CN109798202A - A kind of liquid-propellant rocket engine ejector filler integrating electric igniter - Google Patents
A kind of liquid-propellant rocket engine ejector filler integrating electric igniter Download PDFInfo
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- CN109798202A CN109798202A CN201910268289.8A CN201910268289A CN109798202A CN 109798202 A CN109798202 A CN 109798202A CN 201910268289 A CN201910268289 A CN 201910268289A CN 109798202 A CN109798202 A CN 109798202A
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- fuel
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- hole
- outer cylinder
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E20/00—Combustion technologies with mitigation potential
- Y02E20/34—Indirect CO2mitigation, i.e. by acting on non CO2directly related matters of the process, e.g. pre-heating or heat recovery
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- Combustion Methods Of Internal-Combustion Engines (AREA)
Abstract
A kind of liquid-propellant rocket engine ejector filler integrating electric igniter.Present invention composition includes: bottom plate, outer cylinder, fuel nozzle, oxidant nozzle, top cover and sparking plug, outer cylinder is connect with top cover, outer cylinder has central axis, pass through annular transverse slat connection between central axis and outer cylinder barrel, outer tube inner chamber is divided into epicoele and cavity of resorption by annular transverse slat, and fuel through-hole is arranged on the side wall of cavity of resorption；The bottom connecting bottom board of cavity of resorption, multiple fuel nozzle fixation holes are uniformly arranged on bottom plate, multiple oxidant nozzle fixation holes are uniformly arranged on annular transverse slat, what the position of oxidant nozzle fixation hole and fuel nozzle fixation hole one-to-one correspondence, fuel nozzle and oxidant nozzle were adapted is connected between every a pair of of fuel nozzle fixation hole and oxidant nozzle fixation hole；It is uniformly arranged oxidant through-hole on the central axis side wall of upper chamber portion, fuel through-hole under fuel through-hole and one group is uniformly arranged on one group on the central axis side wall of cavity of resorption part.The present invention is suitable for double elements liquid-propellant rocket engine, and electric igniter and ejector filler are integrated in one, and realizes system and simplifies design.
Description
Technical field:
The present invention relates to a kind of liquid-propellant rocket engine ejector fillers for integrating electric igniter.
Background technique:
The developing direction of rocket engine is simplified structure to improve engine reliability, while guaranteeing engine performance.
The ejector filler of traditional rocket engine is responsible for the mixing of tissue oxygen agent and fuel, and electric igniter is as a group
Part is fixed on ejector filler by modes such as bolt or welding, and the high-energy fuel gas that electric igniter generates passes through ejector filler center
Reserved fire hole lights oxidant and fuel.
The electric igniter of traditional rocket engine is an independent component, usually passes through bolt and welding by several parts
Etc. modes connect composition, the oxidant and fuel individually supplied form torch after sparking plug is lighted, and realize high-energy ignition, oxidation
The agent pipeline additional with fuel requirement is controlled with valve, and structure is relative complex.
Further, since oxidant and fuel that traditional rocket engine electric igniter is individually supplied be limited to gas cylinder size with
The factors such as weight cause electric igniter that cannot work long hours, and the multiple starting for certain rocket engines in space is not
Benefit.
Summary of the invention:
The purpose of the present invention is structure is complicated for existing electric igniter, oxidant is individually supplied with fuel requirement, when cannot be long
Between reliably working the problem of, a kind of liquid-propellant rocket engine ejector filler integrating electric igniter is provided.
Above-mentioned purpose is realized by following technical scheme:
A kind of liquid-propellant rocket engine ejector filler integrating electric igniter, composition include: bottom plate, outer cylinder, fuel nozzle,
Oxidant nozzle, top cover and sparking plug, the outer cylinder are connect with top cover, and the outer cylinder has central axis, central axis and outer cylinder cylinder
By annular transverse slat connection between wall, outer tube inner chamber is divided into epicoele and cavity of resorption, fuel is arranged on the side wall of cavity of resorption by annular transverse slat
Through-hole；
The bottom connecting bottom board of the cavity of resorption is uniformly arranged multiple fuel nozzle fixation holes on bottom plate, uniformly sets on annular transverse slat
Set multiple oxidant nozzle fixation holes, the position one-to-one correspondence of oxidant nozzle fixation hole and fuel nozzle fixation hole, fuel spray
What mouth and oxidant nozzle were adapted is connected between every a pair of of fuel nozzle fixation hole and oxidant nozzle fixation hole, and is firing
Expect to form fuel circular passage between nozzle inner walls and oxidant outer nozzle wall；
Central axial bore is set on the central axis, is connect above the central axis with sparking plug, the central axis side wall of upper chamber portion
On be uniformly arranged oxidant through-hole, fuel under fuel through-hole and one group is uniformly arranged on one group on the central axis side wall of cavity of resorption part
Through-hole.
