CN114412660B - Integrated coaxial nozzle of liquid rocket engine and design and manufacturing method thereof - Google Patents
Integrated coaxial nozzle of liquid rocket engine and design and manufacturing method thereof Download PDFInfo
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- CN114412660B CN114412660B CN202111579559.0A CN202111579559A CN114412660B CN 114412660 B CN114412660 B CN 114412660B CN 202111579559 A CN202111579559 A CN 202111579559A CN 114412660 B CN114412660 B CN 114412660B
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- 238000004519 manufacturing process Methods 0.000 title claims abstract description 52
- 239000007788 liquid Substances 0.000 title claims abstract description 15
- 239000000446 fuel Substances 0.000 claims abstract description 116
- 239000007800 oxidant agent Substances 0.000 claims abstract description 91
- 230000001590 oxidative effect Effects 0.000 claims abstract description 91
- 238000003466 welding Methods 0.000 claims abstract description 34
- 238000000034 method Methods 0.000 claims abstract description 13
- 239000000843 powder Substances 0.000 claims description 21
- 238000002844 melting Methods 0.000 claims description 16
- 230000008018 melting Effects 0.000 claims description 16
- 239000000758 substrate Substances 0.000 claims description 15
- 239000000654 additive Substances 0.000 claims description 12
- 230000000996 additive effect Effects 0.000 claims description 12
- 239000000956 alloy Substances 0.000 claims description 12
- 229910045601 alloy Inorganic materials 0.000 claims description 9
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 6
- 238000004458 analytical method Methods 0.000 claims description 6
- 239000000463 material Substances 0.000 claims description 6
- 238000003892 spreading Methods 0.000 claims description 6
- 229910000881 Cu alloy Inorganic materials 0.000 claims description 3
- 229910000831 Steel Inorganic materials 0.000 claims description 3
- 229910052786 argon Inorganic materials 0.000 claims description 3
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 3
- 239000012530 fluid Substances 0.000 claims description 3
- 239000001301 oxygen Substances 0.000 claims description 3
- 229910052760 oxygen Inorganic materials 0.000 claims description 3
- 239000002245 particle Substances 0.000 claims description 3
- 239000007787 solid Substances 0.000 claims description 3
- 239000007921 spray Substances 0.000 claims description 3
- 239000010935 stainless steel Substances 0.000 claims description 3
- 229910001256 stainless steel alloy Inorganic materials 0.000 claims description 3
- 239000010959 steel Substances 0.000 claims description 3
- 238000002485 combustion reaction Methods 0.000 description 11
- 238000005516 engineering process Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 238000002156 mixing Methods 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
- B22F10/20—Direct sintering or melting
- B22F10/28—Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
- B22F5/10—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of articles with cavities or holes, not otherwise provided for in the preceding subgroups
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y10/00—Processes of additive manufacturing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y80/00—Products made by additive manufacturing
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/17—Mechanical parametric or variational design
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/28—Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]
Abstract
The invention relates to an integrated coaxial nozzle of a liquid rocket engine, which comprises a panel welding positioning platform, a fuel nozzle steady flow guide plate, a fuel nozzle, an oxidant nozzle, a fuel inlet, an oxidant nozzle steady flow guide plate, a middle bottom welding positioning platform, a fuel nozzle outer wall and an oxidant nozzle outer wall, wherein the panel welding positioning platform is arranged on the panel; the oxidant nozzle ejects oxidant and acts on the oxidant nozzle outer wall during operation, the oxidant nozzle outer wall inner side is the oxidant nozzle steady flow guide plate, the fuel nozzle ejects fuel and acts between the fuel nozzle outer wall and the oxidant nozzle outer wall during operation, the fuel nozzle steady flow guide plate is arranged between the fuel nozzle outer wall and the oxidant nozzle outer wall, the fuel inlet is positioned at the joint of the fuel nozzle outer wall and the fuel nozzle, the upper end of the fuel nozzle outer wall is a panel welding positioning platform, and the lower end is a middle bottom welding positioning platform. The invention improves the stability and manufacturing efficiency of the nozzle product forming process.
Description
Technical Field
The invention relates to an integrated coaxial nozzle of a liquid rocket engine and a design and manufacturing method thereof, belonging to the technical field of structural design and metal additive manufacturing of combustion devices of liquid rocket engines.
