CN113202656A - Guide plate and injector capable of improving propellant filling synchronism - Google Patents
Guide plate and injector capable of improving propellant filling synchronism Download PDFInfo
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- CN113202656A CN113202656A CN202110592285.2A CN202110592285A CN113202656A CN 113202656 A CN113202656 A CN 113202656A CN 202110592285 A CN202110592285 A CN 202110592285A CN 113202656 A CN113202656 A CN 113202656A
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- fuel
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- injector
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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)
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- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fuel-Injection Apparatus (AREA)
Abstract
The invention relates to a guide plate and an injector capable of improving propellant filling synchronism, and aims to solve the technical problems that the injector filling synchronism is reduced and the working stability is reduced during starting due to the fact that fuel filling is unidirectional and the stroke is long by a guide plate of a fuel cavity of the existing injector. The guide plate comprises a guide plate body, a central hole arranged in the central area of the guide plate body, a plurality of side area branch holes which are uniformly distributed in the edge area of the guide plate body on the circumference, and a plurality of nozzle mounting holes, wherein the ratio of the total area of the side area branch holes to the area of the central hole is 20-30%; the injector comprises an injector face, a plurality of nozzles arranged on the injector face, a fuel cavity and the guide plate, wherein the guide plate is installed in the fuel cavity and divides the fuel cavity into a fuel upper cavity and a fuel lower cavity, and the plurality of nozzles respectively penetrate through the fuel cavity and penetrate through corresponding nozzle installation holes in the fuel cavity. The present invention can compromise injector face cooling and fuel fill rates.
Description
Technical Field
The invention relates to a guide plate and an injector capable of improving the filling synchronism of a liquid propellant, wherein the guide plate is applied to a fuel cavity of the injector, and the injector is applied to a thrust chamber or a fuel gas generator of an engine, in particular to a thrust chamber of a liquid rocket engine with higher requirement on the filling synchronism of the propellant.
Background
Liquid rocket engine thrust chamber injectors are the primary components for atomizing and mixing liquid propellant components. The operating conditions of the injector determine to a large extent the completeness of combustion of the propellant and the stability of the working process of the thrust chamber. On one hand, the synchronism of the filling process of the liquid propellant in the injector influences the ignition quality of the thrust chamber and the working stability during starting; on the other hand, the injector face is close to the highest temperature position of the thrust chamber, the thermal environment is very severe, and cooling needs to be enhanced to ensure the working reliability. Therefore, the improvement of the filling synchronism of the injector of the thrust chamber, the cooling of the injector surface of the thrust chamber and the improvement of the thermal protection safety margin are important problems to be faced in the development of the engine.
In order to solve the problem of cooling the injector surface of the thrust chamber and improve the thermal protection safety margin of the injector surface, flow deflectors are usually arranged in the thrust chamber and the injector fuel cavity of the gas generator, the fuel cavity is divided into an upper part and a lower part through the flow deflectors, and the fuel can keep high flow speed when flowing through a lower cavity with small fuel volume so as to fully cool the injector surface. Then flows into the fuel upper cavity from the central hole of the guide plate, fills the fuel upper cavity and enters the nozzle. Various thrust chambers and gas generators at home and abroad adopt the injector of the guide plate. However, with the adoption of the guide plate, the fuel filling of the fuel cavity of the injector is unidirectional, the stroke is long, the filling synchronism of the injector is reduced, and the working stability during starting is reduced.
Disclosure of Invention
The invention aims to solve the technical problems that the filling synchronism of an injector is reduced and the working stability during starting is reduced due to the fact that fuel filling is unidirectional and the stroke of the existing injector fuel cavity guide plate is long, and provides a guide plate and an injector capable of improving the filling synchronism of a propellant.
