CN111852691B - 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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- CN111852691B CN111852691B CN202010815011.0A CN202010815011A CN111852691B CN 111852691 B CN111852691 B CN 111852691B CN 202010815011 A CN202010815011 A CN 202010815011A CN 111852691 B CN111852691 B CN 111852691B
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- 238000004519 manufacturing process Methods 0.000 title claims abstract description 20
- 239000000446 fuel Substances 0.000 claims abstract description 126
- 239000003795 chemical substances by application Substances 0.000 claims abstract description 69
- 238000002347 injection Methods 0.000 claims abstract description 66
- 239000007924 injection Substances 0.000 claims abstract description 66
- 239000007800 oxidant agent Substances 0.000 claims description 70
- 230000001590 oxidative effect Effects 0.000 claims description 33
- 238000001816 cooling Methods 0.000 claims description 20
- 238000010146 3D printing Methods 0.000 claims description 11
- 210000004243 sweat Anatomy 0.000 claims description 7
- 230000000149 penetrating effect Effects 0.000 claims description 6
- 238000004891 communication Methods 0.000 claims description 4
- 238000005452 bending Methods 0.000 claims 1
- 238000002485 combustion reaction Methods 0.000 abstract description 32
- 238000009826 distribution Methods 0.000 abstract description 10
- 239000000306 component Substances 0.000 description 50
- 238000000034 method Methods 0.000 description 12
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 8
- 230000008569 process Effects 0.000 description 7
- 238000013461 design Methods 0.000 description 6
- 229910052786 argon Inorganic materials 0.000 description 4
- 239000003380 propellant Substances 0.000 description 4
- 230000035900 sweating Effects 0.000 description 4
- 230000007547 defect Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 239000007788 liquid Substances 0.000 description 3
- 238000002156 mixing Methods 0.000 description 3
- 239000000843 powder Substances 0.000 description 3
- 239000000243 solution Substances 0.000 description 3
- 238000012360 testing method Methods 0.000 description 3
- 238000010923 batch production Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000005219 brazing Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000002737 fuel gas Substances 0.000 description 2
- 239000007789 gas Substances 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
- 239000002245 particle Substances 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 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
- 230000009977 dual effect Effects 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000007648 laser printing Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 238000004321 preservation Methods 0.000 description 1
- 238000007639 printing Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- 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
-
- 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 dual-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 communicated between the first bottom surface and the second bottom surface; the first bottom surface and the second bottom surface are both of curved structures. The integrated double-component injector provided by the invention can improve the structural strength of the integrated double-component injector, and ensures that the fuel agent cavity has the isostatic pressure equalizing characteristic, the flow distribution of each injection unit is more uniform, and the injection combustion efficiency is improved.
Description
Technical Field
The invention relates to the technical field of aerospace equipment, in particular to an integrated dual-component injector, a manufacturing method thereof and aerospace equipment.
Background
The injector is a core component of the liquid rocket engine and is positioned at the head of the thrust chamber, and the injector has the functions of uniformly injecting the propellant into the combustion chamber under the specified flow, mixing ratio and injection pressure drop of the propellant, ensuring that the mixing ratio and the mass distribution meet the design state requirements, and rapidly completing the atomization and mixing processes of the propellant so that the propellant is efficiently and fully combusted in the combustion chamber. The design level and machining accuracy of the injector have a great impact on the stability, efficiency and life of the combustion chamber. Each loss of efficiency of combustion through the injector tissue means the same percentage of engine specific performance loss. The combustion efficiency of the thrust chamber of the general high-thrust liquid rocket engine is over 96 percent, and the combustion chamber efficiency of the injector with excellent performance can reach 99 percent. Besides combustion efficiency, the injector is also responsible for the stability of tissue combustion, bearing higher injection cavity pressure, bearing the transmission of the whole engine thrust chamber, and protecting the injector face from thermal erosion by high-temperature and high-pressure fuel gas of the combustion chamber, and sometimes considering the problem of thermal protection of the downstream combustion chamber wall of the injector. In the prior art, although a typical injector design scheme exists, the upper bottom surface and the lower bottom surface of the fuel cavity are generally arranged in parallel, the fuel enters from one side of the fuel cavity, the flow velocity of the fuel near the inlet of the fuel cavity is high, the internal flow velocity is low, so that the flow of each injection unit is unevenly distributed, and the injection combustion efficiency is affected to a certain extent.
