CN113339160A - Liquid oxygen methane thrust chamber injector - Google Patents
Liquid oxygen methane thrust chamber injector Download PDFInfo
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- CN113339160A CN113339160A CN202110762741.3A CN202110762741A CN113339160A CN 113339160 A CN113339160 A CN 113339160A CN 202110762741 A CN202110762741 A CN 202110762741A CN 113339160 A CN113339160 A CN 113339160A
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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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- 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 & Propulsion (AREA)
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Abstract
The invention relates to a thrust chamber injector, in particular to a liquid oxygen methane thrust chamber injector, which aims to solve the problems that the mixing effect of a propellant of the thrust chamber injector is poor and the combustion efficiency is insufficient due to the fact that liquid oxygen and methane belong to liquid low-temperature propellants in the working process of the liquid oxygen methane injector at present and a direct-current shear nozzle or an impact injector structure is adopted. A liquid oxygen methane thrust chamber injector comprises a plurality of injection units, a middle sole, a top cover, a fluid director and an inner bottom which are coaxially and sequentially arranged on the middle sole; the plurality of injection units are all fixed on the middle sole, the fluid director and the inner sole; a liquid oxygen cavity is formed among the top cover, the middle sole and the plurality of jetting units, and a methane cavity is formed among the middle sole, the inner sole and the plurality of jetting units; the plurality of injection units are all nozzles with retraction chambers, and the nozzles comprise a central area nozzle, a main combustion area nozzle and a side area nozzle.
Description
Technical Field
The invention relates to a thrust chamber injector, in particular to a liquid oxygen methane thrust chamber injector.
Background
Oxygen and methane are natural resources with abundant reserves in the nature, and methane is a hydrocarbon fuel which is widely used, and has low price, abundant reserves and no pollution. As a liquid rocket engine propellant combination, the specific impulse of the combination of liquid oxygen and methane is between that of liquid oxygen kerosene and liquid oxygen liquid hydrogen. Compared with kerosene, the liquid methane has better cooling performance, higher coking temperature than the kerosene, less carbon deposition of combustion products and greater superiority as coolant methane. Compared with liquid oxygen and liquid hydrogen, methane belongs to a low-temperature propellant, but has low price and higher density, and can effectively reduce the launching cost of a rocket, so that the liquid oxygen and methane propellant combination has wide application prospect.
The structure of the thrust chamber injector is generally designed by combining the characteristics of a propellant, for example, a direct-current centrifugal injection unit is often adopted by the thrust chamber injector of a liquid oxygen kerosene afterburning cycle engine, a direct-current shear injection unit is adopted by the thrust chamber injector of an oxyhydrogen engine, and a direct-current impact injector is adopted by the conventional thrust chamber injector of the engine. The structure of the injector injection unit is selected, and the purpose of the injector injection unit is to realize efficient mixing and combustion of the propellant in a limited space.
However, in the existing thrust chamber injector adopting liquid oxygen and methane combined propellant, because liquid oxygen and methane both belong to liquid low-temperature propellant, the adopted direct-current shear type nozzle or impact type injector structure can cause poor mixing effect of the thrust chamber injector propellant and insufficient combustion efficiency, and is difficult to meet the design requirements of high efficiency and stable combustion of the existing injector.
Disclosure of Invention
The invention provides a liquid oxygen methane thrust chamber injector, and aims to solve the technical problems that in the working process of the liquid oxygen methane injector, liquid oxygen and methane belong to liquid low-temperature propellants, and due to the adoption of a direct-current shear nozzle or an impact injector structure, the propellant mixing effect of the thrust chamber injector is poor, the combustion efficiency is insufficient, and the design requirements of high-efficiency and stable combustion of the existing injector are difficult to meet.
