A rocket engine combustion chamber with a combined welding structure

Abstract

The application discloses a rocket engine combustion chamber adopting a combined welding structure, which comprises a first inner wall and a second inner wall, wherein the second inner wall is coaxially connected with the first inner wall; a throat is further arranged on the first inner wall; along the axis of the first inner wall, the joint seam between the first inner wall and the second inner wall is offset to one side of the throat; the engine combustion chamber further comprises a first outer wall and a second outer wall, wherein the second outer wall is sleeved on the outer surface of the second inner wall; the second outer wall is coaxially connected with the first outer wall; a bushing is further arranged between the first inner wall and the first outer wall, and the inner wall of the bushing is tightly combined with the throat; the inner wall and the outer wall are cut along the radial direction, but the cutting area is offset to one side of the throat, so that the throat area is completely reserved, the structural strength and stability of the whole combustion chamber are ensured; the outer diameter of the throat is adjusted through the bushing, the throat is connected with the first outer wall in the state of the minimum outer diameter, the assembly interference problem caused by the complete reservation of the throat structure is avoided, and the assembly difficulty is reduced.

Description

Technical Field

[0001] This application relates to the field of aerospace equipment technology, specifically to a rocket engine combustion chamber employing a combined welded structure. Background Technology

[0002] The rocket engine combustion chamber consists of an inner wall and an outer wall. The inner wall is made of copper alloy and has a densely distributed ribbed structure along its axial direction. The outer wall is made of materials such as stainless steel, high-temperature alloy, and high-strength alloy steel. The surface of the inner wall ribs is connected to the inner surface of the outer wall, allowing the inner wall channels to withstand high-pressure fuel.

[0003] Both the inner and outer walls of the combustion chamber are Laval-shaped, with the diameter of the throat in the middle being smaller than that at both ends. This structural form means that the inner and outer walls cannot be assembled by axial insertion. In the prior art, the inner wall is often treated as a whole while the outer wall is cut into two halves along the axial direction, or the outer wall is treated as a whole while the inner wall is cut into two halves along the radial direction. After splicing, they are connected by welding. However, regardless of the processing method, the throat, which has the highest working pressure and the harshest working environment, will be cut off, thus affecting the reliability of the combustion chamber. Utility Model Content

[0004] The main objective of this application is to provide a rocket engine combustion chamber with a combined welded structure, which aims to solve the problem of low reliability of combustion chambers in the prior art.

[0005] This application achieves the above objectives through the following technical solutions:

[0006] A rocket engine combustion chamber employing a combined welded structure includes a first inner wall;

[0007] The second inner wall is coaxially connected to the first inner wall; the first inner wall is also provided with a throat, and along the axis of the first inner wall, the splice between the first inner wall and the second inner wall is offset to one side of the throat.

[0008] The first outer wall is fitted onto the outer surface of the first inner wall;

[0009] The second outer wall is fitted onto the outer surface of the second inner wall; the second outer wall is coaxially connected to the first outer wall.

[0010] A bushing is disposed between the first inner wall and the first outer wall, and the inner wall of the bushing is in close contact with the throat.

[0011] Optionally, a first compensation boss is provided on the first inner wall, and a second compensation boss is provided on the second inner wall, wherein the first compensation boss and the second compensation boss are spliced ​​together.

[0012] Optionally, the height of both the first compensation boss and the second compensation boss is 0.2-0.5mm.

[0013] Optionally, along the axial direction of the first inner wall, the distance between the joint between the first inner wall and the second inner wall and the throat is 2-4 cm.

[0014] Optionally, a splicing ring is provided on the first outer wall, and a splicing groove is provided on the second outer wall, wherein the splicing ring is inserted into the splicing groove.

[0015] Optionally, the bushing includes at least two liner bodies, arranged around the axis of the throat, with each liner body connected end to end in a closed annular structure; the inner wall of each liner body is tightly fitted to the outer surface of the throat.

[0016] Optionally, the first outer wall includes an arc-shaped converging section and a straight section, the small end of the arc-shaped converging section being integrally connected to the straight section; the inner wall of the straight section is tightly fitted to the outer wall of the liner.

[0017] Compared with the prior art, this application has the following beneficial effects:

[0018] This application includes a first inner wall and a second inner wall, the second inner wall being coaxially connected to the first inner wall; a throat is also provided on the first inner wall, and along the axis of the first inner wall, the joint between the first inner wall and the second inner wall is offset to one side of the throat; the engine combustion chamber also includes a first outer wall and a second outer wall, the second outer wall being sleeved on the outer surface of the second inner wall; the second outer wall is coaxially connected to the first outer wall; a bushing is also provided between the first inner wall and the first outer wall, and the inner wall of the bushing is tightly fitted to the throat.

[0019] Compared with the prior art, this application cuts the inner and outer walls in the radial direction, but places the cut area on one side of the throat, thereby completely preserving the structure of the throat area and ensuring the structural strength and stability of the entire combustion chamber.

