Forming method of thrust chamber body

Abstract

The invention discloses a forming method of a thrust chamber body part, which comprises the following steps of: designing a thrust chamber body part model in design software, designing an alloy transition layer on the outer side of an inner runner in the thrust chamber body part model, and processing and forming by adopting first metal additive manufacturing equipment to obtain an alloy inner wall part; secondly, the alloy inner wall piece is machined and formed into an alloy outer wall on the outer side of the alloy inner wall through second metal additive manufacturing equipment, a primary thrust chamber body product is obtained, finish machining equipment is adopted for finish machining of the primary thrust chamber body product, a finished thrust chamber body product is obtained, the alloy transition layer provides an implantation layer for high-temperature alloy cladding, and the finished thrust chamber body product is obtained. According to the thrust chamber body forming method, the overall structural stability is higher, high-quality rapid forming of the thrust chamber body is achieved, a traditional manufacturing mode of segmented finish machining, assembling and welding is replaced, the overall quality consistency is greatly improved, the manufacturing cost is reduced, meanwhile, the manufacturing period is shortened, and the interface tensile strength of the thrust chamber body is higher.

Description

Technical Field

[0001] The present application relates to the technical field of liquid engine manufacturing, and in particular to a method for forming a thrust chamber body. Background Art

[0002] Liquid rocket engines mainly include thrust chambers, turbo pumps, gas generators, gunpowder starters and other components. Their main function is to convert the chemical energy after the propellant is burned into the propulsion kinetic energy of the spacecraft. The body area of ​​the rocket thrust chamber is a special-shaped surface structure, including a cylindrical section, a contraction section and an expansion section. The inner wall of the cavity of the rocket thrust chamber needs to be made of copper alloy materials with high strength, high thermal conductivity and good heat resistance. The outer wall of the rocket thrust chamber needs to be made of high-temperature alloy materials with good high-temperature strength and excellent thermal shock resistance. In the existing manufacturing and forming methods, the traditional process uses a combination of casting, machining and welding. The manufacturing cycle of this process is long and the cost is high. The physical properties of the thrust chamber body obtained vary greatly, especially for the reliability of welding of dissimilar materials. It is difficult to guarantee, and the consistency of the overall operating state in actual working conditions is very poor. Summary of the invention

[0003] In view of the defects existing in the prior art, the present application provides a forming method of a grid rudder to solve the problems of low efficiency and low consistency in the thrust chamber body forming method in the prior art.

[0004] The above-mentioned purpose of the present application is mainly achieved through the following technical solutions:

[0005] A method for forming a thrust chamber body, the method comprising:

[0006] Designing a thrust chamber body model in a design software, and designing an alloy transition layer on the outer side of an inner flow channel in the thrust chamber body model;

[0007] The first metal additive manufacturing equipment is used to process and shape the alloy inner wall part;

[0008] The alloy inner wall part is processed by a second metal additive manufacturing device to form an alloy outer wall on the outer side of the alloy inner wall, thereby obtaining a primary product of the thrust chamber body;

[0009] The thrust chamber body is finely processed by fine processing equipment until the forming requirements are met, and the thrust chamber body is obtained as a finished product.

[0010] In an optional embodiment, when processing and forming the alloy inner wall part, a laser selective melting forming method is adopted.

[0011] In an optional embodiment, before processing and forming the alloy inner wall part, the thrust chamber body model is first three-dimensionally sliced ​​in the design software to obtain a slice model, and the slice model is imported into the first metal additive manufacturing equipment to obtain a slice part, and then laser selective melting is used to process and form the alloy inner wall part.

[0012] In an optional embodiment, when processing and forming the alloy inner wall part, CuCrZr alloy powder is added into the first metal additive manufacturing equipment for processing and forming.

[0013] In an optional embodiment, when the alloy inner wall parts are processed and formed, the printing layer thickness is set and confirmed to be 20μm-40μm, the laser power is 300w-500w, the scanning speed is 500mm / s-650mm / s, and the scanning spacing is 0.07mm-0.10mm in the first metal additive manufacturing equipment.

[0014] In an optional embodiment, when processing and forming the alloy outer wall, a laser melting deposition forming method is adopted.

