CN113982786A - Red copper-stainless steel rocket engine thrust chamber avoiding dissimilar metal welding - Google Patents
Red copper-stainless steel rocket engine thrust chamber avoiding dissimilar metal welding Download PDFInfo
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- CN113982786A CN113982786A CN202111268833.2A CN202111268833A CN113982786A CN 113982786 A CN113982786 A CN 113982786A CN 202111268833 A CN202111268833 A CN 202111268833A CN 113982786 A CN113982786 A CN 113982786A
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- inner shell
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- sealing ring
- end flange
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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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- Engineering & Computer Science (AREA)
- 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 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 extends out from two ends of the outer shell to form a front extending end and a rear extending end; the outer wall surface of the inner shell is circumferentially provided with 20 water tanks, and each water tank is axially arranged along the inner shell; a rib plate is formed between two adjacent water tanks; the front end flange and the rear end flange are made of stainless steel and are respectively welded with the two ends of the shell. The invention adopts the mode of avoiding dissimilar metal welding for assembly, guarantees 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 high energy density of the throat or throat ablation under extreme working conditions in the ignition test process of the rocket engine.
Description
Technical Field
The invention relates to the field of rocket engines, in particular to a red copper-stainless steel rocket engine thrust chamber avoiding dissimilar metal welding.
Background
Aiming at the test of a model rocket engine, thermal protection is needed during the ignition test, so that the inner wall of the thrust chamber is cooled. At present, the common thermal protection methods are two methods as follows:
(1) conventional heat sink cooling
And (3) heat sink cooling, which is the simplest thermal protection means, namely a thicker engine wall surface is selected in the processing process, heat sink cooling is carried out only by depending on the thicker wall surface of the engine during an ignition test, and the whole body of the engine is made of red copper or stainless steel.
The traditional heat sink cooling design is only suitable for the condition that the engine test working condition is low or the test time is short (about 1 second). If the test time is long, the test working condition is high (the energy density of the throat of the model rocket engine is high) or under the extreme working condition (such as high-frequency unstable combustion of the rocket engine), the throat ablation condition is easy to occur in the heat sink cooling design. Simple heat sink cooling has therefore been strongly limited in model rocket engine testing.
(2) Providing cooling channels
The cooling channel is arranged in the thrust chamber structure, the water pump pumps coolant in the liquid tank, the coolant is injected into the cooling channel through the water inlet to carry out convection cooling on the thrust chamber, then the coolant is discharged from the water outlet and returns to the liquid tank, and the thrust chamber is cooled in a reciprocating circulation mode.
The cooling channel can be suitable for the condition with longer test time. But considering thrust chamber structural strength requirement, generally adopt stainless steel material, and steel material's thermal conductivity is relatively poor, is unfavorable for thrust chamber inner wall temperature's reduction. Practical tests show that after the stainless steel is adopted for long-time ignition, the throat still has the ablation problem due to poor heat conductivity of the steel.
If the red copper material is adopted, although the heat conducting property is better, the rigidity of the red copper material is reduced after being heated, and the whole structure is easy to deform.
Disclosure of Invention
The technical problem to be solved by the invention is to provide a rocket engine thrust chamber avoiding dissimilar metal welding of red copper-stainless steel, aiming at the defects of the prior art, the rocket engine thrust chamber avoiding dissimilar metal welding of red copper-stainless steel is assembled by adopting a mode of avoiding dissimilar metal welding, the reliability of the strength of the rocket engine thrust chamber can be effectively improved, the heat conduction performance in the thrust chamber can be considered, and the problem that the throat is high in energy density or ablated under an extreme working condition in the ignition test process of the rocket engine is solved.
In order to solve the technical problems, the invention adopts the technical scheme that:
a rocket engine thrust chamber avoiding dissimilar metal welding of red copper-stainless steel 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 inner shell is coaxial to be inserted and to be established in the shell, and both ends stretch out from the both ends of shell respectively, form preceding tip and the back tip that stretches out.
A plurality of water channels are distributed on the outer wall surface of the inner shell along the circumferential direction, and each water channel is distributed along the axial direction of the inner shell; a rib plate is formed between two adjacent water tanks.
The front end flange and the rear end flange are both made of stainless steel.
The front end flange comprises a propellant injection port and a front inner shell mounting port which are coaxially arranged 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 connected with the front end flange in a sealing mode, and the rear end face of the front end flange is welded with the front end face of the outer shell.
