Liquid rocket engine thrust chamber body structure and rocket engine

Abstract

The utility model provides a liquid rocket engine thrust chamber body structure and a rocket engine. The utility model relates to a high-strength steel pipe which comprises an inner wall, main ribs, insertion ribs and an outer wall, the inner wall and the outer wall are of a structure with the two ends communicated, the outer wall is arranged on the outer side of the inner wall in a sleeving mode, and the main ribs and the insertion ribs are alternately and evenly distributed between the inner wall and the outer wall in the circumferential direction. The two sides of the main ribs and the two sides of the inserting ribs are tightly attached to the outer side surface of the inner wall and the inner side surface of the outer wall respectively so that channels can be formed between the adjacent main ribs and the adjacent inserting ribs. And a gap is formed between one end, close to the large end of the inner wall, of the insertion rib and the large end of the inner wall, so that the channels positioned on the two sides of the insertion rib are communicated with each other. The outer wall is provided with an opening channel, one end of the opening channel is used for being communicated with a cold medium channel, and the other end of the opening channel is communicated with the channels in the two sides of the main rib. According to the thrust chamber body structure, on the premise that thermal protection of the body is achieved, pipelines can be simplified, the weight of an engine is reduced, and meanwhile installation or welding of external components of the thrust chamber is facilitated.

Description

Technical Field

[0001] This utility model relates to the field of liquid rocket technology, and in particular to a thrust chamber structure of a liquid rocket engine and a rocket engine. Background Technology

[0002] In recent years, the aerospace industry has developed rapidly, especially spacecraft engine technology, which has achieved rapid iteration and upgrading. As a major component of the engine, the thrust chamber is a key component for completing the energy conversion of propellant and generating thrust.

[0003] Current liquid rocket engines employ an external split-flow design to distribute the cooling medium, primarily using throttling devices or regulating valves to control the split ratio. While this design typically meets cooling requirements, it increases the number of external pipes and manifolds within the thrust chamber, leading to a more complex and heavier engine structure. Furthermore, the external split-flow design can cause interference when welding structural components to the outer wall of the thrust chamber, hindering overall assembly layout. Additionally, the increased complexity of the flow path system affects the engine's start-up process and can easily cause ablation of the inner surface of the thrust chamber, thus impacting the rocket engine's usability.

[0004] There is an urgent need to provide a thrust chamber body structure for a liquid rocket engine that, while meeting the requirements for body thermal protection, can simplify piping, reduce structural weight, and facilitate the installation or welding of external thrust chamber components. Summary of the Invention

[0005] The purpose of this invention is to overcome the shortcomings of the prior art and provide a thrust chamber body structure for a liquid rocket engine. While meeting the requirements for body thermal protection, it can simplify the piping, reduce the engine weight, and facilitate the installation or welding of external components of the thrust chamber, thereby improving the stability of the rocket engine.

[0006] This utility model provides a thrust chamber structure for a liquid rocket engine, comprising an inner wall, main ribs, insert ribs, and an outer wall, wherein...

[0007] Both the inner wall and the outer wall are structures that are connected at both ends, and the outer wall is fitted on the outside of the inner wall. The main ribs and the insert ribs alternate with each other and are evenly distributed circumferentially between the inner wall and the outer wall. The two sides of the main ribs and the insert ribs are respectively in close contact with the outer surface of the inner wall and the inner surface of the outer wall so that a channel is formed between adjacent main ribs and insert ribs.

[0008] A gap is provided between the end of the insert rib near the large end of the inner wall and the large end of the inner wall so that the channels on both sides of the insert rib can communicate with each other. The outer wall is provided with an opening channel, one end of which is used to communicate with the cold medium channel, and the other end is used to communicate with the channels on both sides of the main rib.

[0009] Furthermore, the inner wall, the main rib, and the insert rib are integrally molded.

[0010] Furthermore, the main rib and the insert rib are fixed to the outer wall by welding.

[0011] Furthermore, the main rib includes a plurality of alternating first main ribs and second main ribs, and the opening channel is correspondingly disposed on the upper side of the first main rib.

[0012] Furthermore, the opening channel is located between the insert ribs adjacent to both sides of the first main rib.

[0013] Furthermore, the portion of the main rib corresponding to the opening channel is provided with a lower groove.

[0014] Furthermore, the lower groove is recessed towards the side closer to the inner wall.

[0015] Furthermore, the opening channel has a rectangular shape.

[0016] Furthermore, the inner wall and the outer wall are roughly frustum-shaped.

[0017] This utility model also provides a rocket engine, which includes any of the above-mentioned liquid rocket engine thrust chamber body structures.

[0018] Compared with the prior art, the present invention has at least one of the following beneficial effects:

[0019] This utility model provides a liquid rocket engine thrust chamber structure. By setting a flow diversion system inside the thrust chamber, the coolant enters the two sides of the main rib through the open channel and is then diverted. One part flows into the engine throat through the channel on the side of the main rib towards the small end of the thrust chamber, while the other part flows into the engine throat through the channel on the same side of the main rib towards the large end of the thrust chamber. After passing through the gap between the insert rib and the large end, it flows back along the channel adjacent to the side of the main rib, and then flows from the large end of the thrust chamber towards the small end of the thrust chamber into the engine throat.