Disclosure of Invention
Therefore, the technical problem to be solved by the invention is to overcome the defect of lower combustion efficiency of the injector in the prior art, thereby providing the integrated dual-component injector with higher combustion efficiency.
The invention aims to overcome the defect of high preparation cost of the integrated double-component injector in the prior art, thereby providing a manufacturing method of the integrated double-component injector with reduced manufacturing cost.
The invention aims to overcome the defect of low combustion efficiency of the 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 technical problems, the invention provides an integrated dual-component injector, which 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; and
at least one injection unit communicated between the first bottom surface and the second bottom surface;
the first bottom surface and the second bottom surface are both of curved structures.
Further, the first bottom surface is close to the curved middle part of the second bottom surface, so that the fuel agent cavity is constructed into a hyperboloid concave lens structure.
Further, at least one side of the fuel agent cavity is provided with a fuel agent inlet.
Further, at least one sweating cooling channel is arranged on the first bottom surface in a penetrating way.
Further, the sweat cooling channels are configured in a curved loop configuration.
Further, the method further comprises the following steps:
and the oxidant cavity takes the second bottom surface as the bottom and takes a third bottom surface which is 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 adapted to communicate the fuel agent chamber and/or the oxidant chamber with the outside; the insufflating unit includes:
a fuel agent nozzle at least partially communicating with the fuel agent chamber, the fuel agent nozzle having one end connected to and penetrating 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 inside the fuel agent nozzle.
Further, the fuel agent nozzle sidewall is provided with at least one radial hole;
the inside of the oxidant nozzle penetrates through and is communicated with the injection port together with the radial hole.
Further, an inner sidewall of the oxidant nozzle remote from one end of the injection port is provided with at least one orifice.
Further, the radial holes are 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 holes are arranged opposite to the annular accommodating cavity.
Further, an annular gap is formed between the inner side wall of the fuel agent nozzle and the outer side wall of the oxidant nozzle, one end of the annular gap is communicated with the annular containing cavity, and the other end of the annular gap is communicated with the injection port.
The integrated double-component injector manufacturing method provided by the invention is characterized in that the integrated double-component injector is manufactured through 3D printing.
The aerospace device provided by the invention comprises the integrated dual-component injector.
The technical scheme of the invention has the following advantages:
1. according to the integrated dual-component injector provided by the invention, the first bottom surface and the second bottom surface are of the curved surface structures, so that the pressure bearing capacity of the fuel agent cavity is improved, and as the curved surface with the same thickness is higher than the plane pressure bearing capacity, the curved surface can uniformly disperse the bearing pressure along the whole surface and uniformly spread the pressure to all positions of the bottom surface, so that the curved surface can bear larger pressure, and the structural strength of the integrated dual-component injector is improved.
2. According to the integrated dual-component injector provided by the invention, the fuel agent cavity is constructed into the hyperboloid concave lens structure, and the first bottom surface is close to the curved middle part of the second bottom surface, so that the fuel agent flow velocity of the edge area of the fuel agent cavity is lower, the fuel agent flow velocity of the central area of the fuel agent cavity is higher, the fuel agent cavity has the isostatic pressure flow equalization characteristic, the flow distribution of each injection unit is more uniform, and the improvement of the injection combustion efficiency is facilitated.
3. According to the integrated dual-component injector provided by the invention, the perspiration cooling channel structure group with the curved-back structure is arranged on the first bottom surface in a matrix manner, so that the fuel agent in the fuel agent cavity can slowly flow out from the curved-back channel, and the perspiration cooling effect is achieved on the fuel gas surface of the first bottom surface.
4. According to the integrated dual-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 combustion stability is improved.
