CN111852691A - Integrated double-component injector, manufacturing method thereof and aerospace equipment - Google Patents
Integrated double-component injector, manufacturing method thereof and aerospace equipment Download PDFInfo
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- CN111852691A CN111852691A CN202010815011.0A CN202010815011A CN111852691A CN 111852691 A CN111852691 A CN 111852691A CN 202010815011 A CN202010815011 A CN 202010815011A CN 111852691 A CN111852691 A CN 111852691A
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- 238000004519 manufacturing process Methods 0.000 title claims abstract description 20
- 239000000446 fuel Substances 0.000 claims abstract description 123
- 239000003795 chemical substances by application Substances 0.000 claims abstract description 91
- 238000002347 injection Methods 0.000 claims abstract description 67
- 239000007924 injection Substances 0.000 claims abstract description 67
- 239000007800 oxidant agent Substances 0.000 claims description 75
- 230000001590 oxidative effect Effects 0.000 claims description 53
- 238000001816 cooling Methods 0.000 claims description 19
- 238000010146 3D printing Methods 0.000 claims description 11
- 230000005068 transpiration Effects 0.000 claims 2
- 238000002485 combustion reaction Methods 0.000 abstract description 32
- 238000009826 distribution Methods 0.000 abstract description 11
- 238000004891 communication Methods 0.000 abstract description 4
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 239000000306 component Substances 0.000 description 50
- 230000035900 sweating Effects 0.000 description 13
- 238000000034 method Methods 0.000 description 12
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 8
- 238000013461 design Methods 0.000 description 6
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- 239000003380 propellant Substances 0.000 description 4
- 239000000243 solution Substances 0.000 description 4
- 230000007547 defect Effects 0.000 description 3
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- 238000002156 mixing Methods 0.000 description 3
- 238000012360 testing method Methods 0.000 description 3
- 238000010923 batch production Methods 0.000 description 2
- 238000005219 brazing Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 238000001513 hot isostatic pressing Methods 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
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- 238000004458 analytical method Methods 0.000 description 1
- 238000000889 atomisation Methods 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000004140 cleaning Methods 0.000 description 1
- 239000002826 coolant Substances 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
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- 239000007769 metal material Substances 0.000 description 1
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- 210000004243 sweat Anatomy 0.000 description 1
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Classifications
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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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- 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
- F02K9/60—Constructional parts; Details not otherwise provided for
-
- 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
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
- F02K9/64—Combustion or thrust chambers having cooling arrangements
Abstract
The invention relates to the technical field of aerospace equipment, in particular to an integrated double-component injector, a manufacturing method thereof and aerospace equipment. The integrated two-component injector comprises: a fuel agent chamber; the first bottom surface is arranged at the bottom of the fuel agent cavity; the second bottom surface is arranged at the top of the fuel agent cavity and is opposite to the first bottom surface; the injection unit is arranged between the first bottom surface and the second bottom surface in a communication mode; the first bottom surface and the second bottom surface are both curved surface structures. The integrated double-component injector provided by the invention can improve the structural strength of the integrated double-component injector, enables a fuel agent cavity to have isostatic pressure flow equalizing property, enables the flow distribution of each injection unit to be more uniform, and is beneficial to improving the injection combustion efficiency.
Description
Technical Field
The invention relates to the technical field of aerospace equipment, in particular to an integrated double-component injector, a manufacturing method thereof and aerospace equipment.