[0020] The engine thrust chamber body structure of this application makes full use of the available pressure drop through parallel flow paths, effectively reducing the flow resistance of the cooling flow path and improving engine performance; it simplifies the complexity of the cooling flow path, reduces the weight of the engine, eliminates the need for external flow splitting devices, facilitates the installation or welding of external components of the thrust chamber, and improves the stability of the engine; it ensures that the flow splitting ratio remains basically constant under a wide range of engine operating conditions, and improves the reliability of thermal protection under various operating conditions.

[0021] It should be understood that the above general description and the following specific embodiments are merely exemplary and illustrative, and do not limit the scope of the present invention. Attached Figure Description

[0022] The accompanying drawings are part of the specification of this utility model and illustrate exemplary embodiments of the utility model. The drawings, together with the description in the specification, are used to illustrate the principles of this utility model.

[0023] Figure 1 This is a schematic diagram of the rocket engine thrust chamber in an embodiment of the present invention;

[0024] Figure 2 This is a simplified diagram illustrating the principle of cold medium diversion within the thrust chamber body in this embodiment of the present invention.

[0025] Figure 3 This is a cross-sectional view of the rocket engine thrust chamber body in an embodiment of this utility model;

[0026] Figure 4 This is a schematic diagram of the structure of the first main rib and the lower groove in an embodiment of this utility model.

[0027] Explanation of reference numerals in the attached figures:

[0028] 1. Inner wall 2. Main ribs

[0029] 3 insert ribs 4 outer wall

[0030] 5 channels, 6 openings

[0031] 7 First main rib 8 Second main rib

[0032] 9. Lower groove; 10. Engine throat

[0033] 51 First Channel 52 Second Channel Detailed Implementation

[0034] Various exemplary embodiments of the present invention are now described in detail. This detailed description should not be considered as a limitation of the present invention, but should be understood as a more detailed description of certain aspects, features and implementations of the present invention.

[0035] Various improvements and variations can be made to the specific embodiments described in this utility model without departing from the scope or spirit of this utility model, which will be obvious to those skilled in the art. Other embodiments derived from this utility model will be obvious to those skilled in the art. This application specification and embodiments are merely exemplary.

[0036] like Figure 1 , Figure 2 and Figure 3As shown, this utility model provides a thrust chamber structure for a liquid rocket engine, comprising an inner wall 1, main ribs 2, insert ribs 3, and an outer wall 4. Both the inner wall 1 and the outer wall 4 are interconnected at both ends, with the outer wall 4 fitted over the outer side of the inner wall 1. The main ribs 2 and insert ribs 3 alternate and are evenly distributed circumferentially between the inner wall 1 and the outer wall 4. The sides of the main ribs 2 and insert ribs 3 are respectively in close contact with the outer surface of the inner wall 1 and the inner surface of the outer wall 4, forming channels 5 between adjacent main ribs 2 and insert ribs 3.

[0037] A gap is provided between the end of the insert rib 3 near the large end of the inner wall 1 and the large end of the inner wall 1 so that the channels 5 located on both sides of the insert rib 3 can communicate with each other. The outer wall 4 is provided with an opening channel 6, one end of which is used to communicate with the cold medium channel, and the other end is used to communicate with the channels 5 on both sides of the main rib 2.

[0038] Specifically, the thrust chamber structure of a liquid rocket engine provided in this embodiment of the invention employs a flow diversion system inside the thrust chamber. During cooling, the cooling medium enters both sides of the main rib through the open channel 6 and is then diverted. A portion flows through the channel on the side of the main rib 2 towards the smaller end of the thrust chamber and into the engine throat 10. The other portion flows through the channel on the same side of the main rib 2 towards the larger end of the thrust chamber and then flows along the channel adjacent to the main rib side from the larger end of the thrust chamber to the smaller end, flowing into the engine throat 10.

[0039] The engine thrust chamber structure of this application utilizes parallel flow paths to fully leverage available pressure drop, effectively reducing flow resistance in the cooling path, improving engine performance, simplifying the complexity of the cooling path, and reducing engine weight. The internal flow-dividing structure eliminates the need for an external flow-dividing device, thus reserving more space for the installation or welding of external thrust chamber components, improving engine stability, and ensuring a relatively constant flow-dividing ratio under a wide range of engine operating conditions, thereby enhancing the reliability of thermal protection under various operating conditions.

[0040] It should be noted that, in order to facilitate the processing of the inner wall 1, main rib 2, and insert rib 3, and to ensure that the main rib 2 and insert rib 3 are more firmly fixed to the inner wall 1, for example, the inner wall 1, main rib 2, and insert rib 3 are designed as a single piece. This single-piece design not only facilitates the processing of the main ribs and insert ribs and improves the reliability of the structure, but also ensures that the channels are evenly distributed, which is beneficial for the uniform flow of the cooling medium and improves the cooling effect.