Background
The liquid rocket engine nozzle is a main functional component in the head injector, and is used for mixing fuel and oxidant into the engine body for combustion. The existing manufacturing process is that a fuel nozzle and an oxidant nozzle are firstly machined, and then two parts are welded into a coaxial nozzle through high-energy beams. The split manufacturing mode has large welding deformation and can influence the coaxiality of the nozzle to a certain extent.
The current manufacturing process can not realize the manufacturing of the steady flow guide plate structure in the fuel and oxidant nozzles, and the addition of the steady flow guide plate can lead the liquid sprayed out of the nozzles to be more uniform, avoid uneven combustion caused by turbulent flow and improve combustion stability. Meanwhile, the number of the nozzles in the engine injector is large, tens or hundreds of nozzles are generally needed for a single part, and the manufacturing period of the nozzles needed for the single part in the existing manufacturing scheme of the sectioning machine and welding is long.
Disclosure of Invention
The invention solves the technical problems that: the integrated coaxial nozzle for the liquid rocket engine and the manufacturing method thereof are provided for overcoming the defects of the prior art, and the stability and the manufacturing efficiency of the nozzle product in the forming process are improved.
The solution of the invention is as follows:
the integrated coaxial nozzle of the liquid rocket engine comprises a panel welding positioning platform, a fuel nozzle steady flow guide plate, a fuel nozzle, an oxidant nozzle, a fuel inlet, an oxidant nozzle steady flow guide plate, a middle bottom welding positioning platform, a fuel nozzle outer wall and an oxidant nozzle outer wall;
the oxidant nozzle ejects oxidant and acts on the oxidant nozzle outer wall during operation, the oxidant nozzle outer wall inner side is the oxidant nozzle steady flow guide plate, the fuel nozzle ejects fuel and acts between the fuel nozzle outer wall and the oxidant nozzle outer wall during operation, the fuel nozzle steady flow guide plate is arranged between the fuel nozzle outer wall and the oxidant nozzle outer wall, the fuel inlet is positioned at the joint of the fuel nozzle outer wall and the fuel nozzle, the upper end of the fuel nozzle outer wall is a panel welding positioning platform, and the lower end is a middle bottom welding positioning platform.
Further, the integrated nozzle is made of high-temperature alloy, stainless steel or copper alloy materials.
Further, the fuel nozzle and the oxidant nozzle are of a coaxial integral structure.
Further, the minimum thickness of the oxidant nozzle steady flow guide plate and the fuel nozzle steady flow guide plate is not less than 0.5mm.
Further, the included angle between the side end surfaces of the oxidant nozzle steady flow guide plate and the fuel nozzle steady flow guide plate and the axis of the nozzle is 0-45 degrees.
Further, the included angle between the lower end surfaces of the oxidant nozzle steady flow guide plate and the fuel nozzle steady flow guide plate and the axis of the nozzle is 0-45 degrees.
Further, the included angle between the lower end surfaces of the panel welding positioning platform and the middle bottom welding positioning platform and the horizontal plane is more than or equal to 45 degrees.
Further, the fuel nozzle is positioned between the fuel nozzle outer wall and the oxidant nozzle outer wall, and a gap between the fuel nozzle outer wall and the oxidant nozzle outer wall is greater than or equal to 0.5mm.
Further, the diameter of the fuel inlet is between 0.5 and 5mm.
The design method of the integrated coaxial nozzle structure comprises the following steps:
the method comprises the steps of firstly, designing the overall outline size of a nozzle according to the size requirement of an injector, wherein an included angle between the lower end surfaces of a panel welding positioning platform and a middle bottom welding positioning platform and a horizontal plane is larger than or equal to 45 degrees;
secondly, confirming the sizes of the oxidant nozzle and the fuel inlet according to the overall technical requirements of the injector and the fuel/oxidant ratio; the fuel nozzle is positioned between the outer wall of the fuel nozzle and the outer wall of the oxidant nozzle, and is in clearance fit with the outer wall of the fuel nozzle and the outer wall of the oxidant nozzle, and the clearance is more than or equal to 0.5mm; the diameter of the fuel inlet is between 0.5 and 5mm;
thirdly, designing a steady flow guide plate in the oxidant nozzle and the fuel nozzle, wherein the fuel nozzle and the oxidant nozzle are of a coaxial integral structure, and the minimum thickness of the steady flow guide plate of the oxidant nozzle and the steady flow guide plate of the fuel nozzle is not less than 0.5mm; the included angle between the side end surfaces of the oxidant nozzle steady flow guide plate and the fuel nozzle steady flow guide plate and the axis of the nozzle is 0-45 degrees; the included angle between the lower end surfaces of the oxidant nozzle steady flow guide plate and the fuel nozzle steady flow guide plate and the axis of the nozzle is 0-45 degrees;
fourthly, analyzing the fluid dynamics and the nozzle structure dynamics of the designed nozzle;
fifthly, comparing the analysis result with the overall technical requirement of the injector, and if the analysis result meets the requirement, determining the structure; and if the requirements are not met, the characteristic dimensions in the second step and the third step are adjusted until the overall technical requirements of the injector are met, and the design of the integrated coaxial nozzle with the steady flow guide plate is completed.