In order to achieve the purpose, the invention adopts the technical scheme that:
a flow guide plate capable of improving propellant filling synchronism is characterized in that:
the guide plate comprises a guide plate body, a central hole 2 arranged in the central area of the guide plate body, a plurality of side area branch holes 3 uniformly distributed on the edge area of the guide plate body in the circumference, and a plurality of nozzle mounting holes 4 arranged in the area between the central hole 2 and the side area branch holes 3;
the nozzle mounting holes 4 correspond to the nozzles 5 of the injector face 10 one by one, and the nozzles 5 penetrate through the nozzle mounting holes 4;
the total area of the plurality of edge area distribution holes 3 is smaller than the area of the central hole 2.
Further, the total area of the plurality of side area branch holes 3 accounts for 20% -30% of the area of the central hole 2, and the cooling requirement of the injector surface and the filling speed of the fuel cavity 6 can be considered.
Further, the total area of the plurality of edge region flow holes 3 occupies 25% of the area of the central hole 2.
Further, the guide plate body is of a disc-shaped stamping structure.
Further, the number of the nozzle mounting holes 4 is not less than 4, the number of the innermost nozzle mounting holes 4 is 12, and the number of the innermost nozzle mounting holes is increased by 6 from inside to outside.
Further, the number of the side area flow holes 3 is the same as that of the outermost nozzle mounting holes 4, so that the distribution uniformity and consistency of a fuel cavity flow field can be ensured to the greatest extent.
The invention also provides an injector, which is characterized in that:
the system comprises an injector face 10, a plurality of nozzles 5 arranged on the injector face 10, a fuel cavity 6 arranged above the injector face 10, and the guide plate 1 capable of improving the propellant filling synchronism;
the guide plate 1 is arranged in the fuel cavity 6 and divides the fuel cavity 6 into a fuel upper cavity 7 and a fuel lower cavity 8;
the upper fuel cavity 7 and the lower fuel cavity 8 are communicated through a plurality of side zone branch holes 3 and a central hole 2 of the guide plate 1, so that fuel can enter the upper fuel cavity 7 from the lower fuel cavity 8 through the plurality of side zone branch holes 3 and the central hole 2;
the plurality of nozzles 5 respectively penetrate the fuel chamber 6, and the plurality of nozzles 5 penetrate the corresponding nozzle mounting holes 4 in the fuel chamber 6.
Furthermore, the volume ratio of the lower fuel cavity 8 to the upper fuel cavity 7 is 0.2-0.6, so that the fuel keeps a certain flow speed in the lower fuel cavity 8 to meet the cooling requirement of the injector surface.
Further, the volume ratio of the lower fuel cavity 8 to the upper fuel cavity 7 is 0.42.
Further, the fuel in the fuel cavity 6 is space kerosene.
The invention has the beneficial effects that:
1) the guide plate capable of improving the propellant filling synchronism is provided with the side area branch hole and the central hole at the same time, and is used in the fuel cavity of the injector, so that the filling mode of the fuel cavity of the injector is changed from one-way filling to two-way filling, the filling speed of the fuel cavity is improved by 40%, the filling synchronism of an engine thrust chamber and a gas generator injector is improved, and the working stability of the engine during starting is further improved.
2) The injector of the invention divides the fuel in proportion by changing the ratio of the total area of the side area flow holes of the guide plate in the fuel cavity of the injector to the area of the central hole of the guide plate, on one hand, the flow speed of the fuel in the lower fuel cavity is adjusted, so that the fuel flow speed can meet the cooling requirement of the injector surface, on the other hand, the time for the fuel to flow into the upper fuel cavity from the lower fuel cavity can be shortened, and the filling speed of the fuel cavity is improved.
3) The guide plate capable of improving the propellant filling synchronism adopts a multi-hole stamping disc-shaped structure, and has the advantages of simple structure, good manufacturability, high reliability and lower production cost.
4) The invention can improve the number of the side area flow holes of the guide plate with propellant filling synchronization, is the same as the number of the nozzle holes of the outermost circle, and can ensure the uniformity of the flow field distribution of the fuel cavity to the maximum extent and the consistency when the guide plate is not arranged.
5) The guide plate capable of improving the propellant filling synchronism adopts a porous structure, and has small influence on the flow resistance of a fuel path.