[0020] At the same time, by setting the bushing, the throat area with the smallest inner diameter is filled, ensuring that the outer diameter of the throat area is exactly the same. That is, the throat is connected to the first outer wall with the smallest outer diameter, thereby realizing the insertion and assembly of the first inner wall and the first outer wall. This avoids the assembly interference problem caused by the complete preservation of the throat structure, reduces the assembly difficulty of the first inner wall and the first outer wall, and reduces the assembly and processing difficulty of the rocket engine combustion chamber.

[0021] Secondly, compared with the prior art, this application reduces the volume of the bushing as much as possible while ensuring the integrity of the throat structure, thereby reducing the mass of the bushing and thus reducing the mass of the entire engine combustion chamber. Attached Figure Description

[0022] Figure 1 A schematic diagram of a rocket engine combustion chamber employing a combined welded structure is provided as an embodiment of this application;

[0023] Figure 2 An exploded view of a rocket engine combustion chamber employing a combined welded structure, provided as an embodiment of this application;

[0024] Figure 3 An axial sectional view of a rocket engine combustion chamber employing a combined welded structure, provided as an embodiment of this application;

[0025] Figure 4 for Figure 2 Enlarged view of section A in the middle;

[0026] Figure 5 This is a schematic diagram of the structure of the first outer wall;

[0027] Reference numerals: 1-First inner wall, 2-Second inner wall, 3-Throat, 4-First outer wall, 5-Second outer wall, 6-Bushing, 7-First compensating boss, 8-Second compensating boss, 9-Splicing ring, 10-Splicing groove, 401-Arc-shaped converging section, 402-Straight section, 601-Nutrition.

[0028] The purpose, features, and advantages of this application will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0029] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0030] It should be noted that all directional indicators (such as up, down, left, right, front, back, etc.) in this utility model embodiment are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indicator will also change accordingly.

[0031] In this utility model, unless otherwise explicitly specified and limited, the terms "connection," "fixing," etc., should be interpreted broadly. For example, "fixing" can mean a fixed connection, a detachable connection, or an integral part; it can mean a mechanical connection or an electrical connection; it can mean a direct connection or an indirect connection through an intermediate medium; it can mean the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0032] Furthermore, if the embodiments of this utility model involve descriptions such as "first" or "second," these descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the meaning of "and / or" throughout the text includes three parallel solutions. Taking "robot coordinate system and / or m" as an example, it includes a robot coordinate system solution, an m solution, or a solution where both the robot coordinate system and m are satisfied simultaneously. Furthermore, the technical solutions of the various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. When the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed by this utility model.

[0033] Implementation Method 1

[0034] Reference Figures 1 to 5 This embodiment, as another optional embodiment of this application, discloses a rocket engine combustion chamber with a combined welded structure, including a first inner wall 1 and a second inner wall 2, both of which are conical in shape; wherein a throat 3 is provided at the small end of the first inner wall 1.

[0035] Furthermore, along the axial direction of the first inner wall 1, the distance between the cross-section of the small end of the first inner wall 1 and the radial cross-section of the minimum inner diameter of the throat 3 is 2-4 cm; the first inner wall 1 and the second inner wall 2 are made of copper alloy materials with good thermal conductivity and strength, such as chromium zirconium copper, etc.

[0036] Furthermore, the rocket engine combustion chamber also includes a first outer wall 4 and a second outer wall 5. The outer structure of the first outer wall 4 is the same as that of the first inner wall 1. The first outer wall 4 includes an arc-shaped converging section 401 and a straight section 402. The small end of the arc-shaped converging section 401 is integrally connected to the straight section 402.

[0037] The outer wall 5 has the same external structure as the inner wall 2;

[0038] The second inner wall 2 is inserted into the first outer wall 4, and the outer surface of the second inner wall 2 is in close contact with the inner wall of the expansion section of the outer wall;

[0039] The first inner wall 1 is inserted into the converging section of the first outer wall 4. The outer surface of the first inner wall 1 is in contact with the inner wall of the converging section of the first outer wall 4. The small end face of the first inner wall 1 and the small end face of the second inner wall 2 are connected to each other along the axial direction of the first outer wall 4. The splice seam of the first inner wall 1 and the second inner wall 2 is connected by friction stir welding.

[0040] Furthermore, the first outer wall 4 and the second outer wall 5 are made of high-strength materials such as GH4169, S-03, and S-06, or stainless steel materials such as 304, 321, and 316L. The first outer wall 4 and the second outer wall 5 can be made of the same material or different materials. The first outer wall 4 and the second outer wall 5 are connected by electron beam welding.

[0041] Furthermore, the rocket engine combustion chamber also includes a bushing 6, which is disposed between the straight section 402 of the first outer wall 4 and the throat 3.

[0042] The bushing 6 is made of stainless steel or the same material as the outer wall;

[0043] The bushing 6 includes at least two bushings 601, preferably two bushings 601. Both bushings 601 are semi-circular in structure, and each bushing 601 is connected end to end to form a closed ring structure. The inner wall of each bushing 601 is in close contact with the outer surface of the throat 3. The outer surface of each bushing 601 is circular in structure and is flush with the outer surface of the small end of the first inner wall 1. At the same time, the outer surface of the bushing 601 is in close contact with the inner wall of the straight section 402 of the first outer wall 4.

