CN203685413U - Self-impact support plate injector for aspirated engine - Google Patents
Self-impact support plate injector for aspirated engine Download PDFInfo
- Publication number
- CN203685413U CN203685413U CN201320839131.XU CN201320839131U CN203685413U CN 203685413 U CN203685413 U CN 203685413U CN 201320839131 U CN201320839131 U CN 201320839131U CN 203685413 U CN203685413 U CN 203685413U
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- China
- Prior art keywords
- self
- support plate
- fuel
- impacting
- base
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- Expired - Fee Related
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- 239000000446 fuel Substances 0.000 claims abstract description 51
- 239000007921 spray Substances 0.000 claims description 30
- 239000000945 filler Substances 0.000 claims description 10
- 239000012530 fluid Substances 0.000 claims description 10
- 238000002485 combustion reaction Methods 0.000 abstract description 12
- 238000002347 injection Methods 0.000 abstract description 6
- 239000007924 injection Substances 0.000 abstract description 6
- 238000003466 welding Methods 0.000 abstract description 4
- 238000002156 mixing Methods 0.000 description 10
- 238000010304 firing Methods 0.000 description 5
- 239000003380 propellant Substances 0.000 description 5
- 108091053398 TRIM/RBCC family Proteins 0.000 description 3
- 102000011408 Tripartite Motif Proteins Human genes 0.000 description 3
- 239000000295 fuel oil Substances 0.000 description 3
- 238000000889 atomisation Methods 0.000 description 2
- 230000035515 penetration Effects 0.000 description 2
- 241001640558 Cotoneaster horizontalis Species 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 239000003921 oil Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
Images
Landscapes
- Fuel-Injection Apparatus (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
- Nozzles (AREA)
Abstract
The utility model relates to a self-impact support plate injector, which is mainly used for injecting fuel into a combustion chamber of a scramjet engine under a high-mach condition. A plurality of injection holes are formed in a self-impact support plate. According to the self-impact support plate injector, the centerlines of every two adjacent injection holes are intersected, so that the fuel and air at the injection holes are stably and efficiently mixed; in addition, a fuel cavity and a base of the self-impact support plate injector form an integrated structure, so that the problem of undesirable impact of a welding seam formed by the welding of the base and the fuel cavity in the prior art on a supersonic flow field is solved.
Description
Technical field
The utility model relates to a kind of self-impacting support plate ejector filler, is 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) simultaneously, for strengening burning, therefore need study emphasis propellant spray, atomization and mixing research.Researcher has carried out a large amount of research work at the aspect such as Configuration Design and spray mode of propellant spray device both at home and abroad, to obtain desirable combustion efficiency, lower pitot loss, good thermal protection structure.
In the design of propellant spray device, need to consider multiple key issues, the problems such as 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; In the time that 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.
Model utility content
In order to solve under existing super combustion combustion chamber fuel injection mode, the mixing efficiency of fuel and air is lower, in the time that 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 utility model provide 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 utility model is:
Self-impacting support plate ejector filler in a kind of 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 multiple 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 utility model has the advantage of:
The center line of two spray orifices that 1, the utility model is adjacent intersects, and the mixing efficiency of fuel and air is improved, and in the time of 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 utility model 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 utility model.
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, in the time that 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 accompanying drawing 1, structure of the present utility model is described:
Self-impacting support plate ejector filler in a kind of 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 multiple 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 utility model 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 multiple 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 |
|---|---|---|---|
| CN201320839131.XU CN203685413U (en) | 2013-12-18 | 2013-12-18 | Self-impact support plate injector for aspirated engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320839131.XU CN203685413U (en) | 2013-12-18 | 2013-12-18 | Self-impact support plate injector for aspirated engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203685413U true CN203685413U (en) | 2014-07-02 |
Family
ID=51007325
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320839131.XU Expired - Fee Related CN203685413U (en) | 2013-12-18 | 2013-12-18 | Self-impact support plate injector for aspirated engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203685413U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103696881A (en) * | 2013-12-18 | 2014-04-02 | 中国航天科技集团公司第六研究院第十一研究所 | Self-hitting type support plate injector in air breathing engine |
| CN115628466A (en) * | 2022-10-12 | 2023-01-20 | 哈尔滨工业大学 | A low-resistance, low-heat-load large-swept strut suitable for supersonic combustion chambers |
-
2013
- 2013-12-18 CN CN201320839131.XU patent/CN203685413U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103696881A (en) * | 2013-12-18 | 2014-04-02 | 中国航天科技集团公司第六研究院第十一研究所 | Self-hitting type support plate injector in air breathing engine |
| CN115628466A (en) * | 2022-10-12 | 2023-01-20 | 哈尔滨工业大学 | A low-resistance, low-heat-load large-swept strut suitable for supersonic combustion chambers |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140702 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |