CN106014684A - Combined flow control method and structure for improving SERN for TBCC - Google Patents
Combined flow control method and structure for improving SERN for TBCC Download PDFInfo
- Publication number
- CN106014684A CN106014684A CN201610378299.3A CN201610378299A CN106014684A CN 106014684 A CN106014684 A CN 106014684A CN 201610378299 A CN201610378299 A CN 201610378299A CN 106014684 A CN106014684 A CN 106014684A
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- Prior art keywords
- sern
- shock wave
- flow control
- control method
- tbcc
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/28—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles (AREA)
Abstract
The invention relates to a combined flow control method and structure for improving an SERN for a TBCC. The combined flow control method and the combined flow control structure are characterized in that a passive cavity structure is added on an upper expansion ramp of the SERN, and a convergent secondary flow nozzle is formed in a lower inclined plate of the SERN; and the oblique shock wave position is controlled in an overexpansion state through adopting the simple passive cavity structure and a secondary flow jet device under the precondition that the required control energy is not obviously added, the pressure distribution of a nozzle on a single ramp is improved, the thrust coefficient of the SERN in the overexpansion state is improved, and the thrust performance of an air-breathing hypersonic velocity propelling system in the transonic velocity stage is improved.
Description
Technical field
The present invention relates to aero engine technology field, particularly relate to one and be applied to the hypersonic propelling of air suction type
The single expansion ramp nozzle of system (turboramjet engine, TBCC) (Single Expansion Ramp Nozzle,
SERN) flow control method and structure, specifically improves SERN and crosses the group of thrust coefficient under swelling state
Close flow control technique.
Background technology
Air-breathing hypersonic vehicle (flight Mach number is more than 5) represents following military, civilian airborne vehicle
Strategic development direction, being called is the third time in World Airways history after propeller, jet propelling aircraft
Revolution.In Air-breathing hypersonic vehicle, Push Technology is the key technology of its core the most, in the world
Showing in the research of various countries, transonic speed region is the stage that aircraft thrust nargin (thrust drag reduction power) is minimum,
Transonic speed resistance determines that the key factor of propulsion system size.
Jet pipe is the vitals that hypersonic propulsion system produces thrust, and its blow down ratio excursion is comparatively wide,
When subsonic speed 2 are until about 300 time hypersonic (Ma=5.0), in order to meet hypersonic flight
The thrust requirements of device, needs jet pipe to must provide for a sizable area ratio on geometry.Research shows,
Consideration based on aircraft/propulsion system/jet pipe integration, uses single expansion ramp nozzle will to have good subtracting
Weight effect, and it is possible to reduce nozzle base drag and friction loss.Therefore, the most most air suction types are superb
Velocity of sound aircraft all have employed SERN and designs as configuration.
SERN uses body and the highly integrated configuration of jet pipe after hypersonic aircraft, though this design
So there is when High Mach number good thrust coefficient, but it is in the transonic speed stage, due under jet pipe blow down ratio
Fall, nozzle gas flow will be in swelling state, served as degrees of expansion serious time, the upper wall surface of SERN is the most not
Thrust can be produced, it is also possible to can produce resistance, now the performance of jet pipe significantly deteriorates, and thrust coefficient significantly drops
Low.Hypersonic aircraft also will be made to produce substantially in transonic speed district additionally, air-flow when expansion crossed by jet pipe separates
Nose-down pitching moment, cause difficulty to the control of aircraft.
This feature of SERN, is the main of air suction type hypersonic propulsion system transonic speed phase thrust deficiency
One of reason, therefore, only solves SERN transonic speed stage gas and flows through the degradation problem expanding induction,
It is only the key point improving propulsion system transonic speed thrust.Just because of having recognized this point, from last century
The nineties, attention has been transferred in the mistake expansion issues of SERN by research worker both domestic and external one after another,
Under the conditions of how improving low blow down ratio, the performance of big expansion ratio SERN becomes a problem demanding prompt solution.Domestic
Proposing many solutions for this problem outward, wherein most schemes need complicated Mechanical course system
System, but mechanical system can increase the weight of electromotor, makes jet pipe moving component in high temperature environments increase, adds
Weight cooling system burden, improves design cost, and increases radar area, reduce the Stealth Fighter of aircraft.
