A rocket engine combustion chamber with a reinforced liner

Abstract

The application discloses a rocket engine combustion chamber with a reinforced bushing, comprising an inner wall and an outer wall, the outer wall is sleeved on the inner wall, and the inner wall is coaxial with the outer wall; a bushing is arranged between the inner wall and the outer wall, the inner wall of the bushing is tightly attached to the throat of the inner wall; the outer diameter of the bushing is not less than the outer diameter of the converging section of the inner wall; since the outer diameter of the bushing is not less than the outer diameter of the converging section of the inner wall, that is, the outer surface of the bushing is at least flush with the maximum outer diameter of the converging section of the inner wall, thereby converting the structure of the inner wall with a large head and a small middle part into a structure with a large one end and a cylindrical other end; therefore, the inner wall and the outer wall no longer need to be divided and connected through welding, and the inner wall and the outer wall can be assembled in an integral structure, so that the structural strength of the combustion chamber is improved as much as possible; meanwhile, the integral structure of the inner wall and the outer wall can also avoid most of the welds, thereby improving the assembly efficiency and effectively reducing the machining difficulty of the combustion chamber.

Description

Technical Field

[0001] This application relates to the field of aerospace equipment technology, specifically to a rocket engine combustion chamber with a reinforcing bushing. 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 central throat being smaller than that of the two 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, the above processing methods require a large number of difficult welding operations, which increases the processing difficulty of the combustion chamber. Utility Model Content

[0004] The main objective of this application is to provide a rocket engine combustion chamber with a reinforced bushing, which aims to solve the problem of high processing difficulty in the prior art.

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

[0006] A rocket engine combustion chamber with a reinforced bushing, including an inner wall;

[0007] An outer wall, which is fitted onto the inner wall, and the outer wall and the inner wall are coaxial;

[0008] A bushing is disposed between the inner wall and the outer wall, the inner surface of the bushing being in close contact with the outer surface of the throat of the inner wall; the outer diameter of the bushing is not less than the outer diameter of the converging section of the inner wall.

[0009] Optionally, the bushing includes at least two liner bodies, which are joined end to end around the axis of the bushing.

[0010] Optionally, each of the linings has a slot on one side and a strip on the other side, and any two adjacent linings are connected by the strip and the slot.

[0011] Optionally, each bushing includes a base layer, a surface layer, and a truss support layer, wherein the truss support layer is located between the base layer and the surface layer, and the truss support layer is integrally connected to both the base layer and the surface layer.

[0012] Optionally, the truss support layer includes a plurality of arrayed truss units, with any two adjacent truss units integrally connected; each truss unit is integrally connected to the base layer and the surface layer respectively.

[0013] Optionally, the truss unit includes connecting spheres and several connecting rods, each of the connecting rods being arranged radially, with one end of each connecting rod connected to a connecting sphere and the other end used to connect to an adjacent connecting sphere.

[0014] Optionally, each bushing includes a base layer, a surface layer, and a support layer, wherein the support layer is provided with a plurality of weight-reducing holes in a regular hexagonal structure.

[0015] Optionally, each bushing includes a base layer, a surface layer, and a foamed weight-reducing layer, wherein the foamed weight-reducing layer is located between the base layer and the surface layer, and the foamed weight-reducing layer is connected to the base layer and the surface layer respectively.

[0016] Optionally, the outer structure of the base layer matches the throat of the inner wall, and the base layer is a solid structure.

[0017] Optionally, the thickness of the base layer is 3-5mm.

[0018] Compared with the prior art, this application has the following beneficial effects:

[0019] This application includes an inner wall and an outer wall, the outer wall being sleeved on the inner wall, and the inner wall and the outer wall being coaxial; a bushing is provided between the inner wall and the outer wall, the inner wall of the bushing being tightly fitted to the throat of the inner wall; the outer diameter of the bushing is not less than the outer diameter of the converging section of the inner wall;

[0020] Compared with the prior art, this application adds a bushing to the rear part of the inner wall. At the same time, the outer diameter of the bushing is not less than the outer diameter of the converging section of the inner wall. That is, the outer surface of the bushing is at least flush with the maximum outer diameter of the converging section of the inner wall. This transforms the structure of the inner wall, which is large at both ends and small in the middle, into a structure that is large at one end and cylindrical at the other end. At this time, the equipment can be assembled by plugging in. The inner wall and the outer wall no longer need to be separated and then connected by welding. It can be assembled as a whole structure, which maximizes the structural strength of the combustion chamber.

[0021] Secondly, since the inner and outer walls no longer need to be separated, most of the welds on the inner and outer walls can be removed, which not only helps to improve production efficiency, but also reduces the assembly and processing difficulty of the combustion chamber.

