CN101435586A - Supersonic speed combustion chamber scheme of step / groove composite injection structure - Google Patents
Supersonic speed combustion chamber scheme of step / groove composite injection structure Download PDFInfo
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- CN101435586A CN101435586A CNA2007101878653A CN200710187865A CN101435586A CN 101435586 A CN101435586 A CN 101435586A CN A2007101878653 A CNA2007101878653 A CN A2007101878653A CN 200710187865 A CN200710187865 A CN 200710187865A CN 101435586 A CN101435586 A CN 101435586A
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Abstract
The innovation of the invention is to provide a proposal for an ultrasonic velocity combustion chamber with a novel step/groove composite jet structure. The proposal is characterized in that fuel nozzles are additionally arranged in the front of a step and a groove of the combustion chamber and are jointly used for fuel jet and use in the combustion chamber. In the design proposal, design proposals of a jet structure of the step and a fuel nozzle structure in the front of the groove are applied in the ultrasonic velocity combustion chamber, and correspondingly improved types of the ultrasonic combustion chambers thereof. The proposal of the designed composite jet structure can ensure evenly jetting of fuel in the ultrasonic velocity combustion chamber, and achieve full mixing of the fuel and air in a low-speed flowing area in the combustion chamber, so as to ensure ignition and stable combustion of the fuel in ultrasonic velocity air flow. Compared with the proposal of a nozzle in the prior ultrasonic velocity combustion chamber, total pressure in the combustion chamber has little loss, thereby shortening structural size of the ultrasonic velocity combustion chamber, improving performance of the whole ultrasonic power system, and having considerable potential economic benefit and value. The proposal for the ultrasonic velocity combustion chamber mainly comprises designs of parts such as the step jet structure in the combustion chamber, the groove, the jet structure in the front of the groove.
Description
One, technical field
One of key technology of scramjet engine and inferior burning ramjet is exactly to adopt effective combustion chamber and fuel injection structure form, in the combustion chamber, spray into fuel better, realize the abundant mixing of fuel and air as early as possible, in the short as far as possible bags, realize burning, make fuel fully discharge chemical energy, and be converted into the heat energy of air-flow, further be converted into the kinetic energy of engine power system.But it should be noted that in the combustion chamber of these engines the speed of general air-flow is very high, the time of staying of air-flow in the combustion chamber is very short, usually is the millisecond magnitude, and fuel can realize that the space of mixing is also very limited.The key issue that will solve when therefore, the injection of fuel, igniting and smooth combustion become these punching engine dynamical system burnings.And be in the punching engine dynamical system of critical piece with supersonic speed combustion chamber, subsonic speed combustion chamber etc., the leading indicator that can influence the aircraft service behaviour all seriously is limited by the physical dimension of combustion chamber.From combustion mechanism, tissue burning etc. more profound on, these performance indications all are limited by the processes such as fuel blending, igniting and smooth combustion in the combustion chamber.
Two, background technology
After the flying speed of aircraft acquires a certain degree, aero-engine just no longer can suit as the dynamical system of aircraft, main cause is, this moment, the ratio punching performance of aero-engine dynamical system began rapid decline, and this moment, punching engine, scramjet engine became desirable propulsion system to surpass aero-engine than higher ratio punching performance etc.Simultaneously, had certain speed punching press owing to enter the air-flow of punching engine and scramjet engine, the design feature that engine can utilize self is converted into certain pressure potential with the kinetic energy of air-flow, lights a fire and burns and directly enter the combustion chamber.Compare with aero-engine, punching engine and scramjet engine can save the compression process of rotary part to air-flow.Therefore, on structure, punching engine and scramjet engine are simple in structure.But, so just need design better and layout chamber structure and nozzle arrangements if in these two kinds of punching engines, realize igniting, burning better.And this is one of key issue in these research fields.
As everyone knows, the combustion chamber of punching engine and scramjet engine is an energy conversion device, and fuel discharges chemical energy by burning, is converted into the heat energy of air-flow.For tissue burning better, usually on support plate that all can be in supersonic speed combustion chamber, the wall (or cavity wall), the fuel nozzle of different structure and mode is set according to different modes, fuel with parallel, vertical or have a certain degree with incoming flow and to be injected in the air-flow, promote fuel and incoming flow Air mixing, strengthen burning and take place, guaranteeing burns to stablize carries out.For these concrete versions, become a very important research aspect of punching engine and ultra-combustion ramjet motivation Combustion chamber design.Lot of domestic and international scholar and research institution drop into great amount of manpower and material resources and financial resources, design different version, study from each side such as mechanism.