5. According to the manufacturing method of the integrated double-component injector, the integrated double-component injector is manufactured through 3D printing, so that the development cost of the integrated double-component injector can be reduced, the production efficiency of products is improved, the three-bottom two-cavity injector structure and hundreds of injection units are printed together in the form of one integral part by means of a 3D printing process technology, the number of parts is greatly reduced, and the product cost of the integrated double-component injector is reduced; meanwhile, the number of parts of the integrated double-component injector is integrated into one piece from hundreds of pieces, 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 a plurality of 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 equipment provided by the invention, the integrated dual-component injector is adopted, so that the combustion stability of the aerospace equipment can be improved, and the overall structural strength of the integrated dual-component injector can be improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the present invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic cross-sectional view of an integrated two-component injector of the present invention;
FIG. 2 is an enlarged view of FIG. 1 at A;
FIG. 3 is a schematic illustration of an injection unit of the present invention;
FIG. 4 is a schematic cross-sectional view of a base structure of an integrated two-component injector of the present invention.
Reference numerals illustrate:
10-a first bottom surface, 11-an sweating cooling channel, 20-a second bottom surface, 30-a third bottom surface;
40-oxidant chamber, 41-oxidant inlet, 50-fuel chamber, 51-fuel inlet;
60-oxidant nozzle, 61-oxidant nozzle inlet end, 62-orifice, 63-oxidant nozzle
An outlet end;
70-fuel agent nozzle, 71-radial hole, 72-annular cavity, 73-annular gap, 74-injection port;
80-combustion chamber.
Detailed Description
The following description of the embodiments of the present invention will be made apparent and fully in view of the accompanying drawings, in which some, but not all embodiments of the invention are shown. 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.
In the description of the present invention, it should be noted that the directions or positional relationships indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, are merely for convenience of describing the present invention and simplifying the description, and do not indicate or imply that the apparatus or elements 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 explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
In addition, the technical features of the different embodiments of the present invention described below may be combined with each other as long as they do not collide with each other.
Example 1
Referring to 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 chamber 50;
a second bottom surface 20 disposed on top of the fuel agent chamber 50 and opposite to the first bottom surface 10; and
at least one injection unit disposed in communication between the first bottom surface 10 and the second bottom surface 20;
the first bottom surface 10 and the second bottom surface 20 are both curved structures.
Preferably, the fuel agent chamber 50 is configured as a closed or partially open chamber structure, the bottom and the top of the fuel agent chamber are respectively surrounded by the first bottom surface 10 and the second bottom surface 20, at least one injection unit is disposed between the first bottom surface 10 and the second bottom surface 20, that is, the injection unit is disposed in the fuel agent chamber 50, and the injection unit is opened up and down, so that the first bottom surface 10 and the second bottom surface 20 penetrate, 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 dual-component injector, the first bottom surface 10 and the second bottom surface 20 are both in curved surface structures, so that the pressure bearing capacity of a fuel agent cavity is improved, and as the curved surface with the same thickness is higher than the plane pressure bearing capacity, the curved surface can uniformly disperse the born pressure along the whole surface and uniformly spread the pressure to the positions of the bottom surface, so that the curved surface can bear larger pressure, and the structural strength of the integrated dual-component injector is improved.
Specifically, the first bottom surface 10 is adjacent to the curved middle portion of the second bottom surface 20, so that the fuel agent chamber 50 is configured as a hyperboloid concave lens structure.
Specifically, at least one side of the fuel chamber 50 is provided with a fuel inlet 51, and the fuel inlet 51 is used for introducing fuel into the fuel chamber 50. Preferably, the fuel inlet 51 is disposed on a vertical wall surface connecting the first bottom surface 10 and the second bottom surface 20, so that the injection direction of the fuel into the fuel inlet 51 is perpendicular to or forms a certain angle with the extending direction of the injection unit. The fuel chamber 50 is configured as a hyperbolic concave lens structure, and the first bottom surface 10 is close to the curved middle portion of the second bottom surface 20, so that the flow area of the fuel chamber 50 at the fuel inlet 51 is larger, the flow rate of the fuel is lower at the center of the fuel chamber 50, the flow area is smaller at the center of the fuel chamber 50, and the flow rate of the fuel is higher at the center of the fuel chamber, so that the internal pressure distribution of the fuel chamber 50 is more uniform, and the pressure distribution is better, and has been verified through three-dimensional fluid simulation analysis.