The technical scheme adopted by the invention is as follows:
a liquid oxymethane thrust chamber injector characterized by:
comprises a plurality of injection units, a middle sole, and a top cover, a fluid director and an inner bottom which are coaxially and sequentially arranged on the middle sole;
the plurality of injection units are all fixed on the middle sole, the fluid director and the inner sole;
a liquid oxygen cavity is formed among the top cover, the middle sole and the plurality of injection units, and a liquid oxygen inlet pipe is arranged on the liquid oxygen cavity;
a methane cavity is formed among the insole, the inner bottom and the plurality of jetting units, and a methane inlet pipe is arranged on the methane cavity;
the centers of the top cover and the inner bottom are provided with ignition gas channels which are communicated up and down;
the plurality of injection units are all nozzles with retraction chambers, and the plurality of nozzles comprise a central area nozzle, a main combustion area nozzle and a side area nozzle;
the central area nozzles are uniformly distributed around the ignition gas channel;
the edge zone nozzles are uniformly distributed at the outermost edge of the inner bottom and comprise N edge zone nozzles which are uniformly distributed circumferentially and a plurality of edge zone main nozzles arranged between two adjacent edge zone nozzles, and N takes a value of 3-6; the flow rate of the side zone nozzle is higher than that of the side zone main nozzle by more than 20 percent;
the main combustion zone nozzles comprise N groups of main combustion zone sub-nozzles which are radially and uniformly distributed, and a plurality of main combustion zone main nozzles which are distributed among the central zone nozzles, the side zone nozzles and the main combustion zone sub-nozzles; the side zone nozzle is positioned at the radial outer end of the main combustion zone nozzle; the flow of the main combustion zone nozzle is higher than that of the main combustion zone nozzle by more than 20%.
Further, the central area nozzle comprises a central area nozzle inner shell and a central area nozzle outer shell which is coaxially fixedly connected to the central area nozzle inner shell, the central area nozzle inner shell is a liquid oxygen nozzle with a centrifugal structure, and a first tangential hole is formed in the position, close to the liquid oxygen cavity, of the central area nozzle inner shell; the central area nozzle outer shell is a methane nozzle with a centrifugal structure, and a second tangential hole is formed in the position, close to the methane cavity, of the central area nozzle outer shell.
Furthermore, the side zone nozzle, the side zone main nozzle, the main combustion zone nozzle and the main combustion zone main nozzle all comprise a nozzle inner shell and a nozzle outer shell which is coaxially and fixedly connected to the nozzle inner shell; the casing is centrifugal structure's liquid oxygen nozzle in the nozzle, the position that the casing is close to the liquid oxygen chamber in the nozzle is provided with the tangential hole, the nozzle shell body is the methane nozzle of shear type structure, the position that the nozzle shell body is close to the methane chamber is provided with radial hole.
Further, the middle parts of the middle sole and the inner sole are fixedly connected with sleeves, the sleeves are coaxially sleeved outside the ignition gas channel, and the sleeves are in interference fit with the ignition gas channel.
Further, the area of the fluid throttling hole of the edge zone-dividing nozzle is 20-25% larger than that of the edge zone main nozzle.
Furthermore, the area of the fluid throttling hole of the main combustion area zone nozzle is 20-25% larger than that of the fluid throttling hole of the main combustion area zone nozzle.
Further, a liquid collector is further arranged on the liquid oxygen inlet pipe.
Further, the nozzles with the retraction chambers are arranged in a concentric circle mode;
the number of the central area nozzles is 6;
the main combustion area is divided into 3 areas, the main combustion area nozzles comprise 3 groups of main combustion area nozzles which are distributed in the radial direction, each group is provided with 3 main combustion area nozzles, and 15 main combustion area nozzles 7 which are distributed in a sector shape are arranged between two adjacent groups of main combustion area nozzles which are distributed in the radial direction;
the side zone nozzle is provided with 3, sets up respectively at the radial outer tip of 3 main combustion zone nozzles of group, and all sets up 9 side zone main nozzles that are the arc and distribute between two adjacent side zone nozzles.
Further, the middle bottom is provided with a flow equalizing hole, and the flow equalizing hole is used for communicating the liquid oxygen inlet pipe and the liquid oxygen cavity.
Compared with the prior art, the invention has the following beneficial effects.