[0015] In an optional embodiment, when processing and forming the alloy outer wall, a coaxial powder feeding method is adopted to melt the alloy powder and deposit it on the outer side of the alloy inner wall part, and overlap with the alloy transition layer.

[0016] In an optional embodiment, when processing and forming the alloy outer wall, GH3625 alloy powder is added to the second metal additive manufacturing equipment for processing and forming.

[0017] In an optional embodiment, when processing and forming the alloy outer wall, the laser capacity ratio of 4.05 kJ / cm2-4.41 kJ / cm2 and the overlap rate of 40%-65% are set and confirmed in the second metal additive manufacturing equipment.

[0018] In an optional embodiment, when finishing the initial product of the thrust chamber body, a five-axis machine tool is used until the finishing requirements are met.

[0019] Compared with the prior art, the advantages of this application are:

[0020] The forming method of the thrust chamber body in the present application is to first design a thrust chamber body model in a design software, and design an alloy transition layer on the outer side of the inner flow channel in the thrust chamber body model, use a first metal additive manufacturing device to process and shape the alloy inner wall part, and then use a second metal additive manufacturing device to process the alloy inner wall part on the outer side of the alloy inner wall to form an alloy outer wall, so as to obtain a thrust chamber body preliminary product, and then use a finishing device to finish the thrust chamber body preliminary product until it meets the forming requirements, so as to obtain a thrust chamber body finished product. When the first metal additive manufacturing device and the second metal additive manufacturing device perform composite material processing and forming at different stations, the alloy transition layer provides a high-temperature alloy cladding implantation layer, so that the overall structural stability is stronger, and high-quality rapid forming of the thrust chamber body is achieved, which replaces the traditional manufacturing method of segmented finishing, assembly and welding, greatly improves the consistency of the overall quality, reduces the manufacturing cost, shortens the manufacturing cycle, and has a higher interface tensile strength of the thrust chamber body. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0022] Figure 1 A schematic diagram of a process flow of a method for forming a thrust chamber body provided in an embodiment of the present application;

[0023] Figure 2 A schematic diagram of the structure of the thrust chamber body model provided in an embodiment of the present application;

[0024] Figure 3 A partial schematic cross-sectional view of a thrust chamber body model provided in an embodiment of the present application;

[0025] In the figure: 100, thrust chamber body; 101, alloy inner wall part; 102, alloy outer wall; 103, alloy transition layer; 104, inner flow channel. DETAILED DESCRIPTION

[0026] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments. It should be noted that the description of these embodiments is used to help understand the present invention, but does not constitute a limitation of the present invention. The specific structures and functional details disclosed herein are only used to describe the exemplary embodiments of the present invention. However, the present invention can be embodied in many alternative forms, and it should not be understood that the present invention is limited to the embodiments set forth herein.

[0027] like Figure 1 As shown, Figure 1A schematic flow chart of a method for forming a thrust chamber body provided in an embodiment of the present application, a method for forming a thrust chamber body, used to produce a thrust chamber body with a complex geometric shape, especially in the field of aerospace, the forming method comprising:

[0028] like Figure 2 , Figure 3 As shown, Figure 2 A schematic diagram of the structure of the thrust chamber body model provided in an embodiment of the present application, Figure 3 A partial schematic cross-sectional view of a thrust chamber body model provided in an embodiment of the present application is provided. The thrust chamber body model is designed in a design software, and an alloy transition layer 103 is designed on the outer side of an inner flow channel 104 in the thrust chamber body model. It should be noted that, when designing the thrust chamber body model, the thrust chamber body model is optimized on the principle of "avoiding internal support while minimizing external support", and the inner flow channel 104 is smoothed. This step ensures that the designed model can meet the performance requirements of the thrust chamber in actual work, including structural strength, heat resistance, pressure resistance, etc.

[0029] like Figure 2 , Figure 3 As shown, an alloy transition layer 103 is provided on the outer side of the inner flow channel 104 of the thrust chamber body model. The overall structure meets the manufacturing process requirements, has a more compact structure, and has smoother streamlines, which is beneficial to improving the thrust of the thrust chamber and shortening the design cycle. In addition, the alloy transition layer 103 can also provide additional strength and heat resistance to protect the inner flow channel 104 from extreme working conditions.

