CN104929808A - Flame stabilization device and engine - Google Patents
Flame stabilization device and engine Download PDFInfo
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- CN104929808A CN104929808A CN201510225080.5A CN201510225080A CN104929808A CN 104929808 A CN104929808 A CN 104929808A CN 201510225080 A CN201510225080 A CN 201510225080A CN 104929808 A CN104929808 A CN 104929808A
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Abstract
The invention provides a flame stabilization device. The flame stabilization device comprises a body (1) and an igniter (2). A cavity (3) used for allowing gas to flow is arranged in the body (1). A fuel inlet (4) and a first cavity (5) are sequentially formed in the side wall of the cavity (3) in the air flowing direction. A second cavity (6) is formed in the bottom of the first cavity (5). The igniter (2) is arranged at the bottom of the second cavity (6). The flame stabilization device solves the problems that the airflow flowing speed of a flow return area formed by supersonic air flow in a cavity in the prior art is high, an initial fire core is hard to form and spread, and flames are not stable.
Description
Technical field
The application relates to supersonic combustion motor preparing technical field, particularly relates to a kind of flame stabilizer, and the application also relates to a kind of motor, is specifically related to supersonic combustion motor.
Background technique
Scramjet engine is the abbreviation of supersonic combustion ramjet propulsion, and it can obtain oxygen in soaring process from air.Obtain oxygen awing, save energy, mean that scramjet engine can produce larger thrust under the condition consuming equal in quality propellant agent.
Because scramjet engine obtains oxygen awing, therefore, its fuel in combustion chamber light comparatively difficulty and the flame instability lighted in after-burner, the flame in firing chamber by the air extinguishment entered, can be unfavorable for the propagation of firing chamber flame and the smooth combustion of fuel.
In order to overcome the above-mentioned defect that scramjet engine exists, flame stabilizer has been there is in prior art, this flame stabilizer comprises body, in body, be provided with the cavity for gas flow, cavity wall is provided with cavity, when supersonic flow flows through cavity, recirculating zone can be formed in cavity, make flame wherein resident, and as the fuel air mixture that new flame source sustained ignition upstream is come, realize flame holding.
But existing flame stabilizer, the recirculating zone air current flow speed that in cavity, supersonic flow is formed is higher, and scalar dissipation is comparatively large, formation and the propagation comparatively difficulty of initial fiery core, flame instability.
Summary of the invention
The invention provides a kind of flame stabilizer, the recirculating zone air current flow speed solving the formation of prior art concave endo-luminal ultrasound speed air-flow is higher, formation and the propagation comparatively difficulty of initial fiery core, the problem of flame instability.
Technological scheme provided by the invention is as follows:
A kind of flame stabilizer, comprise body and igniter, the cavity for gas flow is provided with in described body, described cavity wall is disposed with fuel inlet and the first cavity along air-flow direction, bottom described first cavity, be provided with the second cavity, described igniter is arranged on bottom described second cavity.
Preferably, the length of described first cavity and the ratio of the degree of depth are a, wherein, and 4≤a≤8.
Preferably, the length of described second cavity and the ratio of the degree of depth are b, wherein, and 4≤b≤8.
Preferably, the length of described second cavity is 1/2nd of described first cavity length, and the degree of depth of described second cavity is 1/2nd of the described first cavity degree of depth.
Preferably, the distance between two sidewalls of described second cavity center to described first cavity along air-flow direction is equal, and is 1/4th of described first cavity length along air-flow direction second cavity 6 sidewall to the distance of the first cavity 6 sidewall.
Preferably, described fuel inlet is the more than one hole entering described cavity for fuel be arranged on described cavity wall.
Preferably, the cross section of described cavity is circular or rectangle.
Preferably, described igniter to be arranged on bottom described second cavity and described second cavity near the sidewall locations of described fuel inlet.
A kind of motor, described motor have employed any one flame stabilizer above-mentioned.