Background
The injector is a core component of the liquid rocket engine, is positioned at the head of the thrust chamber, and has the functions of uniformly injecting the propellant into the combustion chamber under the specified propellant flow, mixing ratio and injection pressure drop, ensuring that the mixing ratio and mass distribution meet the design state requirements, and rapidly completing the atomization and mixing processes of the propellant so as to ensure that the propellant is efficiently and fully combusted in the combustion chamber. The design level and machining accuracy of the injector greatly affect the stability, efficiency and life of the combustion chamber. Every one percent loss in efficiency through injector tissue combustion means that the engine specific impulse loses the same percentage. The combustion efficiency of a thrust chamber of a general high-thrust liquid rocket engine is over 96 percent, and the combustion chamber efficiency of an injector with excellent performance can reach 99 percent. Besides the combustion efficiency, the injector is also responsible for organizing the stability of combustion, bearing higher injection cavity pressure, bearing the transmission of the whole engine thrust chamber, protecting the hot erosion of high-temperature and high-pressure gas of the combustion chamber to the injector surface, and sometimes considering the problem of the hot protection of the wall of the combustion chamber at the downstream of the injector. In the prior art, although a typical injector design scheme is provided, the upper bottom surface and the lower bottom surface of a fuel cavity of the injector are generally arranged in parallel, a fuel agent enters from one side of the fuel cavity, the flow rate of the fuel agent close to an inlet of the fuel cavity is high, the internal flow rate is low, so that the flow distribution of each injection unit is uneven, and certain influence is caused on the injection combustion efficiency.
Disclosure of Invention
Therefore, the technical problem to be solved by the present invention is to overcome the defect of low combustion efficiency of the injector in the prior art, and to provide an integrated two-component injector with high combustion efficiency.
The invention aims to solve another technical problem of overcoming the defect of high preparation cost of the integrated two-component injector in the prior art, thereby providing a method for manufacturing the integrated two-component injector, which reduces the manufacturing cost.
The invention aims to solve another technical problem of overcoming the defect of low combustion efficiency of an injector of the aerospace device in the prior art, thereby providing the aerospace device with high combustion efficiency of the injector.
In order to solve the above technical problem, the present invention provides an integrated two-component injector, comprising:
a fuel agent chamber;
the first bottom surface is arranged at the bottom of the fuel agent cavity;
the second bottom surface is arranged at the top of the fuel agent cavity and is opposite to the first bottom surface; and
at least one injection unit which is communicated between the first bottom surface and the second bottom surface;
the first bottom surface and the second bottom surface are both curved surface structures.
Further, the curved middle portions of the first and second bottom surfaces are close to each other, so that the fuel agent chamber is configured as a hyperboloid concave lens structure.
Further, at least one side of the fuel agent cavity is provided with a fuel agent inlet.
Furthermore, at least one sweating cooling channel is arranged on the first bottom surface in a penetrating mode.
Further, the sweating cooling channel is configured as a meander-shaped structure.
Further, still include:
and the oxidant cavity takes the second bottom surface as the bottom and takes a third bottom surface far away from the first bottom surface as the top.
Further, a plurality of injection units with different lengths are arranged between the first bottom surface and the second bottom surface.
Further, the injection unit is suitable for communicating the fuel agent cavity and/or the oxidant cavity with the outside; the injection unit includes:
a fuel agent nozzle which is at least partially communicated with the fuel agent cavity, wherein one end of the fuel agent nozzle is connected with the first bottom surface and penetrates through the first bottom surface; and
and the first end of the oxidant nozzle is connected with the second bottom surface and penetrates through the second bottom surface to be communicated with the oxidant cavity, and the second end of the oxidant nozzle is at least partially arranged in the fuel nozzle.
Further, at least one radial hole is arranged on the side wall of the fuel nozzle;
the oxidant nozzle penetrates through the inner part of the oxidant nozzle and is communicated with the injection port together with the radial hole.
Further, the inner side wall of one end, far away from the injection opening, of the oxidant nozzle is provided with at least one throttling hole.
Further, the radial hole is of a raindrop-shaped structure.
Further, an annular cavity is formed between the inner side wall of the fuel nozzle and the outer side wall of the oxidant nozzle.
Further, the radial hole is arranged opposite to the annular cavity.
Furthermore, an annular gap is formed between the inner side wall of the fuel nozzle and the outer side wall of the oxidant nozzle, one end of the annular gap is communicated with the annular cavity, and the other end of the annular gap is communicated with the injection port.
According to the manufacturing method of the integrated two-component injector, the integrated two-component injector is manufactured through 3D printing.
