CN103696881A - Self-hitting type support plate injector in air breathing engine - Google Patents
Self-hitting type support plate injector in air breathing engine Download PDFInfo
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- CN103696881A CN103696881A CN201310698681.9A CN201310698681A CN103696881A CN 103696881 A CN103696881 A CN 103696881A CN 201310698681 A CN201310698681 A CN 201310698681A CN 103696881 A CN103696881 A CN 103696881A
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Abstract
The invention relates to a self-hitting type support plate injector which is mainly used for injecting fuel into a scramjet engine combustion chamber under high mach number. A plurality of injection holes are formed in a self-hitting type support plate, and center lines of two adjacent injection holes intersect, so that the fuel and the air are mixed stably and efficiently in the injection holes. Meanwhile, a fuel cavity and a base of the self-hitting type support plate injector are of an integrated structure, so that the problem in the prior art that a welding gap formed after the base is welded to the fuel cavity has adverse effects on a supersonic velocity flow field is solved.
Description
Technical field
The present invention relates to a kind of self-impacting support plate ejector filler, be mainly used in to burner oil in the scramjet engine firing chamber under High Mach number.
Background technique
RBCC engine chamber is one of most important parts in RBCC motor, and major function is in limited time and space, to realize the efficient mixing of fuel, for the chemical energy of fuel is converted into heat energy to greatest extent.Super combustion mode is a kind of important operation mode of RBCC motor, indoor at supersonic combustion, gasflow mach number is larger, fuel mixes with air is more difficult, fuel waiting time in firing chamber very short (Millisecond) while, for strengening burning, therefore need study emphasis propellant spray, atomization and mixing research.Both at home and abroad researcher has carried out a large amount of research work at aspects such as the Configuration Design of propellant spray device and spray modes, to obtain desirable combustion efficiency, lower pitot loss, good thermal protection structure.
In the design of propellant spray device, need to consider a plurality of key issues, problems such as pitot loss, air-fuel mixture, fuel distribution, thus make scramjet engine obtain higher combination property.Research experience shows, when fueling injection equipment designs in supersonic flow, need to reduce pitot loss, improves mixing effect, improve fuel space dispersing characteristic etc.
Traditional wall spray mode technology is comparatively ripe, is easier to realize, and the momentum of entry of combustion chamber air-flow is very large, and fuel oil is limited to the penetration range of air-flow centre area, and fuel-oil atmozation, mixing effect are general.In order to improve the depth of penetration of fuel jet, fuel is fully mixed with air, exigent propellant spray pressure drop, this can significantly increase the development difficulty of fuel system; When entry of combustion chamber air flow parameters and fuel flow rate change, this mode is difficult to guarantee fuel with air-stable and mixes efficiently.
Summary of the invention
In order to solve under existing super combustion combustion chamber fuel injection mode, the mixing efficiency of fuel and air is lower, when entry of combustion chamber air flow parameters and fuel flow rate change, the not enough problem that the mixing efficiency of fuel and air declines, the invention provides a kind of can be in firing chamber resistance and air-flow pitot loss lower in the situation that, realize self-impacting support plate ejector filler in the airbreathing motor that fuel mixes with the high efficiency of air.
Concrete technological scheme of the present invention is:
In airbreathing motor, a self-impacting support plate ejector filler, comprises fuel cavity, self-impacting spray support plate and base; Described fuel cavity and self-impacting spray support plate are all fixedly mounted on base, between described fuel cavity and self-impacting spray support plate, offer fluid passage; On described base, offer fuel inlet; Described fluid passage is communicated with fuel inlet; In described self-impacting spray support plate, offer a plurality of spray orifices that are connected with fluid passage; It is characterized in that: the center line of described two adjacent spray orifices intersects.
Above-mentioned fuel cavity and base are integral type structure.
The invention has the advantages that:
The center line of two spray orifices that 1, the present invention is adjacent intersects, and the mixing efficiency of fuel and air is improved, and when propellant spray pressure drop or air flow parameters variation, also can guarantee that fuel mixes with the stability and high efficiency rate of air.
2, the fuel cavity in the present invention and base adopt integral structure, have avoided the weld seam after base and fuel cavity welding in prior art to produce dysgenic problem to supersonic flow field.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention.
1-fuel cavity, 2-self-impacting spray support plate, 21-spray orifice, 3-base, 4-fuel inlet, 5-fluid passage.
Embodiment
In order to overcome under existing super combustion combustion chamber fuel injection mode, the mixing efficiency of fuel and air is lower, when entry of combustion chamber air flow parameters and fuel flow rate change, the deficiency that the mixing efficiency of fuel and air declines, a kind of self-impacting support plate ejector filler is provided, utilize this ejector filler lower in the situation that, realize fuel and to mix with the stability and high efficiency rate of air in firing chamber resistance and air-flow pitot loss.