The flame stabilizer that the application provides, owing to being provided with the second cavity bottom the first cavity, recirculating zone in first cavity drives by main flow in cavity, in recirculating zone, mean velocity obviously reduces relative to cavity mainstream speed, second cavity recirculating zone drives by the backflow of the first cavity recirculating zone, the back-flow velocity of the second cavity recirculating zone obviously reduces relative to the first cavity recirculating zone speed, therefore, the setting of the second cavity adds the residence time of fuel and air mixture, because the flow velocity of fuel and air mixture reduces and residence time, therefore, in terms of existing technologies, enhance the stability of igniting and flame.
Accompanying drawing explanation
In order to be illustrated more clearly in the embodiment of the present application or technological scheme of the prior art, be briefly described to the accompanying drawing used required in embodiment or description of the prior art below, apparently, the accompanying drawing that the following describes is only some embodiments recorded in the application, for those of ordinary skill in the art, under the prerequisite not paying creative work, other accompanying drawing can also be obtained according to these accompanying drawings.
Fig. 1 is flame stabilizer cross section structure schematic diagram;
Fig. 2 is flame stabilizer principle schematic;
Fig. 3 is that flame stabilizer provided by the invention and prior art flame stabilizer streamline contrast schematic diagram;
Fig. 4 is that flame stabilizer provided by the invention and prior art flame stabilizer speed cloud atlas contrast schematic diagram.
Embodiment
Technological scheme in the application is understood better in order to make those skilled in the art person, below in conjunction with the accompanying drawing in the embodiment of the present application, technological scheme in the embodiment of the present application is clearly and completely described, obviously, described embodiment is only some embodiments of the present application, instead of whole embodiments.Based on the embodiment in the application, those of ordinary skill in the art are not making the every other embodiment obtained under creative work prerequisite, all should belong to the scope of the application's protection.
The present embodiment adopts the mode of going forward one by one to write.
Please as shown in Figure 1, the embodiment of the present invention provides a kind of flame stabilizer, comprise body 1 and igniter 2, the cavity 3 for gas flow is provided with in body 1, cavity 3 sidewall is disposed with fuel inlet 4 and the first cavity 5 along air-flow direction, bottom the first cavity 5, be provided with the second cavity 6, igniter 2 is arranged on bottom the second cavity 6.
The flame stabilizer that the present embodiment provides, the second cavity 6 is provided with bottom the first cavity 5, recirculating zone in first cavity 5 drives by main flow in cavity, in recirculating zone, mean velocity obviously reduces relative to cavity 1 mainstream speed, second cavity 6 recirculating zone drives by the backflow of the first cavity 5 recirculating zone, the back-flow velocity of the second cavity 6 recirculating zone obviously reduces relative to the first cavity 5 recirculating zone speed, therefore, the setting of the second cavity 6 adds the residence time of fuel and air mixture, because the flow velocity of fuel and air mixture reduces and residence time, therefore, enhance the stability of igniting and flame.
Please as shown in Figure 2, the fuel of the first cavity 5 upstream is after the horizontal spray of fuel inlet 4, and when the first cavity 5, form shear layer 8, under the Involving velocity of shear layer 8, first enter the first cavity 5, now, fuel mixes with air.The mixture that fuel and air are formed is in the bottom reverse flow of the first cavity 5, a part flows out the first cavity 5 along the comparatively large vortex stucture in the first cavity 5 on the first top, cavity 5 forward position, the mixture that another part fuel and air are formed flows into the second cavity 6, fuel mixes further with air, be arranged on the mixture that igniter 2 pairs of fuel bottom the second cavity 6 and air formed to light a fire, due to be in the second cavity 6 fuel with air mixture compared with cavity 3, flow velocity is lower, and can in the second cavity 6 long period resident, therefore, be conducive to the formation of initial ignition core, relay, and be conducive to the stable of flame, thus strengthen the stability of igniting and flame.
Wherein, the length of the first cavity 5 and the ratio of the degree of depth are a, wherein, and 4≤a≤8.
Wherein, the length of the second cavity 6 and the ratio of the degree of depth are b, wherein, and 4≤b≤8.
Wherein, the length of the second cavity 6 is the degree of depth of the 1/2nd, second cavity 6 of the first cavity 5 length is 1/2nd of first cavity 5 degree of depth.
Wherein, the distance between the second cavity 6 center to the first cavity 5 sidewall is equal, and is 1/4th of the first cavity 5 length along air-flow direction second cavity 6 sidewall to the distance of the first cavity 5 sidewall.
