CN117532131B - Rocket engine combustion chamber and manufacturing method thereof - Google Patents
Rocket engine combustion chamber and manufacturing method thereof Download PDFInfo
- Publication number
- CN117532131B CN117532131B CN202410026202.7A CN202410026202A CN117532131B CN 117532131 B CN117532131 B CN 117532131B CN 202410026202 A CN202410026202 A CN 202410026202A CN 117532131 B CN117532131 B CN 117532131B
- Authority
- CN
- China
- Prior art keywords
- wall
- combustion chamber
- throat
- welding
- section
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 255
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 31
- 238000003466 welding Methods 0.000 claims abstract description 100
- 238000012360 testing method Methods 0.000 claims description 12
- 239000000945 filler Substances 0.000 claims description 9
- 238000009792 diffusion process Methods 0.000 claims description 8
- 238000010894 electron beam technology Methods 0.000 claims description 7
- 239000002826 coolant Substances 0.000 claims description 3
- 239000007788 liquid Substances 0.000 claims description 3
- 238000004140 cleaning Methods 0.000 claims description 2
- 238000012856 packing Methods 0.000 abstract description 15
- 230000015572 biosynthetic process Effects 0.000 abstract 1
- 230000002349 favourable effect Effects 0.000 abstract 1
- 238000000034 method Methods 0.000 description 15
- 230000007547 defect Effects 0.000 description 5
- 210000001503 joint Anatomy 0.000 description 5
- 239000000463 material Substances 0.000 description 5
- 239000002245 particle Substances 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 239000012535 impurity Substances 0.000 description 3
- 230000002035 prolonged effect Effects 0.000 description 3
- 238000005406 washing Methods 0.000 description 3
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 2
- 230000008602 contraction Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 230000000149 penetrating effect Effects 0.000 description 2
- 239000002253 acid Substances 0.000 description 1
- 239000003513 alkali Substances 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 229910052786 argon Inorganic materials 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000001595 contractor effect Effects 0.000 description 1
- 238000005238 degreasing Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000010884 ion-beam technique Methods 0.000 description 1
- JEIPFZHSYJVQDO-UHFFFAOYSA-N iron(III) oxide Inorganic materials O=[Fe]O[Fe]=O JEIPFZHSYJVQDO-UHFFFAOYSA-N 0.000 description 1
- 239000000155 melt Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 239000011819 refractory material Substances 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K15/00—Electron-beam welding or cutting
- B23K15/0006—Electron-beam welding or cutting specially adapted for particular articles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K15/00—Electron-beam welding or cutting
- B23K15/0046—Welding
- B23K15/0053—Seam welding
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/20—Bonding
- B23K26/21—Bonding by welding
- B23K26/24—Seam welding
-
- 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
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/34—Casings; Combustion chambers; Liners thereof
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Optics & Photonics (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Plasma & Fusion (AREA)
- Laser Beam Processing (AREA)
Abstract
The invention provides a rocket engine combustion chamber and a manufacturing method thereof, and relates to the technical field of rocket jet propulsion devices, wherein the manufacturing method of the rocket engine combustion chamber mainly comprises the following steps: assembling the inner wall of the combustion chamber with the throat filling ring in the outer wall of the combustion chamber; and forming a plurality of welding seams in a preset welding mode by utilizing high-energy beam current in a target area on the outer wall of the combustion chamber. Through the embodiment that this application provided, after the combustion chamber outer wall and the combustion chamber inner wall have been assembled, a plurality of welding seams through the welding formation realize that the combustion chamber outer wall is to inboard welding shrink, reduce the internal diameter of combustion chamber outer wall, and then reduce or eliminate the clearance between combustion chamber outer wall and the throat packing ring to apply the throat packing ring and fill the relatively close force of ring and the combustion chamber inner wall to the throat, reduce or eliminate the clearance between throat packing ring and the combustion chamber inner wall, reduce follow-up welded connection's the degree of difficulty, be favorable to improving welding quality.
Description
Technical Field
The invention relates to the technical field of rocket jet propulsion devices, in particular to a rocket engine combustion chamber and a manufacturing method thereof.
