CN108691692A - Mix ejector filler and small liquid rocket engine - Google Patents
Mix ejector filler and small liquid rocket engine Download PDFInfo
- Publication number
- CN108691692A CN108691692A CN201810556674.8A CN201810556674A CN108691692A CN 108691692 A CN108691692 A CN 108691692A CN 201810556674 A CN201810556674 A CN 201810556674A CN 108691692 A CN108691692 A CN 108691692A
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- Prior art keywords
- fuel
- cavity
- oxidant
- eddy flow
- ejector filler
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/52—Injectors
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles (AREA)
Abstract
The present invention relates to Liquid Propellant Rocket Engine fields, more particularly, to a kind of mixing ejector filler and small liquid rocket engine.The mixing ejector filler includes shell, cover board and core;Oxidant cavity and fuel cavity are provided in shell;Oxidant cavity is ring-type, and oxidant cavity is arranged around fuel cavity.Cover plate lid is set on shell upper surface and is mutually welded with shell, for making oxidant cavity seal;Core is set in fuel cavity, and core can be such that the fuel swirl in fuel cavity centrifuges.The lower face of shell is panel, fuel nozzle and oxidant nozzle are corresponded at fuel cavity and offered at oxidant cavity on panel, fuel through the centrifugation of core eddy flow in fuel cavity is sprayed by fuel nozzle, and the oxidant in oxidant cavity can be sprayed by oxidant nozzle.The mixing ejector filler of the present invention realizes the centrifugal spray of fuel by increasing fuel nozzle core, mixes spray mode with single flow oxygen nozzle composition, atomizing effect is good, and efficiency of combustion is higher.
Description
Technical field
The present invention relates to Liquid Propellant Rocket Engine fields, more particularly, to a kind of mixing ejector filler and miniature liquid fire
Arrow engine.
Background technology
Small liquid rocket engine plays extremely important role in terms of many Spacecraft Controls, it can be to defend
Change rail, spacecrafts rendezvous and gesture stability of star and spaceship etc. provides power, and the startup that can be also used for sustainer is protected
Card system and aircraft soft-landing system etc., development of small-scale liquid-propellant rocket engine are current Space Dynamic's control research fields
An important directions.
Ejector filler is the extremely important component part of liquid-propellant rocket engine, is directly related to spray, the atomization of propellant
And mixing, to influence the combustion stability and efficiency of combustion of engine.Due to small liquid rocket engine propellant
Flow is smaller, and head sizes are small, and nozzle quantity can be also restricted, therefore to ensure propellant constituent element good mixing and burn
There is very big difficulty entirely, this proposes the design of ejector filler extremely challenging.REA20-4 engines are used by more hairs
The ejector filler of tubule composition, it is ensured that propellant jet speed is low and is uniformly distributed;R-1E-3 engines use oxidant
The double elements unlike-impinging injector element mutually hit with fuel;RS-2101C engines use double elements and mutually hit single flow nozzle, nozzle edge
Same circumferential arrangement.However the ejector filler structure of above several schemes is complex, it is logical for small liquid rocket engine
It is poor with property.
Invention content
The purpose of the present invention is to provide a kind of mixing ejector filler and small liquid rocket engines, to solve the prior art
Middle ejector filler structure is complex, for the technical problem that small liquid rocket engine versatility is poor.
The present invention provides a kind of mixing ejector fillers, including shell, cover board and core;
Oxidant cavity and fuel cavity are provided in the shell, the oxidant cavity is arranged around the fuel cavity;It is described
Cover plate lid is set on the shell upper surface, for making the oxidant cavity seal;The oxidant cavity is used to contain oxidant,
The fuel cavity is for containing fuel;The core is set in the fuel cavity, for make the fuel in the fuel cavity into
Row eddy flow centrifuges spray.
Further, the core includes mounting portion, interconnecting piece, diversion division and eddy flow portion connected in sequence;The installation
Portion is boss mesa-shaped structure;Half-thread is provided on the outer wall of the interconnecting piece, the both ends of the interconnecting piece are taper contraction type
Structure;The diversion division is column structure;The eddy flow portion is pyramidal structure, and is provided with eddy flow slot in the eddy flow portion.
Further, the quantity of the eddy flow slot is three, and three eddy flow slots are uniformly distributed in the eddy flow portion,
And the type face of the eddy flow slot is curved surface.
