CN109339977A - Scramjet engine and active control method for stabilizing and self-sustaining knocking thereof - Google Patents
Scramjet engine and active control method for stabilizing and self-sustaining knocking thereof Download PDFInfo
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- CN109339977A CN109339977A CN201811226482.7A CN201811226482A CN109339977A CN 109339977 A CN109339977 A CN 109339977A CN 201811226482 A CN201811226482 A CN 201811226482A CN 109339977 A CN109339977 A CN 109339977A
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- suction
- detonation wave
- wall surface
- combustion chamber
- detonation
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/14—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines with external combustion, e.g. scram-jet engines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/26—Controlling the air flow
Abstract
The scramjet engine comprises a combustion chamber, a plurality of pressure sensors are arranged on the upstream wall surface and the middle-stream wall surface of the combustion chamber at equal intervals, and the current propagation position of a detonation wave is judged according to pressure signals monitored by the pressure sensors. A plurality of suction holes are arranged on the upper side wall surface and the lower side wall surface of the upstream side and the middle side of the combustion chamber at equal intervals, and the suction holes are communicated with pipelines in the wall of the combustion chamber and are connected with a suction pump through pipelines. And determining the current effective suction area according to the real-time propagation position information of the detonation waves, starting a suction pump and electronic valves of all suction holes in the current effective suction area, and performing wall boundary suction in the effective suction area. A cavity is provided in the lower side wall downstream of the combustion chamber. The wall surface boundary suction can inhibit the forward transmission of the detonation wave, the cavity can promote the detonation initiation and simultaneously enable the detonation wave to forward transmit, and the cavity complement each other, so that the detonation wave can be dynamically and stably transmitted.
Description
Technical field
The present invention relates to pinking dynamic stability transmission controe technical fields under the conditions of Supersonic Stream, and in particular to be super
Self-holding Active Control Method is stablized in burning ramjet and its pinking.
Background technique
Scramjet engine (Scramjet) function admirable under high Mach (Ma > 5) flying condition, has become superb
The preferred option of velocity of sound aircraft propulsion.However, can be obtained in conjunction with current research and U.S.'s X-51A flight test
Know, the accelerating ability of scramjet engine verification machine is not obvious, and net thrust is less than normal.Therefore, it is based on current research, compels to be essential
Improve motor power performance.Scramjet engine is according to Brighton (Brayton) isobaric combustion cyclic design, heating power
Detonating combustion of the cycle efficieny far below the appearances such as approximation circulation.If thus can realize detonating combustion in supersonic flow,
Even local detonation burns, the thrust performance of engine is very likely substantially improved.
Scramjet engine gradually moves towards engineer application, but the novel ultra-combustion ramjet based on detonating combustion starts
There is presently no be seen in report for machine conceptual design.Using the engineering experience of scramjet engine relative maturity, in combustion chamber
It is middle that isobaric combustion mode is replaced using detonating combustion, it can be realized as early as possible based on quick-fried for other type detonation engines
Shake combustion engine.Prior art people also someone carried out in supersonic flow using thermojet realize pinking detonation experiment and
Numerical simulation study facilitates the understanding for deepening to detonate to pinking in the supersonic flow of combustion chamber.It is adopted in these basic research
Thermojet spray and ignition and detonation are carried out with the thermojet pipe of an independently supplying fuel and oxidant, does not account for specifically sending out
Motivation application is realized.
Summary of the invention
In view of the defects existing in the prior art, the present invention provides a kind of scramjet engine and its pinking stablizes and controls oneself
Active Control Method.
To realize the above-mentioned technical purpose, the technical scheme is that
Scramjet engine, including combustion chamber will successively divide in combustion chamber from entry of combustion chamber to combustor exit
For combustion chamber upstream, combustion chamber middle reaches and combustion chamber downstream, the spacing such as on the side wall surface in combustion chamber upstream and middle reaches
Multiple pressure sensors are installed；Multiple pumpings are equidistantly offered in the upper and lower side wall surface in combustion chamber upstream and middle reaches
Sucker, pipeline in suction hole connection chamber wall and is connect by pipeline with suction pump；Downside wall surface in combustion chamber downstream
It is equipped with a cavity.Detonation wave is measured in real time by pressure sensor, realizes boundary using suction hole and suction pump
Suction and cavity setting, three kinds design organic assemblings, realize in supersonic speed detonation engine combustion chamber pinking can
By detonating and stablizing self-holding control.