In the integrated dual-component injector provided in this embodiment, the fuel agent chamber 50 is configured as a hyperboloid concave lens structure, and the first bottom surface 10 is close to the curved middle of the second bottom surface 20, so that the fuel agent flow rate in the edge area of the fuel agent chamber 50 is lower, and the fuel agent flow rate in the central area of the fuel agent chamber 50 is higher, so that the fuel agent chamber 50 has an isostatic pressure equalizing characteristic, and the flow distribution of each injection unit is more uniform, thereby being beneficial to improving the injection combustion efficiency.
Specifically, at least one sweat cooling channel 11 is further provided on the first bottom surface 10.
Specifically, the sweat cooling channels 11 are configured in a curved-back configuration.
The first bottom surface 10 is penetrated by the sweat cooling channel 11 through a curved channel arrangement form, so that the fuel agent cavity 50 can be communicated with the outside, and in the application environment of the integrated dual-component injector, the outside is usually a combustion chamber, namely, the fuel agent cavity 50 and the combustion chamber are separated by the first bottom surface 10, and the sweat cooling channel 11 arranged on the first bottom surface 10 conducts the fuel agent cavity 50 and the combustion chamber 80. Since the first bottom surface 10 is close to the side of the combustion chamber 80, and the temperature of the combustion chamber 80 is relatively high, the first bottom surface 10 needs to be cooled by adopting a cooling measure, so that the first bottom surface 10 is usually manufactured by adopting a special porous metal material, and the first bottom surface 10 is also usually called a porous panel.
The integrated dual-component injector provided in this embodiment distributes the perspiration cooling channel structure group of the curved shape on the first bottom surface 10, so that the fuel agent in the fuel agent cavity 50 can slowly flow out from the curved shape channel, thereby playing a role in perspiration cooling on the gas surface of the first bottom surface 10.
Specifically, the integrated two-component injector further comprises:
the oxidant chamber 40 is arranged with the second bottom surface 20 as a bottom, and the third bottom surface 30 arranged away from the first bottom surface 10 as a top of the oxidant chamber 40.
The integrated dual-component injector is constructed in a three-bottom two-cavity structure, wherein the three bottoms are a first bottom surface 10, a second bottom surface 20 and a third bottom surface 30 respectively, 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 oxidizer 40 is provided with an oxidizer inlet 41, and the oxidizer inlet 41 is used for introducing an oxidizer into the oxidizer 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 dual-component injector can be improved.
Example two
The embodiment of the integrated two-component injector described in the above embodiment is based on which the injection unit provided inside the integrated two-component injector will be described in detail.
Specifically, a plurality of the injection units having different lengths are disposed between the first bottom surface 10 and the second bottom surface 20.
Since the fuel agent chamber 50 is provided with a plurality of injection units, the distribution form of the injection units in the fuel agent chamber 50 can be honeycomb distribution, checkerboard distribution, concentric circular distribution, etc., and in addition, the structure form of the injection units comprises self-striking type, mutual striking type, coaxial direct current type, coaxial centrifugal type, etc. Preferably, in this embodiment, the injection unit is a coaxial direct-current injection unit.
The embodiment provides an integrated dual-component injector, which is arranged between the first bottom surface 10 and the second bottom surface 20, and the injection units are designed with different lengths, so that the acoustic frequency of the injection units is staggered, and the stability of combustion is 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 insufflating unit includes:
a fuel agent nozzle 70 at least partially communicating with the fuel agent chamber 50, one end of the fuel agent nozzle 70 being connected to the first bottom surface 10 and penetrating the first bottom surface 10; and
an oxidizer nozzle 60 having a first end connected to the second bottom surface 20 and communicating with the oxidizer chamber 40 through the second bottom surface 20, and a second end at least partially disposed inside the fuel nozzle 70.
At least one radial hole 71 is provided in the side wall of the fuel nozzle 70;
the fuel nozzle 70 communicates at least partially with the fuel chamber 50, in this embodiment with the fuel chamber 50, particularly through at least one radial hole 71 provided in a sidewall of the fuel nozzle 70, the radial hole 71 being capable of facilitating the entry of fuel into the injection unit.
The oxidant nozzle 60 penetrates inside and is communicated with the injection port 74 together with the radial hole 71.