Background
The combustion chamber is a device in which fuel or propellant is combusted to generate high-temperature fuel gas, and is combustion equipment made of high-temperature resistant alloy materials. The combustion chamber is an important component of a rocket engine.
The rocket engine combustion chamber comprises a combustion chamber inner wall and a combustion chamber outer wall, after the combustion chamber inner wall and the combustion chamber outer wall are sleeved in the manufacturing rocket engine combustion chamber stage, a gap exists between the throat part of the combustion chamber inner wall and the combustion chamber outer wall, the gap is arranged for ensuring that the combustion chamber inner wall and the combustion chamber outer wall are successfully sleeved in the combustion chamber outer wall, but the gap between the throat part of the combustion chamber inner wall and the combustion chamber outer wall can increase welding difficulty, and welding defects are easily caused in the subsequent combustion chamber inner wall and combustion chamber outer wall welding stage, and the defects can reduce welding quality.
Disclosure of Invention
The application provides a rocket engine combustion chamber and a manufacturing method thereof aiming at the defects of the existing mode, which are used for solving the technical problems that in the prior art, after the combustion chamber inner wall is sleeved with the combustion chamber outer wall, a gap exists between the combustion chamber inner wall and the combustion chamber outer wall, the welding difficulty is increased, welding defects are easily caused in the subsequent welding stage of the combustion chamber inner wall and the combustion chamber outer wall, and the welding quality is reduced due to the defects.
In a first aspect, an embodiment of the present application provides a method for manufacturing a rocket engine combustion chamber, including: assembling a combustor inner wall with a throat packing ring in a combustor outer wall, the throat packing ring being disposed between the combustor inner wall and the combustor outer wall; forming a plurality of welding seams in a preset welding mode by utilizing high-energy beam current in a target area on the outer wall of the combustion chamber so as to reduce gaps between the outer wall of the combustion chamber and the throat filling ring and between the throat filling ring and the inner wall of the combustion chamber; the target area is an area of the combustion chamber outer wall corresponding to the throat packing ring.
As an alternative embodiment, the forming a plurality of welding seams on the target area on the outer wall of the combustion chamber by using high-energy beam in a preset welding mode includes: and welding the outer side of the outer wall of the combustion chamber along the axial direction of the outer wall of the combustion chamber by utilizing electron beams or laser to form the welding seam.
As an optional implementation manner, the forming a plurality of welding seams on the target area on the outer wall of the combustion chamber by using high-energy beam in a preset welding mode further includes: and welding the plurality of welding seams at equal intervals in sequence along the circumferential direction of the outer wall of the combustion chamber.
As an alternative embodiment, the weld seam has a weld depth less than the thickness of the combustion chamber outer wall.
As an alternative embodiment, the assembling the inner wall of the combustion chamber with the throat filling ring into the outer wall of the combustion chamber comprises: loading an inner wall converging section with a throat packing ring into the combustion chamber outer wall such that an outer surface of the throat packing ring is opposite a straight barrel section of the combustion chamber outer wall; the target area is positioned on a straight section of the outer wall of the combustion chamber; the throat filling ring is arranged on the outer side of the throat of the inner wall convergence section in a surrounding mode; loading an inner wall expansion section into the outer wall of the combustion chamber and butting with the inner wall convergence section; the inner wall convergent section and the inner wall divergent section are welded and connected; the inner wall convergent section is higher than the inner wall divergent section, the joint of the inner wall convergent section and the inner wall divergent section is used as a welding position, and the welding position is lower than the throat part of the inner wall convergent section.
As an alternative embodiment, before the inner wall of the combustion chamber with the throat filling ring is assembled in the outer wall of the combustion chamber, the method further comprises: cleaning the surfaces of the throat filling block, the inner wall convergence section and the outer wall of the combustion chamber; and welding a plurality of throat filling blocks on the outer side of the throat of the inner wall convergence section along the throat circumference of the inner wall convergence section.
As an alternative embodiment, the method for manufacturing the rocket engine combustion chamber further comprises: and the inner wall of the combustion chamber and the outer wall of the combustion chamber are connected in a diffusion way to form the rocket engine combustion chamber with complete structure.
