CN207598369U - A kind of precombustion chamber ejector filler structure - Google Patents
A kind of precombustion chamber ejector filler structure Download PDFInfo
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- CN207598369U CN207598369U CN201721626500.1U CN201721626500U CN207598369U CN 207598369 U CN207598369 U CN 207598369U CN 201721626500 U CN201721626500 U CN 201721626500U CN 207598369 U CN207598369 U CN 207598369U
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- hole
- oxidant
- nozzle
- ejector filler
- single flow
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Abstract
The utility model discloses a kind of precombustion chamber ejector filler structures, including ejector filler matrix, a bottom, single flow oxidant nozzle, single flow fuel nozzle and oxidant swirler, the utility model ejector filler outmost turns use single flow fuel nozzle+single flow oxidant nozzle, help to improve the compatibility between nozzle and body portion wall surface, improve body portion wall surface working environment, improve the reliability in body portion；In addition to outmost turns, remaining nozzle of ejector filler is helped to improve precombustion chamber efficiency of combustion, is improved precombustion chamber outlet temperature field uniformity using single flow fuel nozzle+oxidant swirler；The utility model precombustion chamber ejector filler uses two kinds of oxidant nozzle arrangements, and the release for helping avoid burning capacity is excessively concentrated, and reduces the possibility that somatic sypermutation occurs.
Description
Technical field
The utility model is related to a kind of precombustion chamber ejector filler structure, available for liquid-propellant rocket engine field.
Background technology
Important component of the precombustion chamber as liquid-propellant rocket engine, effect are to provide high-temperature fuel gas for driving turbine pump.
Key component of the ejector filler as precombustion chamber, effect be by the fuel of certain mixing ratio and oxidant be injected in combustion chamber into
Row blending burning, and then generate high-temperature fuel gas.It is uniform that the quality of ejector filler design is directly related to efficiency of combustion, outlet temperature field
The precombustion chambers key characteristics such as property, combustion stability.
The bleed type of liquid-propellant rocket engine precombustion chamber ejector filler generally use is as follows：Coaxial eccentricity nozzle (single flow
Fuel nozzle+oxidant swirler), coaxial DC nozzle (single flow fuel nozzle+single flow oxidant nozzle), it is double from
Heart nozzle (fuel swirler+oxidant swirler).At present, liquid-propellant rocket engine precombustion chamber ejector filler is usually adopted
With same type of nozzle.For coaxial eccentricity nozzle, which can make fuel carry out quick blending burning, combustion with oxidant
Burn efficient, while the length of flame is short, helps to improve precombustion chamber outlet temperature field uniformity, but compatible between body portion wall surface
Poor, the easy ablation wall surface of property；For coaxial DC nozzle, the nozzle arrangements are simple, good with body portion wall surface compatibility, but the length of flame
It is longer, it is not easy to obtain uniform combustor exit temperature field；For double swirl atomizers, it is mainly used for oxygen kerosene engine, it should
The blending that nozzle contributes between fuel and oxidant is burnt, improve efficiency of combustion, but with body portion wall surface poor compatibility, body portion wall surface
It needs using corresponding safeguard procedures.Meanwhile with the gradual increase of liquid-propellant rocket engine thrust, volume, the pressure of precombustion chamber
Power, flow have significant increase, and the possibility that combustion instability occurs greatly increases.In the case, if precombustion chamber is sprayed
Device is noted using same type of nozzle, burning capacity release is excessively concentrated, and also easily leads to the generation of combustion instability phenomenon.
Utility model content
The technology of the utility model solves the problems, such as：In order to overcome the deficiencies of the prior art, a kind of precombustion chamber ejector filler is provided
Structure by optimizing arrangement of nozzles mode, improves precombustion chamber efficiency of combustion, while contribute to improvement precombustion chamber outlet temperature field equal
Even property and precombustion chamber combustion stability.
