CN113982786B - Rocket engine thrust chamber of red copper-stainless steel for avoiding dissimilar metal welding - Google Patents
Rocket engine thrust chamber of red copper-stainless steel for avoiding dissimilar metal welding Download PDFInfo
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- CN113982786B CN113982786B CN202111268833.2A CN202111268833A CN113982786B CN 113982786 B CN113982786 B CN 113982786B CN 202111268833 A CN202111268833 A CN 202111268833A CN 113982786 B CN113982786 B CN 113982786B
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- inner shell
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- red copper
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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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- 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
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Butt Welding And Welding Of Specific Article (AREA)
Abstract
The invention discloses a red copper-stainless steel rocket engine thrust chamber for avoiding dissimilar metal welding, which comprises an outer shell, an inner shell, a front end flange and a rear end flange; the shell is made of stainless steel; the inner shell is made of red copper, is coaxially inserted into the outer shell, and two ends of the inner shell extend out of two ends of the outer shell respectively to form a front extending end and a rear extending end; 20 water tanks are circumferentially arranged on the outer wall surface of the inner shell, and each water tank is axially arranged along the inner shell; rib plates are formed between two adjacent water tanks; the front end flange and the rear end flange are made of stainless steel and are welded with the two ends of the shell respectively. The invention adopts a mode of avoiding dissimilar metal welding to assemble, ensures the structural strength of the thrust chamber of the rocket engine and simultaneously gives consideration to the heat dissipation performance in the thrust chamber, thereby solving the problems of higher throat energy density or throat ablation under extreme working conditions in the rocket engine ignition test process.
Description
Technical Field
The invention relates to the field of rocket engines, in particular to a red copper-stainless steel rocket engine thrust chamber for avoiding dissimilar metal welding.
Background
For a model rocket engine test, thermal protection is required during ignition test, so that the inner wall of a thrust chamber is cooled. At present, the common heat protection methods are as follows:
(1) Traditional heat sink cooling
The heat sink cooling is the simplest heat protection means, namely, a thicker engine wall surface is selected in the processing process, and the heat sink cooling is carried out only by the thicker engine wall surface during ignition test, so that the whole engine is made of red copper or stainless steel.
The traditional heat sink cooling design is only suitable for the condition that the test condition of the engine is low or the test time is short (about 1 second). If the test time is long, the test working condition is high (the throat energy density of the model rocket engine is high) or under the extreme working condition (such as the rocket engine has high-frequency unstable combustion), throat ablation is easy to occur in the heat sink cooling design. Simple heat sink cooling has therefore been very limited in model rocket engine testing.
(2) Providing cooling channels
The cooling channel is arranged in the thrust chamber structure, the water pump pumps the coolant in the liquid box, the coolant is injected into the cooling channel through the water inlet, the thrust chamber is cooled by convection, and then the coolant is discharged from the water outlet and returns to the liquid box, and the cooling of the thrust chamber is realized by reciprocating circulation.
The cooling channel is arranged, so that the test device can be suitable for the condition of long test time. However, considering the structural strength requirement of the thrust chamber, stainless steel materials are generally adopted, and the heat conduction performance of the steel materials is poor, so that the temperature of the inner wall of the thrust chamber is not reduced. Practical tests show that after the stainless steel material is adopted for ignition for a long time, the throat part still has ablation problem due to poor heat conductivity of the steel.
If the red copper material is adopted, the heat conduction performance is better, but the rigidity of the red copper is reduced after heating, and the whole structure is easy to deform.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides the red copper-stainless steel rocket engine thrust chamber for avoiding dissimilar metal welding, and the red copper-stainless steel rocket engine thrust chamber for avoiding dissimilar metal welding is assembled in a manner of avoiding dissimilar metal welding, so that the reliability of the strength of the rocket engine thrust chamber can be effectively improved, the heat conduction performance inside the thrust chamber can be considered, and the problems of higher throat energy density or throat ablation under extreme working conditions in the rocket engine ignition test process are solved.
In order to solve the technical problems, the invention adopts the following technical scheme:
a rocket engine thrust chamber of red copper-stainless steel for avoiding dissimilar metal welding comprises an outer shell, an inner shell, a front end flange and a rear end flange.