As an alternative embodiment, the method for manufacturing the rocket engine combustion chamber further comprises: performance testing of the structurally complete rocket engine combustion chamber obtained after diffusion bonding is performed by at least one of the following modes: detecting the connection strength between the inner wall of the combustion chamber and the outer wall of the combustion chamber through a hydraulic test; detecting the smoothness of a cooling medium flow passage between the inner wall of the combustion chamber and the outer wall of the combustion chamber through a liquid flow test; and detecting the air tightness between the inner wall of the combustion chamber and the outer wall of the combustion chamber through an air tightness test.
In a second aspect, an embodiment of the present application provides a rocket engine combustion chamber, which is manufactured by the rocket engine combustion chamber manufacturing method according to any one of the foregoing embodiments.
The application provides a rocket engine combustion chamber and a manufacturing method thereof, and the technical scheme provided by the embodiment of the application at least brings the following beneficial effects:
after the outer wall and the inner wall of the combustion chamber are assembled, a plurality of welding seams formed by welding the target area through high-energy beam flow are used for realizing inward welding shrinkage of the outer wall of the combustion chamber, reducing the inner diameter of the outer wall of the combustion chamber, reducing or eliminating the gap between the outer wall of the combustion chamber and the throat filling ring, and applying the force relatively close to the throat filling ring and the inner wall of the combustion chamber to the throat filling ring so as to reduce or eliminate the gap between the throat filling ring and the inner wall of the combustion chamber, so that the throat filling ring and the inner wall of the combustion chamber and the outer wall of the combustion chamber and the throat filling ring are attached as much as possible, the difficulty of post welding connection is reduced, and the improvement of welding quality is facilitated.
The welding position of the inner wall convergent section and the inner wall divergent section is positioned below the throat part so as to be far away from the throat part, and the rear (downward) movement of the welding position is realized, so that the butt welding position of the inner wall of the combustion chamber is far away from the throat part, which is a severe working environment, and the service life of the combustion chamber of the rocket engine is further prolonged.
It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the application.
Drawings
The foregoing and/or additional aspects and advantages of the present application will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings, in which:
FIG. 1 is a schematic flow chart of a method for manufacturing a rocket engine combustion chamber according to an embodiment of the present disclosure;
fig. 2 is a schematic structural diagram of a rocket engine combustion chamber according to an embodiment of the present disclosure;
FIG. 3 is a schematic view of the positional relationship between the converging section and the throat of the inner wall of the rocket engine combustion chamber according to the embodiment of the present application;
FIG. 4 is a schematic view of the structure of an inner wall expansion section in a rocket engine combustion chamber according to an embodiment of the present disclosure;
FIG. 5 is a schematic view of the outer wall of a combustion chamber in a rocket engine combustion chamber according to an embodiment of the present disclosure;
FIG. 6 is a schematic view of the positional relationship of the inner wall, the outer wall, the throat packing ring and the weld in a rocket engine combustion chamber according to an embodiment of the present disclosure;
FIG. 7 is a schematic cross-sectional view;
FIG. 8 is a schematic diagram of a specific flow of assembling a combustor inner wall with a throat filling ring into a combustor outer wall in step S1 in a rocket engine combustor manufacturing method according to an embodiment of the present application;
FIG. 9 is a schematic view of the relationship between the inner wall of the combustion chamber and the throat packing ring in a rocket engine combustion chamber according to an embodiment of the present disclosure;
FIG. 10 is a schematic diagram of a rocket engine combustion chamber manufacturing method according to an embodiment of the present application after performing step S11 to install an inner wall converging section with a throat filling ring into an outer wall of the combustion chamber;
FIG. 11 is a schematic flow chart of a method for manufacturing a rocket engine combustion chamber according to another embodiment of the present disclosure;
fig. 12 is a schematic flow chart of a method for manufacturing a rocket engine combustion chamber according to still another embodiment of the present disclosure.
Reference numerals and corresponding description:
1: a throat packing ring; 11: a throat filler;
2: the inner wall of the combustion chamber; 21: an inner wall converging section; 22: an inner wall expansion section; 23: a throat;
3: an outer wall of the combustion chamber; 31: an outer wall converging section; 32: an outer wall expansion section; 33: a straight barrel section;
4: and (3) welding seams.
