CN109798202B - Liquid rocket engine injector integrating electric igniter - Google Patents
Liquid rocket engine injector integrating electric igniter Download PDFInfo
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- CN109798202B CN109798202B CN201910268289.8A CN201910268289A CN109798202B CN 109798202 B CN109798202 B CN 109798202B CN 201910268289 A CN201910268289 A CN 201910268289A CN 109798202 B CN109798202 B CN 109798202B
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- fuel
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- fixing holes
- central shaft
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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 Methods Of Internal-Combustion Engines (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
Abstract
A liquid rocket engine injector integrating a current collection igniter. The composition of the invention comprises: the fuel nozzle comprises a bottom plate, an outer barrel, a fuel nozzle, an oxidant nozzle, a top cover and an electric nozzle, wherein the outer barrel is connected with the top cover, the outer barrel is provided with a central shaft, the central shaft is connected with the barrel wall of the outer barrel through an annular transverse plate, the inner cavity of the outer barrel is divided into an upper cavity and a lower cavity by the annular transverse plate, and a fuel through hole is formed in the side wall of the lower cavity; the bottom of the lower cavity is connected with a bottom plate, a plurality of fuel nozzle fixing holes are uniformly formed in the bottom plate, a plurality of oxidant nozzle fixing holes are uniformly formed in the annular transverse plate, the positions of the oxidant nozzle fixing holes and the positions of the fuel nozzle fixing holes are in one-to-one correspondence, and the fuel nozzles and the oxidant nozzles are adaptively connected between each pair of fuel nozzle fixing holes and each pair of oxidant nozzle fixing holes; the central shaft side wall of the upper cavity part is uniformly provided with oxidant through holes, and the central shaft side wall of the lower cavity part is uniformly provided with a group of upper fuel through holes and a group of lower fuel through holes. The invention is suitable for a double-component liquid rocket engine, integrates an electric igniter and an injector, and realizes simplified design of a system.
Description
Technical field:
the invention relates to a liquid rocket engine injector integrating an igniter.
The background technology is as follows:
the development direction of rocket engines is to simplify the structure to improve the engine reliability while guaranteeing the engine performance.
The injector of the traditional rocket engine is responsible for mixing the tissue oxidant and the fuel, the electric igniter is used as a component and is fixed on the injector by a bolt or welding mode, and the high-energy fuel gas generated by the electric igniter ignites the oxidant and the fuel through an ignition hole reserved in the center of the injector.
The electric igniter of the traditional rocket engine is an independent component and is formed by connecting a plurality of parts in a mode of bolts, welding and the like, and the oxidant and the fuel which are independently supplied are ignited by the electric nozzle to form a torch, so that high-energy ignition is realized, and the oxidant and the fuel are controlled by additional pipelines and valves, so that the structure is relatively complex.
In addition, because the oxidizer and fuel separately supplied by the conventional rocket engine electric igniter are limited by factors such as the size and weight of the gas cylinder, the electric igniter cannot be operated for a long time, which is disadvantageous for a plurality of starting of some rocket engines in space.
The invention comprises the following steps:
the invention aims to solve the problems that the existing electric igniter is complex in structure, the oxidant and the fuel are required to be supplied independently and cannot work reliably for a long time, and provides a liquid rocket engine injector integrating the igniter.
The above object is achieved by the following technical scheme:
a liquid rocket engine injector integrating a current collection igniter into a whole comprises the following components: the fuel nozzle comprises a bottom plate, an outer barrel, a fuel nozzle, an oxidant nozzle, a top cover and an electric nozzle, wherein the outer barrel is connected with the top cover, the outer barrel is provided with a central shaft, the central shaft is connected with the barrel wall of the outer barrel through an annular transverse plate, the inner cavity of the outer barrel is divided into an upper cavity and a lower cavity by the annular transverse plate, and a fuel through hole is formed in the side wall of the lower cavity;
the bottom of the lower cavity is connected with a bottom plate, a plurality of fuel nozzle fixing holes are uniformly formed in the bottom plate, a plurality of oxidant nozzle fixing holes are uniformly formed in the annular transverse plate, the positions of the oxidant nozzle fixing holes and the positions of the fuel nozzle fixing holes are in one-to-one correspondence, the fuel nozzles and the oxidant nozzles are adaptively connected between each pair of fuel nozzle fixing holes and the oxidant nozzle fixing holes, and a fuel annular channel is formed between the inner wall of each fuel nozzle and the outer wall of each oxidant nozzle;
the central shaft is provided with a central axial hole, the upper part of the central shaft is connected with the electric nozzle, the side wall of the central shaft of the upper cavity part is uniformly provided with oxidant through holes, and the side wall of the central shaft of the lower cavity part is uniformly provided with a group of upper fuel through holes and a group of lower fuel through holes.
