Rocket engine jet pipe reinforcing structure and manufacturing method of jet pipe structure

Abstract

The invention provides a rocket engine jet pipe reinforcing structure and a manufacturing method of the jet pipe structure.The manufacturing method of the rocket engine jet pipe reinforcing structure comprises the steps that the number and the size of reinforcing ring sections and lapping pieces are preset; a plate with the specified thickness is selected, and according to the preset number and size of the reinforcing ring sections and the lapping pieces, sheet metal forming is conducted on the reinforcing ring sections and the lapping pieces; the two reinforcing ring sections are placed on a welding tool, and the two reinforcing ring sections are in butt joint with each other along the end portions of one sides in the circumferential direction; the lap joint piece is placed at the butt joint position of the ends of the two reinforcing ring sections, and the lap joint piece is fixedly connected with the two reinforcing ring sections; and the process is repeated, the ring sections of the reinforcing ring are connected end to end, and the reinforcing structure comprising the complete annular reinforcing ring is formed. According to the manufacturing method, the forming difficulty of the structural molded surface of the reinforcing ring can be greatly reduced.

Description

Technical Field

[0001] The invention relates to the field of rocket engine nozzles, and in particular to a rocket engine nozzle reinforcement structure and a method for manufacturing the nozzle structure. Background Art

[0002] The nozzle of a rocket engine is usually designed as a large-sized thin-walled part. To improve the structural strength and rigidity of the nozzle, several reinforcement structures with specified radial thickness can be set at the specified axial position of the nozzle, such as reinforcement rings, which are rigidly connected to the thin-walled nozzle. For large-thrust and large-scale engine nozzles, the reinforcement rings set on their surfaces are usually difficult to process, and the connection structure and process between the reinforcement ring and the nozzle often lead to problems such as product weight increase, structural deformation, and material damage.

[0003] In order to reduce the difficulty of processing the reinforcement ring, it is particularly important to design a manufacturing method for the rocket engine nozzle reinforcement structure. Summary of the invention

[0004] The purpose of the present invention is to overcome the deficiencies of the prior art and provide a method for manufacturing a rocket engine nozzle reinforcement structure.

[0005] The present invention provides a method for manufacturing a rocket engine nozzle reinforcement structure, such as a reinforcement ring, comprising: presetting the number and size of reinforcement ring segments and straps; selecting a plate of specified thickness, and forming the reinforcement ring segments and straps by sheet metal according to the preset number and size of reinforcement ring segments and straps; placing two reinforcement ring segments on a welding tool, and butting the ends of the two reinforcement ring segments along one side of the circumferential direction against each other; placing the strap at the end butting position of the two reinforcement ring segments, and fixedly connecting the strap to the two reinforcement ring segments; repeating the above process, connecting the reinforcement ring segments end to end, and forming a complete annular reinforcement ring.

[0006] According to an embodiment of the present invention, both side surfaces in the axial direction of the reinforcement ring segment are respectively provided with outwardly extending ring segment flanges; the ring segment flanges are used for fixed connection with the outer side wall of the nozzle.

[0007] According to one embodiment of the present invention, the flap is provided with a flap flange; placing the flap at the end docking position of the two reinforcement ring segments includes: overlapping and pressing the flap flange with the ring segment flange, so that the gap between the flap flange and the ring segment flange after pressing is less than 1 / 2 of the thickness of the flap flange.

[0008] According to one embodiment of the present invention, corresponding assembly positioning holes are provided on the strap and the reinforcement ring segment; overlapping and pressing the strap flange with the ring segment flange comprises: overlapping the strap flange with the ring segment flange; using positioning pins to penetrate the corresponding assembly positioning holes of the strap and the reinforcement ring segment, and using bolt fasteners to cooperate with the positioning pins to fasten the strap flange with the ring segment flange.

[0009] According to one embodiment of the present invention, fixedly connecting the strap to the two reinforcement ring segments includes: determining welding parameters based on the thickness of the strap flange and the thickness of the ring segment flange, wherein the welding parameters include power, swing amplitude, frequency and duration; welding with the welding gun head according to the specified power, swing amplitude, frequency and duration, so that the thickness of the strap flange and the ring segment flange are melted through, and the strap and the reinforcement ring segment are welded into the integral reinforcement ring.