Further, the vertebra apex angle in the eddy flow portion is 45 ° -60 °.
Further, the fuel cavity is in the form of a column;One end of the fuel cavity is provided with fuel inlet, and the fuel enters
Boss is provided at mouthful, the boss is for connecting fuel pressure inlet;The fuel cavity wall is provided with internal thread, the interior spiral shell
Line is adapted with the half-thread of the core interconnecting piece;The other end of the fuel cavity is provided with fuel nozzle, and the fuel
Frustum type contraction mouth is provided at nozzle, the eddy flow portion of the frustum type contraction mouth and the core matches.
Further, the oxidant cavity is annular in shape, and the side of the oxidant cavity offers oxidant inlet, the oxygen
Agent bottom of chamber portion is uniformly provided with multiple oxidant nozzles.
Further, igniter aperture is additionally provided in the shell, the igniter aperture is used to install igniter, and described
The center of igniter aperture and each oxidant nozzle is located on same circumference.
Further, the housing bottom edge is provided with seal boss, for being connect with combustion chamber sealing.
Further, multiple bolt positioning holes are provided on the shell, it is axial for being carried out to the mixing ejector filler
Positioning.
The present invention also provides a kind of small liquid rocket engines, including the mixing spray described in any of the above-described technical solution
Note device.
Compared with prior art, beneficial effects of the present invention are:
Mixing ejector filler provided by the invention includes shell, cover board and core;Oxidant cavity and fuel are provided in shell
Chamber, oxidant cavity is for containing oxidant, and fuel cavity is for containing fuel;Oxidant cavity is ring-type, and oxidant cavity is around combustion
Expect chamber setting.Preferably, fuel cavity and oxidant cavity arrange that fuel cavity is located at oxidant cavity center using coaxial-type.Cover plate lid
It is mutually welded on shell upper surface and with shell, and the shape of cover board is ring-type, and being adapted for oxidant cavity, for making
Oxidant cavity seals;Core is set in fuel cavity, and core can make the fuel in fuel cavity carry out eddy flow centrifugation spray.Shell
Lower face be panel, correspond on panel and offers fuel nozzle at fuel cavity, the fuel through the centrifugation of core eddy flow in fuel cavity
It is sprayed by fuel nozzle.It is corresponded on panel and offers oxidant nozzle at oxidant cavity, oxidant nozzle sprays for single flow oxygen
Mouth, the oxidant in oxidant cavity can be sprayed by oxidant nozzle.The mixing ejector filler of the present invention is by increasing fuel spray
Mouth core realizes the centrifugal spray of fuel, and spray mode is mixed with single flow oxygen nozzle composition, and atomizing effect is good, burning effect
Rate is higher.
The mixing ejector filler of the present invention is compact-sized, with strong applicability, can be used as most of miniature liquid rocket motor
The injection device of machine, and working pressure range is wider, adjusts propellant flow rate in a certain range, it can be with reliable and stable work
Make.
The present invention also provides a kind of small liquid rocket engines, including the mixing ejector filler.Due to described small
Type liquid-propellant rocket engine includes the mixing ejector filler, thus the small liquid rocket engine also has fuel and oxidation
Agent can realize reliable and stable spray, and reach preferable atomizing effect, the advantageous effect of high combustion efficiency.
Description of the drawings
It, below will be to specific in order to illustrate more clearly of the specific embodiment of the invention or technical solution in the prior art
Embodiment or attached drawing needed to be used in the description of the prior art are briefly described, it should be apparent that, in being described below
Attached drawing is some embodiments of the present invention, for those of ordinary skill in the art, before not making the creative labor
It puts, other drawings may also be obtained based on these drawings.
Fig. 1 is the structural schematic diagram of mixing ejector filler provided in an embodiment of the present invention;
Fig. 2 is another structural schematic diagram of mixing ejector filler provided in an embodiment of the present invention;
Fig. 3 is the overlooking structure diagram of mixing ejector filler provided in an embodiment of the present invention;
Fig. 4 is the schematic cross-sectional view of mixing ejector filler provided in an embodiment of the present invention;
Fig. 5 is the schematic cross-sectional view after the core assembly of mixing ejector filler provided in an embodiment of the present invention;
Fig. 6 is the concrete structure schematic diagram of core provided in an embodiment of the present invention;
Fig. 7 is the bottom substance schematic diagram of mixing ejector filler provided in an embodiment of the present invention.