Spacing are equipped with multiple pressure sensors on the side wall surface in combustion chamber upstream and middle reaches etc..Pressure sensor
Real-time measurement chamber wall surface pressure passes through the combustion chamber at different location in multiple pressure sensor real-time measurements to combustion chamber
Wall pressure judges the current propagation position of detonation wave in turn.In the present invention, each pressure sensor and detonation wave status monitoring system
System connection, each pressure sensor give the pressure signal real-time Transmission monitored to detonation wave condition monitoring system, detonation wave one
Road intense shock wave, detonation wave can cause the wall pressure to rise to suddenly when passing through combustion chamber somewhere wall surface, thus pass through pressure sensing
Device real-time measurement wall pressure, when detecting the current biography of the position i.e. detonation wave of pressure sensor that wall surface rises to suddenly
Position is broadcast, can determine whether the real time communication position of detonation wave with this rule.
Multiple suction holes, suction hole connection are equidistantly offered in the upper and lower side wall surface in combustion chamber upstream and middle reaches
It pipeline in logical chamber wall and is connect by pipeline with suction pump.Pass through the upper and lower side wall in combustion chamber upstream and middle reaches
Suction hole is opened up on face, in pinking detonation, is opened suction pump, is passed through boundary layer low-speed region in suction hole extracting combustion room
Air-flow, it is suppressed that combustion wave forward pass occurs for detonation wave and boundary layer interaction, eliminates detonation of the boundary layer to detonation wave
It influences, detonation wave is enabled to realize that dynamic stability is propagated in a combustion chamber.In the present invention: on the pipeline of each suction hole connection
It is equipped with electronic valve, each suction hole realizes independent switch control by electronic valve.Each electronic valve and suction pump are equal
It is connect with wall surface boundary suction control system.The suction intensity of suction pump is even controlled by wall surface boundary suction control system.Wall surface
Aspirate the control that control system realizes each suction hole switch by controlling the switch of each electronic valve in boundary.
Detonation wave condition monitoring system and wall surface boundary suction control system are connect, and detonation wave condition monitoring system is by pinking
The real time communication location information of wave is transmitted to wall surface boundary suction control system；Control system is aspirated according to detonation wave in wall surface boundary
Real time communication location information determines the currently active suction areas, opens each suction in suction pump and the currently active suction areas
The electronic valve in hole.Under normal circumstances, effective suction areas length can be given as the height of combustion chamber.The currently active suction district
The domain combustion chamber regions equal with the height of combustion chamber for the segment length behind the real time communication position of detonation wave, unlatching currently have
The suction unit imitated in suction areas carries out the suction of wall surface boundary to the currently active suction areas.Real-time monitoring detonation wave of the present invention
Propagation position, current effective suction areas is determined according to the position, only opens current effective suction district when suction every time
Suction hole in domain carries out boundary suction, realizes the flexible control and efficiently suction of boundary suction.When detonation wave forward pass was in
When drive state, the suction hole in effective suction areas is opened.With the forward pass of detonation wave, effective suction areas is also at dynamic and becomes
In change.Wall surface boundary suction system controls the switch of suction hole according to the variation dynamic of effective suction areas, to realize wall surface
Efficiently suction.
A cavity, propagation side of the recessed direction of cavity perpendicular to detonation wave are equipped on the downside wall surface in combustion chamber downstream
To the length direction of cavity is parallel to the length direction of combustion chamber.The ratio of the recessed depth of cavity and the length of cavity is general
For 1:2.Low velocity combustion generates strong pressure oscillation inside cavity, while a subsonic speed is formed between pinking corrugated and cavity
Channel, and the pressure wave formed inside cavity then can be ultimately applied to front detonation wave by this subsonic speed channel forward pass
Face promotes pinking to cross drive forward pass.