One end of the fuel nozzle 70 is connected to the first bottom surface 10 and penetrates through the first bottom surface 10, so that an injection port 74 penetrating through 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 oxidizer nozzle 60 is connected to and penetrates the second bottom surface 20 such that an oxidizer nozzle inlet end 61 penetrating the second bottom surface 20 is formed at a contact position of the injection unit with the second bottom surface 20, and the oxidizer nozzle inlet end 61 communicates the oxidizer chamber 40 with the injection unit such that the oxidizer located in the oxidizer chamber 40 can enter the injection unit from the oxidizer nozzle inlet end 61.
The second end of the oxidant nozzle 60 is at least partially disposed inside the fuel nozzle 70, and the fuel nozzle 70 and the oxidant nozzle 60 of the injection unit are disposed in a nested structure, and the oxidant nozzle 60 is disposed inside the fuel nozzle 70 and forms a certain annular gap 73; meanwhile, since the injection unit is connected to the second bottom surface 20 and the first bottom surface 10 at the upper and lower portions thereof, respectively, and penetrates the inside of the oxidizer nozzle 60, the oxidizer nozzle 60 is formed with the oxidizer nozzle outlet port 63 inside the fuel nozzle 70, and the oxidizer 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 oxidizer entering through the oxidizer nozzle inlet port 61 and flowing out of the oxidizer nozzle outlet port 63, and the mixed fuel and the oxidizer are discharged from the injection port 74 together, and injected into the combustion chamber 80.
Preferably, the oxidant nozzle 60 is provided with at least one orifice 62 on an inner side wall at an end thereof remote from the injection port 74. As a further preferred form, the oxidant nozzle 60 is provided with two orifices 62 in series on the inner side wall at the end remote from the injection port 74. The orifice 62 is formed by protruding the inner wall of the oxidizer nozzle 60 toward the center, so that the initial flow area of the orifice 62 is reduced, and the oxidizer nozzle 60 adopts a double orifice design, so that the anti-interference capability during the flow of the oxidizer can be enhanced, and the combustion stability of the injector can be enhanced.
Preferably, the radial holes 71 are in a raindrop-shaped structure. The radial holes of the raindrop-shaped structure can improve the flow coefficient of the fuel nozzle 70, and are beneficial to reducing the flow resistance of the fuel nozzle 70 at the same injection speed.
Preferably, an annular cavity 72 is formed between the inner sidewall of the fuel 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 volume 72 can enhance the stability and uniformity of the flow of fuel at the annular gap 73.
Preferably, the radial hole 71 is opposite to the annular cavity 72, so that the fuel agent enters the annular cavity 72 preferentially after entering the injection unit from the radial hole 71, which is equivalent to a collector, and plays a role in flow equalization.
Example III
The present embodiment provides a method for manufacturing an integrated dual-component injector, where the integrated dual-component injector is manufactured by 3D printing as described in the first and second embodiments.
According to the manufacturing method of the integrated double-component injector, the integrated double-component injector is manufactured through 3D printing, so that the development cost of the integrated double-component injector can be reduced, the production efficiency of products is improved, the three-bottom two-cavity injector structure and hundreds of injection units are printed together in the form of one integral part by means of a 3D printing process technology, the number of parts is greatly reduced, and the product cost of the integrated double-component injector is reduced; meanwhile, the number of parts of the integrated double-component injector is integrated into one piece from hundreds of pieces, so that the production efficiency of products is improved, the production period is greatly shortened, the inherent reliability of the products is improved, and the yield of the products is improved. In addition, the integrated structural design reduces a plurality of 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 3D printing process is utilized to distribute the bent perspiration cooling channel structure group on the first bottom surface 10, fuel slowly flows out from the bent perspiration cooling channel, and the perspiration cooling effect is achieved 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 by only 1/5 of that of the traditional porous panel, meanwhile, the traditional porous panel has complex process, more working procedures and less working procedures, and the production period can be greatly shortened due to the fact that the first bottom surface 10 is manufactured by the 3D printing process.
Preferably, the integral dual component injector structure and the injection unit are manufactured together by adopting an SLM laser printing forming process.
