CN112628021A - Sealing welding method for end part of thrust chamber and rocket engine thrust chamber - Google Patents
Sealing welding method for end part of thrust chamber and rocket engine thrust chamber Download PDFInfo
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- CN112628021A CN112628021A CN202011384649.XA CN202011384649A CN112628021A CN 112628021 A CN112628021 A CN 112628021A CN 202011384649 A CN202011384649 A CN 202011384649A CN 112628021 A CN112628021 A CN 112628021A
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- copper alloy
- end cover
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
- F02K9/64—Combustion or thrust chambers having cooling arrangements
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Arc Welding In General (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
Abstract
The invention provides a sealing welding method for an end part of a thrust chamber and a rocket engine thrust chamber. The sealing and welding method comprises the following steps: providing a stainless steel outer wall, a copper alloy inner wall and an end cover, performing pre-connection treatment on the stainless steel outer wall, the copper alloy inner wall and the end cover, and arranging the stainless steel outer wall on the outer side of the copper alloy inner wall to enable the end faces of the two ends of the stainless steel outer wall and the two ends of the copper alloy inner wall to be flush; after the pre-connection treatment, the method comprises the following steps: a first oblique butt joint groove is formed in the outer side of the outer wall of the stainless steel, and a first notch is formed in the outer side of the end cover; a second oblique butt joint groove is formed in the inner side of the inner wall of the copper alloy, and a second notch is formed in the inner side of the end cover; slotting on the end faces of the tightly adhered stainless steel outer wall and the copper alloy inner wall; placing an end cover on the end face, and welding the end cover with the stainless steel outer wall and the copper alloy inner wall; and welding the stainless steel outer wall, the copper alloy inner wall and the end cover along the first oblique butt joint groove and the first notch and the second oblique butt joint groove and the second notch respectively. The process is simple, the design is reasonable, and the sealing is tight.
Description
Technical Field
The invention relates to the technical field of spacecraft engines, in particular to a sealing welding method for an end part of a thrust chamber and a rocket engine thrust chamber.
Background
The technology of spacecraft engines is rapidly upgraded with the development of the aerospace industry. As a main component of the engine, the thrust chamber is a key component for performing energy conversion of the propellant and generating thrust. The thrust chamber body is a component which is used for mixing and burning fuel in the spacecraft engine to generate high-temperature and high-pressure fuel gas, and then the fuel gas is accelerated and discharged through the throat part to obtain reverse thrust. The body of the thrust chamber is of a Laval profile structure, and the thrust chamber can be cooled by adopting a regenerative cooling technology. The thrust chamber is composed of a milling groove inner wall and a milling groove outer wall, and a plurality of cooling channels are arranged between the milling groove inner wall and the milling groove outer wall. In general, the gas temperature is as high as 3500K, the wall surface heat exchange power can reach hundreds megawatts, and 20MPa pressure needs to be borne, so that the inner wall material of the thrust chamber body is mostly made of copper alloy. The connection of the copper inner wall and the steel or other material outer wall is an important process, and one important requirement is to seal and weld the end faces of the inner wall and the outer wall, so that a closed space is created for subsequent processes, and the sealing performance of the seal and the welding directly influences the success or failure of the subsequent processes.
Disclosure of Invention
The invention aims to provide a sealing welding method for the end part of a thrust chamber and a rocket engine thrust chamber, which have the advantages of simple process, reasonable design, tight sealing and the like.
In order to achieve the purpose, the invention provides the following technical scheme: a sealing and welding method for the end part of a thrust chamber,
providing a stainless steel outer wall, a copper alloy inner wall and an end cover, and performing pre-connection treatment on the stainless steel outer wall, the copper alloy inner wall and the end cover, wherein the pre-connection treatment comprises the following steps:
arranging the stainless steel outer wall on the outer side of the copper alloy inner wall, enabling the stainless steel outer wall and the copper alloy inner wall to be tightly attached to each other, and enabling end faces of two ends of the stainless steel outer wall and the copper alloy inner wall to be flush;
after the pre-connection treatment, the method specifically comprises the following steps:
a first oblique butt joint groove is formed in the outer side of the outer wall of the stainless steel along the circumferential direction, and a first notch matched with the first oblique butt joint groove is formed in the outer side of the end cover;
a second oblique butt joint groove is formed in the inner side of the inner wall of the copper alloy along the circumferential direction, and a second notch matched with the second oblique butt joint groove is formed in the inner side of the end cover;
slotting along the circumferential direction on the end surfaces of the stainless steel outer wall and the copper alloy inner wall which are tightly attached to each other;
placing an end cover on the end face, and welding and connecting the end cover with the stainless steel outer wall and the copper alloy inner wall along the groove;
and welding along the first oblique butt joint groove and a first notch matched with the first oblique butt joint groove, the second oblique butt joint groove and a second notch matched with the second oblique butt joint groove respectively to complete the welding of the stainless steel outer wall, the copper alloy inner wall and the end cover.