This patent is mainly based upon flow control technique that active/passive mode combines, crosses expansion shape for improving SERN
Thrust coefficient under state then improves the transonic speed thrust performance of the hypersonic propulsion system of air suction type and proposes.
In view of drawbacks described above, creator of the present invention obtains this creation finally through research for a long time and practice.
Summary of the invention
The invention provides a kind of by passive cell method (control of passively flowing) and Secondary Flow spraying technique (active flow
Dynamic control) the combination flow control method improving TBCC SERN that combines and structure.
For achieving the above object, the invention provides a kind of combination flow control method improving TBCC SERN
And structure, the convergent contour Secondary Flow spout at the declined board trailing edge of single expansion ramp nozzle, table on declined board
Face injection Secondary Flow, forms one bowshock before spout, and bowshock passes whole nozzle interior field with upper
Expansion inclined-plane intersects, and the interaction of shock wave and boundary region causes the separation of upper expansion inclined-plane air-flow.
The passive cavity being positioned at expansion inclined-plane has connected induction shock wave upstream and downstream pressure so that above expands inclined-plane and lures
Lead shock wave to flow about form and change；Low speed boundary-layer air-flow pressure reduction pressure effect after shock wave front after shock wave
In lower inflow passive cavity cavity, it is blown outside chamber by the pore of shock wave front, with shock wave front Boundary Layer Interaction
Change nowed forming and the pressure distribution of original shock wave root, induction shock wave front is pushed into first of passive cavity
At hole, now the separated region after shock wave increases the most accordingly, and forms stable recirculating zone.
Present invention also offers combination flow control method and the structure improving TBCC SERN, it is characterised in that
Including being arranged on the passive cavity structure on upper expansion inclined-plane of single expansion ramp nozzle and being positioned at single expansion ramp nozzle
Declined board trailing edge at convergent contour Secondary Flow spout.
Further, described passive cavity structure includes the cavity of passive cavity structure and orifice plate within the cavity.
Further, described single expansion ramp nozzle also includes converging portion and side wall surface；Described declined board position
Lower section in converging portion Yu the connecting portion of side wall surface.
Further, described orifice plate circle hole shape orifice plate and straight trough shape orifice plate.
Further, described circle hole shape orifice plate is the structure in the hole arranging some arrangements on flat board.
Further, described straight trough shape orifice plate is the structure arranging some straight troughs on flat board.
Further, described secondary flow jeting port includes the groove of through declined board upper surface and stretches out declined board
Hatch frame.
Compared with prior art, the invention have the benefit that the present invention adds on the upper expansion inclined-plane of SERN
Passive cavity structure, the declined board at SERN offers convergent contour Secondary Flow spout simultaneously；Needed for inconspicuous increase
On the premise of controlling energy, when using simple passive cavity structure and Secondary Flow injection apparatus to realize swelling state
The control of oblique shock wave position, and then improve jet pipe pressure distribution on monocline face, improve SERN and cross expansion
Thrust coefficient under state, improves the air suction type hypersonic propulsion system thrust performance in the transonic speed stage.
Accompanying drawing explanation
Fig. 1 is that the monocline surface expansion of flow control technique is combined in use passive cavity and the Secondary Flow injection of the present invention
The overall configuration of jet pipe；
Fig. 2 is that the monocline surface expansion of flow control technique is combined in use passive cavity and the Secondary Flow injection of the present invention
The internal structure schematic diagram of jet pipe；
Fig. 3 is that the monocline surface expansion of flow control technique is combined in use passive cavity and the Secondary Flow injection of the present invention
The operation principle schematic diagram of jet pipe；
Fig. 4 is the perforate schematic diagram of the circle hole shape orifice plate of the single expansion ramp nozzle ramp passive cavity of the present invention；
Fig. 5 is the perforate schematic diagram of the straight trough shape orifice plate of the single expansion ramp nozzle ramp passive cavity of the present invention；
Fig. 6 is that the structure that single expansion ramp nozzle declined board Secondary Flow spout is straight slot-shaped spray jet outlet of the present invention is shown
It is intended to；
Fig. 7 is that the structure that single expansion ramp nozzle declined board Secondary Flow spout is circle hole shape spout of the present invention is shown
It is intended to.