Preferably, the 3D printing powder material has a brand GH3625, a powder particle size of 10-80 μm, and a powder particle weight passing through No.100 sieve of 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 and liquid flow test, wherein the specific technological method comprises the following parameters:
hot isostatic pressing: the temperature ranges from 1050 ℃ to 1180 ℃, the pressure is more than 150MPa, the heat preservation and pressure maintaining time is 3-5 h, the argon protection is realized, and the air cooling is realized.
Solution heat treatment: preserving heat for 2h at 1090-1200 ℃ and quickly cooling argon.
And (3) carrying out water resistance tests of the oxidant nozzle and the fuel nozzle according to the use requirements, and completing the production of products after the tests are qualified.
Example IV
In this embodiment, with reference to the specific example, it is preferable that the first bottom surface 10 and the second bottom surface 20 are both curved surfaces, so that the fuel agent chamber 50 is configured as a hyperboloid concave lens structure, and the spherical radius of the first bottom surface 10 and the second bottom surface 20 is preferably 2-4 times the diameter of the integrated dual-component injector.
Preferably, the radial holes 71 are in a raindrop shape, each fuel agent nozzle 70 is provided with 2 rows of radial holes, 4 radial holes in each row, the radial holes 71 are uniformly distributed circumferentially 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 that of the annular gap 73.
Preferably, the oxidant nozzle 60 is coaxially disposed with the fuel nozzle 70 with its axis parallel to the axis of the integrated two-component injector, and the oxidant nozzle outlet end 63 is retracted 4-10 mm relative to the injection port 74.
The orifice diameter D1 is calculated as shown in fig. 3 by using 2 laval orifice segments upstream of the oxidizer nozzle 60 as shown in the following equation 1.
Equation 1:
in the formula, qo-oxidant flow per injection unit
Cdo-oxidant nozzle flow coefficient, generally 0.75-0.95
D1-orifice diameter
ρ -oxidant density
Pio-oxidant Chamber pressure
Pe-Combustion Chamber pressure
An annular chamber is arranged upstream of an annular gap formed by the fuel nozzle and the oxidant nozzle, the cross-sectional area of the annular chamber is generally 3-5 times that of a downstream annular gap, and as shown in fig. 3, the downstream annular gap dimensions D2 and D3 are calculated according to the following formula 2.
Equation 2:
wherein qf—the fuel flow rate of each injection unit;
cdf-fuel nozzle flow coefficient, typically 0.7-0.9
D2-outer diameter of annular gap
D3-inner diameter of annular gap
ρ -Fuel Density
k-fuel adiabatic index
Pif-fuel cavity pressure
Pe-Combustion Chamber pressure
As shown in FIG. 4, the diameter D4 of the curved sweating cooling channel in the first bottom surface 10 is preferably 0.1-1.0 mm, the consumption of the sweating cooling agent is 1% -10% of the total fuel agent, and the channels are uniformly distributed on the first bottom surface 10, and the distance between the channels is not more than 10mm.
Example five
The embodiment provides an aerospace device comprising the integrated two-component injector according to the embodiment.
By adopting the integrated dual-component injector, the combustion stability of the aerospace equipment can be improved, and the overall structural strength of the integrated dual-component injector can be improved.
It is apparent that the above examples are given by way of illustration only and are not limiting of the embodiments. Other variations or modifications of the above teachings will be apparent to those of ordinary skill in the art. It is not necessary here nor is it exhaustive of all embodiments. While still being apparent from variations or modifications that may be made by those skilled in the art are within the scope of the invention.
Claims (12)
1. An integrated two-component injector, comprising:
a fuel agent chamber (50);
a first bottom surface (10) provided at the bottom of the fuel agent chamber (50);
a second bottom surface (20) disposed on top of the fuel agent chamber (50) and disposed opposite to the first bottom surface (10); and
at least one injection unit which is arranged in a communicating manner between the first bottom surface (10) and the second bottom surface (20);
the first bottom surface (10) and the second bottom surface (20) are both of curved structures;
the first bottom surface (10) is close to the bending middle part of the second bottom surface (20), so that the fuel agent cavity (50) is constructed into a hyperboloid concave lens structure;
at least one side of the fuel agent cavity (50) is provided with a fuel agent inlet (51);
further comprises: an oxidizer cavity (40), the oxidizer cavity (40) taking the second bottom surface (20) as a bottom and taking a third bottom surface (30) arranged far away from the first bottom surface (10) as a top;
a plurality of injection units with different lengths are arranged between the first bottom surface (10) and the second bottom surface (20).