And the top cover is provided with an oxidant inlet hole.
The liquid rocket engine injector integrating the current collection igniter into a whole is characterized in that the fuel nozzle is cylindrical, and a plurality of radial fuel inlets are uniformly formed in the side wall of the fuel nozzle along the circumferential direction.
The liquid rocket engine injector integrating the electric igniter and the oxidant nozzle is provided with a central axial hole.
The liquid rocket engine injector integrating the electric igniter and the bottom plate is connected with the outer cylinder through argon arc welding, electron beam welding or brazing and the like, the outer cylinder is connected with the top cover through argon arc welding, electron beam welding or brazing and the like, and the outer cylinder is connected with the electric nozzle through threads.
The liquid rocket engine injector integrating the electric igniter and the fuel nozzle is connected with the bottom plate in a threaded or welding mode, the oxidant nozzle is connected with the outer cylinder in a threaded or welding mode, and the fuel nozzle is connected with the oxidant nozzle in a brazing mode.
The invention has the beneficial effects that:
the invention is suitable for a double-component liquid rocket engine, and provides a space for placing and fixing a fuel nozzle and an oxidant nozzle by combining an outer barrel with a bottom plate on the basis of the integrated design of the outer barrel. The supply of the oxidant and the fuel necessary for the work of the electric igniter is realized through the oxidant circulation hole of the central shaft of the upper cavity part and the fuel circulation hole of the central shaft of the lower cavity part, the ignition of the oxidant and the fuel is realized under the action of the electric nozzle, and the integrated design of the electric igniter and the injector is realized.
The structure of the injector realizes simplified design of the system on the basis of simplifying the structure of the electric igniter, and compared with the traditional electric igniter, the injector does not need additional oxidant, fuel supply pipelines and valves, and improves the reliability of the system.
The structure of the injector has the advantages that the oxidant occupation near the electric nozzle is large, so that the ignition of the oxidant and the fuel of the electric igniter is facilitated, and meanwhile, the gas temperature is relatively low, so that the protection of the central shaft material of the outer cylinder is facilitated; part of fuel enters the ignition channel through a fuel circulation hole near the bottom of the central shaft of the lower cavity part to be burnt with oxygen-enriched fuel gas, so that the further increase of the ignition fuel gas energy is realized.
The invention simplifies the structure of the electric igniter, integrates the electric igniter and the injector, realizes the simplified design of the system, and omits the oxidant and fuel supply pipelines and valves used by the extra electric igniter. On the basis of simplifying the system design, the ignition energy is improved, and meanwhile, the engine can work for a long time, so that the reliable work of the engine is guaranteed.
Description of the drawings:
fig. 1 is a schematic diagram of the structure of the present invention.
Fig. 2 is a top view of fig. 1.
Fig. 3 is a schematic structural view of the base plate of the present invention.
Fig. 4 is a top view of fig. 3.
Fig. 5 is a schematic structural view of the outer cylinder of the present invention.
Fig. 6 is a top view of fig. 5.
FIG. 7 is a schematic illustration of the structure of a fuel nozzle of the present invention.
FIG. 8 is a schematic view of the structure of the oxidant nozzle of the invention.
Fig. 9 is a schematic view of the structure of the top cover of the present invention.
Fig. 10 is a top view of fig. 9.
Fig. 11 is a schematic view of the structure of the mouthpiece of the present invention.