The aerospace device provided by the invention comprises the integrated two-component injector.
The technical scheme of the invention has the following advantages:
1. according to the integrated double-component injector provided by the invention, the first bottom surface and the second bottom surface are both of curved surface structures, so that the pressure bearing capacity of a fuel agent cavity is improved, and because the curved surfaces with the same thickness are higher than the plane pressure bearing capacity, the curved surfaces can uniformly disperse the borne pressure along the whole surface and uniformly diffuse the pressure to all positions of the bottom surface, so that the curved surfaces can bear larger pressure, and the structural strength of the integrated double-component injector is improved.
2. According to the integrated double-component injector provided by the invention, the fuel agent cavity is constructed in a hyperboloid concave lens type structure, and the bent middle parts of the first bottom surface and the second bottom surface are close to each other, so that the fuel agent flow rate of the edge area of the fuel agent cavity is lower, the fuel agent flow rate of the central area of the fuel agent cavity is higher, the fuel agent cavity has an isostatic pressure flow equalizing characteristic, the flow distribution of each injection unit is more uniform, and the injection combustion efficiency is favorably improved.
3. According to the integrated double-component injector provided by the invention, the sweating cooling channel structure group with the zigzag structure is arranged on the first bottom surface in an array manner, so that a fuel agent in the fuel agent cavity can slowly flow out from the zigzag channel, and the sweating cooling effect is realized on the gas surface of the first bottom surface.
4. According to the integrated two-component injector provided by the invention, the injection units arranged between the first bottom surface and the second bottom surface are designed in different lengths, so that the acoustic frequency of the injection units is staggered, and the stability of combustion is improved.
5. According to the manufacturing method of the integrated two-component injector, the integrated two-component injector is manufactured through 3D printing, the development cost of the integrated two-component injector can be reduced, the production efficiency of products is improved, and the three-bottom two-cavity injector structure and hundreds of injection units are printed together in an integral part form by depending on the 3D printing process technology, so that the number of parts is greatly reduced, and the product cost of the integrated two-component injector is reduced; meanwhile, the parts of the integrated double-component injector are integrated into one by hundreds of parts, so that the production efficiency of the product is improved, the production period is greatly shortened, the inherent reliability of the product is improved, and the yield of the product is improved; in addition, the integrated structural design reduces many manual links such as brazing, argon arc welding and the like, and creates conditions for automatic batch production of integrated double-component injector products.
6. According to the aerospace device, the integrated two-component injector is adopted, so that the combustion stability of the aerospace device can be improved, and the overall structural strength of the integrated two-component injector is improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments or the prior art descriptions will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a schematic cross-sectional view of an integrated two-component injector according to the present invention;
FIG. 2 is an enlarged view of FIG. 1 at A;
FIG. 3 is a schematic view of an injector unit of the present invention;
FIG. 4 is a schematic cross-sectional view of a bottom structure of the integrated two-component injector of the present invention.
Description of reference numerals:
10-first base, 11-transpiration cooling channels, 20-second base, 30-third base;
40-oxidant chamber, 41-oxidant inlet, 50-fuel agent chamber, 51-fuel agent inlet;
60-oxidant nozzle, 61-oxidant nozzle inlet end, 62-orifice, 63-oxidant nozzle outlet end;
70-fuel agent nozzle, 71-radial hole, 72-annular cavity, 73-annular gap, 74-injection nozzle;
80-a combustion chamber.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that unless otherwise explicitly stated or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
In addition, the technical features involved in the different embodiments of the present invention described below may be combined with each other as long as there is no conflict between them.
Example one
As shown in fig. 1-4, the present embodiment provides an integrated two-component injector, comprising:
a fuel agent chamber 50;
a first bottom surface 10 disposed at the bottom of the fuel agent chamber 50;
a second bottom surface 20 disposed at the top of the fuel agent chamber 50 and opposite to the first bottom surface 10; and
at least one injection unit, which is arranged between the first bottom surface 10 and the second bottom surface 20 in a communication manner;
the first bottom surface 10 and the second bottom surface 20 are both curved structures.
