CN101418956A - A kind of supersonic speed combustion chamber burner scheme of novel injection structure - Google Patents
A kind of supersonic speed combustion chamber burner scheme of novel injection structure Download PDFInfo
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- CN101418956A CN101418956A CNA2007101633251A CN200710163325A CN101418956A CN 101418956 A CN101418956 A CN 101418956A CN A2007101633251 A CNA2007101633251 A CN A2007101633251A CN 200710163325 A CN200710163325 A CN 200710163325A CN 101418956 A CN101418956 A CN 101418956A
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Abstract
Innovation part of the present invention has been to propose a kind of supersonic speed combustion chamber burner scheme of new structure.The characteristics of this scheme are before the groove of combustion chamber and groove front face place increases fuel nozzle.This design is applied to the fuel nozzle structural design of groove and groove in the supersonic speed combustion chamber, and improves in the supersonic speed combustion chamber of type.Can guarantee in supersonic speed combustion chamber, evenly to spray into fuel, reach sufficient mixing, thereby guarantee igniting and smooth combustion at the fuel of supersonic flow.Compare with the burner scheme in the traditional supersonic speed combustion chamber, the design that the present invention proposes has the following advantages: fuel sprays evenly, blending is abundant, stable ignition, and smooth combustion, thereby shorten the physical dimension of supersonic speed combustion chamber, improve the size of whole ultrasonic powertrain system, sizable potential economic benefit is all arranged.A kind of supersonic speed combustion chamber burner scheme of new structure is formed with the interior fuel nozzle conceptual design of groove before groove and the groove mainly by the pillar in the combustion chamber.
Description
One, technical field
Fuel ignition and smooth combustion are the key issues that realizes smooth combustion in the hypersonic combustion chamber.Be in the punching engine dynamical system of critical piece with supersonic speed combustion chamber, subsonic speed combustion chamber etc., its main performance indications all seriously are limited by the physical dimension of combustion chamber.On more profound, these performance indications all are limited by the processes such as fuel blending, igniting and smooth combustion in the combustion chamber.
Two, background technology
The scramjet engine combustion chamber is an energy conversion device, and fuel discharges chemical energy by burning, is converted into the heat energy of air-flow.In supersonic speed combustion chamber, for tissue burning better, on support plate 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 that the assurance burning can be stablized and be carried out.
Although the structure of supersonic speed combustion chamber is simple relatively, its course of work is very complicated, relates to many branches of learning and subjects such as hypersonic aerodynamics, Combustion, diffusion mass transfer.Basic demand to hypersonic combustion chamber is: (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 the confined 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.
Fuel mix enhancing technology at present relatively more commonly used mainly contains swirl nozzle, mixings of baroclining, sweepback slope are sprayed, support plate injection 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.
Therefore, we can say, to requirement as the hypersonic combustion chamber of scramjet engine energy conversion device, be exactly can be in limited space with in the limited time (Millisecond), in supersonic flow, realize fuel efficient mixing, catch fire and smooth combustion, fuel chemical energy is converted into heat energy to greatest extent.Because the residence time of air-flow in the combustion chamber is very short, fuel effectively mixes with air, lights a fire smoothly and smooth combustion becomes one of difficult point of supersonic speed combustion technology then.Usually, from chamber structure, nozzle arrangements, fuel injection manners etc. are started with, and 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 reaction time; On the other hand, increase the whirlpool in the flow field, combustion chamber,, promote effective mixing of fuel in the supersonic speed combustion chamber, can stablize generation thereby guarantee to burn to increase the convection current diffusion effect of fuel.
Last century the nineties, CIAM proposes groove structure, and applies it in the flight validation test of its axial symmetry bimodal scramjet engine that carries out, and successfully groove structure is applied in the flight validation experiment of designed supersonic speed combustion chamber.Its result of study shows that groove structure can play certain flame stabilization effect.Subsequently, researchers more both domestic and external have carried out some researchs to the flame holding characteristic of 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.