Although supersonic speed combustion chamber is simple in structure, its course of work is very complicated, it is goed deep into detailed research work need consider many branches of learning and subjects such as hypersonic aerodynamics, Combustion, diffusion mass transfer.Simultaneously, the supersonic speed combustion chamber design time also needs to consider the basic demand to the combustion chamber, mainly comprises: (1) in working range under the worst situation, the combustion chamber still can fast and reliable ground ignition start; (2) in predetermined working range, the combustion chamber can smooth combustion, and do not produce judder; (3) fuel can completing combustion to greatest extent in the combustion chamber, and efficiency of combustion is high as far as possible; (4) through after the internal combustion of combustion chamber, the pitot loss that burning causes is as far as possible little; (5) under the condition that satisfies combustion chamber cooling and structural strength, reduce the size of combustion chamber and quality etc. as far as possible.Therefore, the task of carrying out supersonic speed combustion chamber research is, make fuel in limited as far as possible space, finishes fuel injection, atomizing, evaporation, mixing, smooth combustion in the short time in high velocity air, and chemical energy is converted into heat energy to greatest extent.
From present research situation, relatively Chang Yong fuel mix enhancing technology mainly contains swirl nozzle, the mixing of baroclining, sweepback slope are sprayed, support plate sprays and wall cavity etc., mainly is that the change by combustion chamber inner nozzle structure realizes fuel mix enhancing technology.In addition, the number of fuel nozzle, the relative penetration depth of the jet of injection differential pressure, position, layout, fuel equivalence ratio, fuel, chamber structure etc. all have significant effects to combustibility.But can realize or useful exploration trial as technical, and technology realizes the reasons such as restriction of difficulty aspect, these schemes separately do not use wherein one or both to satisfy effect, and need promote fuel mix through combination by multiple mixing enhancing mode.These burning enhancing technology can play a role, and its dominant mechanism is: on the one hand, cause the recirculating zone in the supersonic speed combustion chamber part, increase fuel and the Air mixing and the time of staying in the combustion chamber thereof, guarantee the enough reaction time; On the other hand, change the flow field structure in the combustion chamber, the whirlpool in the increase flow field, combustion chamber to increase the convection current diffusion effect of fuel, promotes effective mixing of fuel in the supersonic speed combustion chamber, can stablize generation thereby guarantee to burn.
Last century the nineties, Moscow CIAM is when uniting the test of bimodal scramjet engine flight validation with France, some chamber structure schemes have been proposed, in the chamber structure that versions such as step, groove is applied to its related axial symmetry bimodal scramjet engine, successfully carried out the flight validation experiment.Although run into some problems in the test, the expert of CIAM thinks that by after analyzing ledge structure, groove structure can play certain flame stabilization effect.Some shortcomings that exist are that ledge structure may bring bigger flow losses.Yet in time more than ten years subsequently, Chinese scholars has been carried out some research work to the flame holding characteristic of ledge structure, groove structure and flow behavior etc.But for the flame stabilization effect that how to make full use of groove structure, and fuel injection structure and groove are combined realize efficient compound fuel to spray, mix, effectively igniting and smooth combustion but do not propose new scheme.
This patent is step injection structure and groove injection structure common application in binary supersonic speed combustion chamber structure, breadboardly research and analyse work in a large number by this, think use step groove hybrid fuel injection structure the combustion chamber to a certain extent, can weaken some shortcomings of pole jet combustors, induce the generation shock wave to cause bigger problems such as pitot loss at distance piece as pole.The work of researching and analysing based on these bases, this paper has proposed a kind of supersonic speed combustion chamber burner design of novel injection structure, be about to step the groove injection structure be used for supersonic speed combustion chamber, spray into fuel by these two kinds of injection structures, improve the performance of aspects such as fuel mix in the combustion chamber, igniting, flame stabilization burning.Spray as long as can guarantee the certain flow-control rule of fuel, the performance of combustion chamber will be greatly improved so.Simultaneously, aspect the physical dimension of combustion chamber, also can reduce the physical dimension of combustion chamber greatly, punching engine and the scramjet engine higher for design performance provide technological reserve, finally can improve the mobility and the overall performance of the aircraft that uses these dynamical systems.
Three, summary of the invention
The innovation part of this patent, be to propose a kind of step the supersonic speed combustion chamber scheme of groove composite injection structure.The proposition of this design is reference with the domestic and international document to step, the research of groove feature structure, and the macromethod research work of the binary supersonic speed combustion chamber being done based on this paper.When proposing the supersonic speed combustion chamber scheme of this version, research and analysis have been carried out to comprising multiple injection structure schemes such as groove structure, ledge structure, composite construction.Therefore, by ledge structure, groove structure burner scheme are provided with and layout, can realize injection, mixing, igniting and the smooth combustion of fuel more fully.