Detailed Description
Examples of embodiments of the present application are illustrated in the accompanying drawings, in which like or similar reference numerals refer to like or similar elements or elements having like or similar functionality throughout. Further, if detailed description of the known technology is not necessary for the illustrated features of the present application, it will be omitted. The embodiments described below by referring to the drawings are exemplary only for the purpose of illustrating the present application and are not to be construed as limiting the present application.
As used herein, the singular forms "a", "an", "the" and "the" are intended to include the plural forms as well, unless expressly stated otherwise, as understood by those skilled in the art. It will be further understood that the terms "comprises" and/or "comprising," when used in this specification, specify the presence of stated features, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, steps, operations, elements, components, and/or groups thereof. The term "and/or" as used herein includes all or any element and all combination of one or more of the associated listed items.
The terms referred to in this application are first introduced and explained:
the high energy beam may be composed of a single electron, photon, ion, or a combination of two or more particles. The high-energy beam can be applied to the welding field. The high energy beam welding is to melt the welded material to form the weld joint 4 by using the energy carried by the high energy beam particles as a heat source. According to the different particles carrying energy, the welding method is divided into laser beam, electron beam and ion beam welding, and is characterized by concentrated energy, high energy density, large penetration, small width, narrow heat affected zone, high welding precision, capability of welding very thin parts and thicker parts. Good effect is obtained for welding refractory materials, active metals and parts with high quality.
The inventor of the present application considered that since the middle lower portion of the outer wall 3 of the combustion chamber has a throat portion recessed inward, which results in that the inner wall 2 of the combustion chamber cannot be directly fitted into the outer wall 3 of the combustion chamber, in the present embodiment, the inventor improves the structure of the outer wall 3 of the combustion chamber, and adds a throat filling ring 1 which is fitted over the outer side of the throat portion 23 of the inner wall 2 of the combustion chamber, and after the inner wall 2 of the combustion chamber and the outer wall 3 of the combustion chamber are assembled, there is a gap between the outer wall 3 of the combustion chamber and the throat filling ring 1, and between the outer wall 3 of the combustion chamber and the inner wall 2 of the combustion chamber, which results in an increase in the difficulty of subsequent welding.
The application provides a rocket engine combustion chamber and a manufacturing method thereof, which aim to solve the technical problems in the prior art.
The following describes the technical solutions of the present application and how the technical solutions of the present application solve the above technical problems in detail with specific embodiments.
As shown in fig. 1, an embodiment of the present application provides a method for manufacturing a rocket engine combustion chamber, which mainly includes steps S1-S2:
step S1: the inner wall 2 of the combustion chamber with the throat filling ring 1 is fitted into the outer wall 3 of the combustion chamber.
Step S2: a plurality of welds 4 are formed in a preset welding manner at a target area on the combustion chamber outer wall 3 using a high energy beam.
As shown in fig. 2 to 5, in the present embodiment, the combustion chamber inner wall 2 and the combustion chamber outer wall 3 each have a substantially cylindrical structure. The combustion chamber inner wall 2 has a hollow structure penetrating in the axial direction. The combustion chamber inner wall 2 is vertically arranged, and the combustion chamber is sequentially connected with an inner wall convergence section 21 and an inner wall expansion section 22 from top to bottom; the lower part of the inner wall convergence section 21 is a throat part 23, and the throat part 23 is a section structure with smaller inner diameter of the inner wall 2 of the combustion chamber, and the throat part 23 is inwards concave to the rest part of the inner wall 2 of the combustion chamber. The throat filling ring 1 is of a circular ring structure, the inner side of the throat filling ring 1 is provided with an inward convex part structure which is matched with the concave part on the outer side of the throat 23, and the convex part structure is filled in the concave part of the throat 23 along the circumferential direction of the throat 23. The throat packing ring 1 has a rectangular cross-sectional shape in the vertical direction.
The combustion chamber outer wall 3 has a hollow structure penetrating in the axial direction. The combustion chamber outer wall 3 is vertically arranged, and the combustion chamber is sequentially connected with an outer wall convergence section 31 and an outer wall expansion section 32 from top to bottom; the lower part of the outer wall convergence section 31 is a straight section 33, the straight section 33 is of a section structure with smaller inner diameter of the outer wall 3 of the combustion chamber, and the straight section 33 is inwards concave in the rest part of the outer wall 3 of the combustion chamber.