[0044] Secondly, dividing the bushing 6 into several bushings 601 can effectively reduce the assembly difficulty of the bushing 6 and improve the assembly efficiency.

[0045] Furthermore, a first compensation protrusion 7 is provided on the first inner wall 1, and a second compensation protrusion 8 is provided on the second inner wall 2. Each first compensation protrusion 7 and each second compensation protrusion 8 correspond one-to-one. After splicing, the corresponding first compensation protrusion 7 and second compensation protrusion 8 are spliced ​​together.

[0046] The height of both the first compensation boss 7 and the second compensation boss 8 is 0.2-0.5mm.

[0047] A splicing ring 9 is provided on the end face of the straight section 402 of the first outer wall 4, and a splicing groove 10 is provided on the end face of the small end of the second outer wall 5. After the first outer wall 4 and the second outer wall 5 are spliced ​​together, the splicing ring 9 is inserted into the splicing groove 10.

[0048] The first outer wall 4 and the second outer wall 5 are connected by electron beam welding;

[0049] The thickness compensation at the bottom of the axial cooling channel can be achieved by setting the first compensation boss 7 and the second compensation boss 8.

[0050] During assembly, the bushing is first fitted onto the throat, and then the first inner wall with the bushing is inserted into the first outer wall. The first inner wall, bushing and first outer wall are then welded together as a whole by diffusion welding.

[0051] The second inner wall is inserted into the second outer wall, and the second outer wall and the second inner wall are welded together as a whole by diffusion welding.

[0052] The two integral components, which have been diffusion welded, are then joined together, with the first inner wall and the second inner wall spliced ​​together, and the first outer wall and the second outer wall spliced ​​together. After the joining is completed, the first inner wall and the second inner wall are welded together by friction stir welding; then the first outer wall and the second outer wall are connected by electron beam welding, thus obtaining a complete rocket engine combustion chamber.

[0053] Compared with the prior art, this application cuts the inner and outer walls in the radial direction, but places the cut area on one side of the throat, thereby completely preserving the structure of the throat area and ensuring the structural strength and stability of the entire combustion chamber.

[0054] At the same time, by setting the bushing, the throat area with the smallest inner diameter is filled, ensuring that the outer diameter of the throat area is exactly the same. That is, the throat is connected to the first outer wall with the smallest outer diameter, thereby realizing the insertion and assembly of the first inner wall and the first outer wall. This avoids the assembly interference problem caused by the complete preservation of the throat structure, reduces the assembly difficulty of the first inner wall and the first outer wall, and reduces the assembly and processing difficulty of the rocket engine combustion chamber.

[0055] Secondly, compared with the prior art, this application reduces the volume of the bushing as much as possible while ensuring the integrity of the throat structure, thereby reducing the mass of the bushing and thus reducing the mass of the entire engine combustion chamber.

[0056] The above are merely preferred embodiments of this application and do not limit the patent scope of this application. Any equivalent structural or procedural transformations made using the content of this application's specification and drawings, or direct or indirect applications in other related technical fields, are similarly included within the patent protection scope of this application.

Claims

1. A rocket engine combustion chamber employing a hybrid weld structure, characterized by, Including the first inner wall; The second inner wall is coaxially connected to the first inner wall; the first inner wall is also provided with a throat, and along the axis of the first inner wall, the splice between the first inner wall and the second inner wall is offset to one side of the throat. The first outer wall is fitted onto the outer surface of the first inner wall; The second outer wall is fitted onto the outer surface of the second inner wall; the second outer wall is coaxially connected to the first outer wall. A bushing is disposed between the first inner wall and the first outer wall, and the inner wall of the bushing is in close contact with the throat.

2. A rocket engine combustion chamber employing a hybrid joint structure according to claim 1, wherein A first compensation boss is provided on the first inner wall, and a second compensation boss is provided on the second inner wall. The first compensation boss and the second compensation boss are spliced ​​together.

3. A rocket engine combustion chamber employing a hybrid joint structure according to claim 2, wherein The height of both the first compensation boss and the second compensation boss is 0.2-0.5mm.

4. The rocket engine combustion chamber with a combined welded structure according to claim 1, characterized in that, Along the axial direction of the first inner wall, the distance between the joint between the first inner wall and the second inner wall and the throat is 2-4 cm.

5. A rocket engine combustion chamber with a combined welded structure according to claim 1, characterized in that, A splicing ring is provided on the first outer wall, and a splicing groove is provided on the second outer wall, wherein the splicing ring is inserted into the splicing groove.

6. A rocket engine combustion chamber with a combined welded structure according to claim 1, characterized in that, The bushing includes at least two bushings, which are connected end to end around the axis of the throat to form a closed annular structure; the inner wall of each bushing is in close contact with the outer surface of the throat.

7. A rocket engine combustion chamber employing a combined welded structure according to claim 6, characterized in that, The first outer wall includes an arc-shaped converging section and a straight section, the small end of the arc-shaped converging section being integrally connected to the straight section; the inner wall of the straight section is tightly fitted to the outer wall of the liner.

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