The circumferential surface of the front end 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 opening and a tail gas discharge opening which are sequentially and coaxially arranged from front to back, the rear inner shell mounting opening is coaxially sleeved on the periphery of the rear extending end of the inner shell, the rear end face of the inner shell is hermetically connected 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 circumferential 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 channel and each rib is equal.
The number of the water grooves and the number of the rib plates are 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 part of the Laval nozzle section, one of two adjacent ribbed plates is provided with a throat opening.
The thickness of the throat of the inner shell is 5.5 mm.
The depths of all the water tanks are equal.
The depth of all water tanks is 9.5 mm.
Also included are a front seal ring and a rear seal ring.
The front end of each water tank is provided with a front plug, the front end face of each front plug is provided with a front sealing ring groove, a front sealing ring is embedded in each front sealing ring groove, a front sealing protruding ring groove is arranged on a front end flange right opposite to the front sealing ring groove, and the front sealing protruding 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 bulge ring groove is formed in the rear end flange right opposite to the rear sealing ring groove, and the rear sealing bulge 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 made of asbestos.
A front water collecting cavity is arranged between the mounting opening of the front inner shell and the front extending end of the inner shell; a rear water collecting cavity is arranged between the mounting port of the rear inner shell and the rear extending end of the inner shell.
The invention has the following beneficial effects:
(1) the thrust chamber structure combining the inner shell made of red copper and the outer shell made of stainless steel has good heat-conducting property in the thrust chamber structure and good cooling effect; meanwhile, after heating, the structure can keep certain rigidity and is not deformed.
(2) The test can bear a long-time ignition test of 20s, the throat part is not ablated, meanwhile, the thickness of the throat part can be reduced to 5.5mm, the traditional heat sink cooling needs 21mm, and long-time ignition cannot be realized.
(3) The mode of avoiding dissimilar metal welding assembles, and overall structure intensity is higher, and the reliability further promotes.
(4) Common materials are adopted, the processing technology is simple, and the cost is further saved.
Drawings
Fig. 1 shows an exploded view of the rocket engine thrust chamber of the present invention circumventing dissimilar metal welded red copper-stainless steel.
Fig. 2 shows an assembly diagram of a rocket engine thrust chamber of the present invention circumventing dissimilar metal welding of copper-stainless steel.
Fig. 3 shows a schematic view of the structure of the housing of the present invention.
Fig. 4 shows a schematic structural view of the inner casing of the present invention.
Fig. 5 shows a schematic view of the front end flange according to the present invention.
Fig. 6 shows a schematic view of the construction of the rear end flange according to the invention.
Fig. 7 shows a schematic diagram of the heat dissipation comparison of two metals in the present invention.
Among them are:
10. a housing;
11. half-section; 12. an axial weld face; 13. a front end weld face; 14. a rear end weld face; welding a chamfer;
20. an inner shell; 21. a water tank; 22. a rib plate; 221. a throat opening; 23. front plugging; 24. a front sealing ring groove; 25. then plugging; 26. a rear sealing ring groove;
30. a front end flange;
31. a propellant injection port; 32. a front sealing bulge ring groove; 33. a water outlet hole; 34. a front water collection cavity; 35. a front flange weld face;
40. a rear end flange;
41. a tail gas discharge port; 42. the convex ring groove is sealed; 43. a water inlet hole; 44. a rear water collecting cavity; 45. and welding surface of the rear flange.
Detailed Description
The present 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 is to be understood that the terms "left side", "right side", "upper part", "lower part", etc., indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and that "first", "second", etc., do not represent an important degree of the component parts, and thus are not to be construed as limiting the present invention. The specific dimensions used in the present example are only for illustrating the technical solution and do not limit the scope of protection of the present invention.
As shown in fig. 1 and 2, a rocket engine thrust chamber of red copper-stainless steel avoiding 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-sections 11, and one opposite sides of the two half-sections 11 are axial welding surfaces 12, so that the two half-sections 11 form a complete laval nozzle by welding with the same metal.
The front end face (i.e., the left end face) of the housing is a front end weld face 13, and the rear end face (i.e., the right end face) of the housing is a rear end weld face 14.
Further, the outside of the axial welding surface 12, the end welding surface 13 and the rear end welding surface 14 is preferably provided with a welding chamfer 15 for facilitating welding after assembly.
As shown in fig. 2, the inner shell is made of red copper, and is coaxially inserted into the outer shell, and two ends of the inner shell respectively extend out from two ends of the outer shell 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 channels 21 are circumferentially arranged on the outer wall surface of the inner shell, and each water channel is axially arranged along the inner shell; a rib plate 22 is formed between two adjacent water tanks. The design of floor not only can increase the compressive capacity of inner part, has played the effect of fin simultaneously, increases the area of contact with water, can further promote the radiating efficiency.