Reference numeral:
1- shells, 11- igniter apertures, 12- seal bosses, 13- bolt positioning holes, 14- panels, 2- cover boards, 3- cores,
31- mounting portions, 32- interconnecting pieces, 33- diversion divisions, 34- eddy flows portion, 341- eddy flow slots, 4- oxidant cavities, 41- oxidant inlets,
42- oxidant nozzles, the pressure inlet of 43- oxidant supply systems, 5- fuel cavities, 51- fuel inlets, 52- fuel nozzles, 53-
The pressure inlet of fuel system.
Specific implementation mode
Technical scheme of the present invention is clearly and completely described below in conjunction with attached drawing, it is clear that described implementation
Example is a part of the embodiment of the present invention, instead of all the embodiments.
It usually here can be with a variety of different configurations with the component of the embodiment of the present invention shown described in attached drawing
To arrange and design.Therefore, the detailed description of the embodiment of the present invention to providing in the accompanying drawings is not intended to limit and wants below
The scope of the present invention of protection is sought, but is merely representative of the selected embodiment of the present invention.
Based on the embodiments of the present invention, those of ordinary skill in the art are obtained without making creative work
The every other embodiment obtained, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that term "center", "upper", "lower", "left", "right", "vertical",
The orientation or positional relationship of the instructions such as "horizontal", "inner", "outside" be based on the orientation or positional relationship shown in the drawings, merely to
Convenient for the description present invention and simplify description, do not indicate or imply the indicated device or element must have a particular orientation,
With specific azimuth configuration and operation, therefore it is not considered as limiting the invention.In addition, term " first ", " second ",
" third " is used for description purposes only, and is not understood to indicate or imply relative importance.
In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or be integrally connected;It can
Can also be electrical connection to be mechanical connection;It can be directly connected, can also indirectly connected through an intermediary, Ke Yishi
Connection inside two elements.For the ordinary skill in the art, above-mentioned term can be understood at this with concrete condition
Concrete meaning in invention.
Mixing ejector filler according to some embodiments of the invention and miniature liquid rocket hair are described referring to Fig. 1 to Fig. 7
Motivation.
The present invention provides a kind of mixing ejector fillers, as shown in Figures 1 to 5, including shell 1, cover board 2 and core 3;Shell
Oxidant cavity 4 and fuel cavity 5 are provided in 1, oxidant cavity 4 is arranged around fuel cavity 5;Cover board 2 is covered on 1 upper surface of shell
On, for making oxidant cavity 4 seal;Oxidant cavity 4 is for containing oxidant, and fuel cavity 5 is for containing fuel;Core 3 is arranged
In in fuel cavity 5, spray is centrifuged for making the fuel in fuel cavity 5 carry out eddy flow.
Mixing ejector filler provided by the invention includes shell 1, cover board 2 and core 3;4 He of oxidant cavity is provided in shell 1
Fuel cavity 5, oxidant cavity 4 is for containing oxidant, and fuel cavity 5 is for containing fuel;Oxidant cavity 4 is cyclic annular, and oxidant
Chamber 4 is arranged around fuel cavity 5.Preferably, fuel cavity 5 and oxidant cavity 4 arrange that fuel cavity 5 is located at oxidant using coaxial-type
4 center of chamber.Cover board 2 is covered on 1 upper surface of shell and is welded with 1 phase of shell, and the shape of cover board 2 is ring-type, with oxidation
Agent chamber 4 is adapted, for making oxidant cavity 4 seal;Core 3 is set in fuel cavity 5, and core 3 can make in fuel cavity 5
Fuel carries out eddy flow and centrifuges spray.The lower face of shell 1 is panel 14, is corresponded on panel 14 and offers fuel spray at fuel cavity 5
Mouth 52, the interior fuel through the centrifugation of 3 eddy flow of core of fuel cavity 5 are sprayed by fuel nozzle 52.It is corresponded on panel 14 at oxidant cavity 4
Oxidant nozzle 42 is offered, oxidant nozzle 42 is single flow oxygen nozzle, and the oxidant in oxidant cavity 4 can pass through oxidation
Agent nozzle 42 sprays.The mixing ejector filler of the present invention realizes the centrifugal spray of fuel by increasing by 52 core of fuel nozzle, 3 structure,
Spray mode is mixed with single flow oxygen nozzle composition, atomizing effect is good, and efficiency of combustion is higher.