[0010] According to one embodiment of the present invention, a gas nozzle is provided at a welding gun head; before the welding gun head welds according to specified power, swing amplitude, frequency and duration so that the thickness of the lap flange and the ring segment flange are melted through, and the lap and the reinforcement ring segment are welded into the integral reinforcement ring, it includes: adjusting the position of the gas nozzle at the welding gun head so that the height of the gas nozzle outlet from the welding surface is less than 20 mm; supplying shielding gas to the gas nozzle, and the gas nozzle guides the shielding gas to the weld.

[0011] On the other hand, the present invention provides a method for manufacturing a nozzle structure, comprising: sleeve-arranging the reinforcement ring as described above at a specified height position on the circumferential outer side surface of the nozzle; hoisting the nozzle and the reinforcement ring as a whole to a welding fixture; using bolt fasteners on the welding fixture to pull the reinforcement ring along the axial direction of the nozzle toward the outlet direction of the nozzle so that the ring segment flange is tightly fitted with the outer side surface of the nozzle; the gap between the ring segment flange and the outer side surface of the nozzle is less than 1 / 2 of the thickness of the ring segment flange; welding the ring segment flange to the outer side surface of the nozzle to obtain a nozzle with the reinforcement ring.

[0012] According to one embodiment of the present invention, welding the ring segment flange and the outer side surface of the nozzle to obtain the nozzle with a reinforcement ring includes: making the welding gun head perpendicular to the ring segment flange and the nozzle welding surface; determining the welding parameters according to the thickness of the lap flange, the thickness of the ring segment flange and the thickness of the nozzle; welding the ring segment flange and the outer side surface of the nozzle to obtain the nozzle with a reinforcement ring includes: welding with the welding gun head according to specified power, swing amplitude, frequency and duration to make the thickness of the lap flange, the ring segment flange and the nozzle melt through, and welding the reinforcement ring and the nozzle.

[0013] According to one embodiment of the present invention, the welding gun head welds according to the specified power, swing amplitude, frequency and duration to make the thickness of the lap flange, the ring segment flange and the nozzle melt through, and weld the reinforcement ring and the nozzle, including: according to the requirements of the connection strength between the reinforcement ring and the nozzle, forming evenly arranged circular welds in the ring segment flange area along the circumferential direction of the reinforcement ring.

[0014] According to one embodiment of the present invention, the welding tool is provided with a gas protection groove; the width of the gas protection groove is greater than or equal to twice the front diameter of the weld, and the depth of the gas protection groove is not less than 5 mm; before welding the ring segment flange and the outer side surface of the nozzle to obtain the nozzle with a reinforcement ring, it includes: placing the gas protection groove on the inner side surface of the nozzle close to the weld; passing protective gas to the gas protection groove, and the ventilation time is greater than 10 minutes.

[0015] According to the manufacturing method of the rocket engine nozzle reinforcement structure (reinforcement ring) of the present invention, the difficulty of forming the reinforcement ring structure surface can be greatly reduced.

[0016] It should be understood that the above general description and the following detailed description are merely exemplary and illustrative and are not intended to limit the scope of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The following drawings are a part of the specification of the present invention, and illustrate exemplary embodiments of the present invention. Together with the description of the specification, the accompanying drawings are used to explain the principles of the invention.

[0018] Figure 1 A flow chart of a method for manufacturing a rocket engine nozzle reinforcement ring according to one embodiment of the present invention; Figure 2 is a schematic diagram of a nozzle structure with a reinforcement ring according to an embodiment of the present invention; Figure 3 is a cross-sectional view of a reinforcement ring according to an embodiment of the present invention; Figure 4 is a cross-sectional view of a reinforcement ring according to another embodiment of the present invention; Figure 5 A cross-sectional view of a reinforcement ring according to another embodiment of the present invention; Figure 6 is a schematic diagram of a reinforced ring weld according to an embodiment of the present invention; Figure 7 is a flow chart of a method for manufacturing a nozzle structure according to an embodiment of the present invention; Figure 8 is a schematic diagram of a reinforced ring weld according to another embodiment of the present invention; Fig. 9 Schematic diagram of a reinforced ring weld according to another embodiment of the present invention.