2. The integrated two-component injector according to claim 1, characterized in that the first bottom surface (10) is further provided with at least one sweat cooling channel (11) therethrough.
3. The integrated two-component injector according to claim 2, characterized in that the sweat cooling channel (11) is configured as a curved-back structure.
4. The integrated two-component injector according to claim 1, characterized in that the injection unit is adapted to communicate the fuel agent chamber (50) and/or the oxidant chamber (40) with the outside; the insufflating unit includes:
a fuel agent nozzle (70) at least partially communicating with the fuel agent chamber (50), one end of the fuel agent nozzle (70) being connected to the first bottom surface (10) and penetrating the first bottom surface (10); and
and an oxidant nozzle (60) having a first end connected to the second bottom surface (20) and communicating with the oxidant chamber (40) through the second bottom surface (20), and a second end at least partially disposed inside the fuel nozzle (70).
5. The integrated two-component injector of claim 4, wherein the fuel agent nozzle (70) sidewall has at least one radial hole (71) disposed therein;
the oxidant nozzle (60) penetrates inside and is communicated with the injection port (74) together with the radial hole (71).
6. The integrated two-component injector of claim 5, wherein an inner sidewall of the oxidant nozzle (60) distal from the injection port (74) is provided with at least one orifice (62).
7. The integrated two-component injector according to claim 5, characterized in that the radial holes (71) are of a raindrop-shaped structure.
8. The integrated two-component injector of claim 5, wherein an annular cavity (72) is formed between an inner sidewall of the fuel nozzle (70) and an outer sidewall of the oxidant nozzle (60).
9. The integrated two-component injector according to claim 8, characterized in that the radial hole (71) is arranged directly opposite the annular cavity (72).
10. The integrated two-component injector of claim 8, wherein an annular gap (73) is further formed between the inner sidewall of the fuel agent nozzle (70) and the outer sidewall of the oxidant nozzle (60), one end of the annular gap (73) is in communication with the annular cavity (72), and the other end is in communication with the injection port (74).
11. A method of manufacturing an integrated two-component injector according to any of the preceding claims 1-10, characterized in that the integrated two-component injector is manufactured by 3D printing.
12. An aerospace device comprising an integrated two-component injector according to any one of claims 1 to 10.
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Families Citing this family (4)
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| CN113339159B (en) * | 2021-07-06 | 2022-08-16 | 西安航天动力研究所 | Coaxial double-centrifugal injector based on 3D printing and liquid oxygen kerosene rocket engine |
| CN113523735B (en) * | 2021-09-01 | 2022-07-22 | 西安远航真空钎焊技术有限公司 | Preparation method of injector |
| CN114000959B (en) * | 2021-11-09 | 2022-11-22 | 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 |
Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2222124A1 (en) * | 1973-03-23 | 1974-10-18 | Pillard Chauffage | Combustion gases homogenizing equipment - ensures uniform temperatures for drying plants, gas turbines and jet engines |
| US6253539B1 (en) * | 1996-09-24 | 2001-07-03 | Boeing North America Inc. | Convective and turbulent shear mixing injector |
| RU2497012C1 (en) * | 2012-06-27 | 2013-10-27 | Владимир Викторович Черниченко | Liquid propellant rocket engine |
| JP2014037838A (en) * | 2013-10-23 | 2014-02-27 | Mitsubishi Heavy Ind Ltd | Injector for rocket, combustor for rocket and liquid fuel rocket |