The pressure oscillations that low speed recirculating zone inside cavity of the present invention generates can act on detonation wave by subsonic area
Face can promote detonation and the forward pass of detonation wave.On the contrary, the suction of wall surface boundary is able to suppress the forward pass of detonation wave.Work as use
Cavity setting promotes also make detonation wave forward pass while pinking detonation, this is to inhibit pinking using being aspirated by wall surface boundary
Wavefront passes, so that detonation wave can be realized dynamic stability.The two complements each other, final to realize that propagation is stablized in pinking.
Detonation wave propagation speed is supersonic speed (1000-2000m/s) in the present invention, under the conditions of Supersonic Stream, relatively
For the coordinate system of combustion chamber, relative propagation velocity is about between 0-500m/s.Therefore want real-time monitoring detonation wave
Spread state needs relatively high reaction sensitivity for pressure sensor, could effectively realize that pinking is wavy in this way
State feedback carries out relatively accurate adjusting control.
The present invention is based on scramjet engines provided above, and it is stable self-holding to provide a kind of scramjet engine pinking
Active Control Method, the real-time monitoring detonation wave dynamical state in supersonic speed channel, according to feedback states dynamic control wall surface
It aspirates, detonation wave is stable in certain section, realize that dynamic stability is controlled oneself and propagate, stablize certainly to reach detonation wave
Hold the purpose of control.The specific method is as follows:
In pinking detonation, by one group of pressure sensor real-time measurement combustion chamber being mounted in combustion chamber wall surface not
With the chamber wall surface pressure at position, each pressure sensor supervises the pressure signal real-time Transmission monitored to detonation wave state
The pressure signal monitored is judged the current biography of detonation wave according to each pressure sensor by examining system, detonation wave condition monitoring system
Broadcast position.
The current propagation location information of detonation wave is transmitted to wall surface boundary suction control system by detonation wave condition monitoring system.
Wall surface boundary aspirates control system and determines the currently active suction areas according to the real time communication location information of detonation wave, opens suction
The electronic valve of pump and each suction hole in the currently active suction areas carries out wall surface boundary pumping in effective suction areas
It inhales.With the forward pass of detonation wave, the propagation position dynamic change of detonation wave, corresponding effectively suction areas is also at dynamic change
In, wall surface boundary suction system controls the switch of suction hole according to the variation dynamic of effective suction areas, to realize wall surface height
Effect suction.
When detonation wave is transmitted to the cavity of combustion chamber downstream setting, the pressure that the low speed recirculating zone inside cavity generates is shaken
Pinking corrugated can be acted on by subsonic area by swinging, and can promote detonation and the forward pass of detonation wave.Wherein wall surface boundary is taken out
The forward pass for being able to suppress detonation wave is inhaled, and the setting of cavity can promote pinking that can also make detonation wave forward pass while detonation,
The two complements each other, so that detonation wave can be realized dynamic stability propagation.
Compared with prior art, the present invention can generate following technical effect:
The present invention passes through the propagation position of one group of pressure sensor real-time detection detonation wave, and works as according to position determination is propagated
Preceding effective suction areas, in combination with the design of cavity, to realize the function that control pinking dynamic stability is propagated.Its concave
Chamber setting can promote pinking to detonate, while boundary suction also may be implemented flexibly to control, to realize quick-fried in supersonic flow field
Self-holding transmission controe is stablized in shake.
Detonation wave real-time detection, the organic assembling of boundary suction control and three kinds of cavity settings, send out for supersonic speed pinking
The reliable initiation of pinking and stable control of controlling oneself provide a kind of New Scheme in motivation combustion chamber.
Detailed description of the invention
Fig. 1 is structural schematic diagram of the invention；
Appended drawing reference:
1, pressure sensor；
2, suction hole；
3, cavity.
Specific embodiment
With reference to the accompanying drawing, embodiments of the present invention are described in further detail.
Scramjet engine, including combustion chamber will successively divide in combustion chamber from entry of combustion chamber to combustor exit
For combustion chamber upstream, combustion chamber middle reaches and combustion chamber downstream, the spacing such as on the side wall surface in combustion chamber upstream and middle reaches
Multiple pressure sensors 1 are installed, 1 real-time measurement chamber wall surface pressure of pressure sensor is real by multiple pressure sensors 1
When measure chamber wall surface pressure in combustion chamber at different location and then judge the current propagation position of detonation wave.