[0030] The first metal additive manufacturing equipment is used to process and shape the alloy inner wall part 101. According to the thrust chamber body model, metal raw materials are added layer by layer to form the alloy inner wall part 101. This process requires precise control of the melting and solidification of the metal raw materials to ensure the dimensional accuracy of the alloy inner wall part 101 and the integrity of the internal structure.

[0031] The alloy inner wall part 101 is processed into an alloy outer wall 102 on the outer side of the alloy inner wall by a second metal additive manufacturing device to obtain a preliminary product of the thrust chamber body 100. The processed alloy inner wall part 101 is placed in the second metal additive manufacturing device to continue processing the alloy outer wall 102 to form a complete outer shell of the thrust chamber body 100. It is necessary to ensure that the inner and outer walls are firmly bonded and that the shape and size of the outer wall meet the design requirements.

[0032] The thrust chamber body 100 is finely processed by fine processing equipment until it meets the molding requirements, and then the thrust chamber body 100 is obtained. The structure and size of the thrust chamber body 100 are basically formed, and the thrust chamber body 100 is finely processed by fine processing equipment, including removing excess material, smoothing the surface, improving dimensional accuracy, etc. It is very important to ensure the performance of the thrust chamber body 100 in actual applications, and any minor defects may affect its working performance under extreme conditions.

[0033] After finishing, the thrust chamber body 100 product is subjected to comprehensive quality inspection, including material performance test, dimensional accuracy test, pressure and heat resistance test, etc., to ensure that it meets all design and performance requirements. After strict quality inspection and confirmation, the thrust chamber body 100 product is officially completed. This thrust chamber body 100 product will be used to assemble rocket engines to provide powerful thrust for space missions.

[0034] In an optional embodiment, the working principle of the forming method of the thrust chamber body 100 in the present application is: the forming method first designs a thrust chamber body model in a design software, and designs an alloy transition layer 103 on the outer side of an inner flow channel 104 in the thrust chamber body model, adopts a first metal additive manufacturing device to process and shape an alloy inner wall part 101, and then adopts a second metal additive manufacturing device to process the alloy inner wall part 101 on the outer side of the alloy inner wall to form an alloy outer wall 102, thereby obtaining a primary product of the thrust chamber body 100, and then adopts a finishing device to process the thrust chamber body 100. 0 After the initial product is finely processed until it meets the molding requirements, the thrust chamber body 100 is obtained as a finished product. When the first metal additive manufacturing equipment and the first metal additive manufacturing equipment perform composite material processing and molding at different stations, the alloy transition layer 103 provides a bed layer for high-temperature alloy cladding, so that the overall structural stability is stronger, and high-quality rapid molding of the thrust chamber body 100 is achieved, replacing the traditional manufacturing method of segmented fine processing, assembly and welding. The consistency of the overall quality is greatly improved, the manufacturing cost is reduced, the manufacturing cycle is shortened, and the interface tensile strength of the thrust chamber body 100 is higher.

[0035] In an optional embodiment, when processing and forming the alloy inner wall part 101, a laser selective melting forming method is adopted.

[0036] The first metal additive manufacturing equipment adopts the selective laser melting (SLM) forming method. Selective laser melting uses a high-energy density laser beam to melt metal powder layer by layer according to the slicing data of the three-dimensional model, and constructs a three-dimensional solid part by stacking layers.

[0037] Before the SLM process begins, a layer of metal powder is evenly laid on the build platform to form a powder bed. Under computer control, a high-power laser beam selectively melts the metal powder along the path of the sliced ​​model to form a layer of the part. The melted metal powder quickly solidifies to form a solid layer of the part, which is bonded to the next layer of powder bed. The build platform is lowered a certain distance, and a new layer of metal powder is laid again, repeating the laser scanning and melting process until the entire part is built.

[0038] In an optional embodiment, before processing and forming the alloy inner wall part 101, the thrust chamber body model is first three-dimensionally sliced ​​in the design software to obtain a slice model, and the slice model is imported into a first metal additive manufacturing device to obtain a slice part, and then a laser selective melting molding method is used to process and form the alloy inner wall part 101.