The inner wall 2 of the combustion chamber with the throat filling ring 1 is assembled in the outer wall 3 of the combustion chamber, the outer wall convergence section 31 is opposite to the inner wall convergence section 21, the outer wall expansion section 32 is opposite to the inner wall expansion section 22, wherein the throat filling ring 1 is arranged between the inner wall 2 of the combustion chamber and the outer wall 3 of the combustion chamber, the throat filling ring 1 is opposite to the straight barrel section 33, and the outer side surface of the throat filling ring 1 is matched with the inner surface of the straight barrel section 33 to be a circular surface. Compared with the prior art, only a gap exists between the outer wall 3 of the combustion chamber and the inner wall 2 of the combustion chamber, and in the embodiment of the application, the gap exists between the outer wall 3 of the combustion chamber and the throat filling ring 1, so that the gap is more and larger.
According to the rocket engine combustion chamber manufacturing method provided by the embodiment of the application, after the combustion chamber outer wall 3 and the combustion chamber inner wall 2 are assembled, the high-energy beam welding equipment is utilized to weld a plurality of welding seams 4 formed in the corresponding area (straight barrel section 33) of the combustion chamber outer wall 3 and the throat filling ring 1, so that the combustion chamber outer wall 3 is shrunk inwards in a welding mode, the inner diameter of the combustion chamber outer wall 3 is reduced, the gap between the combustion chamber outer wall 3 and the throat filling ring 1 is reduced or eliminated, the throat filling ring 1 and the combustion chamber inner wall 2 are applied to the throat filling ring 1 by applying the relatively close force between the throat filling ring 1 and the combustion chamber inner wall 2, the throat filling ring 1 and the combustion chamber outer wall 3 are attached to each other as much as possible, namely, the difficulty of subsequent welding connection is reduced by reducing or eliminating the local double-layer gap, and the welding quality is improved.
As an alternative embodiment, forming the plurality of weld joints 4 in the target area on the outer wall 3 of the combustion chamber by using the high energy beam in the aforementioned step S2 in a preset welding manner includes:
the weld 4 is formed by welding outside the combustion chamber outer wall 3 in the axial direction of the combustion chamber outer wall 3 using an electron beam or a laser.
As shown in fig. 6, according to the foregoing embodiment, in the present embodiment, the combustion chamber outer wall 3 is in a vertically arranged state, and the combustion chamber outer wall 3 is also in a vertical direction in the axial direction. The electron beam is used for welding the outer wall 3 of the combustion chamber along the vertical direction, the electron beam melts the material of the outer wall 3 of the combustion chamber, and before the melted material is cooled and shaped to form a welding line 4, the inner diameter of the outer wall 3 of the combustion chamber is reduced due to the fact that the welding line is melted to form a 'missing' space, and the parts 3 of the outer wall 3 of the combustion chamber on two opposite sides of the welding line shrink along the circumferential welding part of the straight barrel section 33.
As an alternative embodiment, forming the plurality of welds 4 in a preset welding manner using the high energy beam at the target area on the combustion chamber outer wall 3 includes: the weld 4 is formed by welding outside the combustion chamber outer wall 3 in the axial direction of the combustion chamber outer wall 3 using an electron beam or a laser.
As shown in fig. 6, in this embodiment, based on the foregoing embodiment, the circumferential direction of the outer wall 3 of the combustion chamber and the circumferential direction of the straight tube section 33 are the same, by adopting the above technical scheme, the welding seams 4 formed in sequence in the circumferential direction of the outer wall 3 of the combustion chamber realize that the outer wall 3 of the combustion chamber contracts in the circumferential direction, and after one round of welding, a plurality of welding seams 4 distributed radially along the straight tube section 33 are formed, so that the "dead-angle-free overall" contraction of the outer wall 3 of the combustion chamber is realized, and even contraction of the outer wall 3 of the combustion chamber can be realized by even interval welding, so as to further improve the welding contraction effect.
As an alternative embodiment, the weld seam 4 has a weld depth which is smaller than the thickness of the combustion chamber outer wall 3.