| CN104154566A (en) * | 2014-07-08 | 2014-11-19 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Dual-fuel nozzle structure of gas turbine |
| CN104989552A (en) * | 2015-06-15 | 2015-10-21 | 西北工业大学 | Minitype solid rocket engine structure based on 3D printing technology |
| CN107939551A (en) * | 2017-11-29 | 2018-04-20 | 北京航天动力研究所 | A kind of precombustion chamber ejector filler structure |
| CN108691692A (en) * | 2018-05-31 | 2018-10-23 | 北京航空航天大学 | Mix ejector filler and small liquid rocket engine |
| CN109578167A (en) * | 2018-11-21 | 2019-04-05 | 中国人民解放军国防科技大学 | Engine injector and engine with same |
| CN110131074A (en) * | 2019-05-24 | 2019-08-16 | 西安航天动力研究所 | A kind of double elements air turbo rocket propulsion system |
| KR20190105997A (en) * | 2018-03-07 | 2019-09-18 | 두산중공업 주식회사 | Pilot fuelinjector, fuelnozzle and gas turbinehaving it |
| KR20190108414A (en) * | 2018-03-14 | 2019-09-24 | 두산중공업 주식회사 | Combustor and gas turbine having the same |
| CN110805506A (en) * | 2019-09-29 | 2020-02-18 | 北京航天动力研究所 | Combined combustion stabilizing device |
| CN111174232A (en) * | 2018-11-12 | 2020-05-19 | 中国联合重型燃气轮机技术有限公司 | Gas turbine and micro-mixing nozzle thereof |
| CN213899134U (en) * | 2020-08-13 | 2021-08-06 | 北京星际荣耀空间科技股份有限公司 | Integrated double-component injector and aerospace equipment |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH06272862A (en) * | 1993-03-18 | 1994-09-27 | Hitachi Ltd | Method and apparatus for mixing fuel into air |
| CN101782030B (en) * | 2009-01-19 | 2013-03-27 | 北京航空航天大学 | Multiunit coaxial injector component for test and manufacturing method |
| CN108915899B (en) * | 2018-06-29 | 2020-02-14 | 北京航天动力研究所 | Four-bottom three-cavity injector |
-
2020
- 2020-08-13 CN CN202010815011.0A patent/CN111852691B/en active Active
Patent Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2222124A1 (en) * | 1973-03-23 | 1974-10-18 | Pillard Chauffage | Combustion gases homogenizing equipment - ensures uniform temperatures for drying plants, gas turbines and jet engines |
| US6253539B1 (en) * | 1996-09-24 | 2001-07-03 | Boeing North America Inc. | Convective and turbulent shear mixing injector |
| RU2497012C1 (en) * | 2012-06-27 | 2013-10-27 | Владимир Викторович Черниченко | Liquid propellant rocket engine |
| JP2014037838A (en) * | 2013-10-23 | 2014-02-27 | Mitsubishi Heavy Ind Ltd | Injector for rocket, combustor for rocket and liquid fuel rocket |
| CN104154566A (en) * | 2014-07-08 | 2014-11-19 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Dual-fuel nozzle structure of gas turbine |
| CN104989552A (en) * | 2015-06-15 | 2015-10-21 | 西北工业大学 | Minitype solid rocket engine structure based on 3D printing technology |
| CN107939551A (en) * | 2017-11-29 | 2018-04-20 | 北京航天动力研究所 | A kind of precombustion chamber ejector filler structure |
| KR20190105997A (en) * | 2018-03-07 | 2019-09-18 | 두산중공업 주식회사 | Pilot fuelinjector, fuelnozzle and gas turbinehaving it |
| KR20190108414A (en) * | 2018-03-14 | 2019-09-24 | 두산중공업 주식회사 | Combustor and gas turbine having the same |
| CN108691692A (en) * | 2018-05-31 | 2018-10-23 | 北京航空航天大学 | Mix ejector filler and small liquid rocket engine |
| CN111174232A (en) * | 2018-11-12 | 2020-05-19 | 中国联合重型燃气轮机技术有限公司 | Gas turbine and micro-mixing nozzle thereof |
| CN109578167A (en) * | 2018-11-21 | 2019-04-05 | 中国人民解放军国防科技大学 | Engine injector and engine with same |
| CN110131074A (en) * | 2019-05-24 | 2019-08-16 | 西安航天动力研究所 | A kind of double elements air turbo rocket propulsion system |
| CN110805506A (en) * | 2019-09-29 | 2020-02-18 | 北京航天动力研究所 | Combined combustion stabilizing device |
| CN213899134U (en) * | 2020-08-13 | 2021-08-06 | 北京星际荣耀空间科技股份有限公司 | Integrated double-component injector and aerospace equipment |
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