CN212615073U - Outer wall of combustion chamber of liquid rocket engine - Google Patents
Outer wall of combustion chamber of liquid rocket engine Download PDFInfo
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- CN212615073U CN212615073U CN202022100422.XU CN202022100422U CN212615073U CN 212615073 U CN212615073 U CN 212615073U CN 202022100422 U CN202022100422 U CN 202022100422U CN 212615073 U CN212615073 U CN 212615073U
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Abstract
The utility model discloses a liquid rocket engine combustion chamber outer wall relates to liquid rocket engine technical field, and the sandwich structure design of having solved throat section among the prior art is unfavorable for the technical problem of liquid rocket engine combustion chamber production assembly. The throat-type water-saving device comprises a straight cylinder section, a throat section and an expansion section, wherein the straight cylinder section and the expansion section are respectively of an integral structure, and the minimum inner diameter of the expansion section is larger than that of the straight cylinder section; the throat section is of a split structure, and the whole throat section is in a Laval tube shape; the end parts of the straight cylinder section, the throat section and the expansion section are provided with positioning connecting parts which are in sliding butt joint. The straight cylinder section, the throat section and the expansion section of the utility model are positioned and connected in a sliding fit manner through the positioning and connecting part, so that the assembly precision among all parts is ensured, and the structural integrity and the structural strength of the outer wall of the combustion chamber are effectively ensured; the whole throat section is made into a Laval tube shape, and the design of a sandwich structure is cancelled.
Description
Technical Field
The utility model relates to a liquid rocket engine technical field particularly, indicates a liquid rocket engine combustion chamber outer wall.
Background
The manufacturing scheme of the groove structure combustion chamber of the liquid rocket engine at home and abroad is divided into two modes of electroforming and diffusion welding (including brazing). Among them, the electroforming scheme has a long production cycle, low efficiency, heavy weight and serious pollution to the environment during the production process. The diffusion welding scheme has short production period and high efficiency, and the outer wall of the diffusion welding scheme can adopt high-strength steel or high-temperature alloy steel with lighter weight, so that the diffusion welding scheme is more and more favored by liquid rocket engine engineers at home and abroad. However, the structural scheme of the diffusion welding engine combustion chamber is difficult to design, most structural schemes cannot meet the use requirement of the engine, and the problem of high rejection rate exists.
In the prior art, the throat section is designed into a sandwich structure in a structural design scheme commonly used at home and abroad, and the sandwich structure can meet the requirements of design and use, but also has the defects of complex structure, high assembly difficulty, heavy structure, poor structural sealing reliability, high rejection rate and the like, and is not beneficial to the production and assembly of the combustion chamber of the liquid rocket engine. Therefore, with the rapid development of welding technology and processing and manufacturing technology, a more efficient, simpler and more reliable diffusion welding structure scheme is needed to be provided so as to meet the urgent need of the construction of the aerospace strong country for more advanced and efficient liquid rocket engines.
SUMMERY OF THE UTILITY MODEL
In view of this, the utility model aims at overcoming the not enough of prior art, provide a liquid rocket engine combustion chamber outer wall to the sandwich structure design of throat section is unfavorable for the technical problem of liquid rocket engine combustion chamber production assembly among the solution prior art.
The utility model provides a technical scheme that this technical problem adopted is:
the utility model provides a liquid rocket engine combustion chamber outer wall, includes straight section, throat section and expansion segment, wherein:
the straight cylinder section and the expansion section are respectively of an integral structure, and the minimum inner diameter of the expansion section is larger than that of the straight cylinder section;
the throat section is of a split structure, and the whole throat section is in a Laval tube shape;
positioning connecting parts in sliding butt joint are arranged between the end parts of the straight cylinder section and the throat section, between the end parts of the throat section and the expansion section and between the end parts of the throat section of the split structure, and the straight cylinder section, the throat section and the expansion section are assembled on the inner wall of the combustion chamber in a sliding fit mode.
On the basis of the technical scheme, the outer wall of the combustion chamber of the liquid rocket engine can be improved as follows.