The specific embodiment is as follows:
for the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The invention provides a liquid rocket engine injector integrating a current collection igniter, which is shown in the accompanying drawings from 1 to 11, and comprises the following components: the fuel nozzle comprises a bottom plate 1, an outer barrel 2, a fuel nozzle 3, an oxidant nozzle 4, a top cover 5 and an electric nozzle 6, wherein the outer barrel 2 is provided with a central shaft 201, the central shaft 201 is connected with the barrel wall of the outer barrel 2 through an annular transverse plate 202, and the annular transverse plate 202 divides the inner cavity of the outer barrel 2 into an upper cavity and a lower cavity; the side wall of the lower cavity is provided with a fuel hole 203, and the bottom of the lower cavity is connected with the bottom plate 1;
a plurality of fuel nozzle fixing holes 101 are uniformly formed in the base plate 1, a plurality of oxidant nozzle fixing holes 204 are uniformly formed in the annular transverse plate 202, and the positions of the oxidant nozzle fixing holes 204 and the positions of the fuel nozzle fixing holes 101 are in one-to-one correspondence; the fuel nozzle 3 and the oxidant nozzle 4 are connected between each pair of the fuel nozzle fixing holes 101 and the oxidant nozzle fixing holes 204 in a fitting manner; and forms a fuel annular passage between the inner wall of the fuel nozzle 3 and the outer wall of the oxidant nozzle 4;
the number of the oxidant nozzle fixing holes 204 is the same as that of the fuel nozzle fixing holes 101, and the positions of the oxidant nozzle fixing holes are in one-to-one correspondence to be used for correspondingly connecting the fuel nozzle 3 and the oxidant nozzle 4, so that the assembly of the nozzles is simplified. Taking the fuel nozzle fixing holes 101 as an example, the fuel nozzle fixing holes 101 are uniformly distributed in the radial and circumferential directions on the base plate 1, as shown in fig. 4.
As an example, the thickness of the bottom plate 1 may be 2-8mm, and the number of the fuel nozzle fixing holes 101 may be 4-360, forming a uniform distribution of a plurality of turns on the bottom plate 1. The aperture size of the fuel nozzle fixing hole 101 is adapted to the fuel nozzle 3.
As an example, the fuel holes 203 are uniformly distributed on the wall of the outer cylinder 2, and the diameter of the holes may be Φ4mm_Φ40mm, and the number of the holes may be 1-4.
As an example, the number of the oxidant nozzle fixing holes 204 may be 4 to 360 as the number of the fuel nozzle fixing holes 101. The aperture size of the oxidizer nozzle fixing holes 204 is adapted to the oxidizer nozzle 4.
As an example, the annular cross plate 202 may be welded to the central shaft 201 through a central hole; the annular transverse plate 202 and the wall of the outer cylinder 2 can be welded and fixed. The welding and fixing method comprises welding and fixing modes such as electron beam and argon arc welding.
As an example, the fuel nozzle fixing hole 101 and the fuel nozzle 3 may be fixed by screw or welding, and the welding includes welding such as electron beam and brazing. The oxidant nozzle fixing holes 204 and the oxidant nozzle 4 may be fixed by screw or welding, including welding such as electron beam and brazing.
In this embodiment, part of the oxidant enters the central axial hole 205 through the central axial side wall through hole 206 of the upper chamber portion of the outer cylinder 2, and part of the fuel enters the central axial hole 205 through the fuel through hole 207 of the central axial side wall of the lower chamber portion of the outer cylinder 2, and the part of the oxidant and the fuel are ignited by the electric nozzle 6; part of the fuel enters the central axial hole 205 through the central shaft side wall lower fuel through hole 208 of the lower cavity part of the outer barrel 2 and burns with the oxygen-enriched fuel gas, thereby realizing the further increase of the ignition fuel gas energy.
By way of example, the number of the oxidant through holes 206 in the central axis side wall of the upper chamber portion of the outer cylinder 2 is 3 to 8, and the aperture is 0.5mm to 2mm.
By way of example, the number of upper fuel through holes 207 in the central axis side wall of the lower chamber portion of the outer cylinder 2 is 3 to 8, and the aperture is 0.5mm to 2mm.
By way of example, the number of lower fuel through holes 208 in the central axis side wall of the lower chamber portion of the outer cylinder 2 is 3 to 8, and the aperture is 0.5mm to 2mm.