The liquid oxygen methane thrust chamber injector adopts a central area nozzle with a coaxial double-centrifugal structure to ensure the reliability of an ignition process, adopts a main combustion area nozzle and a side area nozzle with a centrifugal shear structure, improves the flow rate of the main combustion area nozzle by about 20 percent compared with that of the main combustion area nozzle, improves the flow rate of the side area nozzle by about 20 percent compared with that of the side area main nozzle, effectively improves the atomization of liquid oxygen and the mixing effect between propellants, ensures the efficient combustion of the propellants, further realizes the energy area release, improves the combustion stability of the injector, and converts the chemical energy of the liquid propellants into the internal energy of high-temperature gas in order and efficiently through tissue combustion.
In the liquid oxygen methane thrust chamber injector, the sleeves are welded on the inner bottom and the middle bottom, so that an interference fit connection mode is formed between the ignition gas channel of the top cover and the sleeves, the possibility of propellant cavity crossing caused by failure of a brazing seam between the sleeves and the middle bottom due to deformation of the top cover is prevented, and the working reliability of the injector is improved.
Thirdly, the nozzles with retraction chambers are arranged in a concentric circle mode, so that the structure of the injection unit is more compact, the efficient mixing and stable combustion of the liquid oxymethane propulsion combination can be ensured, and the design requirement of a miniaturized injector is met.
Drawings
FIG. 1 is a perspective view of a liquid methanone thrust chamber injector according to the present invention.
FIG. 2 is a cross-sectional view of a liquid oxymethane thrust chamber injector of the present invention.
FIG. 3 is a diagram showing the position distribution of an injection unit in the injector of the liquid oxymethane thrust chamber according to the present invention.
FIG. 4 is a schematic diagram of a central nozzle in the injector of the liquid oxymethane thrust chamber according to the present invention.
FIG. 5 is a schematic structural diagram of a side area nozzle and a main combustion area nozzle of the injector of the liquid oxygen methane thrust chamber.
FIG. 6 is a schematic diagram of a sleeve of the injector for liquid oxymethane thrust chamber according to the present invention.
FIG. 7 is a schematic structural diagram of a deflector in the injector for liquid oxymethane thrust chamber according to the present invention.
In the figure:
1-top cover, 2-middle sole, 21-methane cavity, 22-methane inlet pipe, 3-flow guider, 31-liquid oxygen cavity, 32-flow equalizing hole, 33-flow guiding hole, 4-inner bottom, 5-sleeve, 50-ignition gas channel, 51-igniter interface, 6-center area nozzle, 61-center area nozzle inner shell, 611-first tangential hole, 62-center area nozzle outer shell, 621-second tangential hole, 7-main combustion area main nozzle, 71-nozzle inner shell, 711-third tangential hole, 72-nozzle outer shell, 721-radial hole, 8-side area main nozzle, 9-main combustion area nozzle, 10-side area nozzle, 11-liquid collector and 12-liquid oxygen inlet pipe.
Detailed Description
The technical solution of the present invention will be clearly and completely described below with reference to the embodiments of the present invention and the accompanying drawings, and it is obvious that the described embodiments do not limit the present invention.
As shown in fig. 1 and 2, the liquid oxygen methane thrust chamber injector in the present embodiment comprises a plurality of injection units, a midsole 2, and a top cover 1, a flow guider 3 and an inner bottom 4 coaxially and sequentially arranged on the midsole 2;
a plurality of injection units are all fixed on the middle sole 2, the fluid director 3 and the inner sole 4;
a liquid oxygen cavity 31 is formed among the top cover 1, the midsole 2 and the plurality of injection units, a liquid oxygen inlet pipe 12 is arranged on the liquid oxygen cavity 31, and a liquid collector 11 is further arranged on the liquid oxygen inlet pipe 12; the middle sole 2 is provided with a flow equalizing hole 32, and the flow equalizing hole 32 is used for communicating the liquid oxygen inlet pipe 12 with the liquid oxygen cavity.