As shown in fig. 7, in the present embodiment, the welding of the outer wall 3 of the combustion chamber by using the high-energy beam cannot be completed, if the welding is completed, the formed fine impurity particles may adhere to the post-repair filling ring, affect the welding of the outer wall and the throat filling ring, and may adhere to the inner wall 2 of the combustion chamber, enter between the inner wall 2 of the combustion chamber and the throat filling ring 1, and reduce the diffusion connection effect of the subsequent throat filling ring 1 and the inner wall 2 of the combustion chamber, and reduce the connection strength of the outer wall 3 of the combustion chamber and the inner wall 2 of the combustion chamber and the integrity of the combustion chamber of the rocket engine.
As an alternative embodiment, as shown in fig. 8, the assembling of the inner wall 2 of the combustion chamber with the throat-filling ring 1 in the outer wall 3 of the combustion chamber in the aforementioned step S1 comprises:
step S11: an inner wall converging section 21 with a throat packing ring 1 is fitted into the combustion chamber outer wall 3.
Step S12: the inner wall expansion section 22 is fitted into the combustion chamber outer wall 3 and interfaces with the inner wall convergence section 21.
Step S13: the inner wall convergent section 21 and the inner wall divergent section 22 are welded together.
As shown in fig. 9-10, in the present embodiment, the combustion chamber outer wall 3 includes an upper opening and a lower opening, and the inner wall converging section 21 with the throat-filling ring 1 extends downward from the upper opening into the combustion chamber outer wall 3 such that the outer surface of the throat-filling ring 1 is opposed to the straight cylindrical section 33 of the combustion chamber outer wall 3; the aforementioned target zone is located on the straight section 33 of the combustion chamber outer wall 3, more specifically on the outside of the straight section 33; the throat filling ring 1 is arranged on the outer side of the throat 23 of the inner wall convergence section 21 in a surrounding manner; after the inner wall converging section 21 with the throat filling ring 1 is assembled, the inner wall diverging section 22 is fitted into the combustion chamber outer wall 3 from the lower opening of the combustion chamber outer wall 3. The inner wall convergence section 21 is higher than the inner wall expansion section 22, the bottom end of the inner wall convergence section 21 is in butt joint with the top end of the inner wall expansion section 22, and the butt joint of the inner wall convergence section 21 and the inner wall expansion section 22 is used as a subsequent welding position, for example, the welding can be performed in an argon arc welding mode, so that an annular welding seam is formed between the bottom end of the inner wall convergence section 21 and the top end of the inner wall expansion section 22; the weld location is lower than the throat 23 of the converging section 21 of the inner wall to achieve a weld remote from the throat 23.
The throat 23 of the inner wall 2 of the combustion chamber is the most severe place in the rocket engine combustion chamber during operation, and the temperature, pressure and gas flow rate are high. In the prior art, when the combustor inner wall 2 is assembled along the throat 23 in a sectioning way, the welding position of the inner wall convergent section 21 and the inner wall divergent section 22 is positioned at the throat 23, and the welding structure is positioned at the position where the working environment of the combustor is worst, so that the overall strength of the combustor inner wall 2 can be reduced, the combustor inner wall 2 is easy to damage, and the operation of the rocket engine combustor is not facilitated. In the embodiment of the application, the welding position (butt joint position) of the inner wall convergence section 21 and the inner wall expansion section 22 is located below the throat 23, so as to be away from the throat 23, and realize the back (or lower) movement of the welding position, so that the butt joint welding position of the inner wall 2 of the combustion chamber is away from the severe working environment of the throat 23, the working environment of the welding position is improved, the welding position of the inner wall 2 of the combustion chamber is prevented from being damaged due to the severe working environment, and the service life of the inner wall 2 of the combustion chamber is further prolonged.
In addition, in the prior art, the bottom end of the inner wall convergence section 21 can be hard-plugged into the outer wall 3 of the combustion chamber by heating the throat 23 and by utilizing the curvature of the throat 23, and the welding position can be moved backwards (downwards) by a few tenths of a millimeter and is very limited due to the limitation of materials and structural safety, while the technical scheme can be moved backwards (downwards) by 10 millimeters to 20 millimeters or even more than 100 millimeters, so that the working environment of the welding position is greatly improved. Where "rear" in "rear (or downward) movement" is a reference gas flowing direction, and "downward" is a reference direction in a state where the inner wall convergent section 21 is higher than the inner wall divergent section 22.