The present invention has proposed a kind of supersonic speed combustion chamber burner design of novel injection structure on the basis that the groove structure characteristic is fully studied.The organization plan that this fuel sprays is that groove structure and fuel injection structure are combined, and realizes the even injection of fuel in the combustion chamber and fully mixing, realizes effective igniting of fuel simultaneously and obtains stable flame.This design can be used for the Scheme design of supersonic speed combustion chamber, realize fuel injection, mixing, igniting and the smooth combustion of supersonic speed combustion chamber, thereby can reduce the physical dimension of combustion chamber potentially, provide a kind of mentality of designing and design considerations for designing high performance supersonic speed combustion chamber.
Three, summary of the invention
Innovation part of the present invention has been to propose a kind of supersonic speed combustion chamber burner design of novel injection structure.This design, with domestic and international research to the groove feature structure, and this paper is the basis to the result of study that groove structure and fuel injection structure carried out, burner scheme is reset and layout, thereby can be realized injection, mixing, igniting and the smooth combustion of fuel more fully.
The supersonic speed combustion chamber burner design of novel injection structure proposed by the invention mainly is made up of designs such as wall nozzle before groove, groove front nozzle and groove part:
1. 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, thereby can guarantee fuel ignition, and then forms a more stable incendiary source.
2. 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.
3. the design of wall nozzle before the groove further is injected to fuel in the supersonic flow.Because these nozzles are positioned at groove top, combustion chamber, therefore, fuel further can be injected in the air-flow, realize the mixing of fuel and air-flow.Simultaneously, wall nozzle and groove front nozzle realize that wrong row's mode arranges when arranging before the groove, further realize the mixing of air-flow and fuel.
4. in the above-mentioned design 2 and 3, effective mixing that wall nozzle can improve fuel and air before groove front nozzle and the groove, the low speed recirculating zone characteristic of fit inside can guarantee that groove and nozzle arrangements realize the effective igniting and the flame stabilization of fuel.
Use the combustion chamber ignition schemes of single structure design to compare with other, the supersonic speed combustion chamber burner design of novel injection structure proposed by the invention has the following advantages:
1. even burner oil;
2. fuel and air mix fully;
3. the pitot loss that fuel sprays and mixing brings is less;
4. fuel ignition and flame stabilization performance are good;
5. the chamber structure size can reduce;
6. the potential performance and the economic benefit height that bring of global design.
Four, description of drawings
Fig. 1 is the designs of nozzles scheme graphics of the supersonic speed combustion chamber of novel injection structure.
Fig. 2 is the perspective view of novel injection structure supersonic speed combustion chamber burner design, has shown the position of newly-designed burner scheme among the figure, before the groove of combustion chamber and groove in the step position.
Fig. 3 is the two dimension view of supersonic speed combustion chamber design.
1. combustion chamber import 2. inducer pillars 3. step front nozzles
4. step rear nozzle 5. combustion chamber grooves 6. combustor exits
Five, the specific embodiment
The specific embodiment of the supersonic speed combustion chamber burner design of the novel injection structure that the present invention proposes can be carried out according to following design.When carrying out the design of Actual combustion cell structure, according to concrete designing requirement to groove, groove front nozzle and groove before the placement position of wall nozzle can suitably revise, and cooperate with after certain numerical computations sunykatuib analysis, in the structural design that the mentality of designing and the scheme of fuel nozzle is applied to supersonic speed combustion chamber.Like this, can reduce in the design work in the past the research fund expense at design initial stage on the one hand; On the other hand, to a great extent, reduce the weight of supersonic speed punching engine, reduce the size of final products, increase the mobility of final dynamical system product, improve the economic performance of its dynamical system.When otherwise conditions being possessed, after finishing as the design of parts such as material, regulating system, can make design of the present invention obtain the most practical application by the angle of regulating nozzle, the fuel flow rate that sprays into etc.
Claims (3)
1. the supersonic speed combustion chamber burner scheme of a novel injection structure is characterized in that proposing novel groove and fuel nozzle scheme.
2. the supersonic speed combustion chamber burner scheme of novel injection structure according to claim 1 is characterized by before the groove of combustion chamber and adopts fuel nozzle.