Optionally, the positioning connection portion includes a first spigot and a second spigot that are paired with each other, the first spigot is disposed at one end of the straight tube section, the second spigot that is butted with the straight tube section is disposed at one end of the throat section, the first spigot is disposed at the other end of the throat section, and the second spigot that is butted with the throat section is disposed at one end of the expansion section.
Optionally, the throat section includes a first throat section and a second throat section, and a fracture between the first throat section and the second throat section is a straight line or a spiral curve.
Optionally, the first throat section is provided with a first seam allowance, and the second throat section is provided with a second seam allowance in butt joint with the first throat section.
Optionally, the first seam allowance is an outer seam allowance, and the thickness of the first seam allowance is not less than 2 mm; the second seam allowance is an inner seam allowance, and the thickness of the second seam allowance is not less than 1mm and not more than 2 mm.
Optionally, the positioning connection portion is provided with two reinforcing portions, and the two reinforcing portions are welded to form the positioning connection portion integrally.
Optionally, the two reinforcing portions are the same size, so that the weld between the two reinforcing portions is located at the center of the two reinforcing portions.
Optionally, the width of the two reinforcing parts is not less than 4mm, the sum of the thicknesses of the two reinforcing parts and the positioning connection part is not less than 3mm, and the melting depth of the welding seam.
Optionally, the straight tube section, the throat section and the expanding section are all made of stainless steel or GH4169 alloy steel.
Compared with the prior art, the utility model provides a beneficial effect that liquid rocket engine combustion chamber outer wall has is:
(1) the straight cylinder section, the throat section and the expansion section of the utility model are independent parts, and the throat section is divided into a split structure, so that the structure of each part is simple, the assembly, production and manufacture of the outer wall of the combustion chamber of the liquid rocket engine are convenient, and the production efficiency is improved;
(2) the straight cylinder section, the throat section and the expansion section of the utility model are positioned and connected in a sliding fit manner through the positioning connecting part, so that the assembly precision among all parts is ensured, and the structural integrity and the structural strength of the outer wall of the combustion chamber are effectively ensured;
(3) the whole throat section is made into a Laval tube shape, the sandwich structure design is cancelled, the weight of the outer wall of the combustion chamber of the liquid rocket engine is reduced, and the thrust-weight ratio of the liquid rocket engine is improved;
(4) the utility model discloses a liquid rocket engine combustion chamber outer wall structure and assembly process thereof, simple high efficiency, structure are reliable, have improved the qualification rate and the production efficiency of liquid rocket engine combustion chamber by a wide margin.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a schematic cross-sectional view of the outer wall of a combustion chamber of a liquid rocket engine;
FIG. 2 is a schematic view showing the overall structure of the outer wall of the combustion chamber of the liquid rocket engine;
FIG. 3 is a schematic view of the connection between the straight tube section and the throat section of FIG. 1;
FIG. 4 is a schematic view of the connection of the throat section and the diverging section of FIG. 1;
FIG. 5 is a flow chart of a process for assembling the outer wall of a combustion chamber of a liquid rocket engine.
In the figure:
1-straight cylinder section; 2-throat section; 21 — a first throat section; 22 — a second throat section; 3-an expansion section; 4, the inner wall of the combustion chamber; 5, positioning the connecting part; 51-a first spigot; 52-second seam allowance; 6-a reinforcement; d1-inner diameter of straight cylinder section; d2 — minimum inner diameter of the dilating segment; l-the width of the reinforcement.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention clearer, the technical solutions of the present invention will be described in detail below. It is to be understood that the embodiments described are merely exemplary of the invention and are not intended to be exhaustive. Based on the embodiments of the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.
Example 1:
the utility model provides a liquid rocket engine combustion chamber outer wall, as shown in figure 1 and figure 2, including straight section of thick bamboo 1, throat section 2 and the 3 triplets of expansion section, wherein, throat section 2 includes two parts of first throat section 21 and second throat section 22. The straight cylinder section 1 and the expansion section 3 are respectively of an integral cylinder structure, and the minimum inner diameter D2 of the expansion section 3 is larger than the inner diameter D1 of the straight cylinder section 1, so that the expansion section 3 can be conveniently assembled. The throat section 2 is in a Laval tube shape as a whole so as to meet the assembly requirement with the inner wall 4 of the combustion chamber. All be provided with location connecting portion 5 between the tip of straight section of thick bamboo section 1 and throat section 2, between the tip of throat section 2 and expansion section 3 and between the fracture of first throat section 21 and second throat section 22, straight section of thick bamboo section 1, throat section 2 and expansion section 3 all assemble on combustion chamber inner wall 4 through location connecting portion 5. Wherein, the straight cylinder section 1, the throat section 2 and the expansion section 3 can be made of stainless steel, GH4169 alloy steel or other high-strength special steel.