A methane cavity 21 is formed among the midsole 2, the insole 4 and the plurality of injection units, and a methane inlet pipe 22 is arranged on the methane cavity 21;
the centers of the top cover 1 and the inner bottom 4 are provided with ignition gas channels 50 which are vertically communicated, and the interface of the ignition gas channel 50 at the top cover 1 is an igniter interface 51;
the plurality of injection units are all nozzles with retraction chambers, and the plurality of nozzles comprise a central area nozzle 6, a main combustion area nozzle and a side area nozzle which are concentrically arranged from inside to outside;
as shown in fig. 3, the nozzles with retraction chambers are arranged in concentric circles, and 6 nozzles 6 in the central area are uniformly distributed around the ignition gas channel 50;
the edge zone nozzles are uniformly distributed at the outermost edge of the inner bottom 4, each edge zone nozzle comprises 3 edge zone nozzles 10 which are uniformly distributed circumferentially and a plurality of edge zone main nozzles 8 arranged between every two adjacent edge zone nozzles 10, and the value of N is 3; 3 edge zone partition nozzles 10 are respectively arranged at the radial outer end parts of 3 groups of main combustion zone partition nozzles 9, 27 edge zone main nozzles 8 are arranged, and 9 edge zone main nozzles 8 distributed in an arc shape are arranged between every two adjacent edge zone partition nozzles 10;
the area of the fluid throttling hole of the edge zone-dividing nozzle 10 is 25 percent larger than that of the fluid throttling hole of the edge zone main nozzle 8;
the main combustion zone nozzles comprise 3 groups of main combustion zone sub-nozzles 9 which are radially and uniformly distributed, and a plurality of main combustion zone main nozzles 7 which are distributed among the central zone nozzle 6, the side zone nozzles and the main combustion zone sub-nozzles 9; each group is provided with 3 main combustion zone partition nozzles 9, the number of the main combustion zone main nozzles 7 is 45, and 15 main combustion zone main nozzles 7 distributed in a fan shape are arranged between two adjacent groups of the main combustion zone partition nozzles 9 distributed in the radial direction;
the side zone partition nozzles 10 are positioned at the radial outer ends of the main combustion zone partition nozzles 9; the area of the fluid throttling hole of the main combustion zone nozzle 9 is 25% larger than that of the fluid throttling hole of the main combustion zone nozzle 7.
As shown in fig. 4, the center area nozzle 6 comprises a center area nozzle inner shell 61 and a center area nozzle outer shell 62 coaxially connected to the center area nozzle inner shell 61, the center area nozzle inner shell 61 is a liquid oxygen nozzle of a centrifugal structure, and the center area nozzle inner shell 61 is provided with a first tangential hole 611 at a position close to the liquid oxygen chamber; the center area nozzle outer shell 62 is a methane nozzle with a centrifugal structure, and a second tangential hole 621 is formed in the center area nozzle outer shell 62 close to the methane cavity 21.
As shown in fig. 5, each of the edge zone-dividing nozzle 10, the edge zone main nozzle 8, the main combustion zone-dividing nozzle 9 and the main combustion zone main nozzle 7 includes a nozzle inner casing 71 and a nozzle outer casing 72 coaxially connected to the nozzle inner casing 71; the inner nozzle shell 71 is a liquid oxygen nozzle with a centrifugal structure, a tangential hole 711 is formed in the position, close to a liquid oxygen cavity, of the inner nozzle shell 71, the outer nozzle shell 72 is a methane nozzle with a shear structure, and a radial hole 721 is formed in the position, close to the methane cavity 21, of the outer nozzle shell 72.
As shown in fig. 6, the middle parts of the middle sole 2 and the inner sole 4 are fixedly connected with a sleeve 5, the sleeve 5 is coaxially sleeved outside the ignition gas channel 50, and the sleeve 5 is in interference fit with the ignition gas channel 50.
