CN113339159B - Coaxial double-centrifugal injector based on 3D printing and liquid oxygen kerosene rocket engine - Google Patents
Coaxial double-centrifugal injector based on 3D printing and liquid oxygen kerosene rocket engine Download PDFInfo
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- CN113339159B CN113339159B CN202110761629.8A CN202110761629A CN113339159B CN 113339159 B CN113339159 B CN 113339159B CN 202110761629 A CN202110761629 A CN 202110761629A CN 113339159 B CN113339159 B CN 113339159B
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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
Abstract
The invention relates to the technical field of liquid rocket engines, in particular to a coaxial double-centrifugal injector based on 3D printing and a liquid oxygen kerosene rocket engine, and aims to solve the problems that the existing coaxial double-centrifugal injector is high in processing and manufacturing and welding process requirements, multiple in welding seams, poor in reliability, risk of an oxidant cavity and a fuel cavity in series, unstable in combustion and low in efficiency in variable-working-condition work. A coaxial dual-centrifugal injector based on 3D printing comprises an outer bottom, an injection disc and an inner bottom which are 3D printed into a whole; an oxidant cavity is formed between the outer sole and the injection disc, a fuel cavity is formed between the injection disc and the inner sole, an oxidant inlet is formed in the oxidant cavity, and a fuel inlet is formed in the fuel cavity; the invention also discloses another coaxial double-centrifugal injector based on 3D printing, which comprises an outer bottom, an injection disc and an inner bottom which are respectively 3D printed; the invention also discloses two liquid oxygen kerosene rocket engines.
Description
Technical Field
The invention relates to the technical field of liquid rocket engines, in particular to a coaxial double-centrifugal injector based on 3D printing and a liquid oxygen kerosene rocket engine.
Background
The injector is a key component of a thrust chamber of a liquid rocket engine and is used for injecting, atomizing and mixing propellant components, so that the stable and efficient work of the engine is ensured, and the injector plays a decisive role in the working performance of the engine. The coaxial double-centrifugal injector is an injector adopting a coaxial double-component centrifugal injection unit to organize combustion, and has the advantages of good atomization effect, high combustion efficiency and capability of meeting the working requirement of variable thrust.
A common coaxial double-centrifugal injector is of a structure with three bottoms (an outsole, an insole and an insole) and two cavities (an oxidant cavity and a fuel cavity), wherein a plurality of coaxial double-centrifugal injection units, dozens of coaxial double-centrifugal injection units and even hundreds of coaxial double-centrifugal injection units are arranged in different modes and are assembled between the insole and the insole, and the outer bottom, the middle bottom, the inner bottom and the coaxial double-centrifugal injection units are connected by brazing to form an effectively isolated propellant cavity. However, the coaxial dual centrifugal injector has the following problems in use:
on one hand, the coaxial double-centrifugal injector is processed by adopting a brazing process, so that the requirements on processing, manufacturing and welding processes are high, and the processing and manufacturing cost of the injector is increased; meanwhile, as the brazing seams are more, the risk of cavities in the oxidant cavity and the fuel cavity is high, and the reliability is poor. On the other hand, coaxial dual centrifugal injectors use a cryogenic propellant to organize combustion, often with the risk of combustion instability.
Disclosure of Invention
The invention provides a coaxial double-centrifugal injector based on 3D printing and a liquid oxygen kerosene rocket engine, aiming at solving the problems that the requirements of the processing and manufacturing and welding processes of the existing coaxial double-centrifugal injector are high, more welding lines exist, the reliability is poor, the risk of cavities formed by an oxidant cavity and a fuel cavity is existed, and the combustion is often unstable and the efficiency is low in the working process under variable working conditions.
The technical scheme adopted by the invention is as follows:
a coaxial double-centrifugal injector based on 3D printing is characterized in that:
the injection plate comprises an outsole, an injection plate and an insole which are 3D printed into a whole;
an oxidant cavity is formed between the outer sole and the injection disc, a fuel cavity is formed between the injection disc and the inner sole, an oxidant inlet is formed in the oxidant cavity, and a fuel inlet is formed in the fuel cavity;
the injection tray comprises a plurality of long retraction injection units and a plurality of short retraction injection units;
the long retraction jetting unit and the short retraction jetting unit are coaxial double centrifugal jetting units;
the oxidant and the fuel of the long retracted injection unit are mixed in the retracted length;
the oxidizer and fuel of the short retracting injector unit are mixed downstream of the injector.