Detailed description of the invention
Below in conjunction with accompanying drawing, to the present invention, above-mentioned and other technical characteristic and advantage are described in more detail.
Refer to shown in Fig. 1-7, in the present invention, add passive cavity structure on the upper expansion inclined-plane of SERN,
Declined board at SERN offers convergent contour Secondary Flow spout simultaneously；Before controlling energy needed for inconspicuous increase
Put, use simple passive cavity structure and Secondary Flow injection apparatus to realize oblique shock wave position during swelling state
Control, and then improve jet pipe pressure distribution on monocline face, improve SERN thrust under crossing swelling state
Coefficient, improves the air suction type hypersonic propulsion system thrust performance in the transonic speed stage.
Incorporated by reference to shown in Fig. 1, the combination flowing control structure of the present invention includes being arranged on the upper of monocline surface expansion pipe
Expand the passive cavity structure 5 on inclined-plane 3 and be positioned at the convergent contour at declined board 2 trailing edge of single expansion ramp nozzle
Secondary Flow spout 6.
In embodiments of the present invention, single expansion ramp nozzle also includes converging portion 1 and side wall surface 4；Declined board 2
It is positioned at the lower section of converging portion 1 and the connecting portion of side wall surface 4.
In embodiments of the present invention, described passive cavity structure 5 includes the cavity 51 of passive cavity structure and is positioned at
Orifice plate 52 in cavity 51；Wherein, described orifice plate 52 has two kinds of forms, i.e. circle hole shape orifice plate (Fig. 4
Shown in) and straight trough shape orifice plate (shown in Fig. 5)；Described circle hole shape orifice plate is for arrange some arrangements on flat board
The structure in hole；Described straight trough shape orifice plate is the structure arranging some straight troughs on flat board；Hole on flat board or
Person's groove all allows air-flow to pass through.
The major parameter of described passive cavity structure 5 includes that orifice plate percent opening, aperture and chamber are deep etc..
Described Secondary Flow spout 6, its major parameter includes Secondary Flow injection flow, expulsion pressure and jet angle
Degree etc., wherein expulsion pressure should be greater than the pressure of surrounding flow.In embodiments of the present invention, secondary flow jeting port 6
Including the groove of through declined board 2 upper surface and stretch out the hatch frame of declined board 2.
Incorporated by reference to shown in Fig. 3, when hypersonic aircraft is operated in transonic operating condition, at SERN declined board
2 upper surface injection Secondary Flows, form one bowshock before spout 6, and bowshock passes in whole jet pipe
Flow field is intersected with upper expansion inclined-plane 3, and the interaction of shock wave and boundary region causes dividing of upper expansion inclined-plane 3 air-flow
From.The passive cavity 5 being positioned at expansion inclined-plane 3 has connected induction shock wave upstream and downstream pressure so that upper expansion is tiltedly
Nowed forming near face induction shock wave changes.
After shock wave, low speed boundary-layer air-flow flows under the effect of pressure reduction pressure in passive cavity cavity 51 after shock wave front,
It is blown outside chamber by the pore of shock wave front, changes original shock wave root with shock wave front Boundary Layer Interaction
Nowed forming and pressure distribution, be pushed at first hole of passive cavity 5, now after shock wave by induction shock wave front
Separated region increases the most accordingly, and forms stable recirculating zone, as shown in Figure 3.By passive cavity and Secondary Flow
Being applied in combination of injection etc. two kinds combination flow control technique, improves the pressure expanding on inclined-plane on SERN and amasss
Score value, ultimately improves the air suction type hypersonic propulsion system thrust performance in transonic speed district.
The operation principle of the present invention is as follows:
When hypersonic aircraft is operated in transonic operating condition, the blow down ratio of single expansion ramp nozzle is only
8-15, much smaller than the design blow down ratio (flight Mach number 5.0 times about about 300) of jet pipe, and is in serious
Cross expansion operating mode, single expansion ramp nozzle declined board lip the strongest oblique shock wave sent and jet pipe
Monocline surface expansion section intersects, and induction shock wave interferes effect with boundary-layer, causes the separation of boundary-layer, flow field
The deterioration of quality, now the thrust coefficient of jet pipe will be significantly lower than its design load.The combination flowing that the present invention provides
The central role of control method is through the control to ramp expansion arc flow separation, improves the pressure of ramp
Power distribution i.e. improves the pressure integration of ramp, reaches to improve SERN and crosses the purpose of thrust performance under swelling state.