As shown in Figure 1, in Fig. 1, the distance of fuel inlet 4 to the first cavity 5 is S1, and the length of the first cavity is L1; The degree of depth of the first cavity 5 is the ratio of D1, L1 and D1 is a, wherein, and 4≤a≤8; The length of the second cavity is L2, and the degree of depth of the second cavity is the ratio of D2, L2 and D2 is b, wherein, and 4≤b≤8; The ratio of L2 and L1 is the ratio of 1:2, D2 and D1 is 1:2; Along the direction of air flowing, the second cavity 6 sidewall is S2 and S3, wherein S2=S3 to the length of the first cavity 5 sidewall, and equals 1/4th L1.
Please as shown in Figure 3, Fig. 3 is that flame stabilizer provided by the invention and prior art flame stabilizer streamline contrast schematic diagram, wherein, Fig. 3 (a) is flame stabilizer streamline schematic diagram provided by the invention, the length depth ratio a of the first cavity 5 is the length depth ratio b of the 5, second cavity 6 is 5, wherein, the degree of depth D1 of the first cavity 5 is 16mm, and the degree of depth D2 of the second cavity 6 is 8mm.Fig. 3 (b) and Fig. 3 (c) are existing flame stabilizer streamline schematic diagram, and wherein, in Fig. 3 (b), the cavity degree of depth is 16mm, Fig. 3 (c) cavity degree of depth is 24mm, both cavity uniform length 80mm.
Known by contrasting, relative to existing flame stabilizer, in flame stabilizer first cavity 5 that the present embodiment provides, recirculating zone structure remains unchanged substantially, come wall near zone recirculating zone, flow path direction side near air-flow to diminish, and main backflow is larger at the yardstick flowed to, be conducive to high temperature fluid adverse current conveying in recirculating zone.
Please as shown in Figure 4, Fig. 4 is that flame stabilizer provided by the invention and prior art flame stabilizer speed cloud atlas contrast schematic diagram.Wherein, Fig. 4 (a) is the speed cloud atlas of the flame stabilizer corresponding with Fig. 3 (a); Fig. 4 (b), Fig. 4 (c) are flame stabilizer speed cloud atlas corresponding with Fig. 3 (b), Fig. 3 (c) respectively.
The contoured velocity of 880m/s, 70m/s ,-300m/s is given in Fig. 4.Can find out in figure that the airspeed in the second cavity of the flame stabilizer that the present embodiment provides is lower, and the velocity magnitude of the recess area of flame stabilizer of the prior art reaches 300m/s, and along with the increase of the cavity degree of depth, diapire high-speed counter-current region increases.Known by contrasting, the flame stabilizer that the present embodiment provides, defines the environment of low speed more in the second cavity recirculating zone, is conducive to igniting and flame holding.
The flame stabilizer that the present embodiment provides, its fuel inlet 4 to enter hole in cavity 3 for being arranged on more than one on cavity 3 sidewall for fuel.
The setting of said structure, makes fuel enter cavity 3 with the form of spraying, is convenient to air and spraying Homogeneous phase mixing, the oxygen in air is fully contacted with fuel.
The flame stabilizer that the present embodiment provides, the cross section of its cavity 3 is circular or rectangle.
The flame stabilizer that the present embodiment provides, its igniter 2 to be arranged on bottom the second cavity 6 and to be in the second cavity 6 near the position of the sidewall of fuel inlet 4.By Fig. 3 (a) and Fig. 4 (a), can find out, igniter 2 is in this position, and the speed of this position is lower, enhances igniting, and igniter 2 is arranged on this position, is convenient to propagation of flame.
Igniter in the present embodiment is spark plug or the ignition mechanism such as torch or plasma igniter.
To the above-mentioned explanation of the disclosed embodiments, professional and technical personnel in the field are realized or uses the present invention.To be apparent for those skilled in the art to the multiple amendment of these embodiments, General Principle as defined herein can without departing from the spirit or scope of the present invention, realize in other embodiments.Therefore, the present invention can not be restricted to these embodiments shown in this article, but will meet the widest scope consistent with principle disclosed herein and features of novelty.