Further, a plurality of the long-retracted injection units are all arranged in the central area of the injection tray; the plurality of short-retracting injection units are all arranged on the periphery of the long-retracting injection unit.
Furthermore, oxidant tangential holes are formed in the inner shell of each of the long-retracting injection unit and the short-retracting injection unit, and fuel tangential holes are formed in the outer shell of each of the long-retracting injection unit and the short-retracting injection unit.
The invention also provides a liquid oxygen kerosene rocket engine, which is characterized in that: the coaxial dual-centrifugal injector based on 3D printing is included, liquid oxygen is filled in the oxidant cavity, and kerosene is filled in the fuel cavity.
The invention also provides a coaxial double-centrifugal injector based on 3D printing, which is characterized in that:
comprising an outsole, an injection disc and an insole which are respectively 3D printed;
an oxidant cavity is formed between the outer sole and the jetting disc, a fuel cavity is formed between the jetting disc and the inner sole, an oxidant inlet is formed in the oxidant cavity, and a fuel inlet is formed in the fuel cavity;
the injection tray comprises a plurality of long retraction injection units and a plurality of short retraction injection units;
the long retraction jetting unit and the short retraction jetting unit are coaxial double centrifugal jetting units;
the oxidant and the fuel of the long retracted injection unit are mixed in the retracted length;
the oxidizer and fuel of the short retracting injector unit are mixed downstream of the injector.
Further, a plurality of the long-retracted injection units are all arranged in the central area of the injection tray; the plurality of short-retracting injection units are all arranged on the periphery of the long-retracting injection unit.
Furthermore, oxidant tangential holes are formed in the inner shell of each of the long-retracting injection unit and the short-retracting injection unit, and fuel tangential holes are formed in the outer shell of each of the long-retracting injection unit and the short-retracting injection unit.
The invention also provides another liquid oxygen kerosene rocket engine, which is characterized in that: the coaxial dual-centrifugal injector based on 3D printing is included, liquid oxygen is filled in the oxidant cavity, and kerosene is filled in the fuel cavity.
Compared with the prior art, the invention has the following beneficial effects:
the coaxial dual-centrifugal injector based on 3D printing has the advantages that the structure is simple and reliable, the liquid oxygen and kerosene can be atomized and mixed at different positions of the injector by utilizing the characteristics of high combustion efficiency of the long-retraction coaxial dual-centrifugal injection unit and good combustion stability of the short-retraction coaxial dual-centrifugal injection unit and arranging the liquid oxygen and kerosene dual-component centrifugal injection units with different retraction lengths according to concentric circles, and guarantee conditions are provided for efficient and stable combustion of the liquid oxygen and the kerosene under large-range variable working conditions. In addition, the injector is integrally processed by 3D printing, the design of the injector is simplified, brazing is omitted, an oxidant cavity and a fuel cavity are avoided from being connected in series, reliable sealing and effective isolation of each propellant cavity are realized, and the structural reliability and quality of the injector are greatly improved.
According to the coaxial dual-centrifugal injector based on 3D printing, the outer bottom, the injection disc and the inner bottom are respectively and independently printed in 3D mode, so that the printing state and quality of the oxidant tangential hole and the fuel tangential hole in the dual-centrifugal injection unit can be effectively checked, and the improvement direction of a printing process can be guided.
The coaxial double-centrifugal injector based on 3D printing meets the requirements of efficient, reliable and stable combustion of the open-cycle liquid oxygen kerosene rocket engine, and can be widely applied to other types of propellants.
Drawings
Fig. 1 is a structural diagram of a coaxial dual centrifugal injector based on 3D printing according to the present invention.
Fig. 2 is a distribution schematic diagram of an injection unit in a coaxial dual-centrifugal injector based on 3D printing.
Fig. 3 is a schematic structural diagram of another embodiment of the coaxial dual-centrifugal injector based on 3D printing according to the present invention.
In the figure:
1-outer sole, 2-injection disc, 21-long retracted injection unit, 22-short retracted injection unit, 23-retracted length, 24-downstream injector, 25-oxidant tangential hole, 26-fuel tangential hole, 3-inner sole, 4-oxidant cavity, 41-oxidant inlet, 5-fuel cavity, 51-fuel inlet, 6-first welding seam, and 7-second welding seam.