Multiple suction holes 2, suction hole 2 are equidistantly offered in the upper and lower side wall surface in combustion chamber upstream and middle reaches
It pipeline in connection chamber wall and is connect by pipeline with suction pump.Pass through the upper and lower side in combustion chamber upstream and middle reaches
Suction hole 2 is opened up on wall surface, in pinking detonation, is opened suction pump, is passed through boundary layer low regime in suction hole extracting combustion room
The air-flow in domain, it is suppressed that combustion wave forward pass occurs for detonation wave and boundary layer interaction, eliminates boundary layer and rises to detonation wave
Quick-fried influence enables detonation wave to realize that dynamic stability is propagated in a combustion chamber.It is equipped on the pipeline of each 2 connection of suction hole
Electronic valve, each suction hole 2 realize independent switch control by electronic valve.Each electronic valve and suction pump are and wall surface
Aspirate control system connection in boundary.The suction intensity of suction pump is even controlled by wall surface boundary suction control system.It takes out on wall surface boundary
Inhale the control that control system realizes each suction hole switch by controlling the switch of each electronic valve.
A cavity 3, propagation of the recessed direction of cavity 3 perpendicular to detonation wave are equipped on the downside wall surface in combustion chamber downstream
The length direction in direction, cavity 3 is parallel to the length direction of combustion chamber.The ratio of the recessed depth of cavity 3 and the length of cavity
Generally 1:2.3 inside low velocity combustion of cavity generates strong pressure oscillation because burning there are between detonation wave and cavity
A subsonic speed channel is formed, and the pressure wave formed inside cavity then can be final to make by this subsonic speed channel forward pass
For front pinking corrugated, pinking is promoted to cross drive forward pass.
Each pressure sensor is connect with detonation wave condition monitoring system, and each pressure sensor is real by the pressure signal monitored
When be transferred to detonation wave condition monitoring system, detonation wave is one of intense shock wave, and detonation wave can draw when passing through combustion chamber somewhere wall surface
It plays the wall pressure to rise to suddenly, thus by pressure sensor real-time measurement wall pressure, when detecting that wall surface rises to suddenly
Pressure sensor the current propagation position of position, that is, detonation wave, can determine whether the real time communication of detonation wave with this rule
Position.
Detonation wave condition monitoring system and wall surface boundary suction control system are connect, and detonation wave condition monitoring system is by pinking
The real time communication location information of wave is transmitted to wall surface boundary suction control system；Control system is aspirated according to detonation wave in wall surface boundary
Real time communication location information determines the currently active suction areas, opens each suction in suction pump and the currently active suction areas
The electronic valve in hole.Under normal circumstances, effective suction areas length can be given as the height of combustion chamber.The currently active suction district
The domain combustion chamber regions equal with the height of combustion chamber for the segment length behind the real time communication position of detonation wave.The present invention is real-time
It is only opened currently when suction every time according to the determining current effective suction areas in the position propagation position for monitoring detonation wave
Suction hole in effective suction areas carries out boundary suction, realizes the flexible control and efficiently suction of boundary suction.Work as detonation wave
When forward pass was in drive state, the suction hole in effective suction areas is opened.With the forward pass of detonation wave, effective suction areas
In dynamic change.Wall surface boundary suction system controls the switch of suction hole according to the variation dynamic of effective suction areas, from
And it realizes wall surface and efficiently aspirates.
Detonation wave propagation speed is supersonic speed (1000-2000m/s) in the present invention, under the conditions of Supersonic Stream, relatively
For the coordinate system of combustion chamber, relative propagation velocity is about between 0-500m/s.Therefore want real-time monitoring detonation wave
Spread state needs relatively high reaction sensitivity for pressure sensor, could effectively realize that pinking is wavy in this way
State feedback carries out relatively accurate adjusting control.