Furthermore, the included angle between the first oblique butt joint groove and the axis of the stainless steel outer wall is A, and A is more than or equal to 15 degrees and less than or equal to 75 degrees.
Furthermore, the shape formed by the first oblique butt joint groove and the first notch is a C-shaped structure, and the notch of the C-shaped structure is far away from one side of the inner wall of the copper alloy.
Furthermore, the included angle between the second oblique butt joint groove and the axis of the inner wall of the copper alloy is B, and B is more than or equal to 15 degrees and less than or equal to 75 degrees.
Further, the second oblique butt joint bevel and the second notch are parallel to each other, and the second oblique butt joint bevel extends obliquely to one side of the end cover from the stainless steel outer wall to the copper inner wall.
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Furthermore, the length of the first oblique butt joint groove along the first direction is H, and H is more than or equal to 2mm and less than or equal to 11 mm.
Furthermore, the length of the second oblique butt joint groove along the second direction is E, and E is more than or equal to 2mm and less than or equal to 11 mm.
Further, the stainless steel outer wall and the end cover are subjected to preheating treatment before the first oblique butt joint groove and the first notch are welded.
Further, after the welding of the stainless steel outer wall, the copper alloy inner wall and the end cap is completed, the method includes:
and inflating the cavity between the stainless steel outer wall and the copper alloy inner wall at high pressure, and detecting the sealing performance of the cavity.
Further, after the stainless steel outer wall, the copper alloy inner wall and the end cover high-pressure inflation detection are completed, the method further comprises the following steps: and (4) flattening the welding seams.
Another aspect of the invention provides a rocket engine thrust chamber, which is prepared by adopting the sealing welding method for the end part of the thrust chamber.
Compared with the prior art, the invention has the beneficial effects that: through placing the end cover on the terminal surface, follow the fluting will the end cover with the stainless steel outer wall with copper alloy inner wall welded connection, the slotted design can make the stainless steel outer wall with copper alloy inner wall connects inseparabler, and is fixed more firmly. Meanwhile, the exposed gaps of the end faces of the stainless steel outer wall and the copper alloy inner wall are sealed through the end covers, so that external gas is prevented from entering the gaps between the stainless steel outer wall and the copper alloy inner wall, and the sealing effect is improved. And welding the inner side surface and the outer side surface of the end cover with the stainless steel outer wall and the copper alloy inner wall by respectively welding the first oblique butt joint groove, the first notch matched with the first oblique butt joint groove, the second oblique butt joint groove and the second notch matched with the second oblique butt joint groove, so that secondary sealing is completed. The whole method has the advantages of simple process, reasonable design, tight sealing and the like.
Drawings
FIG. 1 is a schematic view of a rocket engine thrust chamber component of the present invention;
FIG. 2 is a schematic structural view of the stainless steel outer wall, the copper alloy inner wall and the end cap of the present invention;
FIG. 3 is a schematic structural view of the outer wall of stainless steel, the inner wall of copper alloy and the slot of the present invention;
FIG. 4 is a schematic view of the structure of the stainless steel outer wall, the copper alloy inner wall and the end cap of the invention tangent along the axis;
FIG. 5 is a schematic structural diagram of an angle between a first oblique butt joint groove and an axis of a stainless steel outer wall, an angle between a second oblique butt joint groove and an axis of a copper alloy inner wall, a length of the first oblique butt joint groove in a first direction, and a length of the second oblique butt joint groove in a second direction;
FIG. 6 is a top view of the slot of the present invention;
FIG. 7 is a process flow diagram of the sealing method for the thrust chamber end of the present invention.
Description of reference numerals:
1 stainless steel outer wall and 2 copper alloy inner wall
3 end cover 4 first oblique butt joint groove
5 first cut 6 second oblique butt joint groove
7 second cut 8 grooving
Detailed Description
For the purpose of promoting a clear understanding of the objects, aspects and advantages of the embodiments of the invention, reference will now be made to the drawings and detailed description, wherein there are shown in the drawings and described in detail, various modifications of the embodiments described herein, and other embodiments of the invention will be apparent to those skilled in the art.
