CN102877984A - Scramjet engine flame stabilizing device with front edge air cleft structure - Google Patents
Scramjet engine flame stabilizing device with front edge air cleft structure Download PDFInfo
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- CN102877984A CN102877984A CN2012104118357A CN201210411835A CN102877984A CN 102877984 A CN102877984 A CN 102877984A CN 2012104118357 A CN2012104118357 A CN 2012104118357A CN 201210411835 A CN201210411835 A CN 201210411835A CN 102877984 A CN102877984 A CN 102877984A
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Abstract
本发明提供一种带前缘气缝结构的超燃冲压发动机火焰稳定装置，该装置在传统超燃凹槽火焰稳定器的基础上，引入凹槽前缘气缝结构，即在凹槽前缘开一道斜缝，连通凹槽前方流道与凹槽内流场。该凹槽前缘气缝结构的引入，将带动流道壁面附近的气流通过斜缝进入凹槽内，增大凹槽内部的气流量。由于凹槽前方存在燃料喷口，气缝结构的存在可将部分燃料引入凹槽，燃料滞留时间增加且增强凹槽内外的掺混作用，保证了凹槽火焰稳定器的正常工作。
The invention provides a scramjet flame stabilizing device with a leading edge air slot structure, which is based on the traditional scram jet groove flame stabilizer, and introduces the groove leading edge air slot structure, that is, the groove leading edge An oblique slit is opened to connect the flow channel in front of the groove with the flow field in the groove. The introduction of the air slot structure at the front edge of the groove will drive the airflow near the wall surface of the flow channel to enter the groove through the oblique seam, increasing the air flow inside the groove. Because there is a fuel nozzle in front of the groove, the existence of the gas slot structure can introduce part of the fuel into the groove, increase the fuel residence time and enhance the mixing effect inside and outside the groove, and ensure the normal operation of the groove flame stabilizer.
Description
Technical field
The present invention relates to the technical field of scramjet engine, be specifically related to a kind of scramjet engine flame stabilizer with leading edge air cleft structure, is a kind of optimal design to groove flame holder traditional in the firing chamber.
Background technique
Scramjet engine has higher specific impulse under High Mach number.In super combustion firing chamber, flowing velocity is very large, and only several milliseconds of holdup times, mixing, igniting, the burning of finishing fuel within the so short time are very difficult, so must introduce appropriate flame holding measure.In recent years, groove structure has been subject to paying attention to widely as integrating flame holding, mixing enhancing, the multi-functional steady flame means of fuel coupling.Last century the nineties, Russian central aviation office (CIAM) uses groove flame holding apparatus in scramjet engine.This device forms larger, a stable recirculating zone by groove structure, utilizes high temperature in the recirculating zone, low speed environments so that air and part of fuel mixed combustion form a stable incendiary source, so with flame propagation to the firing chamber main flow.Yet the groove flame holder is as the steady flame device of a kind of wall, and the groove flow field is with respect to main flow comparatively " sealing ", and the inside and outside Exchange of material and energy of groove is less, thereby has the mixed problem with primary air.For improving the mixed characteristic of groove flame holder, researchers attempt the setting by fuel nozzle ports or flow spoiler, increase the mass exchange rule that groove shear layer thickness adds big groove air-flow and main flow, but these methods will be introduced extra pitot loss, affect flowing of the interior air-flow of groove, may bring negative effect to the steady flame performance of groove.In sum, traditional groove flame holder exists Gas Mixing in Cross flow weak effect, problem that the flame propagation scope is less in the steady flame.
Summary of the invention
The technical problem that the present invention mainly solves is: overcome existing technical deficiency, under on the less prerequisite of the pitot loss impact in whole when burning, increase the mixing effect of groove flame holder and main flow, take into account simultaneously simple in structurely, do not increase additional weight.
The technical solution adopted in the present invention is: a kind of scramjet engine flame stabilizer with leading edge air cleft structure, this device comprises: the super combustion groove flame holder in the super combustion firing chamber, the fuel nozzle ports in super combustion groove flame holder the place ahead, sprue and the groove leading edge air cleft of super combustion firing chamber, wherein, the super combustion firing chamber sprue air-flow that is positioned at super combustion firing chamber sprue enters super combustion groove flame holder by groove leading edge air cleft, entering of air-flow caused disturbance to flowing in the groove that surpasses combustion groove flame holder in the groove leading edge air cleft, increases the inside and outside mass exchange of groove and restrains.