The pressure oscillations that low speed recirculating zone inside cavity 3 of the present invention generates can act on detonation wave by subsonic area
Face can promote detonation and the forward pass of detonation wave.On the contrary, the suction of wall surface boundary is able to suppress the forward pass of detonation wave.Work as use
Cavity setting promotes also make detonation wave forward pass while pinking detonation, this is to inhibit pinking using being aspirated by wall surface boundary
Wavefront passes, so that detonation wave can be realized dynamic stability.The two complements each other, final to realize that propagation is stablized in pinking.
The present invention is based on scramjet engines provided above, and it is stable self-holding to provide a kind of scramjet engine pinking
Active Control Method, the real-time monitoring detonation wave dynamical state in supersonic speed channel, according to feedback states dynamic control wall surface
It aspirates, detonation wave is stable in certain section, realize that dynamic stability is controlled oneself and propagate, stablize certainly to reach detonation wave
Hold the purpose of control.The specific method is as follows:
When pinking is detonated, by different in one group of pressure sensor real-time measurement combustion chamber being mounted in combustion chamber wall surface
Chamber wall surface pressure at position, each pressure sensor give the pressure signal real-time Transmission monitored to detonation wave status monitoring
The pressure signal monitored is judged the current propagation of detonation wave according to each pressure sensor by system, detonation wave condition monitoring system
Position.The current propagation location information of detonation wave is transmitted to wall surface boundary suction control system by detonation wave condition monitoring system.Wall
Face boundary aspirates control system and determines the currently active suction areas according to the real time communication location information of detonation wave, opens suction pump
And the electronic valve of each suction hole in the currently active suction areas, the suction of wall surface boundary is carried out in effective suction areas.
With the forward pass of detonation wave, the propagation position dynamic change of detonation wave, corresponding effectively suction areas is also at dynamic
In state variation, wall surface boundary suction system controls the switch of suction hole according to the variation dynamic of effective suction areas, to realize
Wall surface efficiently aspirates.When detonation wave is transmitted to the cavity of combustion chamber downstream setting, what the low speed recirculating zone inside cavity generated
Pressure oscillations can act on shock surface by subsonic area, can promote detonation and the forward pass of detonation wave.Wherein wall surface side
The forward pass for being able to suppress detonation wave is aspirated on boundary, and before the setting of cavity can promote pinking that can also make detonation wave while detonation
It passes, the two complements each other, so that detonation wave can be realized dynamic stability propagation.
The foregoing is merely a preferred embodiment of the present invention, are not intended to restrict the invention, for this field
For technical staff, the invention may be variously modified and varied.All within the spirits and principles of the present invention, made any
Modification, equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (8)
1. scramjet engine, including combustion chamber will be in turn divided into combustion chamber from entry of combustion chamber to combustor exit
Combustion chamber upstream, combustion chamber middle reaches and combustion chamber downstream, it is characterised in that: the side wall surface in combustion chamber upstream and middle reaches
On multiple pressure sensors are equidistantly installed；It is equidistantly opened up in the upper and lower side wall surface in combustion chamber upstream and middle reaches
There are multiple suction holes, the pipeline in suction hole connection chamber wall and is connect with suction pump by pipeline；In combustion chamber downstream
Downside wall surface is equipped with a cavity.
2. scramjet engine according to claim 1, it is characterised in that: pressure sensor real-time measurement chamber wall
Surface pressure is judged by the chamber wall surface pressure at different location in multiple pressure sensor real-time measurements to combustion chamber
The current propagation position of detonation wave.
3. scramjet engine according to claim 2, it is characterised in that: each pressure sensor and detonation wave state are supervised
Examining system connection, each pressure sensor give the pressure signal real-time Transmission monitored to detonation wave condition monitoring system, detonation wave
For one of intense shock wave, detonation wave can cause the wall pressure to rise to suddenly when passing through combustion chamber somewhere wall surface, thus pass through pressure
Sensor real-time measurement wall pressure, when the position i.e. detonation wave for detecting pressure sensor that wall surface rises to suddenly is current
Propagation position, the real time communication position of detonation wave can determine whether with this rule.