It can be understood that, according to actual assembly conditions, the throat section 2 may be further divided into a plurality of portions, such as a third throat section, a fourth throat section, etc., so as to facilitate hoisting and transportation of the throat section 2. However, the structural design of the throat section 2 divided into the first throat section 21 and the second throat section 22 can reduce the assembly process flow of the throat section 2 and improve the structural integrity of the throat section 2.
As shown in fig. 3, the positioning connection portion 5 includes a first stop 51 and a second stop 52, and the first stop 51 and the second stop 52 are connected with a gap therebetween. The positioning connection part 5 is arranged at the butt joint end part of the straight cylinder section 1 and the throat section 2, wherein one end of the straight cylinder section 1 is set as a first spigot 51, and one end of the throat section 2 is set as a second spigot 52. The first seam allowance 51 is an outer seam allowance, and the thickness of the first seam allowance 51 is not less than 2 mm. The second seam allowance 52 is an inner seam allowance, and the thickness of the second seam allowance 52 is not less than 1mm and not more than 2 mm. When straight section of thick bamboo section 1 and throat section 2 butt joint, second tang 52 block can avoid taking place relative displacement between straight section of thick bamboo section 1 and the throat section 2 in first tang 51 to guarantee the precision of assembling between straight section of thick bamboo section 1 and the throat section 2.
As shown in fig. 4, the positioning connection portion 5 is further disposed at the end of the throat section 2 that is butted against the expansion section 3, wherein the other end of the throat section 2 is disposed as a first seam allowance 51, and one end of the expansion section 3 is disposed as a second seam allowance 52. When the throat section 2 is butted with the expansion section 3, the second spigot 52 is clamped in the first spigot 51, so that relative displacement between the throat section 2 and the expansion section 3 can be avoided, and the assembly precision between the throat section 2 and the expansion section 3 is ensured.
As shown in fig. 2, the fracture between the first throat section 21 and the second throat section 22 may be a straight line or a spiral curve. When the fracture between the first throat section 21 and the second throat section 22 is a spiral curve, the first throat section 21 and the second throat section 22 can be prevented from being deviated when being assembled. Likewise, the interruption of the first throat section 21 is provided as a first stop 51 and the interruption of the second throat section 22 is provided as a second stop 52. When first throat section 21 docks with second throat section 22, second tang 52 block is in first tang 51, can avoid taking place radial relative displacement between first throat section 21 and the second throat section 22 to guarantee the precision of assembling between first throat section 21 and the second throat section 22.
The utility model discloses design straight section 1, throat section 2 and expansion section 3 for solitary part, divide throat section 2 into the split type structure of first throat section 21 and second throat section 22 again for the simple structure of each part makes things convenient for the assembly and the manufacturing of liquid rocket engine combustion chamber outer wall, improves production efficiency. During assembly, the straight cylinder section 1, the throat section 2 and the expansion section 3 are positioned and connected in a sliding mode from the first stop opening 51 to the second stop opening 52, so that the assembly precision among all parts is ensured, and the structural integrity and the structural strength of the outer wall of the combustion chamber are effectively ensured. The whole throat section 2 is made into a Laval tube shape, compared with the prior art, the design of a sandwich structure is cancelled, the weight of the outer wall of the combustion chamber of the liquid rocket engine is reduced, and the thrust-weight ratio of the liquid rocket engine is improved.