The technical solution of the utility model is：
A kind of precombustion chamber ejector filler structure, including ejector filler matrix, a bottom, single flow oxidant nozzle, single flow fuel
Nozzle and oxidant swirler, a bottom are placed in ejector filler base bottom, form fuel cavity, ejector filler matrix side therebetween
Wall is uniformly provided with the radial hole of logical fuel with the corresponding position of fuel cavity；The top of ejector filler matrix is oxidant cavity；Spray
The through-hole A for installing oxidant nozzle is provided on device matrix, through-hole B, through-hole B for installing fuel nozzle are provided on a bottom
It is corresponding with through-hole location A；
Single flow oxidant nozzle is provided with the through-hole C of logical oxidant in an axial direction；
Oxidant swirler is provided with the blind hole of logical oxidant in an axial direction, is provided with and blind hole on the side wall for blocking upper end
Tangent tangential hole, tangential hole are circumferentially evenly arranged；
Single flow fuel nozzle is provided with the through-hole D of logical fuel in an axial direction, is provided on through-hole D side walls and is circumferentially evenly arranged
Logical fuel through-hole E；
Oxidant nozzle and single flow fuel nozzle coaxial cooperation, throttle clearance of the gap for fuel therebetween, directly
Streaming oxidant nozzle is installed on the outermost ring through hole A of ejector filler matrix, and centrifugation is installed on other through-holes A of ejector filler matrix
Formula oxidant nozzle, single flow fuel nozzle are installed on the through-hole B at a bottom；
An oxidant part in the oxidant cavity on ejector filler matrix top passes through the through-hole C on single flow oxidant nozzle
Combustion chamber is directly entered, another part enters combustion chamber by the tangential hole on oxidant swirler and blind hole；Fuel cavity
In fuel combustion chamber is entered by the through-hole E on single flow fuel nozzle and throttle clearance.
The through-hole upper end that single flow oxidant nozzle leads to oxidant is throttle orifice, and lower end is deflector hole, and deflector hole internal diameter is big
In throttle orifice internal diameter, water conservancy diversion hole length is more than throttling hole length.
Throttle clearance is not more than other throttle clearances between outmost turns oxidant nozzle and single flow fuel nozzle.
Through-hole E on single flow fuel nozzle is arranged for 1-3.
Tangential hole on oxidant swirler is arranged for 1-3.
Often the through-hole A on circle is uniformly distributed circumferentially, the radially equidistant distributions of through-hole A between often enclosing and often enclosing.
The utility model compared with prior art the advantages of be：
(1) the utility model ejector filler outmost turns use single flow fuel nozzle+single flow oxidant nozzle, help to carry
Compatibility between high nozzle and body portion wall surface improves body portion wall surface working environment, improves the reliability in body portion；
(2) for the utility model in addition to outmost turns, remaining nozzle of ejector filler uses single flow fuel nozzle+centrifugal type oxygen agent
Nozzle helps to improve precombustion chamber efficiency of combustion, improves precombustion chamber outlet temperature field uniformity；
(3) the utility model precombustion chamber ejector filler uses two kinds of oxidant nozzle arrangements, helps avoid burning capacity
Release is excessively concentrated, and reduces the possibility of the generation of somatic sypermutation.
Description of the drawings
Fig. 1 is the utility model structural front view；
Fig. 2 is the utility model structure top view；
Fig. 3 is the utility model ejector filler basal body structure schematic diagram；
Fig. 4 is one bottom structure schematic diagram of the utility model；
Fig. 5, Fig. 6 are the utility model nozzle arrangements schematic diagram.
Specific embodiment
The utility model is described in detail referring to attached drawing.
A kind of precombustion chamber ejector filler structure, as shown in Figure 1 and Figure 2, including ejector filler matrix 1, a bottom 2, single flow oxidant
Nozzle 3, single flow fuel nozzle 4 and oxidant swirler 5, a bottom 2 are placed in 1 bottom of ejector filler matrix, therebetween shape
Into fuel cavity, 1 side wall of ejector filler matrix is uniformly provided with the radial hole of logical fuel with the corresponding position of fuel cavity, as shown in Figure 3；
The top of ejector filler matrix 1 is oxidant cavity；The through-hole A for installing oxidant nozzle, a bottom 2 are provided on ejector filler matrix 1
On be provided with through-hole B for installing fuel nozzle, as shown in figure 4, through-hole B is corresponding with through-hole location A；The often through-hole A on circle
It is uniformly distributed circumferentially, the radially equidistant distributions of through-hole A between often enclosing and often enclosing.