Preferably, the fuel agent cavity 50 is configured as a closed or partially open cavity structure, the bottom and the top of the cavity structure are respectively enclosed by a first bottom surface 10 and a second bottom surface 20, at least one injection unit is arranged between the first bottom surface 10 and the second bottom surface 20, that is, the injection unit is arranged in the fuel agent cavity 50, and the injection unit is open up and down, so that the first bottom surface 10 and the second bottom surface 20 penetrate through the injection unit, and the upper space of the second bottom surface 20 is communicated with the lower space of the first bottom surface 10.
The embodiment provides an integrated two-component injector, the first bottom surface 10 and the second bottom surface 20 are both curved surface structures, so that the pressure bearing capacity of a fuel agent cavity is improved, and since the curved surfaces with the same thickness are higher than the flat surface pressure bearing capacity, the curved surfaces can uniformly disperse the borne pressure along the whole surface and uniformly diffuse the pressure to all positions of the bottom surface, so that the curved surfaces can bear larger pressure, and the structural strength of the integrated two-component injector is improved.
Specifically, the curved middle portions of the first and second bottom surfaces 10 and 20 are close to each other, so that the fuel agent chamber 50 is configured as a hyperbolic concave lens structure.
Specifically, at least one side of the fuel agent cavity 50 is provided with a fuel agent inlet 51, and the fuel agent inlet 51 is used for introducing fuel agent into the fuel agent cavity 50. Preferably, the fuel agent inlet 51 is disposed on a vertical wall surface connecting the first bottom surface 10 and the second bottom surface 20, so that an injection direction of the fuel agent from the fuel agent inlet 51 is perpendicular to or at an angle with an extending direction of the injection unit. The fuel agent chamber 50 is constructed in a hyperbolic concave lens structure, and the curved middle portions of the first bottom surface 10 and the second bottom surface 20 are close to each other, so that the flow area of the fuel agent chamber 50 at the fuel agent inlet 51 is large, where the flow rate of the fuel agent is low, and the flow area at the center of the fuel agent chamber 50 is small, where the flow rate of the fuel agent is high, which makes the pressure distribution inside the fuel agent chamber 50 more uniform, preferably, the pressure distribution is verified by three-dimensional fluid simulation analysis.
In the integrated two-component injector provided by this embodiment, the fuel agent cavity 50 is configured as a hyperboloid concave lens structure, and the curved middle portions of the first bottom surface 10 and the second bottom surface 20 are close to each other, so that the fuel agent flow rate in the edge area of the fuel agent cavity 50 is low, the fuel agent flow rate in the central area of the fuel agent cavity 50 is high, and further the fuel agent cavity 50 has an isostatic pressure flow equalizing characteristic, and the flow distribution of each injection unit is more uniform, which is beneficial to improving the injection combustion efficiency.
Specifically, at least one sweating cooling channel 11 is further arranged on the first bottom surface 10 in a penetrating manner.
Specifically, the sweat cooling passage 11 is configured in a meander-shaped structure.
The sweating cooling channel 11 penetrates through the first bottom surface 10 through a zigzag channel arrangement form, so that the fuel agent cavity 50 can communicate with the outside, in an application environment of the integrated two-component injector, the outside is usually a combustion chamber, that is, the fuel agent cavity 50 and the combustion chamber are separated by the first bottom surface 10, and the sweating cooling channel 11 arranged on the first bottom surface 10 communicates the fuel agent cavity 50 with the combustion chamber 80. Since the first bottom surface 10 is close to the combustion chamber 80, the combustion chamber 80 has a high temperature, and the first bottom surface 10 needs to be cooled by a cooling measure, the first bottom surface 10 is usually made of a special porous metal material, and the first bottom surface 10 is also usually called a porous panel.
In the integrated two-component injector provided in this embodiment, the sweating cooling channel structure group with the zigzag structure is arranged on the first bottom surface 10 in an array manner, so that the fuel agent in the fuel agent cavity 50 can slowly flow out from the zigzag channel, thereby performing the sweating cooling function on the gas surface of the first bottom surface 10.