The exemplary embodiments of the present invention and the description thereof are provided to explain the present invention and not to limit the present invention. Additionally, the same or similar numbered elements/components used in the drawings and the embodiments are used to represent the same or similar parts.
As used herein, the terms "first," "second," …, etc., do not denote any order or sequence, nor are they used to limit the present invention, but rather are used to distinguish one element from another or from another element or operation described in the same technical language.
With respect to directional terminology used herein, for example: up, down, left, right, front or rear, etc., are simply directions with reference to the drawings. Accordingly, the directional terminology used is intended to be illustrative and is not intended to be limiting of the present teachings.
As used herein, the terms "comprising," "including," "having," "containing," and the like are open-ended terms that mean including, but not limited to.
As used herein, "and/or" includes any and all combinations of the described items.
As used herein, the terms "substantially", "about" and the like are used to modify any slight variation in quantity or error that does not alter the nature of the variation. Generally, the range of slight variations or errors modified by such terms may be 20% in some embodiments, 10% in some embodiments, 5% in some embodiments, or other values. It should be understood by those skilled in the art that the aforementioned values can be adjusted according to actual needs, and are not limited thereto.
Certain words used to describe the present application are discussed below or elsewhere in this specification to provide additional guidance to those skilled in the art in describing the present application.
An embodiment of the present invention provides a sealing method for an end of a thrust chamber, as shown in fig. 1, fig. 2, fig. 3, fig. 4, fig. 6, and fig. 7, providing a stainless steel outer wall 1, a copper alloy inner wall 2, and an end cap 3, and performing a pre-joining process on the stainless steel outer wall 1, the copper alloy inner wall 2, and the end cap 3, including:
a1: arranging a stainless steel outer wall 1 outside a copper alloy inner wall 2, wherein the stainless steel outer wall 1 and the copper alloy inner wall 2 are tightly attached to each other, and the end surfaces of two ends of the stainless steel outer wall 1 and the copper alloy inner wall 2 are flush;
after the pre-connection treatment, the method specifically comprises the following steps:
a2: a first oblique butt joint groove 4 is formed in the outer side of the stainless steel outer wall 1 along the circumferential direction, and a first notch 5 matched with the first oblique butt joint groove 4 is formed in the outer side of the end cover 3;
a3: a second oblique butt joint groove 6 is formed in the inner side of the copper alloy inner wall 2 along the circumferential direction, and a second notch 7 matched with the second oblique butt joint groove 6 is formed in the inner side of the end cover 3;
a4: slotting 8 on the end surfaces of the stainless steel outer wall 1 and the copper alloy inner wall 2 which are tightly attached to each other along the circumferential direction;
a5: placing the end cover 3 on the end face, and welding the end cover 3 with the stainless steel outer wall 1 and the copper alloy inner wall 2 along the groove 8;
a6: and welding is respectively carried out along the first oblique butt joint groove 4, the first notch 5 matched with the first oblique butt joint groove, the second oblique butt joint groove 6 and the second notch 7 matched with the second oblique butt joint groove, so that the welding of the stainless steel outer wall 1, the copper alloy inner wall 2 and the end cover 3 is completed.
Specifically speaking, through placing end cover 3 on the terminal surface, along fluting 8 with end cover 3 and stainless steel outer wall 1 and copper alloy inner wall 2 welded connection, the slotted design can be so that stainless steel outer wall 1 and copper alloy inner wall 2 are connected inseparabler, and is fixed more firmly. Meanwhile, the exposed gaps of the end faces of the stainless steel outer wall 1 and the copper alloy inner wall 2 are sealed through the end cover 3, so that external gas is prevented from entering the gap between the stainless steel outer wall 1 and the copper alloy inner wall 2, and the sealing effect is improved. Through welding along first oblique butt joint groove 4 and rather than complex first incision 5 and second oblique butt joint groove 6 and rather than complex second incision 7 respectively for the inside and outside surface and the stainless steel outer wall 1 and the copper alloy inner wall 2 of end cover 3 weld, accomplish the secondary seal, make and seal more rigorous. The whole method has the advantages of simple process, reasonable design, tight sealing and the like.
