kind of bump inlet based on plasma synthesis jet stream, including internal surface, lip cover, bulge type face, body
Plane；The lip cover is located on the outside of internal surface, and lip cover and internal surface form the internal channel of air intake duct；The bulge
Type face is as the joint face between connection internal surface and body plane, and bulge type face is outwardly formed relative to body plane
Bulge；It is characterized in that, be additionally provided at least one jet-flow excitor, the jet-flow excitor be arranged in below bulge type face and
Below body plane；
Jet-flow excitor is arranged in below bulge type face, then the jet exit of jet-flow excitor is arranged in bulge surface and/or drum
Edge in face of pouch-type；If jet exit is arranged in bulge surface, jet exit direction is arranged along bulge molded line；If jet exit is arranged
The edge in face of bulge type, jet direction is along driver outlet molded line setting；
Jet-flow excitor is arranged in below body plane, then jet-flow excitor should be arranged in curved surface shock wave/boundary of bulge induction
In layer interference section, the jet exit of jet-flow excitor is arranged in body plane, and jet exit direction goes out along jet-flow excitor
The setting of shape of the mouth as one speaks line direction.
2. bump inlet according to claim 1, it is characterised in that: jet-flow excitor arranged direction and Supersonic Stream
Angular separation is 0~90 °.
3. bump inlet according to claim 1, it is characterised in that: the jet-flow excitor is two electrode horizontals etc.
Gas ions synthesizing jet-flow excitor.
4. bump inlet according to claim 1, it is characterised in that: jet-flow excitor, which is opened up to position, is no more than lip cover side
Edge.
5. a kind of bump inlet based on plasma synthesis jet stream, including internal surface, lip cover, bulge type face, body
Plane；The lip cover is located on the outside of internal surface, and lip cover and internal surface form the internal channel of air intake duct；The bulge
Type face is as the joint face between connection internal surface and body plane, and bulge type face is outwardly formed relative to body plane
Bulge；It is characterized in that, be additionally provided at least one jet-flow excitor, the jet-flow excitor be arranged in below bulge type face or
Below body plane；
If jet-flow excitor is arranged in below bulge type face, the jet exit of jet-flow excitor be arranged in bulge surface and/or
Edge in face of bulge type；If jet exit is arranged in bulge surface, jet exit direction is arranged along bulge molded line, and jet-flow excitor
It opens up to position and is no more than lip cover edge；If jet exit is arranged in edge in face of bulge type, jet direction exports molded line along driver
Setting, and jet-flow excitor is opened up to position and is no more than lip cover edge；
If jet-flow excitor is arranged in below body plane, jet-flow excitor should be arranged in curved surface shock wave/side of bulge induction
Interlayer interferes in section, and the jet exit of jet-flow excitor is arranged in body plane, and jet exit direction is along jet-flow excitor
The setting of molded line direction is exported, and jet-flow excitor is opened up to position and is no more than lip cover edge.
6. bump inlet according to claim 5, it is characterised in that: the jet-flow excitor is that two electrode horizontals are penetrated
Flow driver；Jet-flow excitor, which is opened up to position, is no more than lip cover edge.
7. a kind of using according to claim 1 to the Boundary layer flow method of bump inlet described in any one of 6, feature exists
In, comprising the following steps:
(1) jet-flow excitor position and angle are arranged according to bump inlet flow field；
(2) when air intake duct is when designing Mach number work, jet-flow excitor is connected, gas expansion and sprays height in driver cavity
Rapid fire flows into and injects momentum to inducing in shock wave boundary layer interaction section bulge；
(3) high-speed jet to bulge leading edge low energy stream apply flow direction and open up to disturbance, make low energy flow to bulge two sides row move.
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| CN110805495A (en) * | 2019-12-05 | 2020-02-18 | 江西洪都航空工业集团有限责任公司 | Fixed-geometry wide-speed-range supersonic air inlet, working method thereof and aircraft |
| CN110985208A (en) * | 2019-12-16 | 2020-04-10 | 南京航空航天大学 | Internal rotation type air inlet channel assembly based on plasma vortex generator and control method |
| CN111120108A (en) * | 2019-12-16 | 2020-05-08 | 南京航空航天大学 | Inner rotation type air inlet channel assembly based on momentum injection type plasma synthetic jet and control method thereof |
| CN112572810A (en) * | 2020-11-25 | 2021-03-30 | 北京空天技术研究所 | Air inlet passage boundary layer separation eliminating device and aircraft |
| CN112722249A (en) * | 2021-01-07 | 2021-04-30 | 南京航空航天大学 | Aircraft controlled by combination of pneumatic vortex generator and plasma synthetic jet |
| CN113939072A (en) * | 2021-12-03 | 2022-01-14 | 西北工业大学 | Shock wave focusing electric spark jet exciter |
| CN114872904A (en) * | 2022-05-18 | 2022-08-09 | 南京航空航天大学 | Method and device for controlling induced separation of shock waves in air inlet channel for local particle feeding |
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| CN111120108A (en) * | 2019-12-16 | 2020-05-08 | 南京航空航天大学 | Inner rotation type air inlet channel assembly based on momentum injection type plasma synthetic jet and control method thereof |
| CN110985208B (en) * | 2019-12-16 | 2021-09-24 | 南京航空航天大学 | Internal rotation type air inlet channel assembly based on plasma vortex generator and control method |
| CN112572810A (en) * | 2020-11-25 | 2021-03-30 | 北京空天技术研究所 | Air inlet passage boundary layer separation eliminating device and aircraft |
| CN112722249A (en) * | 2021-01-07 | 2021-04-30 | 南京航空航天大学 | Aircraft controlled by combination of pneumatic vortex generator and plasma synthetic jet |
| CN112722249B (en) * | 2021-01-07 | 2022-04-15 | 南京航空航天大学 | Aircraft controlled by combination of pneumatic vortex generator and plasma synthetic jet |
| CN113939072A (en) * | 2021-12-03 | 2022-01-14 | 西北工业大学 | Shock wave focusing electric spark jet exciter |
| CN114872904A (en) * | 2022-05-18 | 2022-08-09 | 南京航空航天大学 | Method and device for controlling induced separation of shock waves in air inlet channel for local particle feeding |
| CN114872904B (en) * | 2022-05-18 | 2024-06-07 | 南京航空航天大学 | Method and device for controlling shock wave induced separation in air inlet channel for local particle delivery |
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