[0039] In the design software, first create an accurate three-dimensional model of the thrust chamber body 100. This model needs to reflect all geometric features and internal structures of the thrust chamber body 100 in detail to ensure the accuracy and completeness of subsequent processing.

[0040] After the 3D model design is completed, the complex 3D model is divided into a series of continuous 2D cross sections, i.e. “slices”. These slices define the contours of each layer of the object and provide the necessary data support for the subsequent additive manufacturing process.

[0041] The slicing process is usually completed by a special slicing software, which can recognize the three-dimensional file of the thrust chamber body model and convert the three-dimensional file of the thrust chamber body model into a processable data format. The sliced ​​model data is imported into the first metal additive manufacturing equipment, and processed in the first metal additive manufacturing equipment using the laser selective melting technology.

[0042] In the specific operation, a horizontal scraper first evenly spreads a thin layer of metal powder on the substrate, and then a high-energy laser beam selectively melts the powder on the substrate according to the data information of the three-dimensional digital model to form a layer of the part. This process will be repeated layer by layer, and a new layer of powder will be spread after each layer is completed until all layers of the entire part are melted and solidified, and finally the target solid part is manufactured.

[0043] In an optional embodiment, when processing and forming the alloy inner wall part 101, CuCrZr alloy powder is added into a metal additive manufacturing device for processing and forming.

[0044] CuCrZr alloy, also known as C18150, is a copper-based alloy. CuCrZr alloy powder is selected for its good fluidity, high sphericity, low oxygen content and few satellite powders. These characteristics are essential to ensure uniform melting of powder and molding quality of parts during manufacturing. The particle distribution of CuCrZr alloy powder can be selected as needed, such as 15-53um, 20-63um, 50-150um, etc., to adapt to different printing resolutions and part requirements.

[0045] Before starting processing, CuCrZr alloy powder needs to be added to the first metal additive manufacturing device. The alloy inner wall part 101 after processing needs to be post-processed, including removing the support structure, surface treatment, heat treatment, etc., to ensure the dimensional accuracy and mechanical properties of the part. CuCrZr alloy is a precipitation hardening alloy, and its strength and hardness can be significantly improved by appropriate heat treatment.

[0046] In an optional embodiment, when the alloy inner wall part 101 is processed and formed, the printing layer thickness is set and confirmed to be 20μm-40μm, the laser power is 300w-500w, the scanning speed is 500mm / s-650mm / s, and the scanning spacing is 0.07mm-0.10mm in the metal additive manufacturing equipment to control the stability of the processing process.

[0047] In an optional embodiment, when processing and forming the alloy outer wall 102, a laser melting deposition forming method is adopted.

[0048] Laser Meta Deposition (LMD) technology is a directed energy deposition (DED) process that uses a high-energy laser beam to directly melt the metal powder fed synchronously and forms it by layer-by-layer deposition. In the LMD forming process, the alloy powder is first gathered onto the working plane through a nozzle, and the laser beam is also focused to this point, so that the powder and the laser action point coincide. By moving the workbench or nozzle, the metal material is deposited layer by layer to eventually form a three-dimensional part. The thickness of each layer is determined by the scanning speed of the laser beam and the amount of powder fed.

[0049] In an optional embodiment, when the alloy outer wall 102 is processed and formed, a coaxial powder feeding method is adopted to melt the alloy powder and deposit it on the outer side of the alloy inner wall part 101 .

[0050] When processing and forming the alloy outer wall 102, a coaxial powder feeding method is used to melt and deposit the alloy powder on the outer side of the alloy inner wall part 101, and overlap with the alloy transition layer 103. During the manufacturing process, the powder conveying device and the laser are located on the same axis. The powder is directly fed into the laser beam under the push of the protective gas, and moves synchronously with the laser to form a molten pool. This technology can ensure uniform and stable feeding of powder, reduce the divergence angle, improve the accuracy of the cladding layer, and avoid diffuse reflection effects, thereby improving powder utilization.

[0051] The laser beam is transmitted along the central area of ​​the annular nozzle, and its central axis coincides with the central axis of the conical powder beam. Within a certain distance above the focal point where the powder particles converge, the powder particles begin to enter the laser irradiation area, and the powder particles under laser irradiation will undergo corresponding changes.