It is worth mentioning that, set up stainless steel outer wall 1 in the outside of copper alloy inner wall 2, and both hug closely each other, and make the terminal surface at stainless steel outer wall 1 and 2 both ends of copper alloy inner wall flush after, still contain and set up end cover 3 on the terminal surface, can make end cover 3 and terminal surface paste tightly (need end cover 3 and terminal surface contact's surfacing, smooth, and the terminal surface that the interior outer wall formed and each surface of end cover complex lie in the coplanar), guarantee that end cover 3 and terminal surface hug closely the in-process, reduce the clearance between the two, and then reduce impurity or gaseous to end cover 3 and terminal surface welding interference, improve welding precision, make things convenient for the welding of follow-up end cover 3 and terminal surface, improve the tip leakproofness. After the pre-joining process, prior to step a2, the end cap 3 needs to be removed so that the end faces are exposed.
In practical applications, in order to improve efficiency, for example, the cutting of the first oblique butt groove 4 and the second oblique butt groove 6 may be simultaneously completed by two cutting machines. In a similar way, the end cover is provided with the first notch 5, the second notch 7 and the groove 8 which can be cut simultaneously by different cutting machines, so that the cutting time is reduced, and all parts after subsequent cutting can be welded in a combined manner, thereby improving the working efficiency of the whole welding.
It should be noted that, through multiple simulation experiments, when the axis included angle between the first oblique butt joint groove 4 and the stainless steel outer wall 1 is a, and a is equal to or greater than 15 degrees and equal to or less than 75 degrees; the included angle between the second oblique butt joint groove 6 and the axis of the copper alloy inner wall 1 is B, and B is more than or equal to 15 degrees and less than or equal to 75 degrees. Through the contained angle of adjustment butt joint groove and interior outer wall for when the interior outside surface of end cover 3 welds with stainless steel outer wall 1 and copper alloy inner wall 2, the end cover 3 of being convenient for closely combines with stainless steel outer wall 1 and copper alloy inner wall 2, can accomplish secondary seal, further avoids the external gas to get into the gap department between stainless steel outer wall 1 and the copper alloy inner wall 2, improves sealed effect.
In the present embodiment, for welding convenience, for example, the first oblique butt-joint groove 4 and the first notch 5 form a C-shaped configuration in a cross section along the axial direction of the stainless outer wall 1, and the notch of the C-shaped configuration faces away from the copper alloy inner wall 2. When adopting laser welding, because the design of C type structure, not only increase first oblique butt joint groove 4 and 5 welding area of first incision, make things convenient for the welding material to adhere to on C type structure surface moreover for end cover 3 is connected inseparabler with stainless steel outer wall 1, and is fixed more firmly.
In order to ensure the welding strength when welding the copper alloy inner wall 2, for example, laser welding may be employed. For the convenience of using the laser welding head, the second oblique butt joint groove 6 and the second notch 7 are sealed by a welding material, for example, the second oblique butt joint groove 6 and the second notch 7 are parallel to each other and extend from the stainless steel outer wall 1 to the copper inner wall 2, and the outer end of the second oblique butt joint groove 6 extends obliquely to one side of the end cover 3. This design is convenient to be connected the oblique butt joint groove of second 6 and the high-efficient utilization of welding material of second incision 7, reduces the welding material and flows outward from the gap between the oblique butt joint groove of second 6 and the second incision 7, when avoiding final products to introduce welding impurity, improves the fixed strength of welding material to copper alloy inner wall 2 and end cover 3, ensures that the product can property ability. In the process, the end cover is welded with the inner wall and the outer wall at an oblique angle, so that the laser welding head can be welded in an oblique shooting mode, the space occupied by the laser welding head on the end cover 3 or the copper alloy inner wall 2 can be reduced, and the technical difficulty that the laser welding head cannot enter the inner side of the small-sized end cover 3 for welding is solved.
In addition, as shown in fig. 4 and 5, when the length of the first oblique butt joint groove 4 along the first direction (S1 arrow pointing direction) is H, and H is greater than or equal to 2mm and less than or equal to 11mm, the length of the second oblique butt joint groove 6 along the second direction (S2 arrow pointing direction) is E, and E is greater than or equal to 2mm and less than or equal to 11mm, it is convenient for the inner and outer side surfaces of the end cover 3 to be welded with the stainless steel outer wall 1 and the copper alloy inner wall 2, and meanwhile, the end cover 3 can be connected with the stainless steel outer wall 1 and the copper alloy inner wall 2 more tightly, so that the fixation is firmer, and the.