The shell is made of stainless steel.
The material of inner shell is red copper, and the coaxial plug-in of inner shell is established in the shell, and both ends stretch out from the both ends of shell respectively, form the front and stretch out the end after.
A plurality of water tanks are arranged on the outer wall surface of the inner shell along the circumferential direction, and each water tank is arranged along the axial direction of the inner shell; ribs are formed between two adjacent water tanks.
The front end flange and the rear end flange are made of stainless steel.
The front end flange comprises a propellant spraying nozzle and a front inner shell mounting port which are coaxially arranged in sequence from front to back, and the front inner shell mounting port is coaxially sleeved on the periphery of the front extending end of the inner shell; the front end face of the inner shell is in sealing connection with the front end flange, and the rear end face of the front end flange is welded with the front end face of the outer shell.
The front end flange periphery is provided with a plurality of water outlet holes which can be communicated with the water tank.
The rear end flange comprises a rear inner shell mounting opening and a tail gas discharge opening which are coaxially arranged in sequence from front to back, the rear inner shell mounting opening is coaxially sleeved on the periphery of the rear extension end of the inner shell, the rear end face of the inner shell is in sealing connection with the rear end flange, and the front end face of the rear end flange is welded with the rear end face of the outer shell.
The circumference surface of the rear end flange is provided with a plurality of water inlet holes which can be communicated with the water tank.
The circumferential angle of each water tank and each rib plate is equal.
The number of the water grooves and the rib plates is 20, and the circumferential angles of the water grooves and the rib plates are 9 degrees.
The inner shell comprises a cylindrical combustion chamber section and a Laval nozzle section which are integrally arranged; in the throat of the laval nozzle section, one rib plate of two adjacent rib plates is provided with a throat opening.
The throat of the inner shell has a thickness of 5.5mm.
The depth of all the water tanks is equal.
All the water channels were 9.5mm deep.
A front seal ring and a rear seal ring are also included.
The front end of each water tank is provided with a front plug, the front end face of the front plug is provided with a front sealing ring groove, a front sealing ring is embedded in the front sealing ring groove, a front sealing convex ring groove is arranged on a front end flange opposite to the front sealing ring groove, and the front sealing convex ring groove can be in sealing fit with the front sealing ring groove embedded with the front sealing ring.
The rear end of each water tank is provided with a rear plug; the rear end face of the rear plug is provided with a rear sealing ring groove, a rear sealing ring is embedded in the rear sealing ring groove, a rear sealing convex ring groove is arranged on a rear end flange opposite to the rear sealing ring groove, and the rear sealing convex ring groove can be in sealing fit with the rear sealing ring groove embedded with the rear sealing ring.
The front sealing ring and the rear sealing ring are both made of asbestos.
A front water collecting cavity is arranged between the front inner shell mounting opening and the front extending end of the inner shell; a rear water collecting cavity is arranged between the rear inner shell mounting opening and the rear extending end of the inner shell.
The invention has the following beneficial effects:
(1) The thrust chamber structure which is formed by combining the inner shell made of red copper material and the outer shell made of stainless steel material has good heat conduction performance inside and good cooling effect; meanwhile, after heating, the structure can keep certain rigidity and not deform.
(2) Through the test, the long-time ignition test of 20s can be born, the throat is not ablated, meanwhile, the thickness of the throat can be reduced to 5.5mm, and 21mm is required by adopting the traditional heat sink cooling, and the long-time ignition cannot be realized.
(3) The mode of avoiding dissimilar metal welding is assembled, the overall structure strength is higher, and the reliability is further improved.
(4) Common materials are adopted, the processing technology is simpler, and the cost is further saved.
Drawings
FIG. 1 shows an exploded view of a rocket engine thrust chamber of the present invention that avoids dissimilar metal welded red copper-stainless steel.
FIG. 2 shows an assembly view of a rocket engine thrust chamber of the present invention that avoids dissimilar metal welded red copper-stainless steel.
Fig. 3 shows a schematic structural view of the housing in the present invention.
Fig. 4 shows a schematic structural view of the inner shell in the present invention.