[0052] The powder particles under laser irradiation will be in different physical and chemical states due to the difference in laser power density and light-powder interaction time. Part of the laser energy will be absorbed by the powder, part of the energy will be directly lost due to scattering, and the remaining laser energy will reach the workpiece surface to melt the matrix and powder particles.

[0053] The matrix and powder particles under laser irradiation melt together to form a liquid molten pool, and as the laser moves forward, the liquid molten pool solidifies to form a deposition layer. This process is carried out layer by layer, and finally the desired alloy outer wall 102 structure is formed on the outer side of the alloy inner wall part 101.

[0054] In an optional embodiment, when processing and forming the alloy outer wall 102, GH3625 alloy powder is added into the second metal additive manufacturing equipment for processing and forming.

[0055] In an optional embodiment, GH3625 alloy powder is actually used for processing and forming the alloy outer wall 102. GH3625 is a high-performance nickel-based super alloy. GH3625 alloy powder has a complex chemical composition, including nickel, chromium, molybdenum, aluminum and other elements, which give the alloy high strength, thermal fatigue resistance, oxidation resistance and corrosion resistance.

[0056] During the processing, GH3625 alloy powder is fed into the laser beam through a powder feeding device, and the laser beam scans along a preset path, melts the powder and deposits it layer by layer on the outside of the alloy inner wall part 101. This process requires precise control of the laser energy, scanning speed and powder flow rate to ensure the uniformity and density of the alloy outer wall 102.

[0057] In an optional embodiment, when processing and forming the alloy outer wall 102, the laser power ratio of 4.05 kJ / cm2-4.41 kJ / cm2 and the overlap rate of 40%-65% are set and confirmed in the metal additive manufacturing equipment.

[0058] When processing and forming the alloy outer wall 102, the laser energy density and overlap rate in the metal additive manufacturing equipment are accurately set to optimize the melt deposition process and improve the forming quality. Laser energy density is one of the key factors affecting the formation of the molten pool and material deposition in the metal additive manufacturing process. In this embodiment, the laser energy density is set at 4.05 kJ / cm 2 Up to 4.41 kJ / cm 2 This energy density range can ensure that the GH3625 alloy powder is fully melted, while avoiding excessive energy that causes excessive evaporation or spheroidization of the material, affecting the accuracy and performance of the formed part.

[0059] The overlap ratio is set between 40% and 65%. This overlap ratio range helps to ensure that the cladding layer forms a good bond in the alloy transition layer 103 area, reducing defects such as pores and lack of fusion, while avoiding excessive energy input caused by too high an overlap ratio, which may cause spheroidization or poor forming.

[0060] In the actual processing, it is also necessary to monitor and adjust the laser energy density and overlap rate in real time to ensure that the optimal process parameters can be maintained under different forming conditions, and the melt deposition process of GH3625 alloy powder can be effectively controlled to produce an alloy outer wall 102 with excellent performance to meet the strict requirements of high-end industrial applications.

[0061] In an optional embodiment, when finishing the thrust chamber body 100, a five-axis machine tool is used until the finishing requirements are met, which can achieve complex spatial surface processing, reduce the number of clamping times during the processing, and improve processing efficiency and finished product quality.

[0062] It should be understood that the terms first, second, etc. are only used to distinguish descriptions and should not be understood as indicating or suggesting relative importance. Although the terms first, second, etc. may be used herein to describe various units, these units should not be limited by these terms. These terms are only used to distinguish one unit from another unit. For example, the first unit may be referred to as the second unit, and similarly, the second unit may be referred to as the first unit without departing from the scope of the exemplary embodiments of the present invention.

[0063] It should be understood that the term "and / or" in this article is merely a description of the association relationship of associated objects, indicating that three relationships may exist. For example, A and / or B can represent three situations: A exists alone, B exists alone, and A and B exist at the same time. The term " / and" in this article describes another relationship between associated objects, indicating that two relationships may exist. For example, A / and B can represent two situations: A exists alone, and A and B exist alone. In addition, the character " / " in this article generally indicates that the previous and next associated objects are in an "or" relationship.

[0064] It should be understood that in the description of the present invention, the terms "upper", "vertical", "inside", "outside" and the like indicate orientations or positional relationships that are customarily placed when the disclosed product is used, or are orientations or positional relationships that are customarily understood by those skilled in the art. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present invention.