[0019] Description of reference numerals: 1- reinforcing ring segment; 2- lap; 3- nozzle; 4- triangular profile; 5- ring segment flange; 6- assembly positioning hole; 7- circular weld; 8- wavy line weld; 9- parallel line weld; 10- rectangular profile; 11- semicircular profile. DETAILED DESCRIPTION

[0020] The features and exemplary embodiments of various aspects of the present invention will be described in detail below. In order to make the purpose, technical solutions and advantages of the present invention clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only configured to explain the present invention and are used to illustrate the principles of the present invention, and are not configured to limit the present invention. In addition, the structural components in the drawings are not necessarily drawn to scale. For example, the sizes of some structural components or areas in the drawings may be enlarged for other structural components or areas to help understand the embodiments of the present invention.

[0021] The directional words appearing in the following description are all directions shown in the figures, and do not limit the specific structure of the embodiments of the present invention. In the description of the present invention, it should be noted that, unless otherwise specified, the terms "installation", "connection" 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 directly connected or indirectly connected through an intermediate medium. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to the specific circumstances.

[0022] In addition, the terms "include", "comprise", "have" or any other variations thereof are intended to cover non-exclusive inclusion, so that a structure or component including a series of elements includes not only those elements, but also other mechanical elements that are not explicitly listed or inherent in the structure or component. In the absence of more restrictions, the elements defined by the sentence "include..." do not exclude the existence of other identical elements in the article or device including the elements.

[0023] Spatially related terms such as "below", "beneath", "under", "low", "above", "on", "high", etc. are used to facilitate description to explain the positioning of one element relative to a second element, indicating that these terms are intended to cover different orientations of the device in addition to orientations different from those shown in the figures. In addition, for example, "one element is above / below another element" can mean that the two elements are in direct contact, or that there are other elements between the two elements. In addition, terms such as "first", "second", etc. are also used to describe various elements, regions, parts, etc., and do not specifically refer to the meaning of order or sequence, and should not be regarded as limiting. Similar terms are used throughout the description to represent similar elements.

[0024] In the process of describing the present invention below, in certain scene descriptions, only "rocket", "launch vehicle", "spacecraft", "space launch vehicle" or "missile" may be used. This is only for the convenience of description, and its connotation is not limited to the specific words used. Generally, the rocket of the present invention includes both launch vehicles or space launch vehicles for carrying satellites or spacecraft or other probes, and various types of missiles, rockets and other weapons for carrying military payloads, as well as similar products that can send payloads into the air. When interpreting the above specific words, those skilled in the art shall not limit the rocket to only one of the launch vehicle or missile based on the specific words used to describe the scene, thereby narrowing the scope of protection of the present invention.

[0025] For those skilled in the art, the present invention can be implemented without some of these specific details. The following description of the embodiments is only intended to provide a better understanding of the present invention by showing examples of the present invention.

[0026] Figure 1 A flow chart of a method for manufacturing a rocket engine nozzle reinforcement ring according to one embodiment of the present invention; Figure 2 is a schematic diagram of a nozzle structure with a reinforcement ring according to an embodiment of the present invention; Figure 3 is a cross-sectional view of a reinforcement ring according to an embodiment of the present invention; Figure 4 is a cross-sectional view of a reinforcement ring according to another embodiment of the present invention; Figure 5 A cross-sectional view of a reinforcement ring according to another embodiment of the present invention; Figure 6 is a schematic diagram of a reinforced ring weld according to an embodiment of the present invention; Figure 7 is a flow chart of a method for manufacturing a nozzle structure according to an embodiment of the present invention; Figure 8 is a schematic diagram of a reinforced ring weld according to another embodiment of the present invention; Fig. 9 Schematic diagram of a reinforced ring weld according to another embodiment of the present invention.