Fig. 5 shows a schematic structural view of the front flange in the present invention.
Fig. 6 shows a schematic structural view of the rear flange in the present invention.
FIG. 7 shows a comparative heat dissipation schematic of two metals according to the present invention.
The method comprises the following steps:
10. a housing;
11. a half-split piece; 12. an axial welding surface; 13. a front end welding surface; 14. a rear end welding surface; 15. welding and chamfering;
20. an inner case; 21. a water tank; 22. rib plates; 221. a throat opening; 23. front plugging; 24. a front seal ring groove; 25. plugging; 26. a rear sealing ring groove;
30. a front end flange;
31. propellant injection ports; 32. a front sealing convex ring groove; 33. a water outlet hole; 34. a front water collecting cavity; 35. a front flange welding surface;
40. a rear end flange;
41. a tail gas discharge port; 42. a rear sealing convex ring groove; 43. a water inlet hole; 44. a rear water collection chamber; 45. and a rear flange welding surface.
Detailed Description
The invention will be described in further detail with reference to the accompanying drawings and specific preferred embodiments.
In the description of the present invention, it should be understood that the terms "left", "right", "upper", "lower", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the apparatus or element being referred to must have a specific orientation, be configured and operated in a specific orientation, and "first", "second", etc. do not indicate the importance of the components, and thus are not to be construed as limiting the present invention. The specific dimensions adopted in the present embodiment are only for illustrating the technical solution, and do not limit the protection scope of the present invention.
As shown in fig. 1 and 2, a rocket engine thrust chamber of red copper-stainless steel, which avoids dissimilar metal welding, comprises an outer casing 10, an inner casing 20, a front end flange 30 and a rear end flange 40.
As shown in fig. 3, the material of the casing is stainless steel, and preferably includes two symmetrical half-split members 11, wherein one side of each of the two half-split members 11, which is opposite, is an axial welding surface 12, and the two half-split members 11 form a complete laval nozzle by welding the same metal.
The front end surface (i.e., left end surface) of the housing is a front end portion welding surface 13, and the rear end surface (i.e., right end surface) of the housing is a rear end portion welding surface 14.
Further, a welding chamfer 15 is preferably provided on the outer side of each of the axial welding surface 12, the end welding surface 13 and the rear end welding surface 14 to facilitate welding after assembly.
As shown in FIG. 2, the inner shell is made of red copper, the inner shell is coaxially inserted into the outer shell, and two ends of the inner shell extend out from two ends of the outer shell respectively to form a front extending end and a rear extending end. Due to the adoption of the water cooling design, the inner shell can be made into an equal-thickness structure.
As shown in fig. 4, a plurality of water tanks 21 are circumferentially arranged on the outer wall surface of the inner shell, and each water tank is axially arranged on the inner shell; ribs 22 are formed between two adjacent water tanks. The design of the rib plate not only can increase the compression resistance of the inner part, but also has the effect of the radiating fin, increases the contact area with water, and can further improve the radiating efficiency.
The circumferential angle of each water trough and each rib is preferably equal. In this embodiment, the number of the water grooves and the rib plates is 20, and the circumferential angles of the water grooves and the rib plates are preferably 9 °.
The depth of all the water tanks is preferably equal, more preferably 9.5mm.
The front end of each water tank is provided with a front plug 23, the front end surface of the front plug is provided with a front sealing ring groove 24, and a front sealing ring which is preferably made of asbestos material is embedded in the front sealing ring groove; the rear end of each water tank is provided with a rear plug 25; the rear end face of the rear plug is provided with a rear sealing ring groove 26, and a rear sealing ring made of asbestos material is embedded in the rear sealing ring groove.
Alternatively, the front and rear ends of each water tank may be provided so as to be penetrated, and the front seal ring groove may be provided only on the front end surface of the inner case. Similarly, the rear sealing ring groove only needs to be arranged on the rear end face of the inner shell.
The inner shell comprises a cylindrical combustion chamber section and a Laval nozzle section which are integrally arranged from front to back; in the throat of the laval nozzle section, one of the two adjacent ribs is provided with a throat opening 221.