A method of manufacturing an integrated coaxial nozzle structure, comprising the steps of:
the first step, triangular surface patch treatment is carried out on the integrated coaxial nozzle solid model, and the deviation control chord height is not more than 0.05;
step two, layering and slicing the integrated coaxial nozzle triangular patch model, wherein the thickness of a slice layer is 20-40 microns, then setting a row-by-row random island laser scanning path in each slice layer, and setting forming technological parameters to form a program file of laser selective melting additive manufacturing equipment;
thirdly, mounting a forming substrate into laser selective melting additive manufacturing equipment, wherein the forming substrate is 45# steel, and the thickness of the forming substrate is not less than 20mm;
fourth, according to the different materials of the integrated nozzle, alloy powder of the corresponding materials is selected, the particle size of the powder is 15-53 microns, and the powder is normally distributed;
fifthly, guiding the program file into laser selective melting forming equipment;
step six, filling argon with the purity of 99.99 percent into the laser selective melting forming equipment, reducing the oxygen content in the forming cavity of the equipment to below 0.1 percent, and starting the equipment;
seventhly, evenly spreading alloy powder on the forming substrate, wherein the thickness of a powder spreading layer is consistent with the slicing thickness of the part;
eighth step, scanning on the powder bed by adopting laser according to the laser scanning path to melt the powder;
and ninth, descending the substrate for layering, and repeating the seventh step and the eighth step until the manufacture of the integrated coaxial nozzle is completed.
Compared with the prior art, the invention has the beneficial effects that:
(1) The technical scheme provided by the invention realizes the integral manufacture of the nozzle, avoids coaxiality deviation caused by sectional manufacture and welding, and improves the manufacture precision;
(2) According to the invention, the steady flow guide plate is added in the nozzle, so that uneven combustion caused by turbulent flow of the oxidant and the fuel in the nozzle can be avoided, and the combustion stability is improved;
(3) The invention adopts the laser selective melting additive manufacturing technology to realize the integral manufacture of the nozzle structure, reduces the manufacturing procedures, shortens the manufacturing period, realizes the simultaneous manufacture of dozens of nozzles by one-time forming, and satisfies the high-efficiency manufacture of dozens or hundreds of nozzles in a single-part injector.
Drawings
FIG. 1 is a coaxial nozzle employing an overall design based on a laser selective melt additive manufacturing process.
Detailed Description
The invention is further illustrated below with reference to examples.
Aiming at the requirements of high-precision and high-efficiency manufacture of the nozzle in the injector of the liquid rocket engine combustion device, the invention provides the structural design and the manufacturing scheme of the coaxial nozzle with the steady flow guide plate according to the functional requirements and the technical characteristics of laser selective melting additive manufacturing, and realizes the integral manufacture of the integral coaxial nozzle. According to the structural design scheme, the steady flow guide plate can avoid uneven combustion caused by turbulent flow of the oxidant and the fuel in the nozzle, and combustion stability is improved. The laser selective melting additive manufacturing technology can avoid coaxiality deviation caused by machining and welding procedures, improve the manufacturing precision and greatly improve the manufacturing efficiency. The high-precision and high-efficiency manufacturing requirement of the liquid rocket engine nozzle is met.
As shown in fig. 1, the integrated coaxial nozzle of the liquid rocket engine comprises a panel welding positioning platform 1, a fuel nozzle steady flow guide plate 2, a fuel nozzle 3, an oxidant nozzle 4, a fuel inlet 5, an oxidant nozzle steady flow guide plate 6, a middle bottom welding positioning platform 7, a fuel nozzle outer wall 8 and an oxidant nozzle outer wall 9;
the oxidant nozzle 4 sprays oxidant and acts on oxidant nozzle outer wall 9 during operation, oxidant nozzle outer wall 9 inboard is oxidant nozzle steady flow guide 6, fuel nozzle 3 is at the during operation blowout fuel and acts between fuel nozzle outer wall 8 and oxidant nozzle outer wall 9, be fuel nozzle steady flow guide 2 between fuel nozzle outer wall 8 and the oxidant nozzle outer wall 9, fuel inlet 5 is located fuel nozzle outer wall 8 and the department that links to each other of fuel nozzle 3, fuel nozzle outer wall 8 upper end is panel welding position platform 1, the lower extreme is middle-bottom welding position platform 7.