In the embodiment, when the liquid oxygen methane thrust chamber injector is used, liquid oxygen firstly enters a liquid oxygen channel formed by the liquid collector 11 and the insole 2 through the liquid oxygen inlet pipe 12, then uniformly enters the liquid oxygen cavity 31 through the flow equalizing holes 32 on the insole 2, and finally enters the retraction chamber and the downstream through tangential holes on an inner shell body of 90 nozzles welded on the insole 2 and the insole 4;
methane enters the methane cavity 21 through the methane inlet pipe 22 and then enters a lower fuel cavity formed by the fluid director 3 and the inner bottom 4 in the methane cavity 21, and as shown in fig. 7, the methane enters the upper fuel cavity through the diversion holes 33 arranged on the fluid director 3.
The flow guider 3 uniformly supplies methane in the upper fuel cavity into 90 nozzles, and the 90 nozzles comprise a central area nozzle 6, a main combustion area main nozzle 7, an edge area main nozzle 8, a main combustion area partition nozzle 9 and an edge area partition nozzle 10 and enter a retraction chamber and the downstream from tangential holes or radial holes on the outer shell of the nozzle.
The ignition gas channel 50 processed on the top cover 1 can introduce high-temperature ignition gas into the combustion chamber and ignite liquid oxygen and methane entering from the nozzle, the liquid oxygen and the methane start to be atomized, evaporated, mixed and combusted in the nozzle retraction chamber, stable flame is formed at the nozzle outlet and downstream, and the chemical energy of the propellant is converted into the internal energy of the high-temperature gas and flows downstream.
The above description is only an embodiment of the present invention, and is not intended to limit the scope of the present invention, and all equivalent structural changes made by using the contents of the present specification and the drawings, or applied directly or indirectly to other related technical fields, are included in the scope of the present invention.
Claims (9)
1. A liquid oxymethane thrust chamber injector, comprising:
comprises a plurality of injection units, a middle sole (2), and a top cover (1), a fluid director (3) and an inner sole (4) which are coaxially and sequentially arranged on the middle sole (2);
the plurality of injection units are all fixed on the middle sole (2), the fluid director (3) and the inner sole (4);
a liquid oxygen cavity (31) is formed among the top cover (1), the middle sole (2) and the plurality of injection units, and a liquid oxygen inlet pipe (12) is arranged on the liquid oxygen cavity (31);
a methane cavity (21) is formed among the midsole (2), the insole (4) and the plurality of injection units, and a methane inlet pipe (22) is arranged on the methane cavity (21);
the centers of the top cover (1) and the inner bottom (4) are provided with ignition gas channels (50) which are vertically communicated;
the plurality of injection units are all nozzles with retraction chambers, and the plurality of nozzles comprise a central area nozzle (6), a main combustion area nozzle and a side area nozzle which are concentrically arranged from inside to outside;
the central area nozzles (6) are uniformly distributed around the ignition gas channel (50);
the edge zone nozzles are uniformly distributed at the outermost edge of the inner bottom (4), each edge zone nozzle comprises N edge zone nozzles (10) which are uniformly distributed circumferentially and a plurality of edge zone main nozzles (8) which are arranged between every two adjacent edge zone nozzles (10), and N takes a value of 3-6; the flow rate of the side zone nozzle (10) is more than 20% higher than that of the side zone main nozzle (8);
the main combustion area nozzles comprise N groups of main combustion area sub-nozzles (9) which are radially and uniformly distributed, and a plurality of main combustion area main nozzles (7) which are distributed among the central area nozzles (6), the side area nozzles and the main combustion area sub-nozzles (9); the side zone partition nozzle (10) is positioned at the radial outer end of the main combustion zone partition nozzle (9); the flow rate of the main combustion zone nozzle (9) is higher than that of the main combustion zone nozzle (7) by more than 20%.
2. The liquid oxymethane thrust chamber injector of claim 1, wherein:
the central area nozzle (6) comprises a central area nozzle inner shell (61) and a central area nozzle outer shell (62) which is coaxially fixedly connected to the central area nozzle inner shell (61), the central area nozzle inner shell (61) is a centrifugal liquid oxygen nozzle, and a first tangential hole (611) is formed in the position, close to a liquid oxygen cavity, of the central area nozzle inner shell (61); the central area nozzle outer shell (62) is a methane nozzle with a centrifugal structure, and a second tangential hole (621) is formed in the position, close to the methane cavity (21), of the central area nozzle outer shell (62).