Specifically, the integrated two-component injector further comprises:
an oxidizer chamber 40, wherein the oxidizer chamber 40 is at the bottom of the second bottom surface 20 and at the top of a third bottom surface 30 disposed away from the first bottom surface 10.
The integrated double-component injector is of a three-bottom and two-cavity structure, the three bottoms are respectively a first bottom surface 10, a second bottom surface 20 and a third bottom surface 30, a fuel agent cavity 50 is formed between the first bottom surface 10 and the second bottom surface 20, and an oxidant cavity 40 is formed between the second bottom surface 20 and the third bottom surface 30. At least one side of the oxidant chamber 40 is provided with an oxidant inlet 41, and the oxidant inlet 41 is used for introducing an oxidant into the oxidant chamber 40. Preferably, the oxidant inlet 41 is provided on a vertical wall surface connecting the second bottom surface 20 and the third bottom surface 30. The second bottom surface 20 has a curved surface structure, so that the structural strength of the integrated two-component injector can be improved.
Example two
In the integrated two-component injector according to the present embodiment, the injection unit provided inside the integrated two-component injector will be described in detail.
Specifically, a plurality of injection units with different lengths are arranged between the first bottom surface 10 and the second bottom surface 20.
Because a plurality of injection units are arranged in the fuel agent cavity 50, the distribution form of the plurality of injection units in the fuel agent cavity 50 can be honeycomb distribution, checkerboard distribution, concentric circle distribution and the like, and in addition, the structural form of the injection units comprises self-impact type, mutual impact type, coaxial straight-flow type, coaxial centrifugal type and the like. Preferably, in this embodiment, the injection unit is a coaxial direct injection unit.
The embodiment provides an integrated two-component injector, and the injection units arranged between the first bottom surface 10 and the second bottom surface 20 are designed in different lengths, so that the acoustic frequency of the injection units can be staggered, and the stability of combustion can be improved.
In particular, the injection unit is adapted to communicate the fuel agent chamber 50 and/or the oxidant chamber 40 with the outside; the injection unit includes:
a fuel nozzle 70 at least partially communicating with the fuel chamber 50, the fuel nozzle 70 being connected to the first bottom surface 10 at one end and penetrating the first bottom surface 10; and
the first end of the oxidizer nozzle 60 is connected to the second bottom surface 20 and penetrates the second bottom surface 20 to communicate with the oxidizer cavity 40, and the second end of the oxidizer nozzle 60 is at least partially arranged inside the fuel nozzle 70.
At least one radial hole 71 is arranged on the side wall of the fuel nozzle 70;
the fuel agent nozzle 70 is at least partially in communication with the fuel agent chamber 50, in this embodiment, in particular via at least one radial hole 71 provided in a side wall of the fuel agent nozzle 70 in communication with the fuel agent chamber 50, the radial hole 71 being capable of facilitating the entry of fuel agent into the injector unit.
The oxidizer nozzle 60 penetrates the inside thereof and is communicated with the injector 74 together with the radial holes 71.
One end of the fuel nozzle 70 is connected to the first bottom surface 10 and penetrates the first bottom surface 10, so that an injection port 74 penetrating the first bottom surface 10 is formed at a contact position of the injection unit and the first bottom surface 10.
The first end of the oxidant nozzle 60 is connected to and penetrates through the second bottom surface 20, so that an oxidant nozzle inlet end 61 penetrating through the second bottom surface 20 is formed at a contact position of the injection unit and the second bottom surface 20, and the oxidant nozzle inlet end 61 communicates the oxidant chamber 40 with the injection unit, so that oxidant in the oxidant chamber 40 can enter the injection unit from the oxidant nozzle inlet end 61.