Below in conjunction with 1 pair of structure of the present invention of accompanying drawing, be described:
A self-impacting support plate ejector filler in airbreathing motor, comprises fuel cavity 1, self-impacting spray support plate 2 and base 3; Fuel cavity 1 and self-impacting spray support plate 2 are all fixedly mounted on base 3, between fuel cavity 1 and self-impacting spray support plate 2, offer fluid passage 5; On base 3, offer fuel inlet 4; Fluid passage 5 is communicated with fuel inlet 4; In self-impacting spray support plate 2, offer a plurality of spray orifices 21 that are connected with fluid passage 5; Specialization is: above-mentioned two adjacent spray orifice 21 center lines intersect;
Because two adjacent spray orifice 21 center lines in the present invention intersect, fuel oil sprays through spray orifice like this, after bags inner impact, forms uniform and stable atomization field, can effectively improve with the blending of air incoming flow, improve firing effect.
Furtherly, in order to reduce manufacturing procedure, fuel cavity 1 and the base 3 of this ejector filler are integral types; Adding man-hour, the mode that adopts whole block material to cut by line is processed; Meanwhile, avoided the weld seam after base 3 and fuel cavity 1 welding in prior art to produce dysgenic problem to supersonic flow field.
Claims (2)
1. a self-impacting support plate ejector filler in airbreathing motor, comprises fuel cavity, self-impacting spray support plate and base; Described fuel cavity and self-impacting spray support plate are all fixedly mounted on base, between described fuel cavity and self-impacting spray support plate, offer fluid passage; On described base, offer fuel inlet; Described fluid passage is communicated with fuel inlet; In described self-impacting spray support plate, offer a plurality of spray orifices that are connected with fluid passage; It is characterized in that: the center line of described two adjacent spray orifices intersects.
2. self-impacting support plate ejector filler in airbreathing motor according to claim 1, is characterized in that: described fuel cavity and base are integral type structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310698681.9A CN103696881A (en) | 2013-12-18 | 2013-12-18 | Self-hitting type support plate injector in air breathing engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310698681.9A CN103696881A (en) | 2013-12-18 | 2013-12-18 | Self-hitting type support plate injector in air breathing engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103696881A true CN103696881A (en) | 2014-04-02 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310698681.9A Pending CN103696881A (en) | 2013-12-18 | 2013-12-18 | Self-hitting type support plate injector in air breathing engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103696881A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109595096A (en) * | 2018-12-03 | 2019-04-09 | 上海空间推进研究所 | A kind of ejector filler operatic tunes temperature barrier |
| CN114251179A (en) * | 2021-12-22 | 2022-03-29 | 华中科技大学 | Adjustable oil injection support plate structure of ramjet engine and control method |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3667233A (en) * | 1969-11-14 | 1972-06-06 | Us Air Force | Dual mode supersonic combustion ramjet engine |
| US4969327A (en) * | 1988-09-16 | 1990-11-13 | General Electric Company | Hypersonic scramjet engine fuel injector |
| CN102019236A (en) * | 2011-01-04 | 2011-04-20 | 北京航空航天大学 | Self-oscillation jet impact-type nozzle for atomizing complex fluids |
| CN203685413U (en) * | 2013-12-18 | 2014-07-02 | 中国航天科技集团公司第六研究院第十一研究所 | Self-impact support plate injector for aspirated engine |
-
2013
- 2013-12-18 CN CN201310698681.9A patent/CN103696881A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3667233A (en) * | 1969-11-14 | 1972-06-06 | Us Air Force | Dual mode supersonic combustion ramjet engine |
| US4969327A (en) * | 1988-09-16 | 1990-11-13 | General Electric Company | Hypersonic scramjet engine fuel injector |
| CN102019236A (en) * | 2011-01-04 | 2011-04-20 | 北京航空航天大学 | Self-oscillation jet impact-type nozzle for atomizing complex fluids |
| CN203685413U (en) * | 2013-12-18 | 2014-07-02 | 中国航天科技集团公司第六研究院第十一研究所 | Self-impact support plate injector for aspirated engine |
Non-Patent Citations (1)
| Title |
|---|
| 白菡尘 等: "M6双模态冲压模型发动机氢燃料的燃烧试验研究", 《南京航空航天大学学报》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109595096A (en) * | 2018-12-03 | 2019-04-09 | 上海空间推进研究所 | A kind of ejector filler operatic tunes temperature barrier |
| CN114251179A (en) * | 2021-12-22 | 2022-03-29 | 华中科技大学 | Adjustable oil injection support plate structure of ramjet engine and control method |
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Application publication date: 20140402 |