In the embodiment, in order to weld the stainless outer wall 1 and the end cap 3 more firmly, the stainless outer wall 1 and the end cap 3 are subjected to a preheating treatment before the first oblique butt groove 4 and the first notch 5 are welded. Through to stainless steel outer wall 1 and end cover 3 preheating (for example, through heating blower with the temperature of stainless steel outer wall 1 and end cover 3 rise to 100 °), can guarantee that when high temperature welding, stainless steel outer wall 1 and end cover 3 pass through the high-speed joint of welding material, improve the welding quality of the two, improve the leakproofness between stainless steel outer wall 1 and end cover 3.
In order to verify the tightness of the stainless steel outer wall 1 and the copper alloy inner wall 2 in time, for example, after the welding of the stainless steel outer wall 1, the copper alloy inner wall 2 and the end cover 3 is completed, the method includes: the gap between the stainless steel outer wall 1 and the copper alloy inner wall 2 is inflated at high pressure, the sealing performance of the stainless steel outer wall 1, the copper alloy inner wall 2 and the end cover 3 is detected (whether high-pressure gas is leaked from welding seams of the end cover 3, the stainless steel outer wall 1 and the copper alloy inner wall 2 is mainly detected), and when the detected gas leakage is larger than a threshold value, laser or manual repair welding can be carried out.
Furthermore, after the high-pressure inflation detection of the stainless steel outer wall 1, the copper alloy inner wall 2 and the end cover 3 is completed, the original effect is not influenced, and meanwhile, in order to reduce the weight of the thrust chamber component, the welding seams can be flattened.
In order to obtain the final body structure of the thrust chamber, an end cover 3 is connected with the inner wall and the outer wall by a sealing welding method of the end part of the thrust chamber, so that a closed space is formed between the outer wall 1 of the steel and the inner wall 2 of the copper alloy;
vacuumizing the closed space through an air duct welded on the outer wall 1 of the steel;
putting the combined structure consisting of the steel outer wall 1, the copper alloy inner wall 2 and the end cover 3 which are vacuumized into a high-pressure container for primary pressurization treatment;
taking out the combined structure from the high-pressure container, and keeping the air between the inner wall and the outer wall smooth with the external air through the air duct;
putting the inner wall and the outer wall into the high-pressure container again for secondary pressurization treatment, wherein the maximum pressure of the secondary pressurization treatment is greater than that of the primary pressurization treatment;
and taking out the combined structure subjected to the secondary pressurization treatment, and cutting off the parts of the end cover 3 and the stainless steel outer wall 1 matched with the air guide pipe to obtain a thrust chamber body structure consisting of the stainless steel outer wall 1 and the copper alloy inner wall 2.
The above embodiments may be combined with each other with corresponding technical effects.
The foregoing is merely an illustrative embodiment of the present invention, and any equivalent changes and modifications made by those skilled in the art without departing from the spirit and principle of the present invention should fall within the protection scope of the present invention.
Claims (10)
1. A sealing welding method for the end part of a thrust chamber is characterized in that,
providing a stainless steel outer wall, a copper alloy inner wall and an end cover, and performing pre-connection treatment on the stainless steel outer wall, the copper alloy inner wall and the end cover, wherein the pre-connection treatment comprises the following steps:
arranging the stainless steel outer wall on the outer side of the copper alloy inner wall, enabling the stainless steel outer wall and the copper alloy inner wall to be tightly attached to each other, and enabling end faces of two ends of the stainless steel outer wall and the copper alloy inner wall to be flush;
after the pre-connection treatment, the method specifically comprises the following steps:
a first oblique butt joint groove is formed in the outer side of the outer wall of the stainless steel along the circumferential direction, and a first notch matched with the first oblique butt joint groove is formed in the outer side of the end cover;
a second oblique butt joint groove is formed in the inner side of the inner wall of the copper alloy along the circumferential direction, and a second notch matched with the second oblique butt joint groove is formed in the inner side of the end cover;
slotting along the circumferential direction on the end surfaces of the stainless steel outer wall and the copper alloy inner wall which are tightly attached to each other;
placing an end cover on the end face, and welding and connecting the end cover with the stainless steel outer wall and the copper alloy inner wall along the groove;
and welding along the first oblique butt joint groove and a first notch matched with the first oblique butt joint groove, the second oblique butt joint groove and a second notch matched with the second oblique butt joint groove respectively to complete the welding of the stainless steel outer wall, the copper alloy inner wall and the end cover.