3. the supersonic speed combustion chamber burner scheme of novel injection structure according to claim 1 is characterized by on the groove antetheca of combustion chamber and adopts fuel nozzle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2007101633251A CN101418956A (en) | 2007-10-22 | 2007-10-22 | A kind of supersonic speed combustion chamber burner scheme of novel injection structure |
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| CNA2007101633251A CN101418956A (en) | 2007-10-22 | 2007-10-22 | A kind of supersonic speed combustion chamber burner scheme of novel injection structure |
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| CN101418956A true CN101418956A (en) | 2009-04-29 |
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Cited By (11)
| 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 |
| CN103605876A (en) * | 2013-12-11 | 2014-02-26 | 厦门大学 | Design method of fuel injection system for scramjet engine |
| CN103727562A (en) * | 2013-12-23 | 2014-04-16 | 西北工业大学 | Fuel supporting plate for improving non-premixed combustion of RBCC (rocket-based combined cycle) bimodal combustion chamber |
| CN105180212A (en) * | 2015-09-02 | 2015-12-23 | 中国人民解放军国防科学技术大学 | Combustion chamber of supersonic combustion ramjet engine |
| CN109253470A (en) * | 2018-09-11 | 2019-01-22 | 中国人民解放军国防科技大学 | Supersonic mixing reinforcing device |
| CN110762555A (en) * | 2019-10-24 | 2020-02-07 | 南京航空航天大学 | Pneumatic auxiliary type flame stabilizer with concave cavity supporting plate |
| CN111649352A (en) * | 2020-06-02 | 2020-09-11 | 中国人民解放军国防科技大学 | Self-sustaining fluid oscillator and rocket-based combined cycle engine |
| CN112747335A (en) * | 2021-01-06 | 2021-05-04 | 中国人民解放军国防科技大学 | Lobe type backward step structure, lobe type concave cavity device and afterburning chamber |
| CN116181525A (en) * | 2023-02-07 | 2023-05-30 | 中国人民解放军32804部队 | Device and method for enhancing fuel spray characteristics and chemical activity |
| 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 |
| CN116379477A (en) * | 2023-04-20 | 2023-07-04 | 中国人民解放军国防科技大学 | Slope concave cavity combustion chamber and scramjet engine |
-
2007
- 2007-10-22 CN CNA2007101633251A patent/CN101418956A/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 |
| CN103605876A (en) * | 2013-12-11 | 2014-02-26 | 厦门大学 | Design method of fuel injection system for scramjet engine |
| CN103605876B (en) * | 2013-12-11 | 2016-04-06 | 厦门大学 | The method for designing of scramjet engine fuel injection system |
| CN103727562A (en) * | 2013-12-23 | 2014-04-16 | 西北工业大学 | Fuel supporting plate for improving non-premixed combustion of RBCC (rocket-based combined cycle) bimodal combustion chamber |
| CN103727562B (en) * | 2013-12-23 | 2016-01-20 | 西北工业大学 | A kind of fuel support plate for improving the blending burning of RBCC bimodal combustion chamber |
| CN105180212A (en) * | 2015-09-02 | 2015-12-23 | 中国人民解放军国防科学技术大学 | Combustion chamber of supersonic combustion ramjet engine |
| CN109253470A (en) * | 2018-09-11 | 2019-01-22 | 中国人民解放军国防科技大学 | Supersonic mixing reinforcing device |
| CN110762555B (en) * | 2019-10-24 | 2024-04-19 | 南京航空航天大学 | Pneumatic auxiliary type cavity support plate flame stabilizer |
| CN110762555A (en) * | 2019-10-24 | 2020-02-07 | 南京航空航天大学 | Pneumatic auxiliary type flame stabilizer with concave cavity supporting plate |
| CN111649352A (en) * | 2020-06-02 | 2020-09-11 | 中国人民解放军国防科技大学 | Self-sustaining fluid oscillator and rocket-based combined cycle engine |
| CN112747335A (en) * | 2021-01-06 | 2021-05-04 | 中国人民解放军国防科技大学 | Lobe type backward step structure, lobe type concave cavity device and afterburning chamber |
| CN116181525A (en) * | 2023-02-07 | 2023-05-30 | 中国人民解放军32804部队 | Device and method for enhancing fuel spray characteristics and chemical activity |
| CN116181525B (en) * | 2023-02-07 | 2023-08-15 | 中国人民解放军32804部队 | Device and method for enhancing fuel spray characteristics and chemical activity |
| 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 |
| CN116379477A (en) * | 2023-04-20 | 2023-07-04 | 中国人民解放军国防科技大学 | Slope concave cavity combustion chamber and scramjet engine |
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Open date: 20090429 |