[0027] like Figure 1 and 2As shown, the present invention provides a method for manufacturing a rocket engine nozzle reinforcement structure, such as a reinforcement ring, comprising: S01: Preset the number and size of the reinforcing ring segments 1 and the straps 2; S02: Select a plate of a specified thickness, and form the reinforcing ring segments 1 and the straps 2 by sheet metal according to the preset number and size of the reinforcing ring segments 1 and the straps 2; S03: placing two reinforcement ring segments 1 on a welding fixture, and butting one end portion of the two reinforcement ring segments 1 along the circumferential direction against each other; S04: placing the strap 2 at the butt joint position of the ends of the two reinforcement ring segments 1, and fixing the strap 2 to the two reinforcement ring segments 1; S05: Repeat the above process to connect the reinforcing ring segment 1 end to end to form a complete annular reinforcing ring.

[0028] Specifically, the forming and installation and fixing methods of large-scale nozzle reinforcement rings usually have the following problems: 1) When using annular forging machines to form reinforcement rings, the price is high, the cycle is long, the material utilization rate is low, and some special metal materials cannot be used to prepare large-scale ring segments; 2) When using standard pipes to bend and form reinforcement rings, the cross-sectional shape of the reinforcement ring is limited by the shape of the pipe, and the installation and connection matching with the nozzle is poor, and some special metal materials cannot be used to prepare standard pipes; 3) The reinforcement ring and the nozzle can be rigidly connected by welding, among which manual or automatic argon arc welding is more commonly used, but the welding heat input of these two welding methods is large, thin-walled nozzles are prone to thermal deformation, and some metal materials that are extremely prone to oxidation cannot be welded by argon arc welding; 4) The reinforcement ring and the nozzle can be rigidly connected by fasteners, but a large number of fasteners and holes need to be prefabricated on the surface of the nozzle and the reinforcement ring, which is complicated and will cause the structure to increase in weight.

[0029] In this embodiment, a plurality of reinforcing ring segments 1 are connected to each other through straps 2 to form a complete circular ring. For example, the same number of straps 2 as the reinforcing ring segments 1 can be configured, and adjacent reinforcing ring segments 1 are connected through one strap 2. The manufacturing method of the rocket engine nozzle reinforcing ring can greatly reduce the difficulty of forming the reinforcing ring structure profile by forming a designated profile by segmented sheet metal and splicing a plurality of reinforcing ring segments 1 to form the entire ring, thereby increasing the degree of freedom in the design of its cross-sectional shape, thereby providing great convenience for the design of its profile and improving the utilization rate of materials. In addition, for the reinforcing ring structure that requires the use of special metal materials, for example, if the material is supplied in a single form and is small in size, the manufacturing method can eliminate the unfavorable constraints such as size restrictions caused by the raw materials.

[0030] According to one embodiment of the present invention, the reinforcement ring includes six reinforcement ring segments 1 .

[0031] In this embodiment, the number of reinforcement ring segments 1 can be determined according to the product perimeter, raw material width, sheet metal forming process, etc. For example, six reinforcement ring segments 1 can be connected end to end to form a complete annular reinforcement ring.

[0032] like Figure 2 and 3 As shown, according to one embodiment of the present invention, the sheet metal forming reinforcement ring segment 1 includes: The cross section of the reinforcement ring segment 1 along its axial direction is processed into a triangular profile 4 .

[0033] In this embodiment, the reinforcing ring segment 1 is processed into a triangular profile, so that it has the highest structural efficiency and the lightest weight under the same performance requirements. Those skilled in the art will understand that processing the reinforcing ring segment 1 into a triangular profile is the best embodiment, but it is not intended to limit the scope of protection of the present invention. Figure 4 and 5 As shown, for example, the reinforcement ring segment 1 can also be processed into a rectangular profile 10, a semicircular profile 11, etc.

[0034] like Figure 2 and Figure 3 As shown, according to one embodiment of the present invention, the two axial side surfaces of the reinforcing ring segment 1 are respectively provided with outwardly extending ring segment flanges 5. The ring segment flanges 5 are used to be fixedly connected to the outer side wall of the nozzle 3.