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 coaxial dual centrifugal injector based on 3D printing in the present embodiment comprises an outsole 1, an injection disk 2 and an insole 3 which are 3D printed into a whole;
an oxidant cavity 4 is formed between the outsole 1 and the injection disc 2, a fuel cavity 5 is formed between the injection disc 2 and the insole 3, an oxidant inlet 41 is formed in the oxidant cavity 4, and a fuel inlet 51 is formed in the fuel cavity 5;
the injection tray 2 comprises a plurality of long-retraction injection units 21 and a plurality of short-retraction injection units 22;
the long retraction injection unit 21 and the short retraction injection unit 22 are coaxial double-centrifugal injection units;
the oxidizer and fuel of the extended back injector unit 21 are mixed within the retracted length 23;
the oxidant and fuel that are shortened into the injector unit 22 are mixed downstream 24 of the injector.
A plurality of long-retracted injection units 21 are all arranged in the central area of the injection tray 2; a plurality of short-retracted injection units 22 are disposed at the periphery of the long-retracted injection unit 21.
Oxidant tangential holes 25 are formed in the inner shells of the long and short retractable injection units 21 and 22 at positions close to the oxidant cavity 4, and fuel tangential holes 26 are formed in the outer shells of the long and short retractable injection units 21 and 22 at positions close to the fuel cavity 5.
Due to the different retraction lengths of the injection units, the mixing positions of the oxidizer and the fuel are different, in the case of the short retraction L1 injection unit, the oxidizer and the fuel are mixed downstream of the injector, in the case of the long retraction L2 injection unit, the oxidizer and the fuel are mixed in the retraction length, and the mixing positions are different, so that the positions of the combustion flame fronts downstream of the injector are different, and stable combustion is facilitated. In addition, the injector is integrally processed by 3D printing, and after the printing defects are eliminated in the curing and printing process, the risk of cavity crossing between the oxidant cavity and the fuel cavity is avoided, so that the structural reliability and quality of the injector are greatly improved.
The present invention also provides an embodiment, as shown in fig. 3, the structural features are: the outer sole 1, the injection disc 2 and the inner sole 3 of the injector are respectively integrally printed, the outer sole 1 and the inner sole 3 are connected with the injection disc 2 in a welding mode, the middle top end and the middle bottom end of the injection disc 2 are respectively connected with the bottom of the outer sole 1 and the top of the inner sole 3 through first welding seams 6, the bottom of the injection disc 2 is connected with the bottom of the inner sole 3 through second welding seams 7, and therefore the printing state and quality of an oxidant tangential hole 25 and a fuel tangential hole 26 on a double-centrifugal injection unit can be effectively checked, and the improvement direction of a printing process can be guided.
The invention also provides a liquid oxygen kerosene rocket engine which is an open cycle liquid oxygen kerosene rocket engine and comprises the integrated 3D-printed coaxial double-centrifugal injector or the split 3D-printed coaxial double-centrifugal injector, wherein the oxidant cavity 4 is filled with liquid oxygen, and the fuel cavity 5 is filled with kerosene.
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 (4)
1. A coaxial dual-centrifugal injector based on 3D printing is characterized in that:
the injection plate comprises an outsole (1), an injection plate (2) and an insole (3) which are 3D printed into a whole;
an oxidant cavity (4) is formed between the outsole (1) and the injection disc (2), a fuel cavity (5) is formed between the injection disc (2) and the insole (3), an oxidant inlet (41) is formed in the oxidant cavity (4), and a fuel inlet (51) is formed in the fuel cavity (5);
the injection plate (2) comprises a plurality of long-retracting injection units (21) and a plurality of short-retracting injection units (22);
the long retracting injection unit (21) and the short retracting injection unit (22) are coaxial double-centrifugal injection units;
-the oxidizer and fuel of said elongated retracted injector unit (21) are mixed within the retracted length (23);
-the oxidizer and fuel of said short retracting injector unit (22) are mixed downstream (24) of the injector;
the long retracted injection units (21) are all arranged in the central area of the injection disc (2), the short retracted injection units (22) are all arranged on the periphery of the long retracted injection units (21), and the injection units with the same retracted length are arranged according to concentric circles;
the retraction length (23) is a retraction space between an outlet of the inner housing and the outer housing of the injection unit;
the inner shell is coaxial with the outer shell, penetrates through the injection disc (2) and extends into the oxidant cavity (4), and the outer shell extends into the fuel cavity (5); oxidant tangential holes (25) are formed in the inner shells of the long retracting injection unit (21) and the short retracting injection unit (22), and fuel tangential holes (26) are formed in the outer shells of the long retracting injection unit (21) and the short retracting injection unit (22).