Described groove leading edge air cleft height apart from the groove bottom in the groove of super combustion groove flame holder is 3-6mm, and airflow inlet is 0-1mm apart from the height of groove leading edge in the air cleft.
The width of described groove leading edge air cleft is 1mm, angle between the sprue geometric center lines of described groove leading edge air cleft geometric center lines and super combustion firing chamber is 17 ℃, described groove leading edge air cleft height apart from the groove bottom in the groove of super combustion groove flame holder is 6mm, and airflow inlet is 0mm apart from the height of groove leading edge in the air cleft.
Principle of the present invention is as follows: on traditional super combustion groove stabilizer basis, introduce leading edge air cleft structure, namely open R-joining one in the groove leading edge, communication groove the place ahead runner and groove flow field strengthen the mixing of the inside and outside air-flow of groove and the exchange rate of quality.When sprue air-flow process air cleft structure, enter inside grooves along near the air-flow the sprue wall by R-joining, so that the throughput in the super combustion groove increases.Simultaneously, the air-flow that passes through in the air cleft of super combustion groove flame holder front end causes disturbance to the shear layer between super combustion groove and the sprue air-flow, so that the development of its shear layer is more abundant, increases the inside and outside mass exchange rate of super combustion groove.Exist in the situation of fuel nozzle ports in super combustion groove the place ahead, the existence of super combustion groove flame holder front end air cleft structure can be introduced groove with part of fuel, guarantees the normal operation of groove flame holder, improves fuel distribution.
The present invention is with the advantage that the super combustion of tradition groove flame holder is compared: (1) the present invention can strengthen the mixing effect of super combustion groove flame holder; (2) the air cleft width of super combustion groove flame holder leading edge air cleft structure of the present invention, air cleft are imported and exported and highly can be adjusted flexibly, and then so that the air-flow that enters super combustion groove by super combustion groove flame holder leading edge air cleft forms best combustion method in super combustion groove; (3) the present invention is simple in structure, and less to the flow of super combustion firing chamber, flow losses are little.
Description of drawings
Fig. 1 is the section of structure (hereinafter to be referred as Baseline) of the super combustion of tradition groove flame holder;
Fig. 2 is the section of structure of band leading edge air cleft structure of the present invention and the air cleft inlet height super combustion groove flame holder of (hereinafter to be referred as H0) when being 0mm;
Fig. 3 is the section of structure of band leading edge air cleft structure of the present invention and the air cleft inlet height super combustion groove flame holder of (hereinafter to be referred as H1) when being 1mm;
Fig. 4 is the pressure loss comparison diagram of the lower three kinds of super combustion groove flame holder structures of different pressures condition (comprising Baseline, H0, H1); Fig. 4 (a) Pi=0.81MPa, Fig. 4 (b) Pi=1.21MPa;
Fig. 5 is the mixing efficiency comparison diagram of three kinds of groove flame holder structures (comprising Baseline, H0, H1); Fig. 5 (a) Pi=0.81MPa, Fig. 5 (b) Pi=1.21MPa;
Fig. 6 is respectively three kinds of groove flame holder structures and (comprises Baseline, i.e. Fig. 6 (a); H0, i.e. Fig. 6 (b); H1, i.e. Fig. 6 (c)) the distribution map of vorticity phase I;
Fig. 7 is respectively three kinds of groove flame holder structures and (comprises Baseline, i.e. Fig. 7 (a); H0, i.e. Fig. 7 (b); H1, i.e. Fig. 7 (c)) the distribution map of vorticity second stage;
Fig. 8 is respectively three kinds of groove flame holder structures and (comprises Baseline, i.e. Fig. 8 (a); H0, i.e. Fig. 8 (b); H1, i.e. Fig. 8 (c)) the distribution map of vorticity phase III.