In one embodiment of the invention, it is preferable that as shown in fig. 6, core 3 include mounting portion 31 connected in sequence,
Interconnecting piece 32, diversion division 33 and eddy flow portion 34;Mounting portion 31 is boss mesa-shaped structure;Half spiral shell is provided on the outer wall of interconnecting piece 32
The both ends of line, interconnecting piece 32 are taper contraction type structure;Diversion division 33 is column structure;Eddy flow portion 34 is pyramidal structure, and
Eddy flow slot 341 is provided in eddy flow portion 34.
In this embodiment, core 3 includes mounting portion 31 connected in sequence, interconnecting piece 32, diversion division 33 and eddy flow portion 34,
Mounting portion 31 is boss mesa-shaped structure, and diameter of section is less than interconnecting piece 32, is operated when being installed convenient for core 3.Interconnecting piece
Half-thread structure is provided on 32 outer wall, on the one hand the design of half-thread structure can make interconnecting piece 32 and 5 inner wall of fuel cavity
It is fixedly connected, the fuel in fuel cavity 5 can on the other hand passed through and smoothly flows downward to diversion division 33 and eddy flow portion 34;
Preferably, the half of 3 length of of length no more than core of interconnecting piece 32.The both ends of interconnecting piece 32 are taper contraction type structure, just
It is drained in fuel.Diversion division 33 is column structure, can the fuel that flowed down through interconnecting piece 32 be guided to eddy flow portion
At 34.Eddy flow portion 34 is pyramidal structure, offers eddy flow slot 341, curved surface spiral point of the eddy flow slot 341 along eddy flow portion 34 thereon
Cloth makes to enter the fuel in eddy flow slot 341 and realizes eddy flow, then realizes centrifugation spray by fuel nozzle 52, from fuel nozzle 52
The oxidant that the fuel that centrifugation sprays is sprayed with 42 direct current of ambient oxidant nozzle is hit, and fuel and oxidant is made to obtain very
Good atomization and mixing.In addition, because core 3 is threadedly coupled with fuel cavity 5, therefore core 3 is Demountable, installation
Convenient and processing is simple.
In one embodiment of the invention, it is preferable that as shown in fig. 6, the quantity of eddy flow slot 341 is three, three rotations
Chute 341 is uniformly distributed in eddy flow portion 34, and the type face of eddy flow slot 341 is curved surface.
In this embodiment, the quantity of eddy flow slot 341 is three, and three eddy flow slots 341 are uniformly distributed in eddy flow portion 34,
The rectangular cross-section of eddy flow slot 341 makes that a certain amount of fuel can be stored in eddy flow slot 341;The type face of eddy flow slot 341 is song
Face, i.e. 341 trough wall surface of eddy flow slot are a curved surface, and arc is excessively without corner angle so that the centrifugation spray of 341 fuel of eddy flow slot is more
Smoothness, spray effect are more preferable.
In one embodiment of the invention, it is preferable that as shown in fig. 6, the vertebra apex angle in eddy flow portion 34 is 45 ° -60 °.
In this embodiment, eddy flow portion 34 is pyramidal structure, and cone-apex angle is 45 ° -60 °;The front end in eddy flow portion 34 is not
Tip ensures that eddy flow slot 341 exports and just coincide with nozzle ports, and cannot be interfered between eddy flow slot 341.
In one embodiment of the invention, it is preferable that as shown in figure 4, fuel cavity 5 is in the form of a column;One end of fuel cavity 5 is set
It is equipped with fuel inlet 51, and is provided with boss at fuel inlet 51, boss is for connecting fuel pressure inlet;5 inner wall of fuel cavity is set
It is equipped with internal thread, internal thread is adapted with the half-thread of 3 interconnecting piece 32 of core;The other end of fuel cavity 5 is provided with fuel nozzle
52, and frustum type contraction mouth is provided at fuel nozzle 52, frustum type contraction mouth and the eddy flow portion 34 of core 3 match.
