CN209886483U - Thrust chamber forming die for rocket engine - Google Patents
Thrust chamber forming die for rocket engine Download PDFInfo
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- CN209886483U CN209886483U CN201822030782.XU CN201822030782U CN209886483U CN 209886483 U CN209886483 U CN 209886483U CN 201822030782 U CN201822030782 U CN 201822030782U CN 209886483 U CN209886483 U CN 209886483U
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Abstract
The utility model discloses a thrust chamber forming die for rocket engine, including the tip mould, the prelude shape of tip mould is the cylindricality, the afterbody shape of tip mould is the toper, just the tail end external diameter of tip mould is less than its head end external diameter, the head end of big end mould is connected to the tail end detachably of tip mould, the shape of big end mould is the toper, the head end external diameter of big end mould is less than its tail end external diameter, and the head end external diameter of big end mould with the tail end external diameter of tip mould corresponds. The number of the spinning dies is reduced to one, so that the extension of internal defects caused by spinning of multiple sets of dies is avoided, the risk of generating cracks during spinning can be effectively reduced, the yield is improved, the production cost is effectively reduced, and the development investment of new products is reduced.
Description
Technical Field
The utility model relates to a forming die technical field particularly, relates to a thrust chamber forming die for rocket engine.
Background
In a liquid rocket engine, a thrust chamber is used as a key component for generating thrust, and the temperature of gas in a combustion chamber can reach 3500K. In order to ensure reliable operation of the thrust chamber, a high-strength and high-conductivity copper alloy is generally adopted as an inner wall material of the thrust chamber. In general, the inner wall of the thrust chamber is a laval-shaped rotary body having a thin wall. In order to improve the utilization rate of a material for a thrust chamber using a copper alloy as an inner wall material, a conventional thrust chamber forming process is to perform spinning forming by using a copper cake.
In the specific process of preparing the thrust chamber by the spinning forming method in the prior art, because the raw material for spinning is a cake material, the thickness of the cake material is far greater than the wall thickness of the thrust chamber, and 4 sets of dies are required to be used for final forming by a strong spinning process. In the spinning process, firstly, the front two sets of dies are used for shearing spinning, and the thickness of the material after spinning can be greatly reduced. Because the material undergoes large plastic deformation in the trimming spinning, the elongation rate limit of the material is approached, and meanwhile, the yield strengthening effect occurs, the material needs to be subjected to primary annealing or solution treatment. And spinning the small end and the throat area of the inner wall to a straight cylinder by using a third set of spinning die. Since the deformation amount is large in the process, the material needs to be annealed or subjected to solution treatment once again after spinning. And finally, spinning and forming the throat part and the expansion section by using a 4 th set of spinning die.
The above molding process has the following disadvantages:
1) because the shape of the raw material is greatly changed in the spinning process, only a strong spinning process can be adopted. The strong spinning process has high requirements on indexes such as internal quality of raw materials, grain size of the materials and the like, and causes great difficulty in production of the raw materials, low yield and high cost.
2) 4 sets of spinning dies are needed in the spinning process, and the production cost is high.
3) The product and the die need to be assembled and disassembled for 4 times, and simultaneously, 2 times of annealing or solution heat treatment needs to be carried out in the middle, so that the production cost is high, and the production period is long. In addition, because the intermediate links of the forming process are more, the automatic production difficulty is high.
4) The spinning adopts a strong spinning process, which has high requirements on a machine tool and causes high molding cost.
5) When the fourth set of die is adopted for spinning, the material is subjected to the first three times of spinning operation, and internal defects which do not exceed the standard are enlarged, so that the risk of generating cracks is further increased, and the yield is reduced.
6) The area determined by the spinning deformation process to be about 10% ~ 20% of the center of the raw material is unusable, resulting in a decrease in material utilization and an increase in raw material cost.
An effective solution to the problems in the related art has not been proposed yet.