The step that this patent proposed the supersonic speed combustion chamber scheme of groove composite injection structure mainly form by designs such as step injection structure, groove and groove front nozzle parts:
1. in the step injection structure, the air velocity that enters behind the step reduces, and forms a local low speed flow region, with respect to the higher primary air of speed, in this zone, spray into fuel after, can realize igniting, burning and the smooth combustion of fuel.
2. the incoming flow in groove the place ahead can be brought the place ahead, combustion chamber air-flow in the groove into through mass exchange, forms stable recirculating zone in groove, and speed is relatively low, can guarantee fuel ignition, and then forms a more stable incendiary source.
3. the groove front nozzle sprays into fuel in supersonic flow, fuel can be injected in the supersonic flow of certain depth.Simultaneously, because the groove front nozzle relatively near groove, is realized the air quality exchange process in grooved area and combustion chamber main flow area, when bringing air into combustion chamber, fuel and air are brought into the grooved area realization fuel of low speed and the mixing of air-flow.
4. in above-mentioned 1 and 3 the structural design, effective mixing that injection structure can improve fuel and air before step injection structure and the groove cooperates the characteristics of low speed flow region, can guarantee behind the step and near effective igniting, burning and the flame stabilization of the fuel groove.
Use the combustion chamber scheme and the pole jet combustors scheme of single structure designs to compare with other, the step that this patent proposed the supersonic speed combustion chamber scheme of groove composite injection structure have following characteristics and advantage:
1. in a plurality of zones, spray into fuel, and guarantee the igniting of fuel in the combustion chamber;
2. can impel fuel and air fully to mix;
3. the pitot loss that fuel injection, mixing, burning bring is less;
4. the pitot loss that causes of the multishock structural change that brings of structural factor is little;
5. fuel ignition, burning and flame stabilization performance are good;
6. the physical dimension of combustion chamber greatly reduces;
7. can bring higher mobility and potentiality to the aircraft that uses this dynamical system;
8. performance potential and economic potential are than higher.
Four, description of drawings
Fig. 1 be step the graphics of supersonic speed combustion chamber scheme of groove composite injection structure.
Fig. 2 be step the perspective view of supersonic speed combustion chamber scheme of groove composite injection structure, shown the burner scheme of step injection structure among the figure, and the burner scheme of injection structure before combustion chamber groove and the groove.
Fig. 3 be step the supersonic speed combustion chamber scheme two dimension view of groove composite injection structure.
1. step injection structure 2. combustor exits 3. combustion chamber imports
4. injection structure 5. combustion chamber grooves before the groove
Five, the specific embodiment
The step that this patent proposes the specific embodiment of supersonic speed combustion chamber scheme of groove composite injection structure can carry out according to following design process.When carrying out the design of Actual combustion cell structure, according to concrete designing requirement to step before before injection structure, groove and the groove layout of injection structure carry out suitable modification and design as required, and cooperate research and analyse with the numerical computations simulation of certain scale after, the mentality of designing and the scheme of fuel nozzle is applied in the organization plan of designed supersonic speed combustion chamber.Like this, can reduce in the traditional design work in the past on the one hand, need drop into the problem of a large amount of research funds at the research and design initial stage; On the other hand, by use step that this patent proposed the supersonic speed combustion chamber scheme of groove composite injection structure, to a great extent, can reduce the physical dimension of supersonic speed combustion chamber, reduce the weight of supersonic speed punching engine, and then reduce the size of therewith relevant final products, and increase the mobility of final dynamical system product, improve the economic performance of its dynamical system.In design studies, when otherwise various conditions being possesseds, after finishing as the design of parts such as material, regulating system, angle that can be by fuel injector nozzle, spray into the parameter and the factors such as fuel flow rate of combustion chamber, so, the design of this patent can be committed in the practical design application.
Claims (3)
1. the supersonic speed combustion chamber scheme of a Tai Jie groove composite injection structure is characterized in that having proposed Tai Jie groove composite injection structure and fuel nozzle scheme.
2. the supersonic speed combustion chamber scheme of Tai Jie groove composite injection structure according to claim 1 is characterized by the fuel nozzle that is provided with by certain layout type at import step place, combustion chamber.
3. step according to claim 1 the supersonic speed combustion chamber scheme of groove composite injection structure, it is characterized by in the runner before the groove of combustion chamber and fuel nozzle be set by certain layout type.