The provision of the throat opening 221 can realize widening of the throat water channel. When in ignition test, the water temperature of the liquid tank is normal temperature, and the stable working temperature of the flow field in the combustion chamber can reach more than 3000K.
Further, the thickness of the throat of the inner shell is preferably 5.5mm.
The front end flange and the rear end flange are made of stainless steel.
As shown in fig. 5, the front flange includes a propellant injection port 31 and a front inner housing mounting port coaxially disposed in this order from front to back, the front inner housing mounting port is coaxially sleeved on the outer periphery of the front projecting end of the inner housing, and the rear end face (i.e., front flange welding face 35) of the front inner housing mounting port is welded to the front end face (i.e., front end welding face 13) of the outer housing.
Further, the front end face of the front extending end of the inner shell is in sealing connection with the front end flange. In this embodiment, the preferable arrangement mode is: the front end flange opposite to the front sealing ring groove is provided with a front sealing convex ring groove 32 which can be matched with the front sealing ring groove embedded with the front sealing ring in a sealing way.
The periphery of the front inner shell mounting opening is provided with a plurality of water outlet holes 33 which can be communicated with the water tank, preferably 4 water outlet holes marked by circles in fig. 5. Further, the inner diameter of the front inner housing mounting opening is larger than the outer diameter of the front protruding end, thereby forming a front water collection chamber 34 between the front inner housing mounting opening and the front protruding end of the inner housing. The front water collection chamber 34 is provided to enable the water flow between the water tanks to flow uniformly.
As shown in fig. 6, the rear end flange includes a rear inner housing mounting opening and a tail gas discharge opening 41 coaxially disposed in this order from front to rear, the rear inner housing mounting opening being coaxially sleeved on the outer periphery of the rear projecting end of the inner housing, and the front end face (i.e., rear flange welding face 45) of the rear inner housing mounting opening being welded to the rear end face (i.e., rear end portion welding face 14) of the outer housing.
Further, the rear end face of the rear extending end of the inner shell is in sealing connection with the rear end flange. In this embodiment, the preferable arrangement mode is: the rear end flange opposite to the rear sealing ring groove is provided with a rear sealing convex ring groove 42 which can be in sealing fit with the rear sealing ring groove embedded with the rear sealing ring.
The periphery of the rear inner shell mounting opening is provided with a plurality of water inlet holes 43 which can be communicated with the water tank, preferably 4 water inlet holes marked by circles in fig. 6. Further, the inner diameter of the rear inner housing mounting opening is larger than the outer diameter of the rear extension end, thereby forming a rear water collection chamber 44 between the rear inner housing mounting opening and the rear extension end of the inner housing.
Further, the outer diameters of the front end flange and the rear end flange are preferably the same as the outer diameter of the shell, so that the welding and fixing are convenient, and the whole body is attractive.
The thrust chamber is assembled in the following way: firstly, an inner shell with a cooling liquid channel (namely a water channel) is combined with an outer shell, symmetrical half-split parts are combined into a whole through welding after compaction, then front and rear end flanges are additionally arranged, front sealing convex ring grooves are processed on the contact surfaces of the inner shell and the front and rear end flanges and are used for being in butt joint with the sealing ring grooves on the inner shell to realize internal flow channel sealing, and the front and rear end flanges are welded with two ends of the outer shell after being in compaction sealing with the inner shell to realize external flow channel sealing.
The invention adopts a thrust chamber structure with a combination of the inner shell made of red copper material and the outer shell made of stainless steel material, and has good heat conduction performance and good cooling effect; meanwhile, after heating, the structure can keep certain rigidity and not deform. As can be seen from fig. 7, the heat dissipation efficiency of the dissimilar metal and the same metal are different.
After the actual water-through test, the invention finds that the whole structure has good tightness, and the assembly mode proposed by the scheme is feasible. And then performing an ignition test, wherein after the ignition test is performed for 20 seconds for a long time, the temperature of the water outlet is increased to 46 ℃, the throat structure is complete, and no obvious ablation occurs. The problem that the temperature of thrust force room is too high in a long-time ignition test can be effectively solved by adopting the scheme. Meanwhile, the throat thickness can be reduced to 5.5mm in the scheme, and 21mm is required for cooling by adopting a traditional heat sink, and long-time ignition cannot be realized.