3. The liquid oxymethane thrust chamber injector of claim 2, wherein:
the side zone nozzle (10), the side zone main nozzle (8), the main combustion zone nozzle (9) and the main combustion zone main nozzle (7) respectively comprise a nozzle inner shell (71) and a nozzle outer shell (72) which is coaxially fixedly connected on the nozzle inner shell (71); the utility model discloses a methane nozzle, including nozzle inner shell (71), nozzle outer shell (72), the position that the inner shell (71) of nozzle is centrifugal structure's liquid oxygen nozzle, the position that the inner shell (71) of nozzle is close to the liquid oxygen chamber is provided with tangential hole (711), the methane nozzle of nozzle outer shell (72) for shear type structure, the position that the outer shell (72) of nozzle is close to methane chamber (21) is provided with radial hole (721).
4. A liquid oxymethane thrust chamber injector as claimed in claim 3 wherein:
the middle part of insole (2) and insole (4) has linked firmly sleeve (5), sleeve (5) coaxial suit is in the outside of ignition gas passageway (50), and sleeve (5) and ignition gas passageway (50) interference fit.
5. A liquid methanogen thrust chamber injector as set forth in any of claims 1 to 4 wherein:
the area of the fluid throttling hole of the side zone nozzle (10) is 20-25% larger than that of the fluid throttling hole of the side zone main nozzle (8).
6. The liquid oxymethane thrust chamber injector of claim 5, wherein:
the area of the fluid throttling hole of the main combustion zone nozzle (9) is 20-25% larger than that of the fluid throttling hole of the main combustion zone nozzle (7).
7. The liquid oxymethane thrust chamber injector as set forth in claim 6, wherein:
and a liquid collector (11) is also arranged on the liquid oxygen inlet pipe (12).
8. The liquid oxymethane thrust chamber injector of claim 7, wherein:
the nozzles with the retraction chambers are arranged in a concentric circle mode;
the number of the central area nozzles (6) is 6;
the main combustion area is divided into 3 areas, the main combustion area nozzles comprise 3 groups of main combustion area nozzles (9) which are distributed in the radial direction, each group is provided with 3 main combustion area nozzles (9), and 15 main combustion area nozzles (7) which are distributed in a fan shape are arranged between two adjacent groups of main combustion area nozzles (9) which are distributed in the radial direction;
the side zone partition nozzles (10) are 3 and are respectively arranged at the radial outer end parts of the 3 groups of main combustion zone partition nozzles (9), and 9 side zone main nozzles (8) distributed in an arc shape are arranged between every two adjacent side zone partition nozzles (10).
9. The liquid oxymethane thrust chamber injector of claim 8, wherein:
be provided with on insole (2) and all flow hole (32), all flow hole (32) are used for communicateing liquid oxygen inlet pipe (12) and liquid oxygen chamber.
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| CN202110762741.3A CN113339160B (en) | 2021-07-06 | 2021-07-06 | Liquid oxygen methane thrust chamber injector |
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| CN202110762741.3A CN113339160B (en) | 2021-07-06 | 2021-07-06 | Liquid oxygen methane thrust chamber injector |
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| CN113982787A (en) * | 2021-11-25 | 2022-01-28 | 西安航天动力研究所 | Scaling method of gas-liquid pintle injector |
| CN114165358A (en) * | 2021-11-16 | 2022-03-11 | 北京航天动力研究所 | Baffle nozzle structure of precombustion chamber |
| CN114215660A (en) * | 2021-11-16 | 2022-03-22 | 北京航天动力研究所 | High-efficient stable injector |
| CN114320665A (en) * | 2022-01-06 | 2022-04-12 | 中南大学 | Gas generator |
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| CN114876669A (en) * | 2022-03-31 | 2022-08-09 | 中国人民解放军战略支援部队航天工程大学 | Coaxial model engine for researching tangential unstable combustion of rocket engine |
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