[0022] Finally, by avoiding extensive welding, it can fundamentally avoid the reduction in dimensional accuracy caused by welding, thus ensuring the dimensional accuracy of the entire combustion chamber; at the same time, the bushing fitted on the throat can also strengthen the throat, eliminating the need for the throat reinforcing ring structure in the prior art, while also ensuring the reliability and stability of the combustion chamber. Attached Figure Description

[0023] Figure 1 A schematic diagram of a rocket engine combustion chamber with a reinforcing bushing provided for an embodiment of this application;

[0024] Figure 2 An exploded view of a rocket engine combustion chamber with a reinforcing bushing, provided for an embodiment of this application;

[0025] Figure 3 An axial sectional view of a rocket engine combustion chamber with a reinforcing bushing, provided for an embodiment of this application;

[0026] Figure 4 A radial cross-sectional view of a rocket engine combustion chamber with a reinforcing bushing, provided for an embodiment of this application;

[0027] Figure 5 This is a sectional view of the bushing;

[0028] Figure 6 This is a structural schematic diagram of a truss unit;

[0029] Figure 7 An axial cross-sectional view of another feasible embodiment of a rocket engine combustion chamber with a reinforcing bushing;

[0030] Figure 8 An axial cross-sectional view of another feasible method for a rocket engine combustion chamber with a reinforcing bushing;

[0031] Reference numerals: 1-Inner wall, 2-Outer wall, 3-Bushing, 301-Bridging, 302-Slot, 303-Strip, 3011-Base layer, 3012-Surface layer, 3013-Truss support layer, 3014-Connecting ball, 3015-Connecting rod, 3016-Support layer, 3017-Weight reduction hole, 3018-Foamed weight reduction layer.

[0032] 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

[0033] 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.

[0034] 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.

[0035] 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.

[0036] 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.

[0037] Implementation Method 1

[0038] Reference Figures 1 to 6 This embodiment, as another optional embodiment of this application, discloses a rocket engine combustion chamber with a reinforcing bushing, including an inner wall 1 and an outer wall 2, wherein the outer wall 2 is fitted onto the inner wall 1, and the inner wall 1 and the outer wall 2 are coaxially arranged.

[0039] Reference Figure 2 Along the axis of the inner wall 2, the inner wall includes a converging section, a throat, and an expanding section connected in sequence. The throat has the smallest inner diameter and its axial cross-section is generally hyperbolic. The converging section has the next largest inner diameter and its axial cross-section is generally conical with an arc-shaped structure. The small end of the converging section is smoothly connected to the throat. The expanding section has a generally conical structure and its axial cross-section is obliquely V-shaped. The small end of the expanding section is smoothly connected to the throat.

[0040] The combustion chamber also includes a bushing 3, which is disposed between the inner wall 1 and the outer wall 2. The bushing 3 includes a plurality of lining bodies 301. Preferably, there are two lining bodies 301, that is, the two lining bodies 301 are arranged in a semi-circular structure. Along the axial direction of the lining body 301, a groove 302 is provided on one side of the lining body 301, and a retaining strip 303 is provided on the other side. The groove 302 and the retaining strip 303 are interference fit.

[0041] The cross-section of the card slot 302 is rectangular, and the free end of the card strip 303 is also inclined with a guide surface, and the two guide surfaces are arranged in a figure-eight shape.

[0042] Around the axis of the bushing 3, each of the bushings 301 is spliced ​​together end to end. That is, at the joint of two bushings 301, the retaining strip 303 is inserted into the retaining groove 302, thereby achieving the connection of the two bushings 301 through interference fit.

[0043] Furthermore, each bushing 3 includes a base layer 3011, a surface layer 3012, and a truss support layer 3013. Along the radial direction of the bushing 3, the base layer 3011 is located on the inner side, the surface layer 3012 is located on the outer side, and the truss support layer 3013 is located between the inner layer and the surface layer 3012.

[0044] The truss support layer 3013 includes a plurality of truss units, which are arranged in an array and fully distributed between the base layer 3011 and the surface layer 3012. Each truss unit includes a connecting ball 3014 and a plurality of connecting rods 3015. The connecting ball 3014 is the intersection point of each connecting rod 3015. The connecting ball 3014 is integrally connected to the surface layer 3012 or the base layer 3011. Each connecting rod 3015 is arranged radially. One end of each connecting rod 3015 is connected to the connecting ball 3014, and the other end is used to connect to the adjacent connecting ball 3014.

[0045] It should be noted that the liner 301 of the above structure is manufactured by 3D printing technology. Each connecting ball 3014 in the truss support layer 3013 is divided into two groups. The two groups of connecting balls 3014 are placed on the base layer 3011 and the surface layer 3012 respectively, and are facing each other. Each connecting rod 3015 connects any two adjacent connecting balls 3014.

[0046] The truss support layer 3013 can effectively reduce the weight of the bushing 3 without reducing its structural strength. Engineering practice has proven that the porosity of the truss support layer 3013 manufactured by 3D printing technology reaches more than 70%, which means that 70% weight reduction is achieved.

[0047] Reference Figure 7 Furthermore, each of the bushings 3 includes a base layer 3011, a surface layer 3012, and a foamed weight-reducing layer 3018. The foamed weight-reducing layer 3018 is located between the base layer 3011 and the surface layer 3012, and is connected to both the base layer 3011 and the surface layer 3012. The foamed weight-reducing layer 3018 is made of foaming material, which is formed by mixing metal powder with a foaming agent and then forming a porous material through processes such as sintering. It has good rigidity and low density characteristics. Engineering practice has proven that the porosity of metal foaming material can also reach more than 70%, that is, a weight reduction of more than 70% compared with solid materials. Preferably, the metal foaming material is stainless steel foaming material.