The liquid-propellant rocket engine ejector filler for integrating electric igniter, the top cover setting oxidant enter
Hole.
The liquid-propellant rocket engine ejector filler for integrating electric igniter, the fuel nozzle is cylindrical, combustion
Expect along the circumferential direction to be uniformly arranged multiple radial fuel entrances on the side wall of nozzle.
Central axis is arranged in the liquid-propellant rocket engine ejector filler for integrating electric igniter, the oxidant nozzle
Xiang Kong.
The liquid-propellant rocket engine ejector filler for integrating electric igniter, passes through argon between the bottom plate and outer cylinder
The modes such as arc-welding, electron beam welding or soldering connect, and are connected between outer cylinder and top cover by modes such as argon arc welding, electron beam welding or solderings
It connects, is threadedly connected between outer cylinder and sparking plug.
The liquid-propellant rocket engine ejector filler for integrating electric igniter leads between the fuel nozzle and bottom plate
Screw thread or welding manner connection are crossed, is connected between oxidant nozzle and outer cylinder by screw thread or welding manner, fuel nozzle and oxygen
It is connected between agent nozzle by brazing mode.
Beneficial effects of the present invention:
The present invention is suitable for double elements liquid-propellant rocket engine, and the basis that it is the integrated design with outer cylinder passes through outer cylinder and bottom
The combination of plate provides for fuel nozzle and oxidant nozzle and places fixed space.Pass through the oxidant of upper chamber portion central axis
The fuel recirculation hole of recirculation hole and cavity of resorption portion central axes realizes the confession to oxidant and fuel necessary to electric igniter work
It answers, is realized under the action of sparking plug and oxidant and fuel are lighted, realize the integrated design of electric igniter and ejector filler.
The structure of ejector filler of the present invention realizes system simplification and sets on the basis of simplifying electric igniter structure
Meter, compared to traditional electric igniter, it is no longer necessary to which additional oxidant and fuel supply conduit and valve, the system of improving can
By property.
The structure of ejector filler of the present invention, the oxidant accounting near sparking plug is larger, is conducive to light electric igniter
Oxidant and fuel, while fuel gas temperature is relatively low, is conducive to protect outer cylinder center shaft material；Part of fuel passes through under
Cavity segment central axis is fired with oxygen-enriched fuel gas buring to realize and light a fire close to the fuel recirculation hole inlet point fire channel of bottom
The further raising of gas energy.
The present invention is simplifying electric igniter structure, and electric igniter and ejector filler are integrated in one, and realizes system simplification and sets
Meter, eliminates oxidant used in additional electric igniter and fuel supply conduit and valve.It is real on the basis of simplified system design
The raising of ignition energy is showed, while can work long hours, has been provided safeguard for the reliably working of engine.
Detailed description of the invention:
Attached drawing 1 is structural schematic diagram of the invention.
Attached drawing 2 is the top view of attached drawing 1.
Attached drawing 3 is the structural schematic diagram of bottom plate of the present invention.
Attached drawing 4 is the top view of attached drawing 3.
Attached drawing 5 is the structural schematic diagram of outer cylinder of the present invention.
Attached drawing 6 is the top view of attached drawing 5.
Attached drawing 7 is the structural schematic diagram of fuel nozzle of the present invention.
Attached drawing 8 is the structural schematic diagram of oxidant nozzle of the present invention.
Attached drawing 9 is the structural schematic diagram of top cover of the present invention.
Attached drawing 10 is the top view of attached drawing 9.
Attached drawing 11 is the structural schematic diagram of sparking plug of the present invention.
Specific embodiment:
In order to make the object, technical scheme and advantages of the embodiment of the invention clearer, below in conjunction in the embodiment of the present invention
Attached drawing, technical scheme in the embodiment of the invention is clearly and completely described, it is clear that described embodiment is this hair
Bright a part of the embodiment, instead of all the embodiments.Based on the embodiments of the present invention, those of ordinary skill in the art exist
Every other embodiment obtained under the premise of creative work is not made, shall fall within the protection scope of the present invention.