First, passive cell method is a kind of passive flow control method, and the method is derived from supercritical wing in early days and sets
Meter.Increasing passive cavity on the basis of prototype SERN, passive cavity has connected induction shock wave upstream and downstream pressure, has made
Expansion inclined-plane induction shock wave must be gone up flow about form and change.After shock wave, low speed boundary-layer air-flow is at shock wave front
Flow in passive cavity under rear pressure reduction pressure effect, be blown outside chamber by the pore of shock wave front, attached with shock wave front
Layer interacts and changes nowed forming and the pressure distribution of original shock wave root, is pushed into passive by induction shock wave front
At first hole in chamber, now the separated region after shock wave increases the most accordingly, and forms stable recirculating zone.Phase
The upper pressure integrated value expanded on inclined-plane of Ying Di, SERN increases, and passively flow the SERN controlled based on passive cavity
Thrust coefficient has promoted.Additionally, the existence of passive cavity structure will not reduce the axial thrust of SERN design point
Coefficient, and the impact of nose-down pitching moment will not be brought.
Secondly, by spraying Secondary Flow on SERN declined board, a series of expansion can be formed near spray-hole
Ripple, jet is through overexpansion shock system rapid expanding, and crossing the jet expanded again can be by the tubular shock wave of surrounding and mach disk
Recompression, air-flow continues to expand after mach disk, and is blowed to downstream by main flow.Due to the injection of Secondary Flow,
Main flow flowing is hindered in Secondary Flow spout upstream, forms one bowshock in Secondary Flow spout upstream, this
Pressure before Secondary Flow spout is increased, and disturbance is upstream propagated, at Secondary Flow spout by wall boundary region
Upstream near wall produces the separated region of a wedge like, and Disengagement zone can hinder and flow, and is formed and separates
Shock wave, twice shock interaction defines " λ ripple ".Now there is Disengagement zone at two, upstream at inclined-plane in upper expansion
Owing to Secondary Flow sprays the Disengagement zone produced and downstream due to the Disengagement zone that expansion produces of crossing of air-flow, Secondary Flow spray
Penetrate the distribution changing Disengagement zone, expansion inclined-plane so that this areal pressure raises；Additionally, Secondary Flow injection is also
The pressure in expansion inclined-plane downstream area is made to become big.Effect with passive cavity is similar, SERN declined board secondary
The upper expansion wall surface pressure integration increase that stream injection causes is the reason that nozzle thrust coefficient improves.
Above-mentioned detailed description is illustrating for one of them possible embodiments of the present invention, and this embodiment is not
In order to limit the scope of the claims of the present invention, all equivalences done without departing from the present invention are implemented or change, all should comprise
In the range of technical solution of the present invention.
Claims (8)
1. the combination flow control method improving TBCC SERN and structure, it is characterised in that
Convergent contour Secondary Flow spout at the declined board trailing edge of single expansion ramp nozzle, sprays at declined board upper surface
Penetrating Secondary Flow, form one bowshock before spout, bowshock is through whole nozzle interior field and upper expansion
Inclined-plane intersects, and the interaction of shock wave and boundary region causes the separation of upper expansion inclined-plane air-flow.
The passive cavity being positioned at expansion inclined-plane has connected induction shock wave upstream and downstream pressure so that above expands inclined-plane and lures
Lead shock wave to flow about form and change；Low speed boundary-layer air-flow pressure reduction pressure effect after shock wave front after shock wave
In lower inflow passive cavity cavity, it is blown outside chamber by the pore of shock wave front, with shock wave front Boundary Layer Interaction
Change nowed forming and the pressure distribution of original shock wave root, induction shock wave front is pushed into first of passive cavity
At hole, now the separated region after shock wave increases the most accordingly, and forms stable recirculating zone.