Wherein, the structure of Fig. 1, Fig. 3 is similar to Fig. 2, gets identical label, and the label declaration in the sectional drawing 2 is as follows:
1. super combustion groove flame holder 2. surpasses combustion firing chamber sprue, and 3. groove leading edge air cleft 4. surpasses combustion firing chamber sprue air-flow, 5. air-flow in the groove leading edge air cleft, and 6. fuel jet 7. surpasses the fuel nozzle ports in combustion groove flame holder the place ahead.
Embodiment
Describe the present invention in detail below in conjunction with the drawings and the specific embodiments.
The present invention at first provides the embodiment without the front end fuel nozzle ports, because under the different pressures condition, fuel delivery is different, embodiments of the invention carry out at two kinds of pressure conditions, i.e. 0.81MPa and 1.21MPa.Wherein, the structure of super combustion firing chamber sprue 2 and super combustion groove flame holder 1 is identical with the conventional grooves flame holder, introduce groove leading edge air cleft 3 at super combustion groove flame holder 1 front end of H0 and H1 structure, super combustion firing chamber sprue air-flow 4 enters in the super combustion groove flame holder 1 by groove leading edge air cleft 3, reach the effect that increases the inside and outside mass exchange rate of groove, shown in subordinate list 1.List under two kinds of pressure conditions the import and export flow of super combustion groove flame holder 1 in the table 1, wherein, the data of circle indicate under the different pressures condition, with the aloof groove flame holder 1 net export flow of leading edge air cleft structure all greater than the conventional grooves structure.
Table 1 is different pressures condition low groove net export flow;
The present invention also provides the impact on pitot loss characteristic in the groove of H0 and H1 structure, as shown in Figure 4.As shown in Figure 4, introduce leading edge air cleft structure after, it is little that pitot loss is compared the conventional grooves flame holder, illustrates that this structure can't introduce extra pitot loss.A1, A3 are illustrated respectively under the condition that pressure is 0.81MPa and 1.21MPa among Fig. 4, and the H0 structure reaches pressure loss minimum value near fluted tail.A2, A4 represent that respectively the pressure loss minimum value of H1 structure reaches among Fig. 4 near the rear portion of groove flame holder 1 is sprue 2.
In addition, super combustion groove flame holder for the H0 structure, has discontinuity by air-flow 5 in the groove leading edge air cleft in the groove leading edge air cleft 3, and in the H1 structure, continuous by air-flow 5 in the groove leading edge air cleft in the groove leading edge air cleft 3, all can cause the disturbance of air-flow, the unstable wave of H1 structure further groove shear layer is than the H0 structural reinforcing, compare the conventional grooves flame holder, dispersing, match and merging of vorticity band earlier occurs in H0 of the present invention, H1 structure, so that shear layer development time and space increase, thereby strengthen the inside and outside blending process of groove.Simultaneously, the groove leading edge air cleft 3 that passes through of super combustion firing chamber sprue air-flow 4 intermittences (H0 structure) or continuity (H1 structure) enters in the groove that surpasses combustion groove flame holder 1, so that the mobile enhancing of super combustion groove flame holder 1 front area is conducive to the mixing of air-flow in super combustion groove flame holder 1 groove.Wherein, the mixing efficiency of three kinds of groove flame holders described above is described distribution such as Fig. 6, Fig. 7, shown in Figure 8 of air-flow vorticity in the groove as shown in Figure 5.A5, A7 explanation among Fig. 5: when existing air cleft structure and air cleft inlet height to be 1mm owing to the groove front end, the mixing efficiency of air-flow all will be higher than the efficient of benchmark groove and H0 structure; A6, A8 explanation among Fig. 5: in the downstream part of sprue air-flow, the mixing efficiency of H0 all is higher than benchmark groove structure and H1 structure, and three kinds of structures all reach near X=60mm fully mixes.B1, B2, B4 are respectively the shear layer unstable wave of its vorticity development phase I of groove flame holder of three kinds of different structures among Fig. 6, wherein, the B4 place is because the leading edge air cleft is introduced continuous flow, forms one shear layer and interact with the shear layer of main combustion road air-flow in groove.B3 and B5 explanation among Fig. 6: introduce leading edge air cleft structure, the unstability of inside grooves air-flow strengthens.C1, C2, C3 describe the formation in the large whirlpool of second stage of three kinds of different structure vorticity development among Fig. 7, the exchange of C2 and the inside and outside air-flow of C3 explanation groove increases, the vorticity band gathers quickly and discrete is large vorticity group, propagate to the groove downstream, the air-flow situation is compared complexity with the benchmark groove structure, and the time that the vorticity that the H1 structure forms is more obvious and generation vorticity band gathers, disperses more early.Fig. 8 describes the three phases of its vorticity development of groove flame holder of three kinds of different structures, wherein, D1, D2, D3 explanation: fragmentation also occurs and redistributes in vorticity group bump rear surface greatly, the disturbance of air-flow in the H1 structure enters second stage so that unstability occurs the groove shear layer quickly, and the blending zone inside and outside the groove is larger than benchmark groove and H0 structure.