In this embodiment, fuel cavity 5 is in the form of a column, and the upper end is fuel inlet 51, and is provided at fuel inlet 51 convex
Platform, fuel cavity 5 is connected by boss with the pressure inlet 53 of fuel system, for supplying fuel into fuel cavity 5;Fuel
Internal thread compatible with 3 interconnecting piece of core, 32 half-thread is provided on the stage casing inner wall of chamber 5, for installing fuel nozzle 52
3 structure of core;The lower port of fuel cavity 5 is fuel nozzle 52, and frustum type contraction mouth, frustum type are provided at fuel nozzle 52
The eddy flow portion 34 of contraction mouth and core 3 matches.Preferably, it is provided with row sealing ring between the boss and pressure inlet of fuel cavity 5,
For being sealed to fuel cavity 5 and the junction of pressure inlet.In addition, 5 inner wall of fuel cavity offers pressure tap, surveyed for placing
Depressor is detected the fuel pressure in fuel cavity 5.
In one embodiment of the invention, it is preferable that as depicted in figs. 1 and 2, oxidant cavity 4 is annular in shape, oxidant cavity
4 side offers oxidant inlet 41;As shown in fig. 7,4 bottom of oxidant cavity is uniformly provided with multiple oxidant nozzles 42.
In this embodiment, oxidant cavity 4 is annular in shape, and side offers oxidant inlet 41, oxidant inlet 41 with
The pressure inlet 43 of oxidant supply system is connected, and oxidant is supplied into oxidant cavity 4, and oxidant is temporarily stored into oxidant cavity 4
It is interior.The bottom of oxidant cavity 4 is uniformly provided with multiple oxidant nozzles 42, i.e., on the panel 14 of 4 bottom of oxidant cavity uniformly
Multiple oxidant nozzles 42 are opened up, oxidant nozzle 42 is single flow nozzle, and the oxidant in oxidant cavity 4 is sprayed by oxidant
Mouth 42 carries out direct current spray, and is mixed with the fuel of eddy flow spray.Preferably, there are five oxidants for setting on spray panel 14
Nozzle 42, five oxidant nozzles 42 are uniformly distributed and the center of circle is located on same circumference, and fuel nozzle 52 is located at five oxidants
At the center of nozzle 42 so that the fuel sprayed from the centrifugation of central fuel nozzle 52 was sprayed with 42 direct current of ambient oxidant nozzle
Oxidant can be hit, and fuel and oxidant is made to be atomized and be mixed well.
In one embodiment of the invention, it is preferable that as shown in Figure 1, Figure 2 and shown in Fig. 7, igniting is additionally provided in shell 1
Device hole 11, igniter aperture 11 is for installing igniter, and the center of igniter aperture 11 and each oxidant nozzle 42 is positioned at same
On circumference.
In this embodiment, it is additionally provided with igniter aperture 11 on 1 bottom panel 14 of shell, 11 inner wall of igniter aperture is provided with
Screw thread, the spark plug for installing igniting.Preferably, igniter aperture 11 is located at oxidant nozzle 42 on same circumference, and
As shown in figure 4, the central axes of igniter aperture 11 are intersected with the central axes of fuel nozzle 52, i.e., the extending direction of fire hole it is opposite with
Fuel cavity 5 is obliquely installed, and the bottom end of fire hole compared to top closer to fuel cavity 5.
In this embodiment, it should be noted that as shown in Figure 1, for convenience of igniter aperture 11 setting and make can within
It is more reasonable that the structure of oxidant cavity 4, fuel cavity 5 and fire hole is laid, and the oxidant cavity 4 can be the cyclic annular knot of a connection
Structure, the boss that part of it cyclic structure is mounted igniter interrupt.
In one embodiment of the invention, it is preferable that as shown in Fig. 2, 1 bottom margin of shell is provided with seal boss
12, for being connect with combustion chamber sealing.
In this embodiment, 1 bottom margin of shell is provided with seal boss 12, and red copper pad can be installed at seal boss 12
Piece ensures the leakproofness that ejector filler is integrally connect with combustion chamber.
In one embodiment of the invention, it is preferable that as depicted in figs. 1 and 2, it is fixed that multiple bolts are provided on shell 1
Position hole 13, for carrying out axially position to mixing ejector filler.