Further, as shown in fig. 5, a central axial hole 205 is provided in the central shaft 201.
The central axial bore 205 is used to provide a firing path for an electrical igniter.
As an example, the bore diameter of the central axial bore 205 may be Φ4mm_Φ20mm.
Still further, as shown in fig. 7, the fuel nozzle 3 has a cylindrical shape, and a plurality of radial fuel inlets 301 are uniformly provided on a sidewall of the fuel nozzle 3 in a circumferential direction. The fuel enters the lower cavity of the outer barrel 2 from the fuel through hole 203 and then enters the fuel annular channel through the radial fuel inlet 301, and the fuel can be ejected from the outlet of the fuel nozzle 3 at a high speed due to the narrow space of the fuel annular channel.
As an example, the diameter of the radial fuel inlets 301 may be Φ1- Φ4mm, and 3-60 radial fuel inlets 301 are disposed along the circumferential direction.
Still further, as shown in connection with fig. 8, the oxidant nozzle 4 has a circumferential through hole, as through the oxidant.
As an example, the aperture of the axial through hole 401 of the oxidizer nozzle 4 may be Φ0.5- Φ6mm;
as an example, as shown in connection with fig. 1, the fuel nozzle 3 and the oxidizer nozzle 4 are connected by brazing or the like.
Based on the liquid rocket engine injector integrating the electric igniter, the injection method of the liquid rocket engine comprises the following steps:
fuel is introduced into the lower cavity through the fuel through holes 203, enters a fuel annular channel between the fuel nozzle 3 and the oxidant nozzle 4 through the radial fuel inlet 301, and is sprayed out at a high speed by the fuel nozzle 3; the oxidant is sprayed out through the axial through holes 401 of the oxidant nozzle 4; the oxidant is further atomized by the fuel sprayed from the fuel nozzle 3 at a high speed and is mixed with the fuel.
The supply of the oxidant and the fuel necessary for the operation of the electric igniter is realized through the oxidant flow hole 206 of the upper chamber portion center shaft and the upper fuel through hole 207 and the lower fuel through hole 208 of the lower chamber portion center shaft, and the oxidant and the fuel are ignited by the electric nozzle. The oxidant near the electric nozzle occupies a relatively large area, is favorable for igniting the oxidant and fuel, has relatively low gas temperature, and can protect the central shaft material of the outer cylinder; part of fuel enters the ignition channel through the lower fuel through hole 208 near the bottom of the central shaft of the lower cavity part to burn with the oxygen-enriched fuel gas, thereby realizing the further increase of the energy of the ignition fuel gas, ensuring the long-time stable operation and providing guarantee for the reliable operation of the engine.
After the mixture of the oxidant and the fuel is injected by the injector, the oxidant and the fuel are combusted in the thrust chamber under the drive of high-energy fuel gas generated by the electric igniter with integrated design to form high-temperature high-pressure fuel gas, and finally the high-speed fuel gas is sprayed out by the contracted-expanded Laval nozzle.
The invention is suitable for high-performance double-component liquid rocket engines, such as liquid oxygen kerosene, liquid oxygen methane, liquid oxygen liquid hydrogen, dinitrogen tetraoxide and dimethylhydrazine. Wherein the oxidizing agent comprises liquid oxygen or dinitrogen tetroxide; the fuel comprises hydrogen, methane or unsymmetrical dimethylhydrazine.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and are not limiting; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims (6)
1. A liquid rocket engine injector integrating a current collection igniter into a whole comprises the following components: bottom plate (1), urceolus (2), fuel nozzle (3), oxidant nozzle (4), top cap (5) and electric nozzle (6), characterized by: the outer cylinder (2) is provided with a central shaft (201), the central shaft (201) is connected with the cylinder wall of the outer cylinder (2) through an annular transverse plate (202), the annular transverse plate (202) divides the inner cavity of the outer cylinder (2) into an upper cavity and a lower cavity, and a fuel through hole (203) is arranged on the side wall of the lower cavity;
the bottom of the lower cavity is connected with the bottom plate (1), a plurality of fuel nozzle fixing holes (101) are uniformly formed in the bottom plate (1), a plurality of oxidant nozzle fixing holes (204) are uniformly formed in the annular transverse plate (202), the positions of the oxidant nozzle fixing holes (204) and the positions of the fuel nozzle fixing holes (101) are in one-to-one correspondence, the fuel nozzles (3) and the oxidant nozzles (4) are correspondingly connected between each pair of fuel nozzle fixing holes (101) and the oxidant nozzle fixing holes (204), and a fuel annular channel is formed between the inner wall of the fuel nozzles (3) and the outer wall of the oxidant nozzles (4);
the central shaft (201) is provided with a central axial hole (205), the upper part of the central shaft (201) is connected with the electric nozzle (6), the central shaft side wall of the upper cavity part is uniformly provided with an oxidant through hole (206), and the central shaft side wall of the lower cavity part is uniformly provided with a group of upper fuel through holes (207) and a group of lower fuel through holes (208).