The integrated nozzle is made of high-temperature alloy, stainless steel or copper alloy materials. The fuel nozzle 2 and the oxidant nozzle 3 are of a coaxial integral structure. The minimum thickness of the oxidant nozzle steady flow guide plate 6 and the fuel nozzle steady flow guide plate 2 is not less than 0.5mm. The included angle between the side end surfaces of the oxidant nozzle steady flow guide plate 6 and the fuel nozzle steady flow guide plate 2 and the axis of the nozzle is 0-45 degrees. The included angle between the lower end surfaces of the oxidant nozzle steady flow guide plate 6 and the fuel nozzle steady flow guide plate 2 and the axis of the nozzle is 0-45 degrees. The included angle between the lower end surfaces of the panel welding positioning platform 1 and the middle bottom welding positioning platform 7 and the horizontal plane is larger than or equal to 45 degrees. The fuel nozzle 3 is positioned between the fuel nozzle outer wall 8 and the oxidant nozzle outer wall 9, and a gap between the fuel nozzle outer wall 8 and the oxidant nozzle outer wall 9 is greater than or equal to 0.5mm. The diameter of the fuel inlet 5 is between 0.5 and 5mm.
The design method of the integrated coaxial nozzle structure comprises the following steps:
the method comprises the steps of firstly, designing the overall outline size of a nozzle according to the size requirement of an injector, wherein an included angle between the lower end surfaces of a panel welding positioning platform and a middle bottom welding positioning platform and a horizontal plane is larger than or equal to 45 degrees;
secondly, confirming the sizes of the oxidant nozzle and the fuel inlet according to the overall technical requirements of the injector and the fuel/oxidant ratio; the fuel nozzle 3 is positioned between the fuel nozzle outer wall 8 and the oxidant nozzle outer wall 9 and is in clearance fit with the two, and the clearance is more than or equal to 0.5mm; the diameter of the fuel inlet 5 is between 0.5 and 5mm;
thirdly, designing a steady flow guide plate in the oxidant nozzle and the fuel nozzle, wherein the fuel nozzle 2 and the oxidant nozzle 3 are of a coaxial integral structure, and the minimum thickness of the steady flow guide plate 6 of the oxidant nozzle and the steady flow guide plate 2 of the fuel nozzle is not less than 0.5mm; the included angle between the side end surfaces of the oxidant nozzle steady flow guide plate 6 and the fuel nozzle steady flow guide plate 2 and the axis of the nozzle is 0-45 degrees; the included angle between the lower end surfaces of the oxidant nozzle steady flow guide plate 6 and the fuel nozzle steady flow guide plate 2 and the axis of the nozzle is 0-45 degrees;
fourthly, analyzing the fluid dynamics and the nozzle structure dynamics of the designed nozzle;
fifthly, comparing the analysis result with the overall technical requirement of the injector, and if the analysis result meets the requirement, determining the structure; and if the requirements are not met, the characteristic dimensions in the second step and the third step are adjusted until the overall technical requirements of the injector are met, and the design of the integrated coaxial nozzle with the steady flow guide plate is completed.
A method of manufacturing an integrated coaxial nozzle structure, comprising the steps of:
the first step, triangular surface patch treatment is carried out on the integrated coaxial nozzle solid model, and the deviation control chord height is not more than 0.05;
step two, layering and slicing the integrated coaxial nozzle triangular patch model, wherein the thickness of a slice layer is 20-40 microns, then setting a row-by-row random island laser scanning path in each slice layer, and setting forming technological parameters to form a program file of laser selective melting additive manufacturing equipment;
thirdly, mounting a forming substrate into laser selective melting additive manufacturing equipment, wherein the forming substrate is 45# steel, and the thickness of the forming substrate is not less than 20mm;
fourth, according to the different materials of the integrated nozzle, alloy powder of the corresponding materials is selected, the particle size of the powder is 15-53 microns, and the powder is normally distributed;
fifthly, guiding the program file into laser selective melting forming equipment;
step six, filling argon with the purity of 99.99 percent into the laser selective melting forming equipment, reducing the oxygen content in the forming cavity of the equipment to below 0.1 percent, and starting the equipment;
seventhly, evenly spreading alloy powder on the forming substrate, wherein the thickness of a powder spreading layer is consistent with the slicing thickness of the part;
eighth step, scanning on the powder bed by adopting laser according to the laser scanning path to melt the powder;
and ninth, descending the substrate for layering, and repeating the seventh step and the eighth step until the manufacture of the integrated coaxial nozzle is completed.