The present invention provides a kind of liquid-propellant rocket engine ejector filler for integrating electric igniter, in conjunction with attached drawing 1 to attached
Shown in Figure 11, comprising: bottom plate 1, outer cylinder 2, fuel nozzle 3, oxidant nozzle 4, top cover 5 and sparking plug 6, during the outer cylinder 2 has
Mandrel 201 is connected by annular transverse slat 202 between 2 barrel of central axis 201 and outer cylinder, and annular transverse slat 202 is by 2 inner cavity of outer cylinder point
For epicoele and cavity of resorption；Teasehole 203, the bottom connecting bottom board 1 of cavity of resorption are set on the side wall of the cavity of resorption；
It is uniformly arranged multiple fuel nozzle fixation holes 101 on bottom plate 1, multiple oxidant nozzles are uniformly arranged on annular transverse slat 202
The position of fixation hole 204, oxidant nozzle fixation hole 204 and fuel nozzle fixation hole 101 corresponds；Fuel nozzle 3 and oxygen
What agent nozzle 4 was adapted is connected between every a pair of of fuel nozzle fixation hole 101 and oxidant nozzle fixation hole 204；And
Fuel circular passage is formed between 4 outer wall of 3 inner wall of fuel nozzle and oxidant nozzle；
The oxidant nozzle fixation hole 204 is identical as the number of fuel nozzle fixation hole 101, position correspond, for pair
Fuel nozzle 3 and oxidant nozzle 4 should be connected, the assembly of nozzle is simplified.By taking fuel nozzle fixation hole 101 as an example, fuel spray
Mouth fixation hole 101 on bottom plate 1 radially with circumference to being uniformly distributed, as shown in Figure 4.
As an example, the thickness of the bottom plate 1 can be 2-8mm, 101 number of fuel nozzle fixation hole can be 4-360
It is a, being uniformly distributed for multi-turn is formed on bottom plate 1.The pore size and fuel nozzle 3 of fuel nozzle fixation hole 101 are adapted.
As an example, the teasehole 203 is evenly distributed on the barrel of outer cylinder 2, aperture can be Φ 4mm- Φ
40mm, hole count can be 1-4.
It, can also be with as an example, the number of the oxidant nozzle fixation hole 204 is identical as fuel nozzle fixation hole 101
It is 4-360.The pore size and oxidant nozzle 4 of oxidant nozzle fixation hole 204 are adapted.
As an example, the annular transverse slat 202 can be welded and fixed by centre bore and central axis 201；Annular transverse slat 202 with
It can also use and be welded and fixed between 2 barrel of outer cylinder.Mode is welded and fixed including electron beam and argon arc welding etc. in described be welded and fixed.
As an example, can be solid using screw thread or welding manner between the fuel nozzle fixation hole 101 and fuel nozzle 3
Fixed, the welding manner includes the welding manners such as electron beam and soldering.Oxidant nozzle fixation hole 204 and oxidant nozzle 4 it
Between can also be fixed using screw thread or welding manner, the welding manner includes the welding manners such as electron beam and soldering.
In present embodiment, partial oxidation agent enters central axis by the central axis lateral through aperture 206 of 2 upper chamber portion of outer cylinder
Fuel through-hole 207 enters central axial bore 205 on the central axis side wall for passing through 2 cavity of resorption part of outer cylinder to hole 205, part of fuel,
This partial oxidation agent and fuel are lighted by sparking plug 6；Fuel is logical under the central axis side wall that part of fuel passes through 2 cavity of resorption part of outer cylinder
Hole 208 enters central axial bore 205, and oxygen-enriched fuel gas buring, to realize the further raising of igniting combustion gas energy.
As an example, the number of the oxidant through-hole 206 of the central axis side wall of 2 upper chamber portion of outer cylinder is 3 ~ 8, aperture is
0.5mm~2mm。
As an example, the number of the upper fuel through-hole 207 of the central axis side wall of 2 cavity of resorption part of outer cylinder is 3 ~ 8, aperture is
0.5mm~2mm。
As an example, the number of the lower fuel through-hole 208 of the central axis side wall of 2 cavity of resorption part of outer cylinder is 3 ~ 8, aperture is
0.5mm~2mm。
Further, as shown in connection with fig. 5, central axial bore 205 is set on the central axis 201.
The central axial bore 205 is for providing the ignition channel of electric igniter.
As an example, the aperture of the central axial bore 205 can be Φ 4mm- Φ 20mm.
Further, as shown in connection with fig. 7, the fuel nozzle 3 is cylindrical, circumferentially square on the side wall of fuel nozzle 3
To being uniformly arranged multiple radial fuel entrances 301.Fuel is entered the cavity of resorption of outer cylinder 2 by fuel through-hole 203, then passes through radial fuel
Entrance 301 enters fuel circular passage, since the narrow space of fuel circular passage is, it can be achieved that fuel is gone out by fuel nozzle 3
The high speed ejection of mouth.