2. the combination flow control method improving TBCC SERN and structure, it is characterised in that include
It is arranged on the passive cavity structure on the upper expansion inclined-plane of single expansion ramp nozzle and is positioned under single expansion ramp nozzle
Convergent contour Secondary Flow spout at swash plate trailing edge.
The combination flow control method improving TBCC SERN the most according to claim 2 and structure,
It is characterized in that, described passive cavity structure includes the cavity of passive cavity structure and orifice plate within the cavity.
4. according to the combination flow control method improving TBCC SERN described in Claims 2 or 3 and knot
Structure, it is characterised in that described single expansion ramp nozzle also includes converging portion and side wall surface；Described declined board
It is positioned at the lower section of converging portion and the connecting portion of side wall surface.
The combination flow control method improving TBCC SERN the most according to claim 3 and structure,
It is characterized in that, described orifice plate can use circle hole shape orifice plate or straight trough shape well plate format.
The combination flow control method improving TBCC SERN the most according to claim 5 and structure,
It is characterized in that, described circle hole shape orifice plate is the structure in the hole arranging some arrangements on flat board.
The combination flow control method improving TBCC SERN the most according to claim 5 and structure,
It is characterized in that, described straight trough shape orifice plate is the structure arranging some straight troughs on flat board.
The combination flow control method improving TBCC SERN the most according to claim 5 and structure,
It is characterized in that, described secondary flow jeting port includes the groove of through declined board upper surface and stretches out declined board
Hatch frame.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610378299.3A CN106014684A (en) | 2016-05-30 | 2016-05-30 | Combined flow control method and structure for improving SERN for TBCC |
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| CN201610378299.3A CN106014684A (en) | 2016-05-30 | 2016-05-30 | Combined flow control method and structure for improving SERN for TBCC |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109184957A (en) * | 2018-10-17 | 2019-01-11 | 中国人民解放军国防科技大学 | Supersonic incoming flow mixing and reinforcing structure and rocket-based combined engine |
| CN109209679A (en) * | 2018-10-17 | 2019-01-15 | 中国人民解放军国防科技大学 | Supersonic mixing reinforced structure with frequency characteristic and rocket-based combined engine |
| CN109533356A (en) * | 2018-11-21 | 2019-03-29 | 南京航空航天大学 | A kind of shock wave boundary layer interaction controller |
| CN110450964A (en) * | 2018-05-07 | 2019-11-15 | 南京普国科技有限公司 | Class axial symmetry tilt outlet, which is received, expands jet pipe and its design method |
| CN111594340A (en) * | 2020-04-30 | 2020-08-28 | 南京理工大学 | Wedge surface structure for controlling oblique detonation wave initiation by utilizing hot jet |
| CN113123899A (en) * | 2021-04-19 | 2021-07-16 | 中国人民解放军国防科技大学 | Central injection rocket, RBCC engine and fuel injection method thereof |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110450964A (en) * | 2018-05-07 | 2019-11-15 | 南京普国科技有限公司 | Class axial symmetry tilt outlet, which is received, expands jet pipe and its design method |
| CN110450964B (en) * | 2018-05-07 | 2020-11-24 | 南京普国科技有限公司 | Axisymmetric inclined outlet convergent-divergent nozzle and design method thereof |
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| CN109209679A (en) * | 2018-10-17 | 2019-01-15 | 中国人民解放军国防科技大学 | Supersonic mixing reinforced structure with frequency characteristic and rocket-based combined engine |
| CN109533356A (en) * | 2018-11-21 | 2019-03-29 | 南京航空航天大学 | A kind of shock wave boundary layer interaction controller |
| CN111594340A (en) * | 2020-04-30 | 2020-08-28 | 南京理工大学 | Wedge surface structure for controlling oblique detonation wave initiation by utilizing hot jet |
| CN111594340B (en) * | 2020-04-30 | 2022-01-11 | 南京理工大学 | Wedge surface structure for controlling oblique detonation wave initiation by utilizing hot jet |
| CN113123899A (en) * | 2021-04-19 | 2021-07-16 | 中国人民解放军国防科技大学 | Central injection rocket, RBCC engine and fuel injection method thereof |
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Application publication date: 20161012 |