It is understood that the positions of the first and second rabbets 51 and 52 on the straight tube section 1, the throat section 2 and the expanding section 3 can be interchanged. Of course, the structure of the positioning connection portion 5 is not limited to the above structure, and the positioning connection portion 5 may be provided with a tapered structure, or the second seam allowance 52 may be eliminated directly. When straight section of thick bamboo section 1, throat section 2 and expansion section 3 assembled, the bell mouth can make between two parts butt joint with sliding fit's mode equally to make things convenient for counterpoint between straight section of thick bamboo section 1, throat section 2 and the expansion section 3.
As shown in fig. 2 to 4, the outer wall of the positioning connection portion 5 is provided with two reinforcing portions 6, and the positioning connection portion 5 is integrally formed between the two reinforcing portions 6 by welding. The two reinforcing portions 6 are of the same size, so that the weld between the two reinforcing portions 6 is located at the center of the two reinforcing portions 6, thereby making the weld strength between the two parts the same. The width L of the two reinforcing parts 6 is not less than 4mm, the sum of the thickness of the two reinforcing parts 6 and the thickness of the first spigot 51 is not less than 3mm, and the sum of the thickness of the two reinforcing parts 6 and the thickness of the first spigot 51 is not less than the melting depth of the welding seam, so that the welding seam is prevented from extending into the inner wall of the combustion chamber of the liquid rocket engine.
The utility model discloses make straight section of thick bamboo 1, throat section 2 and the 3 assembly backs of expansion section, play the effect of temporary fixation to the part through the welding of two rib 6, put into diffusion welding stove with liquid rocket engine combustion chamber outer wall and combustion chamber inner wall 4 whole at last and carry out diffusion welding, fully guaranteed the assembly structure intensity of liquid rocket engine combustion chamber outer wall. Of course, the reinforcement portion 6 need not be provided for a low thrust engine with a low internal pressure. The welding mode of the combustion chamber of the liquid rocket engine can also adopt brazing.
Example 2:
the utility model discloses still provide the assembly process of a liquid rocket engine combustion chamber outer wall, as shown in figure 5, adopt foretell liquid rocket engine combustion chamber outer wall. Firstly, because the minimum inner diameter D2 of the divergent section 3 is larger than the inner diameter D1 of the straight cylinder section 1, the divergent section 3 can be sleeved into the outer surface of the inner wall 4 of the combustion chamber from one end of the straight cylinder section 1, and the divergent section 3 is attached to the tail end of the inner wall 4 of the combustion chamber. Then, the first throat section 21 and the second throat section 22 are respectively assembled on the outer surface of the inner wall 4 of the combustion chamber, and the first throat section 21 and the second throat section 22 are connected in a positioning manner through the first spigot 51 and the second spigot 52 to form the throat section 2 in the shape of a laval pipe. The entire throat section 2 is then slidably engaged with the diverging section 3 by the first and second detents 51, 52. Finally, the straight cylinder section 1 is sleeved along the outer surface of the inner wall 4 of the combustion chamber, and the straight cylinder section 1 is in sliding butt joint with the whole throat section 2 through the first spigot 51 and the second spigot 52. And finishing the assembly work of the outer wall of the combustion chamber of the whole liquid rocket engine.
As shown in fig. 5, the straight tube section 1 and the end of the throat section 2, the throat section 2 and the end of the divergent section 3, and the first throat section 21 and the second throat section 22 are welded into an integral structure by electron beam welding or laser welding. And then the whole liquid rocket engine combustion chamber is sent into a diffusion welding furnace for diffusion welding or the liquid rocket engine combustion chamber is brazed, thereby finishing the assembly of the outer wall of the whole liquid rocket engine combustion chamber.
The utility model discloses an assembly process is simple, and the assembly precision between each part of liquid rocket engine combustion chamber outer wall is high, can effectively guarantee the structural strength of liquid rocket engine combustion chamber. Of course, according to the design requirements of the outer wall of the combustion chamber of the liquid rocket engine, after the straight barrel section 1, the throat section 2 and the expansion section 3 are diffusion welded, the reinforcing part 6 can be polished.
The above description is only for the specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art can easily think of the changes or substitutions within the technical scope of the present invention, and all should be covered within the protection scope of the present invention.