As an example, the aperture of the radial fuel entrance 301 can be Φ 1- Φ 4mm, radial fuel entrance 301 is along circle
Circumferential direction is arranged 3-60.
Further, as shown in connection with fig. 8, the oxidant nozzle 4 has circumferential through-hole, is same as passing through oxidant.
As an example, the aperture of 4 axially extending bore 401 of oxidant nozzle can be Φ 0.5- Φ 6mm；
As an example, as shown in connection with fig. 1, being connected between the fuel nozzle 3 and oxidant nozzle 4 by modes such as solderings
It connects.
Based on a kind of liquid-propellant rocket engine ejector filler for integrating electric igniter, liquid-propellant rocket engine
Jet method are as follows:
It is passed through fuel from fuel through-hole 203 to the cavity of resorption, fuel enters fuel nozzle 3 and oxygen through radial fuel entrance 301
Fuel circular passage between agent nozzle 4, by 3 high speed ejection of fuel nozzle；Oxidant passes through 4 axially extending bore of oxidant nozzle
401 are sprayed；Oxidant is further atomized, and mix with fuel in the case where the fuel of 3 high speed ejection of fuel nozzle drives.
By the upper fuel through-hole 207 of the oxidant stream through-hole 206 of upper chamber portion central axis and cavity of resorption portion central axes with
Lower fuel through-hole 208 is realized to the supply of oxidant and fuel necessary to electric igniter work, is lighted under the action of sparking plug
Oxidant and fuel.Nearby oxidant accounting is larger for sparking plug, is conducive to light oxidant and fuel, and fuel gas temperature is relatively low,
It can protect outer cylinder center shaft material；Part of fuel by cavity of resorption portion central axes close to bottom lower fuel through-hole 208 into
Enter ignition channel, burn with oxygen rich fuel gas, to realize the further raising of igniting combustion gas energy, while ensure that steady for a long time
Fixed work, provides safeguard for the reliably working of engine.
The mixture of oxidant and fuel produces after ejector filler spray of the present invention in the electric igniter of integrated design
It burns inside thrust chamber under the drive of raw high-energy fuel gas, high-temperature high-pressure fuel gas is formed, most afterwards through the drawing of converging diverging
Wa Er jet pipe high speed ejection.
The present invention is suitable for high-performance double elements liquid-propellant rocket engine, such as oxygen kerosene, liquid oxygen methane, liquid oxygen liquid
The rocket engines such as hydrogen, dinitrogen tetroxide uns-dimethylhydrazine.Wherein, the oxidant includes liquid oxygen or dinitrogen tetroxide；Fuel packet
Include hydrogen, methane or uns-dimethylhydrazine.
Finally, it should be noted that the above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations；Although
Present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that: it still may be used
To modify the technical solutions described in the foregoing embodiments or equivalent replacement of some of the technical features；
And these are modified or replaceed, technical solution of various embodiments of the present invention that it does not separate the essence of the corresponding technical solution spirit and
Range.
Claims (6)
1. a kind of liquid-propellant rocket engine ejector filler for integrating electric igniter, composition include: bottom plate (1), outer cylinder (2),
Fuel nozzle (3), oxidant nozzle (4), top cover (5) and sparking plug (6), it is characterized in that: the outer cylinder (2) has central axis
(201), it is connect between central axis (201) and outer cylinder (2) barrel by annular transverse slat (202), annular transverse slat (202) is by outer cylinder
(2) inner cavity is divided into epicoele and cavity of resorption, and fuel through-hole (203) are arranged on the side wall of cavity of resorption；
The bottom connecting bottom board (1) of the cavity of resorption, multiple fuel nozzle fixation holes (101) are uniformly arranged on bottom plate (1), and annular is horizontal
Multiple oxidant nozzle fixation holes (204) are uniformly arranged on plate (202), oxidant nozzle fixation hole (204) and fuel nozzle are solid
The position for determining hole (101) corresponds, and every a pair of of fuel that is connected to that fuel nozzle (3) and oxidant nozzle (4) are adapted sprays
Between mouth fixation hole (101) and oxidant nozzle fixation hole (204), and fuel nozzle (3) inner wall and oxidant nozzle (4) outside
Fuel circular passage is formed between wall；
Central axial bore (205) are set on the central axis (201), are connect above the central axis (201) with sparking plug (6), on
It is uniformly arranged on the central axis side wall of cavity segment oxidant through-hole (206), is uniformly arranged one on the central axis side wall of cavity of resorption part
Fuel through-hole (208) under fuel through-hole (207) is with one group in group.