In this embodiment, the bolt positioning hole 13 of multiple evaginations, multiple bolt positioning holes are provided on the outer wall of shell 1
13 are equidistantly uniformly arranged, and axially position can be carried out to ejector filler by the way that bolt positioning hole 13 is arranged.It should be noted that spiral shell
It needs to avoid its interference between 4 inlet connection mouth of oxidant cavity in the setting up procedure of bolt location hole 13.
The specific work process of mixing ejector filler of the present invention is:Oxidizing dose of entrance 41 feeds oxidant cavity 4, so
It is sprayed afterwards by oxidant nozzle 42, spray mode is single flow, and fuel feeds fuel cavity 5 from upper end fuel inlet 51, passes through
The cyclonic action of core 3, finally from central fuel nozzle 52 spray, spray mode be it is centrifugal, from central fuel nozzle 52 from
The oxidant that the fuel that the heart sprays is sprayed with 42 direct current of ambient oxidant nozzle is hit, and fuel and oxidant is made to obtain very well
Atomization and mixing.
The present invention also provides a kind of small liquid rocket engines, including the mixing spray described in any of the above-described embodiment
Device.
In this embodiment, since the small liquid rocket engine includes the mixing spray described in any of the above-described embodiment
Device is noted, thus with whole advantageous effects of the mixing ejector filler, this is no longer going to repeat them.
Finally it should be noted that:The above embodiments are only used to illustrate the technical solution of the present invention., rather than its limitations;To the greatest extent
Present invention has been described in detail with reference to the aforementioned embodiments for pipe, it will be understood by those of ordinary skill in the art that:Its according to
So can with technical scheme described in the above embodiments is modified, either to which part or all technical features into
Row equivalent replacement;And these modifications or replacements, various embodiments of the present invention technology that it does not separate the essence of the corresponding technical solution
The range of scheme.
Claims (10)
1. a kind of mixing ejector filler, which is characterized in that including shell, cover board and core;
Oxidant cavity and fuel cavity are provided in the shell, the oxidant cavity is arranged around the fuel cavity;The cover board
It is covered on the shell upper surface, for making the oxidant cavity seal;The oxidant cavity is described for containing oxidant
Fuel cavity is for containing fuel;The core is set in the fuel cavity, for making the fuel in the fuel cavity be revolved
It wanders about as a refugee heart spray.
2. mixing ejector filler according to claim 1, which is characterized in that the core include mounting portion connected in sequence,
Interconnecting piece, diversion division and eddy flow portion;The mounting portion is boss mesa-shaped structure;Half spiral shell is provided on the outer wall of the interconnecting piece
The both ends of line, the interconnecting piece are taper contraction type structure;The diversion division is column structure;The eddy flow portion is pyramidal knot
Structure, and it is provided with eddy flow slot in the eddy flow portion.
3. mixing ejector filler according to claim 2, which is characterized in that the quantity of the eddy flow slot is three, three institutes
It states eddy flow slot to be uniformly distributed in the eddy flow portion, and the type face of the eddy flow slot is curved surface.
4. mixing ejector filler according to claim 2, which is characterized in that the vertebra apex angle in the eddy flow portion is 45 ° -60 °.
5. ejector filler according to claim 2, which is characterized in that the fuel cavity is in the form of a column;One end of the fuel cavity
It is provided with fuel inlet, and is provided with boss at the fuel inlet, the boss is for connecting fuel pressure inlet;The fuel
Cavity wall is provided with internal thread, and the internal thread is adapted with the half-thread of the core interconnecting piece;The fuel cavity it is another
End is provided with fuel nozzle, and frustum type contraction mouth is provided at the fuel nozzle, the frustum type contraction mouth and the core
The eddy flow portion of body matches.
6. mixing ejector filler according to claim 1, which is characterized in that the oxidant cavity is annular in shape, the oxidant
The side of chamber offers oxidant inlet, and the oxidant cavity bottom is uniformly provided with multiple oxidant nozzles.
7. mixing ejector filler according to claim 6, which is characterized in that be additionally provided with igniter aperture, institute in the shell
Igniter aperture is stated for installing igniter, and the center of the igniter aperture and each oxidant nozzle is located at same circumference
On.
8. mixing ejector filler according to claim 1, which is characterized in that it is convex that the housing bottom edge is provided with sealing
Platform, for being connect with combustion chamber sealing.