The second end of the oxidant nozzle 60 is at least partially arranged inside the fuel nozzle 70, the fuel nozzle 70 and the oxidant nozzle 60 of the injection unit are arranged in a nested structure, and the oxidant nozzle 60 is arranged inside the fuel nozzle 70 and forms a certain annular gap 73; meanwhile, since the upper portion and the lower portion of the injection unit are respectively connected to the second bottom surface 20 and the first bottom surface 10 and penetrate through the injection unit, the oxidant nozzle 60 penetrates through the oxidant nozzle 60, so that the oxidant nozzle outlet 63 is formed in the oxidant nozzle 60 inside the fuel nozzle 70, and the oxidant nozzle 60 and the fuel nozzle 70 share the injection port 74, so that the fuel entering the injection unit through the radial holes 71 can be mixed with the oxidant entering through the oxidant nozzle inlet 61 and flowing out of the oxidant nozzle outlet 63, and the mixed fuel and oxidant are discharged from the injection port 74 together and injected into the combustion chamber 80.
Preferably, the inner sidewall of the oxidant nozzle 60 at the end remote from the injection port 74 is provided with at least one orifice 62. As a further preferable form, the inner side wall of the oxidizer nozzle 60 at an end remote from the injection port 74 is continuously provided with two throttle holes 62. The orifice 62 is formed by the inner wall of the oxidant nozzle 60 protruding towards the center, so that the initial flow area of the orifice 62 is reduced, and the oxidant nozzle 60 adopts a double-orifice design, so that the anti-interference capability of oxidant during flowing can be enhanced, and the combustion stability of the injector is enhanced.
Preferably, the radial holes 71 are raindrop-shaped structures. The radial holes of the raindrop-shaped structure can improve the flow coefficient of the fuel agent nozzle 70, and are favorable for reducing the flow resistance of the fuel agent nozzle 70 at the same injection speed.
Preferably, an annular cavity 72 is formed between the inner sidewall of the fuel agent nozzle 70 and the outer sidewall of the oxidant nozzle 60.
Preferably, an annular gap 73 is further formed between the inner side wall of the fuel nozzle 70 and the outer side wall of the oxidant nozzle 60, one end of the annular gap 73 is communicated with the annular cavity 72, and the other end is communicated with the injection port 74.
The annular plenum 72 can enhance the stability and uniformity of fuel agent flow at the annular gap 73.
Preferably, the radial hole 71 is disposed opposite to the annular cavity 72, so that the fuel agent enters the annular cavity 72 preferentially after entering the injection unit through the radial hole 71, and the injector is equivalent to a collector and plays a role in flow equalization.
EXAMPLE III
The present embodiment provides a method for manufacturing an integrated two-component injector, which is manufactured by 3D printing according to the first and second embodiments.
According to the manufacturing method of the integrated two-component injector, the integrated two-component injector is manufactured through 3D printing, the development cost of the integrated two-component injector can be reduced, the production efficiency of products is improved, a three-bottom two-cavity injector structure and hundreds of injection units are printed together in an integral part form by depending on a 3D printing process technology, the number of parts is greatly reduced, and the product cost of the integrated two-component injector is reduced; meanwhile, the parts of the integrated double-component injector are integrated into one by hundreds of parts, so that the production efficiency of the product is improved, the production period is greatly shortened, the inherent reliability of the product is improved, and the yield of the product is improved. In addition, the integrated structural design reduces many manual links such as brazing, argon arc welding and the like, and creates conditions for automatic batch production of integrated double-component injector products.
The zigzag sweating cooling channel structure group is arranged on the first bottom surface 10 in an array mode by utilizing a 3D printing process, and fuel slowly flows out from the zigzag channel to play a role in sweating cooling on the gas surface of the first bottom surface 10. The porous panel has the same functions and effects as the traditional porous panel, but the cost is greatly reduced compared with the traditional porous panel, and the porous panel is only 1/5 of the traditional porous panel, meanwhile, the traditional porous panel is complex in process and multiple in processes, the first bottom surface 10 made by adopting a 3D printing process is simple in process and few in processes, and the production period can be greatly shortened.
Preferably, the integrated two-component injector integral structure and the injection unit are manufactured by adopting an SLM laser printing forming process.