Drawings
FIG. 1 is a schematic view of a deflector according to the present invention for enhancing propellant filling synchronization;
FIG. 2 is a cross-sectional view taken along line A-A of FIG. 1;
FIG. 3 is a schematic view of the installation position of the deflector in the fuel cavity of the injector of the thrust chamber for improving the synchronism of propellant filling.
Description of reference numerals:
the fuel injector comprises a guide plate 1, a central hole 2, a side area flow hole 3, a nozzle mounting hole 4, a nozzle 5, a fuel cavity 6, a fuel upper cavity 7, a fuel lower cavity 8, a fuel inlet 9 and an injector surface 10.
Detailed Description
In order to more clearly explain the technical solution of the present invention, the following detailed description of the present invention is made with reference to the accompanying drawings and specific examples.
The guide plate capable of improving propellant filling synchronism of the invention is shown in fig. 1 and fig. 2, and the guide plate 1 comprises a guide plate body, a central hole 2, a side area flow hole 3 and a nozzle mounting hole 4. Wherein, the guide plate body is porous punching press dish type structure, and the central zone of guide plate body sets up centre bore 2, and the border region evenly sets up a plurality of limit district flow holes 3 along the circumference, and all the other regions set up a plurality of nozzle mounting holes 4. The nozzle mounting holes 4 are arranged into 4 layers, the number of the innermost nozzle mounting holes 4 is 12, the number of the innermost nozzle mounting holes is increased by 6 in sequence from inside to outside, and the number of the edge zone branch holes 3 is 30 and is the same as that of the outermost nozzle mounting holes 4. The baffle 1 can be used in the thrust chamber of a liquid rocket engine or in the fuel chamber 6 of a gas generator injector.
Fig. 3 is a schematic view of the installation position of the guide plate 1 in the fuel cavity 6 of the thrust chamber, the guide plate 1 is located in the fuel cavity 6 and divides the fuel cavity 6 into an upper fuel cavity 7 and a lower fuel cavity 8, the nozzle installation hole 4 is coaxially arranged with the nozzle 5 of the injector face 10, and the nozzle installation hole 4 is used for the nozzle 5 to pass through. Fuel (liquid propellant, in this embodiment, space kerosene) enters the lower fuel cavity 8 from a fuel inlet 9 at the lower side surface of the cylindrical fuel cavity 6, part of the fuel flows through the lower fuel cavity 8 and then flows into the upper fuel cavity 7 from the central hole 2, the other part of the fuel directly flows into the upper fuel cavity 7 from the side branch hole 3, and the fuel simultaneously fills the fuel cavity 6 from two directions respectively, so that the filling time is shortened, and the filling synchronism is improved.
The total area of the plurality of edge area flow holes 3 in the guide plate 1 is smaller than the area of the central hole 2, and the ratio of the total area of the edge area flow holes 3 to the area of the central hole 2 can be determined according to the flow speed of specific fuel in the fuel cavity 6 and the filling speed of the fuel in the fuel cavity 6. When the ratio of the total area of the side area branch holes 3 to the area of the central hole 2 is increased, the flow speed of the fuel in the lower fuel cavity 8 is reduced, and the reasonable area ratio of the central hole 2 to the side area branch holes 3 is selected to divide the fuel in proportion, so that the fuel in the lower fuel cavity 8 keeps a certain flow speed to meet the cooling requirement of the injector face 10, the time for the fuel to flow into the upper fuel cavity 7 from the lower fuel cavity 8 is shortened due to the arrangement of the side area branch holes 3, the filling speed of the fuel cavity 6 is increased, and the cooling of the injector face and the synchronism of injector filling can be considered. According to the structure of the guide plate 1, the specific working conditions of the injector and the fuel cavity 6, the value range of the ratio of the total area of the side area branch holes 3 in the guide plate 1 to the area of the central hole 2 is determined to be 20% -30%, and in the embodiment, the total area of the side area branch holes 3 is 25% of the area of the central hole 2.