[0035] According to one embodiment of the present invention, the flap 2 is provided with a flap flange. Placing the flap 2 at the end butt joint position of two reinforcement ring segments 1 includes: The flap flange and the ring segment flange 5 are overlapped and pressed together so that the gap between the flap flange and the ring segment flange 5 after pressing together is smaller than 1 / 2 of the thickness of the flap flange.

[0036] like Figure 6 As shown, according to one embodiment of the present invention, the strap 2 and the reinforcing ring segment 1 are provided with corresponding assembly positioning holes 6. Overlapping and pressing the flap of the strap and the flange of the ring segment 5, including: S041: Overlap the flap edge with the ring segment flange 5; S042: Use a positioning pin to penetrate the assembly positioning holes 6 corresponding to the strap 2 and the reinforcement ring segment 1, and use bolt fasteners to cooperate with the positioning pin to fasten the strap flange and the ring segment flange 5.

[0037] The manufacturing method provided in this embodiment processes assembly positioning holes 6 at corresponding positions of the lap 2 and the reinforcing ring segment 1. When assembling the lap 2 and the reinforcing ring segment 1, the docking position accuracy of the reinforcing ring segment 1 and the lap can be ensured by aligning the assembly positioning holes 6 corresponding to the lap 2 and the reinforcing ring segment 1.

[0038] According to one embodiment of the present invention, fixedly connecting the strap 2 to the two reinforcement ring segments 1 includes: S043: Determine welding parameters according to the thickness of the flange of the strap and the thickness of the flange of the ring segment 5, wherein the welding parameters include power, swing amplitude, frequency and duration; S044: The welding gun head welds according to the specified power, swing amplitude, frequency and duration, so that the thickness of the lap flange and the ring segment flange 5 are melted through, and the lap 2 and the reinforcement ring segment 1 are welded into an integral reinforcement ring.

[0039] In this embodiment, for example, the laser welding gun can be made perpendicular to the welding surface of the ring segment flange and the flap flange, and according to the preset laser power parameters, the lens group at the head of the laser welding gun is used to perform a circle welding process with a specified power, swing amplitude, frequency, and duration, and the flap flange and the ring segment flange 5 are overlap-welded and fused (for example, laser overlap welding), and the weld shape is a circular weld 7, ensuring that the flap flange and the ring segment flange are melted through, and then the whole is welded and connected with the outer wall of the nozzle 3. For example, the profile of the flap 2 can be similar to the profile of the reinforcing ring segment 1 to improve the adaptability to the reinforcing ring segment 1. For example, the flap 2 also adopts a triangular profile structure with a flange.

[0040] According to one embodiment of the present invention, after the strap 2 and the reinforcement ring segment 1 are welded into an integral reinforcement ring, the method comprises: Check the quality of the joints between the lap and the reinforcing ring section to ensure that there are no obvious depressions on the front and back sides of the weld.

[0041] For example, if the connection between the strap and the reinforcement ring segment is in the form of a circular weld, the front diameter of the circular weld should be no less than 5 mm, and the back diameter of the circular weld should be no less than 1 / 2 of the front diameter.

[0042] According to an embodiment of the present invention, two assembly positioning holes 6 are respectively provided on both sides of the strap 2 close to the corresponding reinforcement ring segment, and each two assembly positioning holes 6 are used for fixed connection with the corresponding reinforcement ring segment 1 .

[0043] According to one embodiment of the present invention, the welding gun head is provided with a gas nozzle. Before the welding gun head welds at a specified power, swing amplitude, frequency and duration, so that the thickness of the lap flange and the ring segment flange 5 are melted through, and the lap 2 and the reinforcement ring segment 1 are welded into an integral reinforcement ring, the steps include: S0441: Adjust the position of the gas nozzle at the welding gun head so that the height of the gas nozzle outlet from the welding surface is less than 20mm; S0442: Supply shielding gas to the gas nozzle, which directs the shielding gas to the weld.

[0044] In this embodiment, the gas nozzle and the welding gun head can be coaxially arranged, and the outlet diameter of the gas nozzle is greater than or equal to twice the front diameter of the weld. The gas output of the gas nozzle can be ensured by air pressure, for example, the gas pressure of the gas nozzle can be not less than 0.2MPa.