Preferably, the grade of the 3D printing powder material is GH3625, the particle size of the powder particles is 10-80 μm, the powder particles can pass through a No.100 sieve, and the weight of the powder particles passing through the No.100 sieve is not less than 95%.
The production process flow of the product mainly comprises the following steps: printing by adopting SLM laser 3D printing equipment → cleaning products → hot isostatic pressing → solution heat treatment → machining → liquid flow test, wherein the specific technological parameters are as follows:
hot isostatic pressing: the temperature range is 1050-1180 ℃, the pressure is more than 150MPa, the heat preservation and pressure maintaining time is 3-5 h, and the air cooling is carried out under the protection of argon.
Solution heat treatment: keeping the temperature for 2h in a temperature range of 1090-1200 ℃, and rapidly cooling by argon.
And (4) performing a water flow resistance test of the oxidant nozzle and the fuel nozzle according to the use requirements, and finishing the production of the product after the test is qualified.
Example four
In this embodiment, referring to specific examples, the integrated two-component injector provided in the above embodiments is described in more detail, preferably, the first bottom surface 10 and the second bottom surface 20 are both curved structures, so that the fuel agent cavity 50 is configured as a hyperboloid concave lens structure, and the spherical arc radius of the first bottom surface 10 and the second bottom surface 20 is preferably 2 to 4 times the diameter of the integrated two-component injector.
Preferably, the radial holes 71 are raindrop-shaped, each fuel agent nozzle 70 is provided with 2 rows of radial holes, 4 radial holes are arranged in each row, the radial holes 71 are circumferentially and uniformly distributed on the side wall of the fuel agent nozzle 70, and the total area of the raindrop-shaped radial holes is preferably 4-6 times the area of the annular gap 73.
Preferably, the oxidant nozzle 60 and the fuel nozzle 70 are coaxially arranged, the axis of the oxidant nozzle is parallel to the axis of the integrated two-component injector, and the outlet end 63 of the oxidant nozzle is retracted by 4-10 mm relative to the injection port 74.
Upstream of the oxidizer nozzle 60, 2 laval-type orifice segments were used, and as shown in fig. 3, the orifice diameter D1 was calculated according to equation 1 below.
Equation 1:
qo-oxidant flow per injection unit
The Cdo-oxidant nozzle flow coefficient is generally 0.75-0.95
D1-orifice diameter
Rho-density of oxidizing agent
Pio-oxidant chamber pressure
Pe-combustion chamber pressure
An annular cavity is arranged at the upstream of an annular gap formed by the fuel nozzle and the oxidant nozzle, the cross-sectional area of the annular cavity is generally 3-5 times of that of the downstream annular gap, and as shown in fig. 3, the sizes of the downstream annular gaps D2 and D3 are calculated according to the following formula 2.
Equation 2:
where Qf-fuel agent flow per injector unit;
cdf-the flow coefficient of the fuel nozzle, generally 0.7-0.9
D2-outer diameter of annular gap
D3-inner diameter of annular gap
Rho-fuel density
k-fuel adiabatic index
Pif-Fuel cell pressure
Pe-combustion chamber pressure
The structure of the zigzag sweating cooling channel in the first bottom surface 10 is shown in fig. 4, the diameter D4 of the channel is preferably 0.1-1.0 mm, the consumption of the sweating cooling agent accounts for 1% -10% of the total amount of the fuel agent, the channels are uniformly distributed on the first bottom surface 10, and the distance between the channels is not more than 10 mm.
EXAMPLE five
The present embodiment provides an aerospace device comprising an integrated two component injector as described in the previous embodiments.
By adopting the integrated double-component injector, the combustion stability of the aerospace equipment can be improved, and the overall structural strength of the integrated double-component injector is improved.
It should be understood that the above-described embodiments are merely examples for clarity of description and are not intended to limit the scope of the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. This list is neither intended to be exhaustive nor exhaustive. And obvious variations or modifications therefrom are within the scope of the invention.