As shown in figure 5, single flow oxidant nozzle 3 is provided with the through-hole C of logical oxidant in an axial direction；Single flow oxidant nozzle
The through-hole upper end of 3 logical oxidants is throttle orifice, and lower end is deflector hole, and deflector hole internal diameter is more than throttle orifice internal diameter, water conservancy diversion hole length
More than throttling hole length.
As shown in fig. 6, oxidant swirler 5 is provided with the blind hole of logical oxidant in an axial direction, in the side wall for blocking upper end
On be provided with the tangential hole tangent with blind hole, tangential hole is circumferentially evenly arranged；Tangential hole on oxidant swirler 5 is 1-
3 rows.
Single flow fuel nozzle 4 is provided with the through-hole D of logical fuel in an axial direction, and circumferentially uniform cloth is provided on through-hole D side walls
The through-hole E for the logical fuel put, the through-hole E on single flow fuel nozzle 4 are 1-3 rows.
Oxidant nozzle and 4 coaxial cooperation of single flow fuel nozzle, throttle clearance of the gap for fuel therebetween, directly
Streaming oxidant nozzle 3 is installed on the outermost ring through hole A of ejector filler matrix 1, is installed on other through-holes A of ejector filler matrix 1
Oxidant swirler 5, single flow fuel nozzle 4 are installed on the through-hole B at a bottom 2；
An oxidant part in the oxidant cavity on 1 top of ejector filler matrix passes through logical on single flow oxidant nozzle 3
Hole C is directly entered combustion chamber, and another part enters combustion chamber by the tangential hole on oxidant swirler 5 and blind hole；Combustion
Fuel in material chamber enters combustion chamber, the spray of outmost turns oxidant by the through-hole E on single flow fuel nozzle 4 and throttle clearance
Throttle clearance is not more than other throttle clearances between mouth and single flow fuel nozzle 4.
A kind of novel precombustion chamber ejector filler structure specific embodiment is as follows：First by single flow fuel nozzle 4
It is assembled with single flow oxidant nozzle 3, oxidant swirler 5, above-mentioned assembly is next mounted on spray again
On device matrix 1, then a bottom 2 is installed and weld itself and ejector filler matrix 1, finally again carried out the ejector filler of assembling whole
Body is brazed.
A kind of novel precombustion chamber ejector filler arrangement works mode is as follows：Oxidation above ejector filler matrix 1
Agent enters combustion chamber by single flow oxidant nozzle 3 and oxidant swirler 5, positioned at 1 and one bottom 2 of ejector filler matrix it
Between fuel by single flow fuel nozzle 4 enter combustion chamber.
The advantages of the utility model is using single flow nozzle and good body portion wall surface compatibility, ejector filler outmost turns use direct current
Formula fuel nozzle+single flow oxidant nozzle improves the working environment of body portion wall surface, improves the reliability in body portion；
The utility model blends the characteristics of performance is good using rotarytype injector atomization, in addition to outmost turns, remaining spray of ejector filler
Mouth uses single flow fuel nozzle+oxidant swirler, contributes to the raising of precombustion chamber efficiency of combustion and outlet temperature field
The improvement of uniformity.
The characteristics of the utility model utilizes coaxial DC nozzle different with coaxial eccentricity nozzle flame length, ejector filler use
Two kinds of oxidant nozzle arrangements help avoid energy release when fuel burns with oxidant and excessively concentrate, and reduction is burnt
The possibility of wild effect.
The content not being described in detail in the utility model specification belongs to the known technology of those skilled in the art.