Claims (9)
1. A liquid rocket engine combustion chamber outer wall, characterized by, including straight section (1), throat section (2) and expanding section (3), wherein:
the straight cylinder section (1) and the expansion section (3) are respectively of an integral structure, and the minimum inner diameter of the expansion section (3) is larger than that of the straight cylinder section (1);
the throat section (2) is of a split structure, and the whole throat section (2) is in a Laval tube shape;
positioning connecting parts (5) in sliding butt joint are arranged between the end parts of the straight cylinder section (1) and the throat section (2), between the end parts of the throat section (2) and the expansion section (3) and between the end parts of the throat section (2) of the split structure, and the straight cylinder section (1), the throat section (2) and the expansion section (3) are assembled on the inner wall (4) of the combustion chamber in a sliding fit mode.
2. The liquid rocket engine combustion chamber outer wall of claim 1, wherein the positioning connection portion (5) comprises a first spigot (51) and a second spigot (52) which are paired with each other, one end of the straight barrel section (1) is provided with the first spigot (51), one end of the throat section (2) is provided with the second spigot (52) which is butted with the straight barrel section (1), the other end of the throat section (2) is provided with the first spigot (51), and one end of the expansion section (3) is provided with the second spigot (52) which is butted with the throat section (2).
3. A liquid rocket engine combustion chamber outer wall according to claim 2, characterized in that said throat section (2) comprises a first throat section (21) and a second throat section (22), the break between said first throat section (21) and second throat section (22) being a straight line or a spiral curve.
4. A liquid rocket engine combustion chamber outer wall according to claim 3, characterized in that the interruption of said first throat section (21) is provided with said first seam allowance (51) and the interruption of said second throat section (22) is provided with said second seam allowance (52) interfacing with said first throat section (21).
5. The liquid rocket engine combustion chamber outer wall according to claim 4, wherein the first spigot (51) is an outer spigot, the thickness of the first spigot (51) being not less than 2 mm; the second seam allowance (52) is an inner seam allowance, and the thickness of the second seam allowance (52) is not less than 1mm and not more than 2 mm.
6. The liquid rocket engine combustion chamber outer wall of claim 1, wherein two reinforcements (6) are respectively arranged on the positioning connection portion (5), and the positioning connection portion (5) is integrally formed between the two reinforcements (6) by welding.
7. A liquid rocket engine combustion chamber outer wall according to claim 6, characterized in that both said reinforcements (6) are of the same size, so that the weld between both said reinforcements (6) is located in the center of both said reinforcements (6).
8. The liquid rocket engine combustion chamber outer wall according to claim 7, wherein the width of two said reinforcements (6) is not less than 4mm, the sum of the thicknesses of two said reinforcements (6) and said locating connection (5) is not less than 3mm and the melting depth of the weld.
9. The liquid rocket engine combustion chamber outer wall according to any one of claims 1 to 8, wherein the straight section (1), the throat section (2) and the divergent section (3) are all made of stainless steel or GH4169 alloy steel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022100422.XU CN212615073U (en) | 2020-09-23 | 2020-09-23 | Outer wall of combustion chamber of liquid rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022100422.XU CN212615073U (en) | 2020-09-23 | 2020-09-23 | Outer wall of combustion chamber of liquid rocket engine |
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| Publication Number | Publication Date |
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| CN212615073U true CN212615073U (en) | 2021-02-26 |
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| CN202022100422.XU Active CN212615073U (en) | 2020-09-23 | 2020-09-23 | Outer wall of combustion chamber of liquid rocket engine |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112065606A (en) * | 2020-09-23 | 2020-12-11 | 航天科工火箭技术有限公司 | Outer wall of combustion chamber of liquid rocket engine and assembly process thereof |
| CN115740965A (en) * | 2022-11-01 | 2023-03-07 | 北京智创联合科技股份有限公司 | Method for manufacturing rocket engine combustion chamber with integral structure |
-
2020
- 2020-09-23 CN CN202022100422.XU patent/CN212615073U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112065606A (en) * | 2020-09-23 | 2020-12-11 | 航天科工火箭技术有限公司 | Outer wall of combustion chamber of liquid rocket engine and assembly process thereof |
| CN115740965A (en) * | 2022-11-01 | 2023-03-07 | 北京智创联合科技股份有限公司 | Method for manufacturing rocket engine combustion chamber with integral structure |
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