2. The method of claim 1, wherein the first oblique butt groove forms an angle a with the axis of the stainless steel outer wall, and the angle a is 15 ° or more and 75 ° or less.
3. The method for sealing and welding the end part of the thrust chamber according to claim 2, wherein the first oblique butt-joint groove and the first notch form a C-shaped structure in a cross section along the axis of the stainless steel outer wall, and the notch of the C-shaped structure faces to the side away from the copper alloy inner wall.
4. The method of claim 1, wherein the angle between the second oblique butt groove and the axis of the inner wall of the copper alloy is B, and is in a range of 15 ° to 75 °.
5. The method of claim 4, wherein the second oblique butt-joint bevel and the second notch are parallel to each other, and the second oblique butt-joint bevel extends obliquely toward the end cover side in a direction from the stainless outer wall toward the copper inner wall.
6. The seal welding method for the end part of the thrust chamber as claimed in claim 1, wherein the length of the first oblique butt groove in the first direction is H, H is 2mm or more and 11mm or less.
7. The seal welding method for the end part of the thrust chamber as claimed in claim 1, wherein the length of the second oblique butt groove in the second direction is E, and E is 2mm or more and 11mm or less.
8. The method of claim 1, wherein the pre-heating of the outer stainless steel wall and the end cap prior to welding the first bevel butt groove and the first cut comprises, after welding the outer stainless steel wall, the inner copper alloy wall and the end cap:
and inflating the cavity between the stainless steel outer wall and the copper alloy inner wall at high pressure, and detecting the sealing performance of the cavity.
9. The method of claim 8, wherein after the testing of the outer stainless steel wall, the inner copper alloy wall, and the end cap for high pressure inflation, the method further comprises: and (4) flattening the welding seams.
10. A rocket engine thrust chamber characterized by being prepared by the method of sealing the thrust chamber end according to any one of claims 1 to 9.
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| CN202011384649.XA CN112628021B (en) | 2020-12-01 | 2020-12-01 | Sealing welding method for end part of thrust chamber and rocket engine thrust chamber |
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| CN202011384649.XA CN112628021B (en) | 2020-12-01 | 2020-12-01 | Sealing welding method for end part of thrust chamber and rocket engine thrust chamber |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6205661B1 (en) * | 1999-04-15 | 2001-03-27 | Peter John Ring | Method of making a rocket thrust chamber |
| US6249967B1 (en) * | 1997-08-29 | 2001-06-26 | Hughes Electronics Corporation | Fabrication of a rocket engine with a transition structure between the combustion chamber and the injector |
| CN106050474A (en) * | 2016-05-23 | 2016-10-26 | 上海空间推进研究所 | Novel connecting structure for head and regenerative cooling body of rocket engine |
| CN107956602A (en) * | 2017-11-23 | 2018-04-24 | 北京航天动力研究所 | A kind of new Joining Structure of composite thrust room |
| CN209724523U (en) * | 2019-03-13 | 2019-12-03 | 蓝箭航天技术有限公司 | A kind of thrust chamber's structure |
| CN110653569A (en) * | 2019-09-30 | 2020-01-07 | 湖北三江航天江北机械工程有限公司 | Forming method of combustion chamber of liquid rocket engine |
-
2020
- 2020-12-01 CN CN202011384649.XA patent/CN112628021B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6249967B1 (en) * | 1997-08-29 | 2001-06-26 | Hughes Electronics Corporation | Fabrication of a rocket engine with a transition structure between the combustion chamber and the injector |
| US6205661B1 (en) * | 1999-04-15 | 2001-03-27 | Peter John Ring | Method of making a rocket thrust chamber |
| CN106050474A (en) * | 2016-05-23 | 2016-10-26 | 上海空间推进研究所 | Novel connecting structure for head and regenerative cooling body of rocket engine |
| CN107956602A (en) * | 2017-11-23 | 2018-04-24 | 北京航天动力研究所 | A kind of new Joining Structure of composite thrust room |
| CN209724523U (en) * | 2019-03-13 | 2019-12-03 | 蓝箭航天技术有限公司 | A kind of thrust chamber's structure |
| CN110653569A (en) * | 2019-09-30 | 2020-01-07 | 湖北三江航天江北机械工程有限公司 | Forming method of combustion chamber of liquid rocket engine |
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