[0048] Reference Figure 8 Furthermore, each bushing 3 includes a base layer 3011, a surface layer 3012, and a support layer 3016. The support layer 3016 is provided with a plurality of weight-reducing holes 3017 in a regular hexagonal structure.

[0049] The weight of the support layer 3016 is reduced by the weight reduction hole 3017, and the structural strength of the support layer 3016 after weight reduction is improved by the weight reduction hole 3017 with a regular hexagonal structure.

[0050] Furthermore, both the base layer 3011 and the surface layer 3012 are solid structures. The outer shape of the base layer 3011 matches the throat of the inner wall 1, that is, the inner surface of the base layer is completely attached to the outer surface of the throat of the inner wall 1. The base layer 3011 is a solid structure and its thickness is 3-5mm.

[0051] Furthermore, the outer diameter of the bushing 3 is not less than the outer diameter of the converging section of the inner wall, i.e., referring to... Figure 3 , 7 And 8, the maximum outer diameter of the bushing is the same as the maximum outer diameter of the converging section of the inner wall;

[0052] Compared with the prior art, this application adds a bushing to the rear part of the inner wall. At the same time, the outer diameter of the bushing is not less than the outer diameter of the converging section of the inner wall. That is, the outer surface of the bushing is at least flush with the maximum outer diameter of the converging section of the inner wall. This transforms the structure of the inner wall, which is large at both ends and small in the middle, into a structure that is large at one end and cylindrical at the other end. At this time, the equipment can be assembled by plugging in. The inner wall and the outer wall no longer need to be separated and then connected by welding. It can be assembled as a whole structure, which maximizes the structural strength of the combustion chamber.

[0053] Secondly, since the inner and outer walls no longer need to be separated, most of the welds on the inner and outer walls can be removed, which not only helps to improve production efficiency, but also reduces the assembly and processing difficulty of the combustion chamber.

[0054] Finally, by avoiding a large amount of welding, it can fundamentally avoid the reduction in dimensional accuracy caused by welding, thus ensuring the dimensional accuracy of the entire combustion chamber.

[0055] Meanwhile, the bushing fitted into the throat can also strengthen the throat, eliminating the need for the throat reinforcement ring structure in the existing technology, while ensuring the reliability and stability of the combustion chamber.

[0056] The above are merely preferred embodiments of this application and do not limit the scope of this patent 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 scope of patent protection of this application.

Claims

1. A rocket engine combustion chamber with a reinforcing bushing, characterized in that, Including the inner wall; An outer wall, which is fitted onto the inner wall, and the outer wall and the inner wall are coaxial; A bushing is disposed between the inner wall and the outer wall, the inner surface of the bushing being in close contact with the outer surface of the throat of the inner wall; the outer diameter of the bushing is not less than the outer diameter of the converging section of the inner wall.

2. The rocket engine combustion chamber with a reinforcing bushing according to claim 1, characterized in that, The bushing includes at least two bushings, which are joined end to end around the axis of the bushing.

3. A rocket engine combustion chamber with a reinforcing bushing according to claim 2, characterized in that, Each of the linings has a slot on one side and a strip on the other side. Any two adjacent linings are connected by the strip and the slot.

4. A rocket engine combustion chamber with a reinforcing bushing according to claim 2, characterized in that, Each bushing includes a base layer, a surface layer, and a truss support layer, wherein the truss support layer is located between the base layer and the surface layer, and the truss support layer is integrally connected to both the base layer and the surface layer.

5. A rocket engine combustion chamber with a reinforcing bushing according to claim 4, characterized in that, The truss support layer includes a plurality of arrayed truss units, with any two adjacent truss units integrally connected; each truss unit is integrally connected to the base layer and the surface layer respectively.

6. A rocket engine combustion chamber with a reinforcing bushing according to claim 5, characterized in that, The truss unit includes connecting spheres and several connecting rods, each of which is arranged radially. One end of each connecting rod is connected to a connecting sphere, and the other end is used to connect to an adjacent connecting sphere.

7. A rocket engine combustion chamber with a reinforcing bushing according to claim 2, characterized in that, Each bushing includes a base layer, a surface layer, and a support layer, wherein the support layer is provided with a plurality of weight-reducing holes in a regular hexagonal structure.

8. A rocket engine combustion chamber with a reinforcing bushing according to claim 2, characterized in that, Each bushing includes a base layer, a surface layer, and a foamed weight-reducing layer, wherein the foamed weight-reducing layer is located between the base layer and the surface layer, and is connected to both the base layer and the surface layer.

9. A rocket engine combustion chamber with a reinforcing bushing according to any one of claims 4-8, characterized in that, The outer structure of the base layer matches the throat of the inner wall, and the base layer is a solid structure.

10. A rocket engine combustion chamber with a reinforcing bushing according to claim 9, characterized in that, The thickness of the base layer is 3-5mm.

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