Parameters such as depth, length, number, interval distance, energy of high-energy beam and the like of the welding seam 4 in the embodiment of the application can be obtained through a large number of experiments.
As an alternative embodiment, as shown in fig. 11, the foregoing step S1 further includes steps S100-S200 before assembling the inner wall 2 of the combustion chamber with the throat-filling ring 1 in the outer wall 3 of the combustion chamber:
step S100: the surfaces of the throat packing block 11, the inner wall converging section 21 and the outer wall 3 of the combustion chamber are cleaned.
Step S200: a plurality of throat fillers 11 are welded circumferentially along the throat 23 of the inner wall convergent section 21 outside the throat 23 of the inner wall convergent section 21.
Based on the foregoing embodiment, in this embodiment, the throat filler 11 is a subunit constituting the throat filler ring 1, and one side of the throat filler 11 is connected to the combustion chamber inner wall 2, and the opposite side is connected to the combustion chamber outer wall 3. The surfaces of both the throat packing block 11 and the inner wall convergence section 21 are cleaned, such as alkali washing degreasing, acid washing rust removal and clear water washing, to remove impurities on the surfaces, preventing the impurities from reducing the connection strength of the subsequent diffusion connection. The plurality of throat filler blocks 11 are welded circumferentially along the throat 23 of the inner wall converging section 21 (this welding is simply a location to facilitate loading into the outer wall 3 of the combustion chamber, this strength is not an indicator of ensuring the performance of the combustion chamber, and eventually the inner wall 2 of the combustion chamber and the throat filler ring 1 are integrally joined by a diffusion connection) to form an annular throat filler ring 1 outside the throat 23 of the inner wall converging section 21.
As shown in fig. 12, as an alternative embodiment, the rocket engine combustion chamber manufacturing method further includes step S3:
diffusion connects the inner combustion chamber wall 2 and the outer combustion chamber wall 3.
By adopting the scheme, the stable connection between the inner wall 2 and the outer wall 3 of the combustion chamber can be realized, and the rocket engine combustion chamber with complete structure is formed.
As an alternative embodiment, the method for manufacturing the rocket engine combustion chamber further comprises:
performance testing of the diffusion-bonded, structurally complete rocket engine combustion chamber is performed by at least one of the following means:
detecting the connection strength between the inner wall 2 and the outer wall 3 of the combustion chamber through a hydraulic test;
detecting the flow channel smoothness of a cooling medium between the inner wall 2 and the outer wall 3 of the combustion chamber through a liquid flow test;
the air tightness between the inner wall 2 and the outer wall 3 of the combustion chamber was checked by an air tightness test.
By adopting the scheme, the performance verification of the rocket engine combustion chamber with complete structure is realized.
Based on the same inventive concept, the embodiment of the application provides a rocket engine combustion chamber, which is manufactured by the rocket engine combustion chamber manufacturing method in any one of the previous embodiments.
By applying the embodiment of the application, at least the following beneficial effects can be realized:
after the outer wall 3 and the inner wall 2 of the combustion chamber are assembled, the high-energy beam welding equipment is utilized to weld a plurality of welding seams 4 formed in the corresponding area (straight barrel section 33) of the outer wall 3 and the throat filling ring 1 of the combustion chamber so as to realize inward welding shrinkage of the outer wall 3 of the combustion chamber, reduce or eliminate the inner diameter of the outer wall 3 of the combustion chamber, reduce or eliminate the gap between the outer wall 3 of the combustion chamber and the throat filling ring 1, and apply the relatively close force between the throat filling ring 1 and the inner wall 2 of the combustion chamber to the throat filling ring 1 so as to reduce or eliminate the gap between the throat filling ring 1 and the inner wall 2 of the combustion chamber, and the throat filling ring 1 and the outer wall 3 of the combustion chamber as much as possible, namely, reduce the difficulty of subsequent welding connection by reducing or eliminating the partial double-layer gap, thereby being beneficial to improving the welding quality.