The circumferential angle of each trough and each rib is preferably equal. In this embodiment, the number of the water grooves and the ribs are each 20, and the circumferential angles of the water grooves and the ribs are each preferably 9 °.
The depth of all the water tanks is preferably equal, and more preferably 9.5 mm.
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 preferably made of asbestos 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, in which a rear sealing ring preferably made of asbestos is embedded.
Alternatively, the front end and the rear end of each water tank can be arranged in a penetrating way, and at the moment, the front sealing ring groove only needs to be arranged on the front end surface of the inner shell. 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 two adjacent ribs is provided with a throat opening 221.
The arrangement of the throat opening 221 can realize the widening of the water channel flow passage of the throat. During 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 portion of the inner shell is preferably 5.5 mm.
The front end flange and the rear end flange are both made of stainless steel.
As shown in fig. 5, the front end flange includes a propellant injection port 31 and a front inner shell mounting port coaxially arranged from front to back, the front inner shell mounting port is coaxially sleeved on the periphery of the front protruding end of the inner shell, and the rear end surface (i.e. the front flange welding surface 35) of the front inner shell mounting port is welded with the front end surface (i.e. the front end welding surface 13) of the outer shell.
Furthermore, the front end surface of the front protruding end of the inner shell is connected with the front end flange in a sealing mode. In this embodiment, the preferable setting method is as follows: the front end flange opposite to the front sealing ring groove is provided with a front sealing bulge ring groove 32 which can be in sealing fit with the front sealing ring groove embedded with the front sealing ring.
The periphery of preceding inner shell installing port is provided with a plurality of apopore 33 that can communicate with the basin, and the preferred circle mark in figure 5 is 4. Further, the inner diameter of the front inner shell mounting opening is larger than the outer diameter of the front protruding end, so that a front water collecting cavity 34 is formed between the front inner shell mounting opening and the front protruding end of the inner shell. The front water collecting 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 shell mounting opening and a tail gas discharge opening 41 coaxially arranged from front to back, the rear inner shell mounting opening is coaxially sleeved on the periphery of the rear protruding end of the inner shell, and the front end surface (i.e., the rear flange welding surface 45) of the rear inner shell mounting opening is welded to the rear end surface (i.e., the rear end welding surface 14) of the outer shell.
Furthermore, the rear end face of the rear extending end of the inner shell is hermetically connected with the rear end flange. In this embodiment, the preferable setting method is as follows: the rear end flange opposite to the rear sealing ring groove is provided with a rear sealing bulge 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 mounting opening of the rear inner shell is provided with a plurality of water inlet holes 43 which can be communicated with the water tank, and the number of the water inlet holes is preferably 4 as indicated by a circle in figure 6. Further, the inner diameter of the rear inner shell mounting opening is larger than the outer diameter of the rear protruding end, so that a rear water collecting cavity 44 is formed between the rear inner shell mounting opening and the rear protruding end of the inner shell.
Furthermore, 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 manner: the inner shell that will have the coolant liquid channel (also contain the basin) is at first made up with the shell, compresses tightly the back, closes into a whole with the half section spare of symmetry through the welding, installs front and back end flange additional afterwards, all processes preceding sealed protruding annular on the contact surface of inner shell and front and back end flange for realize inside runner with the butt joint of the sealed annular on the inner shell and seal, front and back end flange is sealed mutually with the outer shell both ends after pressing closely with the inner shell, realizes that the outside runner is sealed.
The thrust chamber structure combining the inner shell made of red copper and the outer shell made of stainless steel is adopted, so that the inner part has good heat-conducting property, and the cooling effect is good; meanwhile, after heating, the structure can keep certain rigidity and is not deformed. As can be seen from fig. 7, the heat dissipation efficiency of the two schemes of the dissimilar metal and the same metal is different.
After actual water test, the invention finds that the integral structure has good sealing performance, and shows that the assembly mode provided by the scheme is feasible. And then, carrying out an ignition test, wherein after the long-time ignition test for 20s, the temperature of the water outlet is increased to 46 ℃, the throat part structure is complete, and no obvious ablation occurs. The problem that the temperature of the thrust chamber is too high in the long-time ignition test can be effectively solved by adopting the scheme. Meanwhile, the thickness of the throat part in the scheme can be reduced to 5.5mm, the traditional heat sink cooling needs 21mm, and long-time ignition cannot be realized.
Meanwhile, the invention avoids the assembly by welding dissimilar metals, has higher integral structure strength and further improves the reliability.