[0065] In the description of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "setting", "installation" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be a communication between the two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0066] The terms used herein are only used to describe specific embodiments and are not intended to limit the exemplary embodiments of the present invention. As used herein, the singular forms "a", "an", and "the" are intended to include the plural forms unless the context clearly indicates the opposite meaning. It should also be understood that the terms "include", "comprising", "including", and / or "comprising" when used herein specify the existence of the claimed features, integers, steps, operations, units, and / or components, and do not exclude the existence or increase of one or more other features, quantities, steps, operations, units, components, and / or their combinations.

[0067] Specific details are provided in the following description to facilitate a complete understanding of the exemplary embodiments. However, it should be understood by those of ordinary skill in the art that the exemplary embodiments may be implemented without these specific details. In other embodiments, well-known processes, structures, and techniques may not be shown in unnecessary detail to avoid making the exemplary embodiments unclear.

[0068] The above is only a specific implementation of the present application, so that those skilled in the art can understand or implement the present application. Various modifications to these embodiments will be apparent to those skilled in the art, and the general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the present application. Therefore, the present application will not be limited to the embodiments shown herein, but will conform to the widest range consistent with the principles and novel features applied for herein.

[0069] It should be noted that the information disclosed in the above background technology section is only used to enhance the understanding of the background of the present disclosure, and therefore may include information that does not constitute the prior art known to ordinary technicians in the field.

Claims

1. A method for forming a thrust chamber body, characterized in that: The molding method comprises: Designing a thrust chamber body model in a design software, and designing an alloy transition layer on the outer side of an inner flow channel in the thrust chamber body model; The first metal additive manufacturing equipment is used to process and shape the alloy inner wall part; The alloy inner wall part is processed by a second metal additive manufacturing device to form an alloy outer wall on the outer side of the alloy inner wall, thereby obtaining a primary product of the thrust chamber body; The thrust chamber body is finely processed by fine processing equipment until the forming requirements are met, and the thrust chamber body is obtained as a finished product.

2. The method for forming a thrust chamber body according to claim 1, characterized in that: When processing and forming the alloy inner wall part, a laser selective melting forming method is adopted.

3. The method for forming a thrust chamber body according to claim 2, characterized in that: Before processing and forming the alloy inner wall part, the thrust chamber body model is first three-dimensionally sliced ​​in the design software to obtain a slice model, and the slice model is imported into the first metal additive manufacturing equipment to obtain a slice part, and then the alloy inner wall part is processed and formed by laser selective melting.

4. The method for forming a thrust chamber body according to claim 3, characterized in that: When processing and forming the alloy inner wall part, CuCrZr alloy powder is added into the first metal additive manufacturing equipment for processing and forming.

5. The method for forming a thrust chamber body according to claim 2, characterized in that: When the alloy inner wall part is processed and formed, the printing layer thickness is set and confirmed to be 20μm-40μm, the laser power is 300w-500w, the scanning speed is 500mm / s-650mm / s, and the scanning spacing is 0.07mm-0.10mm in the first metal additive manufacturing equipment.

6. The method for forming a thrust chamber body according to claim 1, characterized in that: When processing and forming the alloy outer wall, a laser melting deposition forming method is adopted.

7. The method for forming a thrust chamber body according to claim 6, characterized in that: When the alloy outer wall is processed and formed, a coaxial powder feeding method is adopted to melt the alloy powder and deposit it on the outer side of the alloy inner wall part, and overlap with the alloy transition layer.

8. The method for forming a thrust chamber body according to claim 7, characterized in that: When processing and forming the alloy outer wall, GH3625 alloy powder is added into the second metal additive manufacturing equipment for processing and forming.

9. The method for forming a thrust chamber body according to claim 7, characterized in that: When processing and forming the alloy outer wall, the laser capacity ratio of 4.05 kJ / cm2-4.41 kJ / cm2 and the overlap rate of 40%-65% are set and confirmed in the second metal additive manufacturing equipment.

10. The method for forming a thrust chamber body according to claim 1, characterized in that: When finishing the initial product of the thrust chamber body, a five-axis machine tool is used until the finishing requirements are met.

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