Claims (16)
1. An integrated two-component injector, comprising:
a fuel agent chamber (50);
a first bottom surface (10) arranged at the bottom of the fuel agent cavity (50);
a second bottom surface (20) disposed at the top of the fuel agent chamber (50) and opposite to the first bottom surface (10); and
at least one injection unit, which is arranged in a communicating manner between the first bottom (10) and the second bottom (20);
the first bottom surface (10) and the second bottom surface (20) are both curved surface structures.
2. The integrated two-component injector according to claim 1, wherein the curved midpoints of the first and second bottom surfaces (10, 20) are proximate such that the fuel agent chamber (50) is configured as a hyperbolic concave lens structure.
3. The integrated two-component injector according to claim 2, wherein at least one side of the fuel agent chamber (50) is provided with a fuel agent inlet (51).
4. The integrated two-component injector according to claim 1, characterized in that said first bottom surface (10) is further provided with at least one transpiration cooling channel (11) therethrough.
5. The integrated two-component injector according to claim 4, characterized in that the transpiration cooling channel (11) is configured as a meander-shaped structure.
6. The integrated two-component injector of any of claims 1 to 5, further comprising:
an oxidizer chamber (40), the oxidizer chamber (40) having the second bottom surface (20) as a bottom and a third bottom surface (30) disposed away from the first bottom surface (10) as a top.
7. The integrated two-component injector according to claim 6, characterized in that between said first bottom surface (10) and said second bottom surface (20) several of said injection units of different length are provided.
8. The integrated two-component injector according to claim 7, characterized in that said injection unit is adapted to communicate said fuel agent chamber (50) and/or said oxidizer chamber (40) with the outside; the injection unit includes:
a fuel agent nozzle (70) at least partially communicated with the fuel agent cavity (50), wherein one end of the fuel agent nozzle (70) is connected with the first bottom surface (10) and penetrates through the first bottom surface (10); and
and the first end of the oxidant nozzle (60) is connected with the second bottom surface (20) and penetrates through the second bottom surface (20) to be communicated with the oxidant cavity (40), and the second end of the oxidant nozzle is at least partially arranged inside the fuel nozzle (70).
9. The integrated two-component injector according to claim 8, characterized in that said fuel agent nozzle (70) is provided with at least one radial hole (71) in its side wall;
the oxidant nozzle (60) penetrates through the interior and is communicated with the injection opening (74) together with the radial hole (71).
10. The integrated two-component injector according to claim 9, wherein an inner side wall of an end of the oxidizer nozzle (60) remote from the injection port (74) is provided with at least one orifice (62).
11. The integrated two-component injector according to claim 9, characterized in that said radial holes (71) are of a raindrop-shaped configuration.
12. The integrated two-component injector of claim 9, wherein an annular pocket (72) is formed between the inner sidewall of the fuel nozzle (70) and the outer sidewall of the oxidant nozzle (60).
13. The integrated two-component injector according to claim 12, characterized in that said radial holes (71) are disposed directly opposite said annular volume (72).
14. The integrated two-component injector according to claim 12, wherein an annular gap (73) is further formed between an inner sidewall of the fuel nozzle (70) and an outer sidewall of the oxidizer nozzle (60), and one end of the annular gap (73) is communicated with the annular cavity (72) and the other end is communicated with the injection port (74).
15. A method of manufacturing an integrated two component injector, characterized in that the integrated two component injector as claimed in any of the claims 1-14 is made by 3D printing.
16. An aerospace device comprising an integrated two component injector as claimed in any one of claims 1 to 14.
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| CN113339159A (en) * | 2021-07-06 | 2021-09-03 | 西安航天动力研究所 | Coaxial double-centrifugal injector based on 3D printing and liquid oxygen kerosene rocket engine |
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| CN114000959A (en) * | 2021-11-09 | 2022-02-01 | 合肥中科重明科技有限公司 | Integrated injector |
| CN117514519A (en) * | 2023-11-10 | 2024-02-06 | 北京智创联合科技股份有限公司 | Novel rocket engine injector sweating panel and manufacturing method |
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