2. The liquid rocket engine injector integrating a current collecting igniter as defined in claim 1 wherein: the top cover (5) is provided with an oxidant inlet hole (501).
3. The liquid rocket engine injector integrating a current collecting igniter as defined in claim 2 wherein: the fuel nozzle (3) is cylindrical, and a plurality of radial fuel inlets (301) are uniformly arranged on the side wall of the fuel nozzle (3) along the circumferential direction.
4. A liquid rocket engine injector integrating a current collecting igniter as defined in claim 1, 2 or 3 wherein: the oxidant nozzle (4) is provided with a central axial bore (401).
5. The liquid rocket engine injector integrating a current collecting igniter as defined in claim 4 wherein: the base plate (1) is connected with the outer cylinder (2) through argon arc welding, electron beam welding or brazing, the outer cylinder (2) is connected with the top cover (5) through argon arc welding, electron beam welding or brazing, and the outer cylinder (2) is connected with the electric nozzle (6) through a thread mode.
6. The liquid rocket engine injector integrating a current collecting igniter as defined in claim 5 wherein: the fuel nozzle (3) is connected with the bottom plate (1) in a threaded or welding mode, the oxidant nozzle (4) is connected with the outer cylinder (2) in a threaded or welding mode, and the fuel nozzle (3) is connected with the oxidant nozzle (4) in a brazing mode.
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| CN201910268289.8A CN109798202B (en) | 2019-04-04 | 2019-04-04 | Liquid rocket engine injector integrating electric igniter |
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| CN201910268289.8A CN109798202B (en) | 2019-04-04 | 2019-04-04 | Liquid rocket engine injector integrating electric igniter |
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| CN109798202A CN109798202A (en) | 2019-05-24 |
| CN109798202B true CN109798202B (en) | 2023-08-22 |
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| CN111412086B (en) * | 2020-05-21 | 2024-11-12 | 安徽九州云箭航天技术有限公司 | A weldless liquid rocket engine injector |
| CN111765017B (en) * | 2020-06-11 | 2023-11-03 | 安徽九州云箭航天技术有限公司 | Torch electric ignition chamber for liquid rocket engine |
| CN111810987A (en) * | 2020-08-13 | 2020-10-23 | 北京星际荣耀空间科技有限公司 | An injection unit structure and a two-component injector |
| CN112431693B (en) * | 2020-11-19 | 2021-11-30 | 北京航空航天大学 | Pin injector, rocket engine and rocket |
| CN113202656B (en) * | 2021-05-28 | 2022-03-04 | 西安航天动力研究所 | Guide plate and injector capable of improving propellant filling synchronism |
| CN113787305B (en) * | 2021-09-01 | 2022-07-22 | 西安远航真空钎焊技术有限公司 | Machining method of injector of air heater |
| CN114215660B (en) * | 2021-11-16 | 2023-07-28 | 北京航天动力研究所 | High-efficient stable injector |
| CN114412664B (en) * | 2021-12-23 | 2023-08-29 | 北京航天动力研究所 | Thrust chamber head structure for reducing ignition impact |
| CN115075983A (en) * | 2022-08-18 | 2022-09-20 | 北京宇航推进科技有限公司 | Gas generator and liquid rocket engine |
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| CN109798202A (en) | 2019-05-24 |
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