[0045] On the other hand, Figure 7 As shown, the present invention provides a method for manufacturing a nozzle structure, comprising: S11: The reinforcement ring as described above is sleeved at a specified height position of the outer circumferential surface of the nozzle 3; S12: hoisting the nozzle 3 and the reinforcement ring as a whole to the welding fixture; S13: Use the bolt fasteners on the welding tool to pull the reinforcement ring along the axial direction of the nozzle 3 toward the outlet direction of the nozzle 3, so that the ring segment flange 5 is tightly fitted with the outer side surface of the nozzle 3; wherein the gap between the ring segment flange 5 and the outer side surface of the nozzle 3 needs to be less than 1 / 2 of the thickness of the ring segment flange 5; S14: welding the ring segment flange 5 and the outer side surface of the nozzle 3 to obtain a nozzle with a reinforcement ring.

[0046] In this embodiment, for example, multiple reinforcement rings can be respectively sleeved at different designated height positions of the nozzle 3 and welded to increase the structural strength of the nozzle 3. For example, the nozzle and the reinforcement ring can be welded by laser welding process. In this embodiment, based on the sheet metal forming and laser welding process of metal materials, the structural reinforcement of the engine nozzle can be achieved efficiently, reliably and conveniently. Especially for thin-walled nozzles, the advantages of laser welding process are more obvious.

[0047] According to one embodiment of the present invention, welding the ring segment flange 5 and the outer side surface of the nozzle 3 to obtain the nozzle with a reinforcement ring includes: S141: Make the welding gun head perpendicular to the welding surface of the ring flange and the nozzle; S142: Determine welding parameters according to the thickness of the flange of the lap, the thickness of the flange of the ring segment 5 and the thickness of the nozzle 3.

[0048] Welding the ring segment flange 5 to the outer side surface of the nozzle 3 to obtain the nozzle with a reinforcement ring includes: S143: The welding gun head welds according to the specified power, swing amplitude, frequency and duration, so that the thickness of the lap flange, the ring segment flange 5 and the nozzle 3 are melted through, and the reinforcing ring and the nozzle 3 are welded.

[0049] In this embodiment, the laser welding gun can be made perpendicular to the welding surface of the ring segment flange and the nozzle, and the power parameters of the laser are determined according to the total thickness of the ring segment flange 5 (and the flap flange) and the nozzle that need to be melted through. The lens group at the head of the laser welding gun is used to perform a circle welding process with a specified power, swing amplitude, frequency, and duration, and the ring segment flange 5 (and the flap flange) and the nozzle 3 are welded together (for example, laser welded together). The shape of the weld is a circular weld 7, which ensures that the ring segment flange (and the flap flange) and the nozzle are melted through, so as to rigidly connect the reinforcement ring to the nozzle. Laser welded together on the ring segment flange 5 structure can reduce the process difficulty of connecting it with the nozzle, improve the reliability of the connection, and eliminate the problem of structural deformation caused by excessive heat input when the traditional nozzle and reinforcement ring are welded by argon arc welding, and more easily achieve reliable atmosphere protection and anti-oxidation. Especially for special metal materials that are very easy to oxidize, the reinforcement ring structure has more advantages in use, so that designers can use such special materials in the field of rocket engines more conveniently and more controllably. In addition, laser welding the reinforcement ring to the nozzle 3 through the ring segment flange 5 can avoid the use of additional fasteners for connecting the reinforcement ring and the nozzle, making the process simpler and reducing the weight of the structure.

[0050] According to one embodiment of the present invention, after the reinforcement ring and the nozzle 3 are welded, the following steps are included: Check the quality of the joint between the reinforcement ring and the nozzle to ensure that there are no obvious depressions on the front and back sides of the weld.

[0051] For example, if the connection between the reinforcement ring and the nozzle is a circular weld, the front diameter of the circular weld should be no less than 5 mm, and the back diameter of the circular weld should be no less than 1 / 2 of the front diameter.