As another embodiment of the invention, the present invention can be applicable to the situation that there is fuel jet 6 in super combustion groove flame holder 1 the place ahead.Shown in Fig. 2,3, fuel jet 6 is from fuel nozzle ports 7 ejections in super combustion groove flame holder the place ahead, when fuel jet flow 6 is larger, groove leading edge air cleft 3 is little on the fuel jet impact, the fuel that enters super combustion groove flame holder 1 by air-flow 5 in the groove leading edge air cleft is less, when fuel flow rate 6 hour, fuel can surpass combustion groove flame holder 1 by 5 more the entering of air-flow in the groove leading edge air cleft, this part fuel is because in the trough return current district, have longer residence time, can guarantee the normal operation of super combustion groove flame holder 1.Groove leading edge air cleft 3 is in the less situation of fuel jet 6, and the amount that enters the fuel of groove by leading edge air cleft 3 increases, thereby increases the residence time of fuel in super combustion groove.When fuel nozzle ports pressure increases, when namely fuel jet 6 was larger, near the fuel enrichment zone the air cleft outlet guaranteed have a certain amount of fuel to supply with in the super combustion groove, to keep the stable operation of groove flame holder.
The super combustion of the described tradition groove flame holder degree of depth is 10mm, and groove is wide to be 50mm, and namely length depth ratio is 5, the rear surface tilt angle is 45 °, groove the place ahead fuel nozzle ports is apart from groove leading edge 20mm, and spout is reduced to the rectangle of 1.5*1.5mm, and super combustion firing chamber sprue height is 25mm.
Described groove leading edge air cleft height apart from the groove bottom in the groove of super combustion groove flame holder is 3-6mm, and airflow inlet is 0-1mm apart from the height of groove leading edge in the air cleft.
Preferably, the width of described groove leading edge air cleft 3 is 1mm, angle between sprue 2 geometric center lines of described groove leading edge air cleft geometric center lines and super combustion firing chamber is 17 ℃, described groove leading edge air cleft height apart from the groove bottom in the groove of super combustion groove flame holder 1 is 6mm, and airflow inlet is 0mm apart from the height of groove leading edge in the air cleft.
Preferably, the width of described H1 structure groove leading edge air cleft is 1mm, angle between sprue 2 geometric center lines of described groove leading edge air cleft geometric center lines and super combustion firing chamber is 17 ℃, described groove leading edge air cleft height apart from the groove bottom in the groove of super combustion groove flame holder 1 is 6mm, and airflow inlet is 1mm apart from the height of groove leading edge in the air cleft.
Parameter according to description structure of the present invention: pitot loss, mixing efficiency, mass exchange rule, shear layer motion etc., the H0 of band leading edge air cleft of the present invention and H1 structure are compared the super combustion of tradition groove flame holder, its mixing efficiency and inside and outside flow quality commutative law are higher, mixing effect is obvious, is conducive to the stable of flame.In addition, the unstability that the H1 structure is compared its shear layer motion of H0 is higher, and the inside and outside blending of groove zone becomes large.
The non-elaborated part of the present invention belongs to techniques well known.
Below only be concrete exemplary applications of the present invention, protection scope of the present invention is not constituted any limitation.All employing equivalents or equivalence are replaced and the technological scheme of formation, all drop within the rights protection scope of the present invention.