SUMMERY OF THE UTILITY MODEL
To the above-mentioned technical problem among the correlation technique, the utility model provides a thrust chamber forming die for rocket engine can be with thrust chamber spin forming for the rocket engine through this mould.
In order to achieve the technical purpose, the technical scheme of the utility model is realized as follows:
the utility model provides a thrust chamber forming die for rocket engine, includes the tip mould, the head shape of tip mould is the cylindricality, the afterbody shape of tip mould is the toper, just the tail end external diameter of tip mould is less than its head end external diameter, the head end of big end mould is connected to the tail end detachably of tip mould, the shape of big end mould is the toper, the head end external diameter of big end mould is less than its tail end external diameter, and the head end external diameter of big end mould with the tail end external diameter of tip mould corresponds.
Furthermore, the small end die and the large end die are both provided with holes which are communicated end to end and can be penetrated by the mandrel.
Furthermore, two locking nuts with adjustable intervals are arranged on the mandrel.
Further, the mandrel is in threaded connection with the lock nut.
Further, the hole is coaxially arranged with the small-end die and the large-end die respectively.
The utility model has the advantages that: the number of the spinning dies is reduced to one set, so that the extension of internal defects caused by spinning of multiple sets of dies is avoided, the risk of generating cracks during spinning can be effectively reduced, the yield is improved, the production cost is effectively reduced, and the development investment of new products is reduced; the thrust chamber and the spinning die are only required to be assembled and disassembled once, and heat treatment is not required in the spinning process, so that the production cost can be effectively reduced, the production period is greatly shortened, and the automatic production is possible due to the fact that intermediate links are greatly reduced; the strong spinning process is not needed, the requirement on a spinning machine tool is reduced, and the production cost is effectively reduced; can effectively improve the utilization rate of materials and reduce the production cost.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required to be used in the embodiments will be briefly described below, and 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 view of a cartridge according to an embodiment of the present invention;
FIG. 2 is a schematic view of a thrust chamber forming die for a rocket engine according to an embodiment of the present invention;
fig. 3 is a schematic diagram of a diameter expanding spinning process according to an embodiment of the present invention;
fig. 4 is a schematic diagram of a diameter-reducing spinning process according to an embodiment of the present invention.
In the figure:
1. a cylindrical member; 2. briquetting; 3. rotating the wheel; 4. a small-end mold; 5. a large-end mold; 6. a mandrel; 7. and locking the nut.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art all belong to the protection scope of the present invention.
As shown in fig. 1-4, according to the embodiment of the present invention, a thrust chamber forming die for rocket engine, includes small end die 4, the head shape of small end die 4 is the cylindricality, the afterbody shape of small end die 4 is the toper, just the tail end external diameter of small end die 4 is less than its head end external diameter, the head end of big end die 5 is connected to tail end detachably of small end die 4, the shape of big end die 5 is the toper, the head end external diameter of big end die 5 is less than its tail end external diameter, and the head end external diameter of big end die 5 with the tail end external diameter of small end die 4 corresponds.
In a specific embodiment of the utility model, all set up the hole that end to end link up and can supply dabber 6 to pass on tip mould 4 with big end mould 5, the shape and the size of hole can match with 6 external diameters of dabber to improve the reliability of mould.
In a specific embodiment of the present invention, two lock nuts 7 with adjustable distance are disposed on the mandrel 6, and the two lock nuts 7 can move along the axial direction of the mandrel 6, so that the small end mold 4 and the large end mold 5 disposed on the mandrel 6 are fixed from both ends of the mandrel 6 along the axial direction.
In an embodiment of the present invention, both ends of the core shaft 6 include external thread structures, and the core shaft 6 is connected to the locking nut 7 through the external threads of both ends. By rotating the lock nuts 7, the depth of engagement with the external thread of the mandrel 6 can be adjusted, thereby changing the distance of the two lock nuts 7 in the axial direction of the mandrel 6. Specifically, when the small end mold 4 and the large end mold 5 are arranged in the mandrel 6 in a head-to-tail matching manner, the two locking nuts 7 arranged at the two ends of the mandrel 6 can fix the two from the two outer sides (the locking degree of the two locking nuts 7 to the molds is realized by adjusting the depth of the two locking nuts 7 and the external threads of the mandrel 6), so that the small end mold 4 and the large end mold 5 are prevented from moving along the axial direction of the mandrel 6 when the inner wall of the thrust chamber is molded.