[0052] According to one embodiment of the present invention, the welding gun head welds according to the specified power, swing amplitude, frequency and duration, so that the thickness of the flap flange, the ring segment flange 5 and the nozzle 3 are melted through, and the reinforcing ring and the nozzle 3 are welded, including: According to the requirement of connection strength between the reinforcement ring and the nozzle 3, uniformly arranged circular welds 7 are formed in the region of the ring segment flange 5 along the circumferential direction of the reinforcement ring.

[0053] In this embodiment, according to the design requirements of the connection strength between the reinforcement ring and the nozzle, the upper and lower ( Figure 2 A specified number of circular welds 7 are evenly arranged in the circumferential direction of the two ring segment flange areas on both sides (as shown in the upper and lower positions).

[0054] Those skilled in the art will understand that the laser stitch welding process used in this embodiment to weld the reinforcement ring and the nozzle to form a circular weld is only used to illustrate the connection method between the reinforcement ring and the nozzle in this embodiment, and is not used to limit the scope of protection of the present invention. Figure 8 and 9As shown, there may also be a wavy weld 8 or a parallel weld 9 between the ring segment flange 5 and the side wall of the nozzle 3 .

[0055] According to one embodiment of the present invention, the welding tool is provided with a gas protection groove. The width of the gas protection groove is greater than or equal to twice the diameter of the front face of the weld, and the depth of the gas protection groove is not less than 5 mm. Before welding the ring segment flange 5 and the outer side surface of the nozzle 3 to obtain the nozzle 3 with a reinforcement ring, the following steps are included: S131: placing the gas protection groove on the inner side of the nozzle 3 close to the weld; S132: Supply protective gas to the gas protection tank, and the ventilation time is greater than 10 minutes.

[0056] In this embodiment, especially for special metal materials that are prone to oxidation during welding, it is necessary to perform inert gas protection on the front and back sides of the weld before welding (for example, laser welding). The gas protection on the front side of the weld can be achieved through the gas nozzle at the welding gun head, and the gas protection on the back side of the weld can be achieved through the gas protection groove on the welding tool.

[0057] For example, the gas nozzle and the welding gun head can be coaxially arranged so that the height of the gas nozzle outlet from the welding surface is less than 20 mm, and the outlet diameter of the gas nozzle is greater than or equal to twice the front diameter of the weld. Before and after welding, it is necessary to adjust the gas output of the gas nozzle by controlling the air pressure so that the air pressure is not less than 0.2 MPa. In addition, it is necessary to adjust the gas output of the gas shielding tank by the volume flow rate so that the volume flow rate of the shielding gas is not less than 10 L / min. Before welding, the weld is pre-inertly replaced by the gas nozzle and the gas shielding tank, wherein the front replacement time is not less than 1 minute, and the back replacement time is not less than 10 minutes, which can ensure that the easily oxidized metal materials will not be exposed to the air during the entire welding process, thereby ensuring the mechanical properties of the weld.

[0058] Those skilled in the art will appreciate that, in the present invention, the description of laser welding is only an auxiliary means for illustrating the structure of the present invention, and is not intended to limit the scope of protection of the present invention. For example, the reinforcing ring structure can also be fixedly connected to the nozzle by electron beam welding or the like.

[0059] The above-mentioned embodiments of the present invention can be combined with each other and have corresponding technical effects.

[0060] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A method for manufacturing a rocket engine nozzle reinforcement structure, characterized in that: include: Preset the number and size of reinforcing ring segments and straps; Selecting a plate of a specified thickness, and forming the reinforcing ring segments and the straps by sheet metal according to the preset number and size of the reinforcing ring segments and the straps; Placing the two reinforcement ring segments on a welding fixture, and butting one end portion of the two reinforcement ring segments along the circumferential direction against each other; Placing the strap at the butt joint position of the ends of the two reinforcement ring segments, and fixedly connecting the strap to the two reinforcement ring segments; The above process is repeated to connect the reinforcement ring segments end to end to form a reinforcement structure including a complete annular reinforcement ring.

2. The manufacturing method according to claim 1, characterized in that: The two side surfaces of the reinforcing ring segment in the axial direction are respectively provided with ring segment flanges extending outwards; the ring segment flanges are used for fixed connection with the outer side wall of the nozzle.