Meanwhile, the invention avoids the mode of dissimilar metal welding for assembly, and has higher overall structural strength and further improved reliability.
Furthermore, as an alternative, the invention can change the welding combination mode of two parts of the combustion chamber shell, and the sealing structure of the front end flange and the rear end flange and the combustion chamber is used as a reference, the flange surface with the bolt holes is increased upwards and downwards at the split position of the two parts, and the welding is replaced by the bolt connection. Meanwhile, a bulge and a groove are arranged on the joint end surfaces of the two parts of the shell, and an asbestos sealing gasket is arranged in the groove to finish sealing.
The preferred embodiments of the present invention have been described in detail above, but the present invention is not limited to the specific details of the above embodiments, and various equivalent changes can be made to the technical solution of the present invention within the scope of the technical concept of the present invention, and all the equivalent changes belong to the protection scope of the present invention.
Claims (10)
1. A rocket engine thrust chamber of red copper-stainless steel for avoiding dissimilar metal welding is characterized in that: the device comprises an outer shell, an inner shell, a front end flange and a rear end flange;
the shell is made of stainless steel;
the inner shell is made of red copper, is coaxially inserted into the outer shell, and two ends of the inner shell extend out of two ends of the outer shell respectively to form a front extending end and a rear extending end;
a plurality of water tanks are arranged on the outer wall surface of the inner shell along the circumferential direction, and each water tank is arranged along the axial direction of the inner shell; rib plates are formed between two adjacent water tanks;
the front end flange and the rear end flange are made of stainless steel;
the front end flange comprises a propellant spraying nozzle and a front inner shell mounting port which are coaxially arranged in sequence from front to back, and the front inner shell mounting port is coaxially sleeved on the periphery of the front extending end of the inner shell; the front end face of the inner shell is in sealing connection with the front end flange, and the rear end face of the front end flange is welded with the front end face of the outer shell;
the periphery of the front flange is provided with a plurality of water outlet holes which can be communicated with the water tank;
the rear end flange comprises a rear inner shell mounting port and a tail gas discharge port which are coaxially arranged in sequence from front to back, the rear inner shell mounting port is coaxially sleeved on the periphery of the rear extension end of the inner shell, the rear end face of the inner shell is in sealing connection with the rear end flange, and the front end face of the rear end flange is welded with the rear end face of the outer shell;
the circumference surface of the rear end flange is provided with a plurality of water inlet holes which can be communicated with the water tank.
2. A rocket engine thrust chamber of dissimilar metal welded red copper-stainless steel evading of claim 1, wherein: the circumferential angle of each water tank and each rib plate is equal.
3. A rocket engine thrust chamber of red copper-stainless steel for avoiding dissimilar metal welding as recited in claim 2, wherein: the number of the water grooves and the rib plates is 20, and the circumferential angles of the water grooves and the rib plates are 9 degrees.
4. A rocket engine thrust chamber of dissimilar metal welded red copper-stainless steel evading of claim 1, wherein: the inner shell comprises a cylindrical combustion chamber section and a Laval nozzle section which are integrally arranged; in the throat of the laval nozzle section, one rib plate of two adjacent rib plates is provided with a throat opening.
5. A rocket engine thrust chamber of dissimilar metal welded red copper-stainless steel as recited in claim 4, wherein: the throat of the inner shell has a thickness of 5.5mm.
6. A rocket engine thrust chamber of dissimilar metal welded red copper-stainless steel evading of claim 1, wherein: the depth of all the water tanks is equal.
7. A rocket engine thrust chamber of dissimilar metal welded red copper-stainless steel as recited in claim 6, wherein: all the water channels were 9.5mm deep.