In a specific embodiment of the present invention, the holes are respectively coaxial with the small end mold 4 and the large end mold 5, so that on one hand, the small end mold 4 and the large end mold 5 can be installed coaxially behind the mandrel 6, and on the other hand, the shape accuracy of the thrust chamber can be ensured when the thrust chamber is formed by the forming mold.
For the convenience of understanding the above technical solutions of the present invention, the above technical solutions of the present invention will be described in detail through specific use modes.
Utilize a thrust chamber forming die for rocket engine (hereinafter referred to as forming die) can become thrust chamber with section of thick bamboo 1 spinning.
The inner diameter of the cylindrical member 1 corresponds to the outer diameter of the head end of the small end die 4.
When the spinning machine is used, the mandrel 6 is firstly installed on a spinning machine tool, the small end die 4 is installed on the mandrel 6, the front end of the cylindrical part 1 is pressed on the small end die 4 through the pressing block 2, then the rear end of the cylindrical part 1 is expanded and spun to be conical from the inner side of the cylindrical part 1 by using the spinning wheel 3 on the spinning machine tool, the large end die 5 is installed on the mandrel 6, then the throat area of the cylindrical part 1, which is positioned at the joint of the small end die 4 and the large end die 5, is subjected to reducing spinning from the outer side of the cylindrical part 1 by using the spinning wheel 3, and then the conical part is reduced and spun from the outer side of the cylindrical part 1 to be attached to the large end die 5.
In one embodiment, when a copper alloy material is used as the material of the cylindrical member 1, the specific forming process is as follows:
1) smelting the copper alloy ingot according to the component requirement of the copper alloy.
2) And forging the cast ingot into a cylindrical part 1, wherein the specific values of the thickness and the length of the cylindrical part 1 are determined by the size and the structure of a thrust chamber, and the inner diameter of the cylindrical part 1 is the same as the outer diameter of the head end of the small-end die 4.
3) The raw material is annealed or solutionized to reduce the raw material hardness.
4) The internal quality of the cylindrical member 1 is determined by ultrasonic flaw detection, requiring zero internal defects.
5) And confirming that the grain size meets the spinning requirement through crystal phase inspection.
6) And (4) confirming that the strength and the elongation of the material meet the spinning requirement through a strength tensile test.
7) The spinning process is realized through one set of forming die, and forming die includes dabber 6, little end mould 4, big end mould 5 and lock nut 7, and little end mould 4, big end mould 5 fasten on dabber 6 through lock nut 7.
8) During spinning, the cylindrical part 1, the small-end die 4 and the mandrel 6 are installed on a spinning machine, the rear end of the cylindrical part 1 is spun to be conical through expanding and spinning of the spinning wheel 3, and the size of the conical part needs to ensure that the large-end die 5 can be installed in place.
9) After the large-end die 5 is installed in place, reducing and spinning a throat area (located at the joint of the small-end die 4 and the large-end die 5) on the cylindrical part 1, and spinning the conical part to be attached to the large-end die 5 to obtain the thrust chamber.
10) And (4) carrying out aging treatment on the thrust chamber, and detecting the mechanical property and the conductivity of the material after the aging treatment to finish the production of the thrust chamber.
11) In order to ensure that the cylindrical part 1 has better shaping in the spinning process, the cylindrical part 1 can be continuously heated in the spinning process, and the heating temperature is controlled below the aging temperature.