[0041] In this embodiment, to ensure that the main rib 2, the insert rib 3, and the outer wall 4 are firmly fixed, for example, the main rib 2 and the insert rib 3 are fixed to the outer wall 4 by welding. The welding design can ensure a tight circumferential seal of the channel, preventing cross-flow of the cold medium in the channel with other channels.

[0042] like Figure 1 and Figure 2 As shown, in order to facilitate the connection between the opening channel 6 and the channel 5, for example, the main rib 2 includes a plurality of alternating first main ribs 7 and second main ribs 8, and the opening channel 6 is correspondingly arranged on the upper side of the first main rib 7.

[0043] In this embodiment, in order to accurately divert the cold medium, for example, the opening channel 6 is provided on the side of the first main rib 7 facing the outer wall 4, and is located between the two insert ribs 3 adjacent to the two sides of the first main rib 7. The opening channel 6 is also connected to the channels 5 on both sides of the first main rib 7.

[0044] For example, such as Figure 2 As shown, the first main rib 7 and its adjacent insert rib 3 form a first channel 51, and the insert rib 3 and its adjacent second main rib 8 form a second channel 52. The first channel 51 and the second channel 52 are connected. The cold medium is divided into two paths through the opening channel 6 and enters the first channels 51 on both sides of the first main rib 7 respectively. The cold medium entering each first channel 51 is further divided as follows: Figure 2 The two marked channels S1 and S2 flow into the throat of the thrust chamber to cool the body of the thrust chamber.

[0045] like Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown, in order to allow the cooling medium to quickly enter the channels on both sides of the main rib 2, for example, the part of the main rib 2 corresponding to the opening channel 6 is provided with a lower groove 9.

[0046] In this embodiment, the lower groove 9 is recessed towards the side closer to the inner wall 1.

[0047] In the same embodiment, in order to ensure the stability of the thrust chamber body structure and facilitate the connection between the opening channel 6 and the channel of the thrust chamber body, for example, the opening channel 6 opened on the outer wall 4 is rectangular in shape.

[0048] In addition, to ensure that the rocket engine generates greater thrust after starting, for example, the inner wall 1 and the outer wall 4 are roughly truncated cone-shaped.

[0049] This utility model also provides a rocket engine, which includes any of the above-mentioned liquid rocket engine thrust chamber body structures.

[0050] The above embodiments can be combined with each other and have corresponding technical effects.

[0051] The above description is merely an illustrative embodiment of this utility model. Any equivalent changes and modifications made by those skilled in the art without departing from the concept and principles of this utility model shall fall within the scope of protection of this utility model.

Claims

1. A thrust chamber structure for a liquid rocket engine, characterized in that, It includes an inner wall, main ribs, insert ribs, and outer wall, among which, Both the inner wall and the outer wall are structures that are connected at both ends, and the outer wall is fitted on the outside of the inner wall. The main ribs and the insert ribs alternate with each other and are evenly distributed circumferentially between the inner wall and the outer wall. The two sides of the main ribs and the insert ribs are respectively in close contact with the outer surface of the inner wall and the inner surface of the outer wall so that a channel is formed between adjacent main ribs and insert ribs. A gap is provided between the end of the insert rib near the large end of the inner wall and the large end of the inner wall so that the channels on both sides of the insert rib can communicate with each other. The outer wall is provided with an opening channel, one end of which is used to communicate with the cold medium channel, and the other end is used to communicate with the adjacent channels on both sides of the main rib.

2. The liquid rocket engine thrust chamber body structure according to claim 1, characterized in that, The inner wall, the main rib, and the insert rib are integrally molded.

3. The liquid rocket engine thrust chamber body structure according to claim 2, characterized in that, The main rib and the insert rib are fixed to the outer wall by welding.

4. The liquid rocket engine thrust chamber body structure according to claim 1, characterized in that, The main rib includes a plurality of alternating first and second main ribs, and the opening channel is disposed on the outer wall corresponding to the first main rib.

5. The liquid rocket engine thrust chamber body structure according to claim 4, characterized in that, The opening channel is located between the insert ribs adjacent to both sides of the first main rib.

6. The liquid rocket engine thrust chamber body structure according to claim 1, characterized in that, The portion of the main rib corresponding to the opening channel is provided with a lower groove.

7. The liquid rocket engine thrust chamber body structure according to claim 6, characterized in that, The lower groove is recessed towards the side closer to the inner wall.

8. The thrust chamber structure of the liquid rocket engine according to claim 1, characterized in that, The opening channel is rectangular in shape.

9. The liquid rocket engine thrust chamber body structure according to claim 1, characterized in that, The inner wall and the outer wall are roughly truncated cone structures.

10. A rocket engine, characterized in that, The liquid rocket engine thrust chamber body structure includes any one of claims 1-9.

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