Claims (6)
1. a kind of precombustion chamber ejector filler structure, which is characterized in that including ejector filler matrix (1), a bottom (2), single flow oxidant
Nozzle (3), single flow fuel nozzle (4) and oxidant swirler (5), a bottom (2) are placed in ejector filler matrix (1) bottom,
Therebetween fuel cavity is formed, ejector filler matrix (1) side wall is uniformly provided with the radial direction of logical fuel with the corresponding position of fuel cavity
Hole；The top of ejector filler matrix (1) is oxidant cavity；The through-hole for installing oxidant nozzle is provided on ejector filler matrix (1)
A, is provided with the through-hole B for installing fuel nozzle on a bottom (2), through-hole B is corresponding with through-hole location A；
Single flow oxidant nozzle (3) is provided with the through-hole C of logical oxidant in an axial direction；
Oxidant swirler (5) is provided with the blind hole of logical oxidant in an axial direction, is provided with and blind hole on the side wall for blocking upper end
Tangent tangential hole, tangential hole are circumferentially evenly arranged；
Single flow fuel nozzle (4) is provided with the through-hole D of logical fuel in an axial direction, is provided on through-hole D side walls and is circumferentially evenly arranged
Logical fuel through-hole E；
Oxidant nozzle and single flow fuel nozzle (4) coaxial cooperation, throttle clearance of the gap for fuel therebetween, direct current
Formula oxidant nozzle (3) is installed on the outermost ring through hole A of ejector filler matrix (1), on other through-holes A of ejector filler matrix (1)
Oxidant swirler (5) is installed, single flow fuel nozzle (4) is installed on the through-hole B at a bottom (2)；
An oxidant part in the oxidant cavity on ejector filler matrix (1) top passes through logical on single flow oxidant nozzle (3)
Hole C is directly entered combustion chamber, and another part enters combustion chamber by the tangential hole on oxidant swirler (5) and blind hole；
Fuel in fuel cavity enters combustion chamber by the through-hole E on single flow fuel nozzle (4) and throttle clearance.
2. a kind of precombustion chamber ejector filler structure as described in claim 1, which is characterized in that single flow oxidant nozzle (3) is logical
The through-hole upper end of oxidant is throttle orifice, and lower end is deflector hole, and deflector hole internal diameter is more than throttle orifice internal diameter, and water conservancy diversion hole length is more than
Throttle hole length.
3. a kind of precombustion chamber ejector filler structure as described in claim 1, which is characterized in that outmost turns oxidant nozzle and direct current
Throttle clearance is not more than other throttle clearances between formula fuel nozzle (4).
4. a kind of precombustion chamber ejector filler structure as described in claim 1, which is characterized in that on single flow fuel nozzle (4)
Through-hole E is arranged for 1-3.
5. a kind of precombustion chamber ejector filler structure as described in claim 1, which is characterized in that on oxidant swirler (5)
Tangential hole be 1-3 row.
6. a kind of precombustion chamber ejector filler structure as described in claim 1, which is characterized in that the through-hole A often on circle is circumferentially equal
Even distribution, the radially equidistant distributions of through-hole A between often enclosing and often enclosing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721626500.1U CN207598369U (en) | 2017-11-29 | 2017-11-29 | A kind of precombustion chamber ejector filler structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721626500.1U CN207598369U (en) | 2017-11-29 | 2017-11-29 | A kind of precombustion chamber ejector filler structure |
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| Publication Number | Publication Date |
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| CN207598369U true CN207598369U (en) | 2018-07-10 |
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|---|---|---|---|
| CN201721626500.1U Active CN207598369U (en) | 2017-11-29 | 2017-11-29 | A kind of precombustion chamber ejector filler structure |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107939551A (en) * | 2017-11-29 | 2018-04-20 | 北京航天动力研究所 | A kind of precombustion chamber ejector filler structure |
| CN114280219A (en) * | 2021-12-29 | 2022-04-05 | 中国人民解放军战略支援部队航天工程大学 | Multifunctional mixing combustion experimental device |
| 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 |
-
2017
- 2017-11-29 CN CN201721626500.1U patent/CN207598369U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107939551A (en) * | 2017-11-29 | 2018-04-20 | 北京航天动力研究所 | A kind of precombustion chamber ejector filler structure |
| CN107939551B (en) * | 2017-11-29 | 2024-02-09 | 北京航天动力研究所 | Pre-combustion chamber injector structure |
| 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 |
| CN114280219A (en) * | 2021-12-29 | 2022-04-05 | 中国人民解放军战略支援部队航天工程大学 | Multifunctional mixing combustion experimental device |
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