In addition, the flow velocity of the fuel in the lower fuel cavity 8 is related to the position of the guide plate 1 in the fuel cavity 6, the lower the partition plate is placed, the faster the flow velocity of the lower fuel cavity 8 is, and the volume ratio of the lower fuel cavity 8 to the upper fuel cavity 7 is usually set to be 0.2-0.6; in this embodiment, the volume ratio of the lower fuel cavity 8 to the upper fuel cavity 7 is 0.42, so that the fuel can maintain a certain flow rate in the lower fuel cavity 8 to meet the cooling requirement of the injector face 10.
In the engine thrust chamber injector shown in fig. 3, an injector face 10 is positioned below a fuel cavity 6, fuel gas is positioned above the fuel cavity 6, a nozzle 5 of the injector penetrates through the fuel cavity 6, and the nozzle 5 penetrates through a nozzle mounting hole 4 of a guide plate 1 in the fuel cavity 6. During operation, fuel enters the lower fuel cavity 8 from the fuel inlet 9 on the lower side surface of the fuel cavity 6, enters the upper fuel cavity 7 from the central hole 2 and the side area branch holes 3, enters the nozzle 5 from the upper fuel cavity 7, is mixed with fuel gas entering the nozzle 5 from the upper side surface of the fuel cavity 6 in the nozzle, and finally is combusted and reacted on the injector surface 10.
The guide plate capable of improving the propellant filling synchronism can be used for a liquid oxygen kerosene engine thrust chamber and an injector fuel cavity of a plurality of fuel generators, and experimental results show that the guide plate is safe and reliable in design structure, good in filling synchronism and free of obvious pressure peaks during starting. The invention has important reference significance for the development of other engines.
The above description is only for the purpose of describing the preferred embodiments of the present invention and is not intended to limit the technical solutions of the present invention, and any known modifications made by those skilled in the art based on the main technical concepts of the present invention are within the technical scope of the present invention.
Claims (10)
1. The utility model provides a can improve guide plate of propellant filling synchronism which characterized in that: the guide plate comprises a guide plate body, a central hole (2) arranged in the central area of the guide plate body, a plurality of side area branch holes (3) uniformly distributed in the edge area of the guide plate body on the circumference, and a plurality of nozzle mounting holes (4) arranged in the area between the central hole (2) and the side area branch holes (3);
the nozzle mounting holes (4) correspond to the nozzles (5) of the injector face (10) one by one and are used for the nozzles (5) to penetrate through the nozzle mounting holes (4);
the total area of the plurality of edge area branch holes (3) is smaller than the area of the central hole (2).
2. The deflector for improving propellant filling synchronicity of claim 1, wherein: the total area of the side area branch holes (3) is 20-30% of the area of the central hole (2).
3. A deflector for improving propellant filling synchronization as recited in claim 2, wherein: the total area of the plurality of edge area flow holes (3) is 25% of the area of the central hole (2).
4. A deflector for improving propellant filling synchronicity according to claim 1, 2 or 3 wherein: the guide plate body is of a disc-shaped stamping structure.
5. The deflector for improving propellant filling synchronicity of claim 4, wherein: the nozzle mounting holes (4) are not smaller than 4 layers, the number of the innermost nozzle mounting holes (4) is 12, and the number of the innermost nozzle mounting holes is increased by 6 from inside to outside.
6. The deflector for improving propellant filling synchronicity of claim 5, wherein: the number of the edge area branch holes (3) is the same as that of the outermost layer nozzle mounting holes (4).
7. An injector, characterized by:
comprising an injector face (10), a plurality of nozzles (5) arranged on the injector face (10), a fuel cavity (6) arranged above the injector face (10), and a baffle plate (1) according to any one of claims 1 to 6;
the guide plate (1) is arranged in the fuel cavity (6) and divides the fuel cavity (6) into a fuel upper cavity (7) and a fuel lower cavity (8);
the upper fuel cavity (7) is communicated with the lower fuel cavity (8) through a plurality of side area branch holes (3) of the guide plate (1) and the central hole (2);
the plurality of nozzles (5) penetrate through the fuel cavity (6) respectively, and the plurality of nozzles (5) penetrate through the corresponding nozzle mounting holes (4) in the fuel cavity (6).