4. scramjet engine according to claim 1, it is characterised in that: by combustion chamber upstream and middle reaches
Suction hole is opened up in upper and lower side wall surface, in pinking detonation, suction pump is opened, passes through boundary layer in suction hole extracting combustion room
The air-flow of low-speed region, it is suppressed that combustion wave forward pass occurs for detonation wave and boundary layer interaction, eliminates boundary layer to pinking
The influence of the detonation of wave enables detonation wave to realize that dynamic stability is propagated in a combustion chamber.
5. scramjet engine according to claim 4, it is characterised in that: be equipped on the pipeline of each suction hole connection
Electronic valve, each suction hole realize independent switch control by electronic valve；Each electronic valve and suction pump are and wall surface
Aspirate control system connection in boundary；The suction intensity of suction pump is even controlled by wall surface boundary suction control system；It takes out on wall surface boundary
Inhale the control that control system realizes each suction hole switch by controlling the switch of each electronic valve.
6. scramjet engine according to claim 1, it is characterised in that: the recessed direction of cavity is perpendicular to detonation wave
The direction of propagation, the length direction of cavity is parallel to the length direction of combustion chamber；Low velocity combustion generates strong pressure inside cavity
Fluctuation because burning there are between detonation wave and cavity formed a subsonic speed channel, and cavity inside formed pressure
Wave then can be ultimately applied to front pinking corrugated, pinking is promoted to cross drive forward pass by this subsonic speed channel forward pass.
7. scramjet engine according to claim 6, it is characterised in that: the length of cavity recessed depth and cavity
Ratio be 1:2.
8. self-holding Active Control Method is stablized in scramjet engine pinking, it is characterised in that: in claim 1 to 7
Scramjet engine described in any claim passes through one group of pressure being mounted in combustion chamber wall surface in pinking detonation
Chamber wall surface pressure in force snesor real-time measurement combustion chamber at different location, the pressure that each pressure sensor will monitor
Signal real-time Transmission gives detonation wave condition monitoring system, and detonation wave condition monitoring system will be monitored according to each pressure sensor
Pressure signal judges the current propagation position of detonation wave；
The current propagation location information of detonation wave is transmitted to wall surface boundary suction control system by detonation wave condition monitoring system；Wall surface
It aspirates control system and the currently active suction areas, the currently active suction is determined according to the real time communication location information of detonation wave in boundary
The region combustion chamber regions equal with the height of combustion chamber for the segment length behind the real time communication position of detonation wave, open suction
The electronic valve of pump and each suction hole in the currently active suction areas carries out wall surface boundary pumping in effective suction areas
It inhales；With the forward pass of detonation wave, the propagation position dynamic change of detonation wave, corresponding effectively suction areas is also at dynamic change
In, wall surface boundary suction system controls the switch of suction hole according to the variation dynamic of effective suction areas, to realize wall surface height
Effect suction；
When detonation wave is transmitted to the cavity of combustion chamber downstream setting, the pressure oscillations energy of the low speed recirculating zone generation inside cavity
Pinking corrugated is enough acted on by subsonic area, detonation and the forward pass of detonation wave can be promoted；Wherein energy is aspirated on wall surface boundary
Enough inhibit the forward pass of detonation wave, and the setting of cavity can promote pinking that can also make detonation wave forward pass, the two while detonation
It complements each other, so that detonation wave can be realized dynamic stability propagation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811226482.7A CN109339977B (en) | 2018-10-22 | 2018-10-22 | Scramjet engine and active control method for stabilizing and self-sustaining knocking thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811226482.7A CN109339977B (en) | 2018-10-22 | 2018-10-22 | Scramjet engine and active control method for stabilizing and self-sustaining knocking thereof |
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| CN109339977A true CN109339977A (en) | 2019-02-15 |
| CN109339977B CN109339977B (en) | 2019-12-13 |
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Cited By (1)
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| CN113048516A (en) * | 2021-04-08 | 2021-06-29 | 中国人民解放军国防科技大学 | Detonation combustion chamber, scramjet engine and hypersonic aircraft |
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| CN113048516B (en) * | 2021-04-08 | 2022-04-19 | 中国人民解放军国防科技大学 | Detonation combustion chamber, scramjet engine and hypersonic aircraft |
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| CN109339977B (en) | 2019-12-13 |
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