Claims (2)
1. scramjet engine flame stabilizer with leading edge air cleft structure, it is characterized in that this device comprises: the super combustion groove flame holder (1) in the super combustion firing chamber, the fuel nozzle ports (7) in super combustion groove flame holder the place ahead, sprue (2) and the groove leading edge air cleft (3) of super combustion firing chamber, wherein, the super combustion firing chamber sprue air-flow (4) that is positioned at the sprue (2) of super combustion firing chamber enters super combustion groove flame holder (1) by groove leading edge air cleft (3), entering of air-flow (5) caused disturbance to flowing in the groove of super combustion groove flame holder (1) in the groove leading edge air cleft, increases the inside and outside mass exchange rule of groove;
Described groove leading edge air cleft height apart from the groove bottom in the groove of super combustion groove flame holder (1) is 3-6mm, and airflow inlet is 0-1mm apart from the height of groove leading edge in the air cleft.
2. a kind of scramjet engine flame stabilizer with leading edge air cleft structure according to claim 1, the width that it is characterized in that described groove leading edge air cleft (3) is 1mm, angle between sprue (2) geometric center lines of described groove leading edge air cleft geometric center lines and super combustion firing chamber is 17 ℃, described groove leading edge air cleft height apart from the groove bottom in the groove of super combustion groove flame holder (1) is 6mm, and airflow inlet is 0-1mm apart from the height of groove leading edge in the air cleft.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201210411835.7A CN102877984B (en) | 2012-10-24 | 2012-10-24 | Scramjet engine flame stabilizing device with front edge air cleft structure |
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| CN201210411835.7A CN102877984B (en) | 2012-10-24 | 2012-10-24 | Scramjet engine flame stabilizing device with front edge air cleft structure |
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| CN102877984A true CN102877984A (en) | 2013-01-16 |
| CN102877984B CN102877984B (en) | 2014-12-03 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN110805503A (en) * | 2018-08-06 | 2020-02-18 | 通用电气公司 | Ramjet engine with rotary detonation combustion system and method of operation |
| CN115013185A (en) * | 2022-06-27 | 2022-09-06 | 江苏大学 | Injection configuration for fuel injection module of scramjet engine |
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| GB2231093A (en) * | 1989-03-23 | 1990-11-07 | Gen Electric | Scramjet combustor |
| USH1008H (en) * | 1985-05-28 | 1992-01-07 | The United States Of America As Represented By The Secretary Of The Navy | Dump combustor with noncoherent flow |
| CN1165937A (en) * | 1996-04-09 | 1997-11-26 | Abb研究有限公司 | Combustion chamber |
| US20080229756A1 (en) * | 2006-12-01 | 2008-09-25 | General Electric Company | System and method for passive valving for pulse detonation combustors |
| CN101907038A (en) * | 2009-06-05 | 2010-12-08 | 西北工业大学 | A Ramjet Combustion Chamber with Injection Elimination of Combustion Oscillation |
| CN202220677U (en) * | 2011-09-15 | 2012-05-16 | 西北工业大学 | Center rocket type bi-modal ramjet engine with circular structure |
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2012
- 2012-10-24 CN CN201210411835.7A patent/CN102877984B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| USH1008H (en) * | 1985-05-28 | 1992-01-07 | The United States Of America As Represented By The Secretary Of The Navy | Dump combustor with noncoherent flow |
| GB2231093A (en) * | 1989-03-23 | 1990-11-07 | Gen Electric | Scramjet combustor |
| CN1165937A (en) * | 1996-04-09 | 1997-11-26 | Abb研究有限公司 | Combustion chamber |
| US20080229756A1 (en) * | 2006-12-01 | 2008-09-25 | General Electric Company | System and method for passive valving for pulse detonation combustors |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN110805503A (en) * | 2018-08-06 | 2020-02-18 | 通用电气公司 | Ramjet engine with rotary detonation combustion system and method of operation |
| CN110805503B (en) * | 2018-08-06 | 2022-06-03 | 通用电气公司 | Ramjet engine with rotary detonation combustion system and method of operation |
| US11359578B2 (en) | 2018-08-06 | 2022-06-14 | General Electric Company | Ramjet engine with rotating detonation combustion system and method for operation |
| CN115013185A (en) * | 2022-06-27 | 2022-09-06 | 江苏大学 | Injection configuration for fuel injection module of scramjet engine |
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