8. The injector of claim 7, wherein: the volume ratio of the fuel lower cavity (8) to the fuel upper cavity (7) is 0.2-0.6.
9. The injector of claim 8, wherein: the volume ratio of the lower fuel cavity (8) to the upper fuel cavity (7) is 0.42.
10. The injector of any of claims 7 to 9, wherein: the fuel in the fuel cavity (6) is space kerosene.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110592285.2A CN113202656B (en) | 2021-05-28 | 2021-05-28 | Guide plate and injector capable of improving propellant filling synchronism |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110592285.2A CN113202656B (en) | 2021-05-28 | 2021-05-28 | Guide plate and injector capable of improving propellant filling synchronism |
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| Publication Number | Publication Date |
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| CN113202656A true CN113202656A (en) | 2021-08-03 |
| CN113202656B CN113202656B (en) | 2022-03-04 |
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| CN202110592285.2A Active CN113202656B (en) | 2021-05-28 | 2021-05-28 | Guide plate and injector capable of improving propellant filling synchronism |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6397580B1 (en) * | 1998-07-09 | 2002-06-04 | Bi-Propellant Rocket Research Corporation | High performance rocket engine having a stepped expansion combustion chamber and method of making the same |
| CN102400815A (en) * | 2011-03-18 | 2012-04-04 | 北京航空航天大学 | Layer-board type injection device for oxygen/ methane low-thrust engine |
| CN107676196A (en) * | 2017-09-12 | 2018-02-09 | 中国人民解放军战略支援部队航天工程大学 | What a kind of cover plate connected can blocking type rocket engine propellant biasing spray panel |
| CN108691692A (en) * | 2018-05-31 | 2018-10-23 | 北京航空航天大学 | Mix ejector filler and small liquid rocket engine |
| CN109798202A (en) * | 2019-04-04 | 2019-05-24 | 北京宇航推进科技有限公司 | A kind of liquid-propellant rocket engine ejector filler integrating electric igniter |
| CN110805506A (en) * | 2019-09-29 | 2020-02-18 | 北京航天动力研究所 | Combined combustion stabilizing device |
| CN112253333A (en) * | 2020-09-17 | 2021-01-22 | 北京航天动力研究所 | Collector inlet flow guide structure with flow equalizing function |
-
2021
- 2021-05-28 CN CN202110592285.2A patent/CN113202656B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6397580B1 (en) * | 1998-07-09 | 2002-06-04 | Bi-Propellant Rocket Research Corporation | High performance rocket engine having a stepped expansion combustion chamber and method of making the same |
| CN102400815A (en) * | 2011-03-18 | 2012-04-04 | 北京航空航天大学 | Layer-board type injection device for oxygen/ methane low-thrust engine |
| CN107676196A (en) * | 2017-09-12 | 2018-02-09 | 中国人民解放军战略支援部队航天工程大学 | What a kind of cover plate connected can blocking type rocket engine propellant biasing spray panel |
| CN108691692A (en) * | 2018-05-31 | 2018-10-23 | 北京航空航天大学 | Mix ejector filler and small liquid rocket engine |
| CN109798202A (en) * | 2019-04-04 | 2019-05-24 | 北京宇航推进科技有限公司 | A kind of liquid-propellant rocket engine ejector filler integrating electric igniter |
| CN110805506A (en) * | 2019-09-29 | 2020-02-18 | 北京航天动力研究所 | Combined combustion stabilizing device |
| CN112253333A (en) * | 2020-09-17 | 2021-01-22 | 北京航天动力研究所 | Collector inlet flow guide structure with flow equalizing function |
Non-Patent Citations (2)
| Title |
|---|
| CHENGENLI等: "Flow field and injector heat characteristics of hybrid rocket motor with annular-gap injector", 《AEROSPACE SCIENCE AND TECHNOLOGY》 * |
| 高翔宇，孙纪国: "推力室多孔面板发汗冷却试验研究", 《火箭推进》 * |
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