3. The manufacturing method according to claim 2, characterized in that: The strap is provided with a strap flange; Placing the strap at the end butt joint position of the two reinforcement ring segments includes: The flap flange and the ring segment flange are overlapped and pressed together, so that the gap between the flap flange and the ring segment flange after pressing is less than 1 / 2 of the thickness of the flap flange.

4. The manufacturing method according to claim 3, characterized in that: The strap and the reinforcement ring segment are provided with corresponding assembly positioning holes; The overlapping and pressing of the flap flange and the ring segment flange comprises: Overlapping the flap flange with the ring segment flange; A positioning pin is used to penetrate the assembly positioning holes corresponding to the strap and the reinforcement ring segment, and a bolt fastener is used to cooperate with the positioning pin to fasten the flap flange and the ring segment flange.

5. The manufacturing method according to claim 4, characterized in that: The fixed connection of the strap to the two reinforcement ring segments comprises: Determining welding parameters according to the flange thickness of the strap and the flange thickness of the ring segment, wherein the welding parameters include power, swing amplitude, frequency and duration; The welding gun head welds according to the specified power, swing amplitude, frequency and duration, so that the thickness of the flange of the strap and the flange of the ring segment are melted through, and the strap and the reinforcement ring segment are welded into the integral reinforcement ring.

6. The manufacturing method according to claim 5, characterized in that: The welding gun head is provided with a gas nozzle; Before the welding gun head welds according to the specified power, swing amplitude, frequency and duration, so that the thickness of the flange of the strap and the flange of the ring segment are melted through, and the strap and the reinforcement ring segment are welded into the integral reinforcement ring, the method includes: Adjust the position of the gas nozzle at the welding gun head so that the height of the gas nozzle outlet from the welding surface is less than 20 mm; Shielding gas is passed to the gas nozzle, and the gas nozzle guides the shielding gas to the weld.

7. A method for manufacturing a nozzle structure, characterized in that: include: The reinforcing ring in the manufacturing method according to any one of claims 1 to 6 is sleeved at a specified height position on the circumferential outer side of the nozzle; Lift the nozzle and reinforcement ring as a whole to the welding fixture; Use the bolt fasteners on the welding fixture to pull the reinforcement ring along the axial direction of the nozzle toward the nozzle outlet, so that the ring flange fits tightly with the outer side of the nozzle; the gap between the ring flange and the outer side of the nozzle is less than 1 / 2 of the thickness of the ring flange; The ring segment flange is welded to the outer side surface of the nozzle to obtain a nozzle with a reinforcement ring.

8. The manufacturing method according to claim 7, characterized in that: Before welding the ring segment flange and the outer side surface of the nozzle to obtain the nozzle with a reinforcement ring, the process includes: Make the welding gun head perpendicular to the flange of the ring segment and the welding surface of the nozzle; Determining welding parameters according to the flange thickness of the strap, the flange thickness of the ring segment and the nozzle thickness; Welding the ring segment flange and the outer side surface of the nozzle to obtain the nozzle with a reinforcement ring includes: The welding gun head welds according to the specified power, swing amplitude, frequency and duration, so that the thickness of the lap flange, the ring segment flange and the nozzle are melted through, and the reinforcement ring and the nozzle are welded.

9. The manufacturing method according to claim 8, characterized in that: The welding gun head welds according to the specified power, swing amplitude, frequency and duration, so that the thickness of the flap flange, the flange of the ring segment and the nozzle are melted through, and the reinforcement ring and the nozzle are welded, including: According to the requirement of connection strength between the reinforcement ring and the nozzle, evenly arranged circular welds are formed in the flanged area of ​​the ring segment along the circumferential direction of the reinforcement ring.

10. The manufacturing method according to claim 7, characterized in that: The welding tool is provided with a gas protection groove; the width of the gas protection groove is greater than or equal to twice the front diameter of the weld, and the depth of the gas protection groove is not less than 5 mm; Before welding the ring segment flange and the outer side surface of the nozzle to obtain the nozzle with a reinforcement ring, the process includes: Placing the gas protection groove on the inner side of the nozzle close to the weld; The protective gas is passed into the gas protection tank, and the ventilation time is greater than 10 minutes.

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