9. mixing ejector filler according to claim 1, which is characterized in that be provided with multiple bolt positioning on the shell
Hole, for carrying out axially position to the mixing ejector filler.
10. a kind of small liquid rocket engine, which is characterized in that including the mixing spray described in any one of claim 1 to 9
Note device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810556674.8A CN108691692A (en) | 2018-05-31 | 2018-05-31 | Mix ejector filler and small liquid rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810556674.8A CN108691692A (en) | 2018-05-31 | 2018-05-31 | Mix ejector filler and small liquid rocket engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108691692A true CN108691692A (en) | 2018-10-23 |
Family
ID=63848603
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810556674.8A Pending CN108691692A (en) | 2018-05-31 | 2018-05-31 | Mix ejector filler and small liquid rocket engine |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109578167A (en) * | 2018-11-21 | 2019-04-05 | 中国人民解放军国防科技大学 | Engine injector and engine with same |
| CN110513719A (en) * | 2019-08-12 | 2019-11-29 | 西安航天动力研究所 | A kind of gas oxygen/gas methane torch lighter |
| CN110595792A (en) * | 2019-08-13 | 2019-12-20 | 西北工业大学 | Simulation device for hypersonic/subsonic combustion thermal environment of combined engine and use method |
| CN111852691A (en) * | 2020-08-13 | 2020-10-30 | 北京星际荣耀空间科技有限公司 | Integrated double-component injector, manufacturing method thereof and aerospace equipment |
| 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 |
| CN114215660A (en) * | 2021-11-16 | 2022-03-22 | 北京航天动力研究所 | High-efficient stable injector |
| CN115263604A (en) * | 2022-06-22 | 2022-11-01 | 北京控制工程研究所 | Hole-aligning mutual-striking injector applied to light quick-response two-component engine |
| CN109798202B (en) * | 2019-04-04 | 2023-08-22 | 北京宇航推进科技有限公司 | Liquid rocket engine injector integrating electric igniter |
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|---|---|---|---|---|
| CN103867340A (en) * | 2012-12-12 | 2014-06-18 | 中国人民解放军国防科学技术大学 | Dual-rotational-flow inspirator |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103867340A (en) * | 2012-12-12 | 2014-06-18 | 中国人民解放军国防科学技术大学 | Dual-rotational-flow inspirator |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109578167B (en) * | 2018-11-21 | 2019-12-13 | 中国人民解放军国防科技大学 | Engine injector and engine with same |
| CN109578167A (en) * | 2018-11-21 | 2019-04-05 | 中国人民解放军国防科技大学 | Engine injector and engine with same |
| CN109798202B (en) * | 2019-04-04 | 2023-08-22 | 北京宇航推进科技有限公司 | Liquid rocket engine injector integrating electric igniter |
| CN110513719B (en) * | 2019-08-12 | 2021-01-12 | 西安航天动力研究所 | Oxygen/methane torch igniter |
| CN110513719A (en) * | 2019-08-12 | 2019-11-29 | 西安航天动力研究所 | A kind of gas oxygen/gas methane torch lighter |
| CN110595792A (en) * | 2019-08-13 | 2019-12-20 | 西北工业大学 | Simulation device for hypersonic/subsonic combustion thermal environment of combined engine and use method |
| CN110595792B (en) * | 2019-08-13 | 2020-06-30 | 西北工业大学 | Simulation device for hypersonic/subsonic combustion thermal environment of combined engine |
| CN111852691A (en) * | 2020-08-13 | 2020-10-30 | 北京星际荣耀空间科技有限公司 | Integrated double-component injector, manufacturing method thereof and aerospace equipment |
| CN111852691B (en) * | 2020-08-13 | 2024-02-06 | 北京星际荣耀空间科技股份有限公司 | Integrated double-component injector, manufacturing method thereof and aerospace equipment |
| 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 |
| CN114215660A (en) * | 2021-11-16 | 2022-03-22 | 北京航天动力研究所 | High-efficient stable injector |
| CN114215660B (en) * | 2021-11-16 | 2023-07-28 | 北京航天动力研究所 | High-efficient stable injector |
| CN115263604A (en) * | 2022-06-22 | 2022-11-01 | 北京控制工程研究所 | Hole-aligning mutual-striking injector applied to light quick-response two-component engine |
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Application publication date: 20181023 |