In summary, with the aid of the technical solution of the present invention, since the thickness variation of the cylindrical part is small, the forced spinning process is not required, and the requirements for the indexes such as the internal quality and the material grain size of the cylindrical part can be reduced to a certain extent, so as to reduce the production difficulty of the thrust chamber, improve the yield of the thrust chamber, and finally reduce the manufacturing cost; the number of the spinning dies is reduced to one set, so that the extension of internal defects caused by spinning of multiple sets of dies is avoided, the risk of generating cracks during spinning can be effectively reduced, the yield is improved, the production cost is effectively reduced, and the development investment of new products is reduced; the thrust chamber and the spinning die are only required to be assembled and disassembled once, and heat treatment is not required in the spinning process, so that the production cost can be effectively reduced, the production period is greatly shortened, and the automatic production is possible due to the fact that intermediate links are greatly reduced; the strong spinning process is not needed, the requirement on a spinning machine tool is reduced, and the production cost is effectively reduced; can effectively improve the utilization rate of materials and reduce the production cost.
The above description is only a preferred embodiment of the present invention, and should not be taken as limiting the invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. The utility model provides a thrust chamber forming die for rocket engine, characterized in that, includes tip mould (4), the head shape of tip mould (4) is the cylindricality, the afterbody shape of tip mould (4) is the toper, just the tail end external diameter of tip mould (4) is less than its head end external diameter, the head end of tip mould (5) is connected to the tail end detachably of tip mould (4), the shape of tip mould (5) is the toper, the head end external diameter of tip mould (5) is less than its tail end external diameter, and the head end external diameter of tip mould (5) with the tail end external diameter of tip mould (4) corresponds.
2. The thrust chamber forming die for the rocket engine according to claim 1, wherein the small end die (4) and the large end die (5) are both provided with holes which are through from end to end and through which the mandrel (6) can pass.
3. Thrust chamber forming die for rocket engines according to claim 2, characterized in that on said mandrel (6) two locking nuts (7) are provided, the spacing of which is adjustable.
4. Thrust chamber forming die for rocket engines according to claim 3, characterized in that said mandrel (6) is threaded with said locking nut (7).
5. Thrust chamber forming die for rocket engines according to claim 2, characterized in that said holes are respectively arranged coaxially with said small end die (4) and said large end die (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822030782.XU CN209886483U (en) | 2018-12-05 | 2018-12-05 | Thrust chamber forming die for rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822030782.XU CN209886483U (en) | 2018-12-05 | 2018-12-05 | Thrust chamber forming die for rocket engine |
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| Publication Number | Publication Date |
|---|---|
| CN209886483U true CN209886483U (en) | 2020-01-03 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201822030782.XU Active CN209886483U (en) | 2018-12-05 | 2018-12-05 | Thrust chamber forming die for rocket engine |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114160651A (en) * | 2021-10-27 | 2022-03-11 | 首都航天机械有限公司 | Process equipment for spin forming of inner wall of thrust chamber of engine |
| CN114589467A (en) * | 2022-03-29 | 2022-06-07 | 成都光明派特贵金属有限公司 | Precious metal multistage reducing channel and manufacturing method thereof |
| US11779985B1 (en) * | 2020-11-15 | 2023-10-10 | Herbert U. Fluhler | Fabricating method for low cost liquid fueled rocket engines |
-
2018
- 2018-12-05 CN CN201822030782.XU patent/CN209886483U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11779985B1 (en) * | 2020-11-15 | 2023-10-10 | Herbert U. Fluhler | Fabricating method for low cost liquid fueled rocket engines |
| CN114160651A (en) * | 2021-10-27 | 2022-03-11 | 首都航天机械有限公司 | Process equipment for spin forming of inner wall of thrust chamber of engine |
| CN114160651B (en) * | 2021-10-27 | 2024-05-14 | 首都航天机械有限公司 | Technological equipment for spin forming of inner wall of engine thrust chamber |
| CN114589467A (en) * | 2022-03-29 | 2022-06-07 | 成都光明派特贵金属有限公司 | Precious metal multistage reducing channel and manufacturing method thereof |
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