The technical scheme provided by the invention realizes the integral manufacture of the nozzle, avoids coaxiality deviation caused by sectional manufacture and welding, and improves the manufacture precision;
according to the invention, the steady flow guide plate is added in the nozzle, so that uneven combustion caused by turbulent flow of the oxidant and the fuel in the nozzle can be avoided, and the combustion stability is improved;
the invention adopts the laser selective melting additive manufacturing technology to realize the integral manufacture of the nozzle structure, reduces the manufacturing procedures, shortens the manufacturing period, realizes the simultaneous manufacture of dozens of nozzles by one-time forming, and satisfies the high-efficiency manufacture of dozens or hundreds of nozzles in a single-part injector.
Although the present invention has been described in terms of the preferred embodiments, it is not intended to be limited to the embodiments, and any person skilled in the art can make any possible variations and modifications to the technical solution of the present invention by using the methods and technical matters disclosed above without departing from the spirit and scope of the present invention, so any simple modifications, equivalent variations and modifications to the embodiments described above according to the technical matters of the present invention are within the scope of the technical matters of the present invention.
Claims (3)
1. The integrated coaxial nozzle of the liquid rocket engine is characterized by comprising a panel welding positioning platform (1), a fuel nozzle steady flow guide plate (2), a fuel nozzle (3), an oxidant nozzle (4), a fuel inlet (5), an oxidant nozzle steady flow guide plate (6), a middle bottom welding positioning platform (7), a fuel nozzle outer wall (8) and an oxidant nozzle outer wall (9);
the oxidant nozzle (4) sprays oxidant and acts on an oxidant nozzle outer wall (9) in the working process, an oxidant nozzle steady flow guide plate (6) is arranged on the inner side of the oxidant nozzle outer wall (9), the fuel nozzle (3) sprays fuel and acts between a fuel nozzle outer wall (8) and the oxidant nozzle outer wall (9) in the working process, a fuel nozzle steady flow guide plate (2) is arranged between the fuel nozzle outer wall (8) and the oxidant nozzle outer wall (9), a fuel inlet (5) is positioned at the joint of the fuel nozzle outer wall (8) and the fuel nozzle (3), a panel welding positioning platform (1) is arranged at the upper end of the fuel nozzle outer wall (8), and a middle-bottom welding positioning platform (7) is arranged at the lower end of the fuel nozzle outer wall (8);
the integrated nozzle is made of high-temperature alloy, stainless steel or copper alloy materials;
the fuel nozzle (3) and the oxidant nozzle (4) are of a coaxial integral structure;
the minimum thickness of the oxidant nozzle steady flow guide plate (6) and the fuel nozzle steady flow guide plate (2) is not less than 0.5mm;
the included angle between the side end surfaces of the oxidant nozzle steady flow guide plate (6) and the fuel nozzle steady flow guide plate (2) and the axis of the nozzle is 0-45 degrees;
the included angle between the lower end surfaces of the oxidant nozzle steady flow guide plate (6) and the fuel nozzle steady flow guide plate (2) and the axis of the nozzle is 0-45 degrees;
the steady flow guide plate prevents the oxidant and fuel in the nozzle from generating turbulence;
the included angle between the lower end surfaces of the panel welding positioning platform (1) and the middle bottom welding positioning platform (7) and the horizontal plane is larger than or equal to 45 degrees;
the fuel nozzle (3) is positioned between the fuel nozzle outer wall (8) and the oxidant nozzle outer wall (9), and a gap between the fuel nozzle outer wall (8) and the oxidant nozzle outer wall (9) is more than or equal to 0.5mm;
the diameter of the fuel inlet (5) is between 0.5 and 5mm.