2. The utility model provides a liquid oxygen kerosene rocket engine which characterized in that: coaxial dual centrifugal injector based on 3D printing according to claim 1, comprising said oxidizer volume (4) filled with liquid oxygen and said fuel volume (5) filled with kerosene.
3. A coaxial dual centrifugal injector based on 3D printing, characterized in that:
comprises an outsole (1), an injection disc (2) and an insole (3) which are respectively printed in a 3D way;
an oxidant cavity (4) is formed between the outsole (1) and the injection disc (2), a fuel cavity (5) is formed between the injection disc (2) and the insole (3), an oxidant inlet (41) is formed in the oxidant cavity (4), and a fuel inlet (51) is formed in the fuel cavity (5);
the injection plate (2) comprises a plurality of long-retracting injection units (21) and a plurality of short-retracting injection units (22);
the long retraction injection unit (21) and the short retraction injection unit (22) are coaxial double-centrifugal injection units;
-the oxidizer and fuel of said elongated retracted injector unit (21) are mixed within the retracted length (23);
-the oxidizer and fuel of said short retracting injector unit (22) are mixed downstream (24) of the injector; the long retracted injection units (21) are all arranged in the central area of the injection disc (2), the short retracted injection units (22) are all arranged on the periphery of the long retracted injection units (21), and the injection units with the same retracted length are arranged according to concentric circles;
the retraction length (23) is a retraction space between an outlet of the inner housing and the outer housing of the injection unit;
the inner shell is coaxial with the outer shell, penetrates through the injection disc (2) and extends into the oxidant cavity (4), and the outer shell extends into the fuel cavity (5); oxidant tangential holes (25) are formed in inner shells of the long-retraction jetting unit (21) and the short-retraction jetting unit (22), and fuel tangential holes (26) are formed in outer shells of the long-retraction jetting unit (21) and the short-retraction jetting unit (22).
4. The utility model provides a liquid oxygen kerosene rocket engine which characterized in that: coaxial dual centrifugal injector based on 3D printing comprising according to claim 3, said oxidant volume (4) being filled with liquid oxygen and said fuel volume (5) being filled with kerosene.
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| CN114412660B (en) * | 2021-12-22 | 2023-12-29 | 首都航天机械有限公司 | Integrated coaxial nozzle of liquid rocket engine and design and manufacturing method thereof |
| CN114320665A (en) * | 2022-01-06 | 2022-04-12 | 中南大学 | Gas generator |
| CN114382614A (en) * | 2022-03-02 | 2022-04-22 | 北京星际荣耀科技有限责任公司 | Injector, engine and aircraft |
| CN115949531B (en) * | 2023-03-09 | 2023-05-09 | 中国空气动力研究与发展中心空天技术研究所 | Wide range continuous adjustable injector |
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| 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 |
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| US6253539B1 (en) * | 1996-09-24 | 2001-07-03 | Boeing North America Inc. | Convective and turbulent shear mixing injector |
| JP2008111340A (en) * | 2006-10-27 | 2008-05-15 | Mitsubishi Heavy Ind Ltd | Injector and combustor for rocket |
| KR101013934B1 (en) * | 2008-09-16 | 2011-02-14 | 한국항공우주연구원 | Liquid rocket engine injector head |
| CN107939551B (en) * | 2017-11-29 | 2024-02-09 | 北京航天动力研究所 | Pre-combustion chamber injector structure |
| CN108194204B (en) * | 2017-12-28 | 2020-03-03 | 西安航天动力研究所 | High-reliability integral injector |
| US11846253B2 (en) * | 2018-10-30 | 2023-12-19 | Aerojet Rocketdyne, Inc. | Injector with injector elements in circumferential rows that alternate between counter-clockwise and clockwise swirl |
| CN109779788B (en) * | 2018-12-13 | 2020-06-30 | 西安航天动力研究所 | Gas-liquid coaxial shear type nozzle based on lip sawtooth design |
| CN109469559B (en) * | 2019-01-24 | 2020-01-31 | 北京宇航推进科技有限公司 | -made injector of liquid rocket engine |
| CN112196697A (en) * | 2020-10-19 | 2021-01-08 | 北京天兵科技有限公司 | Integrated structure injector for rocket engine |
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| 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 |
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