Claims (9)
1. a flame stabilizer, comprise body (1) and igniter (2), the cavity (3) for gas flow is provided with in described body (1), described cavity (3) sidewall is disposed with fuel inlet (4) and the first cavity (5) along air-flow direction, it is characterized in that, described first cavity (5) bottom is provided with the second cavity (6), and described igniter (2) is arranged on described second cavity (6) bottom.
2. flame stabilizer according to claim 1, is characterized in that, the described length of the first cavity (5) and the ratio of the degree of depth are a, wherein, and 4≤a≤8.
3. flame stabilizer according to claim 1, is characterized in that, the described length of the second cavity (6) and the ratio of the degree of depth are b, wherein, and 4≤b≤8.
4. flame stabilizer according to claim 1, it is characterized in that, the length of described second cavity (6) is 1/2nd of described first cavity (5) length, and the degree of depth of described second cavity (6) is 1/2nd of described first cavity (5) degree of depth.
5. flame stabilizer according to claim 1, it is characterized in that, described second cavity (6) center is equal along the distance between two sidewalls of air-flow direction to described first cavity (5), and is 1/4th of described first cavity (5) length along the second cavity (6) sidewall described in air-flow direction to the distance of described first cavity (6) sidewall.
6. flame stabilizer according to claim 1, is characterized in that, described fuel inlet (4) is for being arranged on the more than one hole entering described cavity (3) for fuel on described cavity (3) sidewall.
7. flame stabilizer according to claim 1, is characterized in that, the cross section of described cavity (3) is circular or rectangle.
8. flame stabilizer according to claim 1, it is characterized in that, described igniter (2) is arranged on described second cavity (6) bottom and the sidewall locations of the close described fuel inlet (4) of described second cavity (6).
9. a motor, described motor have employed the flame stabilizer described in claim 1 to 8 any one.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510225080.5A CN104929808B (en) | 2015-05-06 | 2015-05-06 | A kind of flame stabilizer and engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510225080.5A CN104929808B (en) | 2015-05-06 | 2015-05-06 | A kind of flame stabilizer and engine |
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| Publication Number | Publication Date |
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| CN104929808A true CN104929808A (en) | 2015-09-23 |
| CN104929808B CN104929808B (en) | 2017-12-29 |
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| CN201510225080.5A Active CN104929808B (en) | 2015-05-06 | 2015-05-06 | A kind of flame stabilizer and engine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105971737A (en) * | 2016-05-09 | 2016-09-28 | 西北工业大学 | Time sequence control method for increasing ignition success rate of ramjet |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS63126766U (en) * | 1987-02-04 | 1988-08-18 | ||
| US7225623B2 (en) * | 2005-08-23 | 2007-06-05 | General Electric Company | Trapped vortex cavity afterburner |
| CN102175043A (en) * | 2002-06-11 | 2011-09-07 | 通用电气公司 | Gas turbine engine combustor can with trapped vortex cavity |
| JP2012013007A (en) * | 2010-07-01 | 2012-01-19 | Mitsubishi Heavy Ind Ltd | Supersonic combustor |
-
2015
- 2015-05-06 CN CN201510225080.5A patent/CN104929808B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS63126766U (en) * | 1987-02-04 | 1988-08-18 | ||
| CN102175043A (en) * | 2002-06-11 | 2011-09-07 | 通用电气公司 | Gas turbine engine combustor can with trapped vortex cavity |
| US7225623B2 (en) * | 2005-08-23 | 2007-06-05 | General Electric Company | Trapped vortex cavity afterburner |
| JP2012013007A (en) * | 2010-07-01 | 2012-01-19 | Mitsubishi Heavy Ind Ltd | Supersonic combustor |
Non-Patent Citations (1)
| Title |
|---|
| 范周琴等: "凹腔喷射超声速燃烧火焰结构实验研究", 《推进技术》, vol. 34, no. 1, 31 January 2013 (2013-01-31) * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105971737A (en) * | 2016-05-09 | 2016-09-28 | 西北工业大学 | Time sequence control method for increasing ignition success rate of ramjet |
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| CN104929808B (en) | 2017-12-29 |
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