2. The design method of the integrated coaxial nozzle structure is characterized by designing the integrated coaxial nozzle of the liquid rocket engine according to claim 1, and the design method comprises the following steps:
the method comprises the steps of firstly, designing the overall outline size of a nozzle according to the size requirement of an injector, wherein an included angle between the lower end surfaces of a panel welding positioning platform and a middle bottom welding positioning platform and a horizontal plane is larger than or equal to 45 degrees;
secondly, confirming the sizes of the oxidant nozzle and the fuel inlet according to the overall technical requirements of the injector and the fuel/oxidant ratio; the fuel nozzle (3) is positioned between the outer wall (8) of the fuel nozzle and the outer wall (9) of the oxidant nozzle, and is in clearance fit with the outer wall (8) of the fuel nozzle and the outer wall of the oxidant nozzle, and the clearance is more than or equal to 0.5mm; the diameter of the fuel inlet (5) is between 0.5 and 5mm;
thirdly, designing a steady flow guide plate in the oxidant nozzle and the fuel nozzle, wherein the fuel nozzle (3) and the oxidant nozzle (4) are of a coaxial integral structure, and the minimum thickness of the steady flow guide plate (6) of the oxidant nozzle and the steady flow guide plate (2) of the fuel nozzle is not less than 0.5mm; the included angle between the side end surfaces of the oxidant nozzle steady flow guide plate (6) and the fuel nozzle steady flow guide plate (2) and the axis of the nozzle is 0-45 degrees; the included angle between the lower end surfaces of the oxidant nozzle steady flow guide plate (6) and the fuel nozzle steady flow guide plate (2) and the axis of the nozzle is 0-45 degrees;
fourthly, analyzing the fluid dynamics and the nozzle structure dynamics of the designed nozzle;
fifthly, comparing the analysis result with the overall technical requirement of the injector, and if the analysis result meets the requirement, determining the structure; and if the requirements are not met, the characteristic dimensions in the second step and the third step are adjusted until the overall technical requirements of the injector are met, and the design of the integrated coaxial nozzle with the steady flow guide plate is completed.
3. A method of manufacturing an integrated coaxial nozzle structure of a liquid rocket engine of claim 1, comprising the steps of:
the first step, triangular surface patch treatment is carried out on the integrated coaxial nozzle solid model, and the deviation control chord height is not more than 0.05;
step two, layering and slicing the integrated coaxial nozzle triangular patch model, wherein the thickness of a slice layer is 20-40 microns, then setting a row-by-row random island laser scanning path in each slice layer, and setting forming technological parameters to form a program file of laser selective melting additive manufacturing equipment;
thirdly, mounting a forming substrate into laser selective melting additive manufacturing equipment, wherein the forming substrate is 45# steel, and the thickness of the forming substrate is not less than 20mm;
fourth, according to the different materials of the integrated nozzle, alloy powder of the corresponding materials is selected, the particle size of the powder is 15-53 microns, and the powder is normally distributed;
fifthly, guiding the program file into laser selective melting forming equipment;
step six, filling argon with the purity of 99.99 percent into the laser selective melting forming equipment, reducing the oxygen content in the forming cavity of the equipment to below 0.1 percent, and starting the equipment;
seventhly, evenly spreading alloy powder on the forming substrate, wherein the thickness of a powder spreading layer is consistent with the slicing thickness of the part;
eighth step, scanning on the powder bed by adopting laser according to the laser scanning path to melt the powder;
and ninth, descending the substrate for layering, and repeating the seventh step and the eighth step until the manufacture of the integrated coaxial nozzle is completed.
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| CN103867340A (en) * | 2012-12-12 | 2014-06-18 | 中国人民解放军国防科学技术大学 | Dual-rotational-flow inspirator |
| CN203130282U (en) * | 2013-03-15 | 2013-08-14 | 北京航天动力研究所 | Integral injector |
| CN106001573A (en) * | 2016-07-08 | 2016-10-12 | 湖北三江航天江北机械工程有限公司 | High-temperature nickel base alloy injector forming method |
| CN109653902A (en) * | 2019-01-16 | 2019-04-19 | 北京星际荣耀空间科技有限公司 | Rocket engine spray structure, injection device, rocket engine and rocket |
| CN111810987A (en) * | 2020-08-13 | 2020-10-23 | 北京星际荣耀空间科技有限公司 | Jetting unit structure and double-component jetting device |
| CN112196697A (en) * | 2020-10-19 | 2021-01-08 | 北京天兵科技有限公司 | Integrated structure injector for rocket engine |
| 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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