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| CNA2007101878653A CN101435586A (en) | 2007-11-15 | 2007-11-15 | Supersonic speed combustion chamber scheme of step / groove composite injection structure |
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| CNA2007101878653A CN101435586A (en) | 2007-11-15 | 2007-11-15 | Supersonic speed combustion chamber scheme of step / groove composite injection structure |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102980206A (en) * | 2012-12-18 | 2013-03-20 | 中国人民解放军国防科学技术大学 | Flame stabilizer and engine combustion chamber comprising same |
| CN104791828A (en) * | 2015-05-06 | 2015-07-22 | 中国人民解放军国防科学技术大学 | Flame stabilization device of supersonic speed combustion chamber |
| CN105351112A (en) * | 2015-11-04 | 2016-02-24 | 中国人民解放军国防科学技术大学 | Fuel jetting mixing device and low-pressure fuel jetting mixing method in supersonic velocity flow field |
| CN106642202A (en) * | 2016-12-23 | 2017-05-10 | 中航空天发动机研究院有限公司 | Flame stabilizing device for TBCC subsonic combustion ramjet engine combustion chamber |
| CN107504517A (en) * | 2017-08-15 | 2017-12-22 | 南京航空航天大学 | A kind of step center cone with circumferentially staggered terrace with edge |
| CN109210573A (en) * | 2018-08-10 | 2019-01-15 | 江苏大学 | A kind of Novel variable-section aeroengine combustor buring room |
| CN109322762A (en) * | 2017-07-31 | 2019-02-12 | 波音公司 | Scramjet and associated aircraft and method |
| CN110319456A (en) * | 2019-05-22 | 2019-10-11 | 西北工业大学 | A kind of solid-rocket scramjet engine using multistage combustion enhancement device |
| CN110779042A (en) * | 2018-07-31 | 2020-02-11 | 中国人民解放军国防科技大学 | Rotary detonation combustion chamber and engine with same |
| CN116293803A (en) * | 2023-03-16 | 2023-06-23 | 中国人民解放军国防科技大学 | Angle-adjustable injection scheme for scramjet engine |
-
2007
- 2007-11-15 CN CNA2007101878653A patent/CN101435586A/en active Pending
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102980206A (en) * | 2012-12-18 | 2013-03-20 | 中国人民解放军国防科学技术大学 | Flame stabilizer and engine combustion chamber comprising same |
| CN104791828A (en) * | 2015-05-06 | 2015-07-22 | 中国人民解放军国防科学技术大学 | Flame stabilization device of supersonic speed combustion chamber |
| CN105351112A (en) * | 2015-11-04 | 2016-02-24 | 中国人民解放军国防科学技术大学 | Fuel jetting mixing device and low-pressure fuel jetting mixing method in supersonic velocity flow field |
| CN105351112B (en) * | 2015-11-04 | 2017-09-29 | 中国人民解放军国防科学技术大学 | Propellant spray mixing arrangement and fuel low pressure spray mixed method in supersonic flow field |
| CN106642202B (en) * | 2016-12-23 | 2019-02-12 | 中航空天发动机研究院有限公司 | A kind of flame stabilizer for the Asia TBCC burning ramjet combustion chamber |
| CN106642202A (en) * | 2016-12-23 | 2017-05-10 | 中航空天发动机研究院有限公司 | Flame stabilizing device for TBCC subsonic combustion ramjet engine combustion chamber |
| CN109322762A (en) * | 2017-07-31 | 2019-02-12 | 波音公司 | Scramjet and associated aircraft and method |
| CN109322762B (en) * | 2017-07-31 | 2023-03-17 | 波音公司 | Supersonic ramjet and related aircraft and method |
| CN107504517A (en) * | 2017-08-15 | 2017-12-22 | 南京航空航天大学 | A kind of step center cone with circumferentially staggered terrace with edge |
| CN107504517B (en) * | 2017-08-15 | 2023-09-29 | 南京航空航天大学 | Step type center cone with circumferential staggered terrace |
| CN110779042A (en) * | 2018-07-31 | 2020-02-11 | 中国人民解放军国防科技大学 | Rotary detonation combustion chamber and engine with same |
| CN109210573A (en) * | 2018-08-10 | 2019-01-15 | 江苏大学 | A kind of Novel variable-section aeroengine combustor buring room |
| CN109210573B (en) * | 2018-08-10 | 2023-08-18 | 江苏大学 | Novel variable cross-section aeroengine combustion chamber |
| CN110319456A (en) * | 2019-05-22 | 2019-10-11 | 西北工业大学 | A kind of solid-rocket scramjet engine using multistage combustion enhancement device |
| CN116293803A (en) * | 2023-03-16 | 2023-06-23 | 中国人民解放军国防科技大学 | Angle-adjustable injection scheme for scramjet engine |
| CN116293803B (en) * | 2023-03-16 | 2024-05-14 | 中国人民解放军国防科技大学 | Angle-adjustable injection scheme for scramjet engine |
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Open date: 20090520 |