8. A rocket engine thrust chamber of dissimilar metal welded red copper-stainless steel evading of claim 1, wherein: the sealing device also comprises a front sealing ring and a rear sealing ring;
the front end of each water tank is provided with a front plug, the front end face of the front plug is provided with a front sealing ring groove, a front sealing ring is embedded in the front sealing ring groove, a front sealing convex ring groove is arranged on a front end flange opposite to the front sealing ring groove, and the front sealing convex ring groove can be in sealing fit with the front sealing ring groove embedded with the front sealing ring;
the rear end of each water tank is provided with a rear plug; the rear end face of the rear plug is provided with a rear sealing ring groove, a rear sealing ring is embedded in the rear sealing ring groove, a rear sealing convex ring groove is arranged on a rear end flange opposite to the rear sealing ring groove, and the rear sealing convex ring groove can be in sealing fit with the rear sealing ring groove embedded with the rear sealing ring.
9. A rocket engine thrust chamber of dissimilar metal welded red copper-stainless steel evading of claim 8, wherein: the front sealing ring and the rear sealing ring are both made of asbestos.
10. A rocket engine thrust chamber of dissimilar metal welded red copper-stainless steel evading of claim 1, wherein: a front water collecting cavity is arranged between the front inner shell mounting opening and the front extending end of the inner shell; a rear water collecting cavity is arranged between the rear inner shell mounting opening and the rear extending end of the inner shell.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111268833.2A CN113982786B (en) | 2021-10-29 | 2021-10-29 | Rocket engine thrust chamber of red copper-stainless steel for avoiding dissimilar metal welding |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111268833.2A CN113982786B (en) | 2021-10-29 | 2021-10-29 | Rocket engine thrust chamber of red copper-stainless steel for avoiding dissimilar metal welding |
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| CN113982786A CN113982786A (en) | 2022-01-28 |
| CN113982786B true CN113982786B (en) | 2023-06-06 |
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| CN114876674B (en) * | 2022-07-08 | 2022-11-15 | 太原理工大学 | Water-cooling spray pipe for experimental liquid rocket engine |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6134782A (en) * | 1998-11-30 | 2000-10-24 | United Technologies Corporation | Method of forming a rocket thrust chamber |
| KR20090077248A (en) * | 2008-01-10 | 2009-07-15 | 한국항공우주연구원 | Method for nozzzle of combustor |
| CN106640424A (en) * | 2016-10-26 | 2017-05-10 | 湖北航天技术研究院总体设计所 | Combustion chamber of liquid rocket engine |
| 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 |
| CN112462714A (en) * | 2020-12-01 | 2021-03-09 | 陕西蓝箭航天技术有限公司 | Processing method of spacecraft thrust chamber double-layer structure |
| CN113530718A (en) * | 2021-08-31 | 2021-10-22 | 西安航天动力研究所 | Body module for hot test of rocket engine thrust chamber |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2158840C2 (en) * | 1999-01-21 | 2000-11-10 | Открытое акционерное общество "НПО Энергомаш им. акад. В.П. Глушко" | Housing of liquid-propellant rocket engine chamber |
| US6829884B2 (en) * | 2002-11-19 | 2004-12-14 | The Boeing Company | Rocket engine combustion chamber having multiple conformal throat supports |
| US20060032212A1 (en) * | 2004-08-10 | 2006-02-16 | The Boeing Company | Lightweight rocket engine combustion chamber and associated method |
-
2021
- 2021-10-29 CN CN202111268833.2A patent/CN113982786B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6134782A (en) * | 1998-11-30 | 2000-10-24 | United Technologies Corporation | Method of forming a rocket thrust chamber |
| KR20090077248A (en) * | 2008-01-10 | 2009-07-15 | 한국항공우주연구원 | Method for nozzzle of combustor |
| CN106640424A (en) * | 2016-10-26 | 2017-05-10 | 湖北航天技术研究院总体设计所 | Combustion chamber of liquid rocket engine |
| 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 |
| CN112462714A (en) * | 2020-12-01 | 2021-03-09 | 陕西蓝箭航天技术有限公司 | Processing method of spacecraft thrust chamber double-layer structure |
| CN113530718A (en) * | 2021-08-31 | 2021-10-22 | 西安航天动力研究所 | Body module for hot test of rocket engine thrust chamber |
Non-Patent Citations (1)
| Title |
|---|
| 铜─钢推力室身部扩散钎焊工艺研究;王长寿;宇航材料工艺(第03期);第54-57页 * |
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