2. the liquid-propellant rocket engine ejector filler according to claim 1 for integrating electric igniter, it is characterized in that: described
Oxidant access aperture (501) are arranged in top cover (5).
3. the liquid-propellant rocket engine ejector filler according to claim 2 for integrating electric igniter, it is characterized in that: described
Fuel nozzle (3) is cylindrical, and multiple radial fuel entrances are along the circumferential direction uniformly arranged on the side wall of fuel nozzle (3)
(301).
4. the liquid-propellant rocket engine ejector filler according to claim 1 or 2 or 3 for integrating electric igniter, feature
Be: central axial bore (401) are arranged in the oxidant nozzle (4).
5. the liquid-propellant rocket engine ejector filler according to claim 4 for integrating electric igniter, it is characterized in that: described
It is connected between bottom plate (1) and outer cylinder (2) by modes such as argon arc welding, electron beam welding or solderings, between outer cylinder (2) and top cover (3)
It is connected by modes such as argon arc welding, electron beam welding or solderings, is threadedly connected between outer cylinder (2) and sparking plug (6).
6. the liquid-propellant rocket engine ejector filler according to claim 5 for integrating electric igniter, it is characterized in that: described
It is connected between fuel nozzle (3) and bottom plate (1) by screw thread or welding manner, is passed through between oxidant nozzle (4) and outer cylinder (2)
Screw thread or welding manner connection, are connected between fuel nozzle (3) and oxidant nozzle (4) by brazing mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910268289.8A CN109798202B (en) | 2019-04-04 | 2019-04-04 | Liquid rocket engine injector integrating electric igniter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910268289.8A CN109798202B (en) | 2019-04-04 | 2019-04-04 | Liquid rocket engine injector integrating electric igniter |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109798202A true CN109798202A (en) | 2019-05-24 |
| CN109798202B CN109798202B (en) | 2023-08-22 |
Family
ID=66563416
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| CN201910268289.8A Active CN109798202B (en) | 2019-04-04 | 2019-04-04 | Liquid rocket engine injector integrating electric igniter |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111412086A (en) * | 2020-05-21 | 2020-07-14 | 安徽九州云箭航天技术有限公司 | Weldless injector for liquid rocket engine |
| CN111765017A (en) * | 2020-06-11 | 2020-10-13 | 安徽九州云箭航天技术有限公司 | Torch electric ignition chamber for liquid rocket engine |
| CN112431693A (en) * | 2020-11-19 | 2021-03-02 | 北京航空航天大学 | Pin injector, rocket engine and rocket |
| CN113202656A (en) * | 2021-05-28 | 2021-08-03 | 西安航天动力研究所 | Guide plate and injector capable of improving propellant filling synchronism |
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| JP4215203B2 (en) * | 2003-08-20 | 2009-01-28 | 株式会社Ｉｈｉエアロスペース | Igniter-integrated fuel injector using liquid fuel and liquid oxidant |
| CN106134417B (en) * | 2006-10-19 | 2012-04-04 | 上海空间推进研究所 | Low-thrust rocket |
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| JP5455411B2 (en) * | 2009-03-30 | 2014-03-26 | 三菱重工業株式会社 | Rocket injector |
| CN102996284B (en) * | 2012-11-27 | 2015-02-25 | 北京航空航天大学 | Solid-liquid rocket engine annular igniter suitable for head jet of hydrogen peroxide |
| CN103867340B (en) * | 2012-12-12 | 2017-07-25 | 中国人民解放军国防科学技术大学 | A kind of double-cyclone ejector filler |
| RU2607918C1 (en) * | 2015-12-28 | 2017-01-11 | Владислав Юрьевич Климов | Coaxial spray nozzle |
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| CN108286478B (en) * | 2017-12-20 | 2019-07-12 | 北京控制工程研究所 | A kind of pre- rotating pintle ejector filler applied to double elements liquid-propellant rocket engine |
| CN108691692A (en) * | 2018-05-31 | 2018-10-23 | 北京航空航天大学 | Mix ejector filler and small liquid rocket engine |
| CN108915899B (en) * | 2018-06-29 | 2020-02-14 | 北京航天动力研究所 | Four-bottom three-cavity injector |
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| CN111412086A (en) * | 2020-05-21 | 2020-07-14 | 安徽九州云箭航天技术有限公司 | Weldless injector for liquid rocket engine |
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| CN111765017B (en) * | 2020-06-11 | 2023-11-03 | 安徽九州云箭航天技术有限公司 | Torch electric ignition chamber for liquid rocket engine |
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