Further, as a replacement, the invention can change the welding combination mode of the two parts of the combustion chamber shell, and by using the sealing structure of the front end flange and the rear end flange and the combustion chamber as a reference, the flange surface with the bolt hole is added upwards and downwards at the split part of the two parts, and the welding is replaced by the bolt connection. Meanwhile, bulges and grooves are arranged on the joint end surfaces of the two parts of the shell, and asbestos sealing pads are placed in the grooves to finish sealing.
Although the preferred embodiments of the present invention have been described in detail, the present invention is not limited to the details of the embodiments, and various equivalent modifications can be made within the technical spirit of the present invention, and the scope of the present invention is also within the scope of the present invention.
Claims (10)
1. The utility model provides a avoid dissimilar metal welded red copper-stainless steel rocket engine thrust room which characterized in that: 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 extends out from two ends of the outer shell to form a front extending end and a rear extending end;
a plurality of water channels are distributed on the outer wall surface of the inner shell along the circumferential direction, and each water channel is distributed along the axial direction of the inner shell; a rib plate is 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 injection port and a front inner shell mounting port which are coaxially arranged 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 surface of the inner shell is hermetically connected with the front end flange, and the rear end surface of the front end flange is welded with the front end surface of the outer shell;
a plurality of water outlet holes which can be communicated with the water tank are formed in the circumferential surface of the front end flange;
the rear end flange comprises a rear inner shell mounting opening and a tail gas discharge opening which are coaxially arranged from front to back, the rear inner shell mounting opening is coaxially sleeved on the periphery of the rear extending end of the inner shell, the rear end surface of the inner shell is hermetically connected with the rear end flange, and the front end surface of the rear end flange is welded with the rear end surface of the outer shell;
the circumferential 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 copper-stainless steel evading dissimilar metal welding according to claim 1 wherein: the circumferential angle of each water channel and each rib is equal.
3. A rocket engine thrust chamber of copper-stainless steel evading dissimilar metal welding according to claim 2, characterized in that: the number of the water grooves and the number of the rib plates are 20, and the circumferential angles of the water grooves and the rib plates are 9 degrees.
4. A rocket engine thrust chamber of copper-stainless steel evading dissimilar metal welding according to claim 1 wherein: the inner shell comprises a cylindrical combustion chamber section and a Laval nozzle section which are integrally arranged; in the throat part of the Laval nozzle section, one of two adjacent ribbed plates is provided with a throat opening.
5. A rocket engine thrust chamber of red copper-stainless steel avoiding dissimilar metal welding according to claim 4, characterized in that: the thickness of the throat of the inner shell is 5.5 mm.
6. A rocket engine thrust chamber of copper-stainless steel evading dissimilar metal welding according to claim 1 wherein: the depths of all the water tanks are equal.
7. A rocket engine thrust chamber of red copper-stainless steel avoiding dissimilar metal welding according to claim 6, characterized in that: the depth of all water tanks is 9.5 mm.
8. A rocket engine thrust chamber of copper-stainless steel evading dissimilar metal welding according to claim 1 wherein: the sealing ring 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 surface of each front plug is provided with a front sealing ring groove, a front sealing ring is embedded in each front sealing ring groove, a front sealing bulge ring groove is arranged on a front end flange opposite to the front sealing ring groove, and the front sealing bulge 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 bulge ring groove is formed in the rear end flange right opposite to the rear sealing ring groove, and the rear sealing bulge 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 copper-stainless steel evading dissimilar metal welding according to claim 8, wherein: the front sealing ring and the rear sealing ring are made of asbestos.
10. A rocket engine thrust chamber of copper-stainless steel evading dissimilar metal welding according to claim 1 wherein: a front water collecting cavity is arranged between the mounting opening of the front inner shell and the front extending end of the inner shell; a rear water collecting cavity is arranged between the mounting port of the rear inner shell 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 true CN113982786A (en) | 2022-01-28 |
| CN113982786B CN113982786B (en) | 2023-06-06 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114876674A (en) * | 2022-07-08 | 2022-08-09 | 太原理工大学 | Water-cooling spray pipe for experimental liquid rocket engine |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114876674A (en) * | 2022-07-08 | 2022-08-09 | 太原理工大学 | Water-cooling spray pipe for experimental liquid rocket engine |
| CN114876674B (en) * | 2022-07-08 | 2022-11-15 | 太原理工大学 | Water-cooling spray pipe for experimental liquid rocket engine |
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| Publication number | Publication date |
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| CN113982786B (en) | 2023-06-06 |
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