The welding position of the inner wall convergence section 21 and the inner wall expansion section 22 is located below the throat 23 so as to be far away from the throat 23, and the rear (downward) movement of the welding position is realized, so that the butt welding position of the inner wall 2 of the combustion chamber is far away from the throat 23, which is a severe working environment, and the service life of the combustion chamber of the rocket engine is further prolonged.
Those of skill in the art will appreciate that the various operations, methods, steps in the flow, actions, schemes, and alternatives discussed in the present application may be alternated, altered, combined, or eliminated. Further, other steps, means, or steps in a process having various operations, methods, or procedures discussed in this application may be alternated, altered, rearranged, split, combined, or eliminated. Further, steps, measures, schemes in the prior art with various operations, methods, flows disclosed in the present application may also be alternated, altered, rearranged, decomposed, combined, or deleted.
In the description of the present application, it should be understood that the terms "upper," "lower," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate an orientation or a positional relationship based on that shown in the drawings, merely for convenience of description and to simplify the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present application.
The terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature. In the description of the present application, unless otherwise indicated, the meaning of "a plurality" is two or more.
In the description of the present application, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the terms in this application will be understood by those of ordinary skill in the art in a specific context.
In the description of the present specification, a particular feature, structure, material, or characteristic may be combined in any suitable manner in one or more embodiments or examples.
It should be understood that, although the steps in the flowcharts of the figures are shown in order as indicated by the arrows, these steps are not necessarily performed in order as indicated by the arrows. The steps are not strictly limited in order and may be performed in other orders, unless explicitly stated herein. Moreover, at least some of the steps in the flowcharts of the figures may include a plurality of sub-steps or stages that are not necessarily performed at the same time, but may be performed at different times, the order of their execution not necessarily being sequential, but may be performed in turn or alternately with other steps or at least a portion of the other steps or stages.
Claims (8)
1. A method of manufacturing a rocket engine combustion chamber, comprising:
assembling a combustion chamber inner wall (2) with a throat filling ring (1) in a combustion chamber outer wall (3), wherein the throat filling ring (1) is arranged between the combustion chamber inner wall (2) and the combustion chamber outer wall (3);
forming a plurality of welding seams (4) on a target area on the outer wall (3) of the combustion chamber in a preset welding mode by utilizing high-energy beam so as to reduce gaps between the outer wall (3) of the combustion chamber and the throat filling ring (1) and gaps between the throat filling ring (1) and the inner wall (2) of the combustion chamber; the target area is an area of the outer wall (3) of the combustion chamber corresponding to the throat filling ring (1);
the assembly of the inner wall (2) of the combustion chamber with the throat filling ring (1) in the outer wall (3) of the combustion chamber comprises the following steps:
loading an inner wall converging section (21) with a throat filling ring (1) into the combustion chamber outer wall (3) such that an outer surface of the throat filling ring (1) is opposite to a straight barrel section (33) of the combustion chamber outer wall (3); the target area is located on a straight section (33) of the combustion chamber outer wall (3); the throat filling ring (1) is arranged on the outer side of the throat (23) of the inner wall convergence section (21) in a surrounding mode;
loading an inner wall expansion section (22) into the combustion chamber outer wall (3) and interfacing with the inner wall convergence section (21);
-welding the inner wall convergent section (21) and the inner wall divergent section (22);
wherein the inner wall convergent section (21) is higher than the inner wall divergent section (22), the junction of the inner wall convergent section (21) and the inner wall divergent section (22) is used as a welding position, and the welding position is lower than the throat (23) of the inner wall convergent section (21).
2. A method of manufacturing a rocket engine combustion chamber according to claim 1, wherein the forming of a plurality of welds (4) on a target area on the combustion chamber outer wall (3) by means of high energy beams in a predetermined welding manner comprises:
and forming the welding seam (4) by utilizing electron beams or laser to weld along the axial direction of the outer wall (3) of the combustion chamber outside the outer wall (3) of the combustion chamber.
3. A method of manufacturing a rocket engine combustion chamber according to claim 2, wherein the forming of a plurality of welds (4) on the target area on the combustion chamber outer wall (3) by means of high energy beam in a predetermined welding manner further comprises:
and welding the plurality of welding seams (4) at equal intervals in sequence along the circumferential direction of the outer wall (3) of the combustion chamber.
4. A rocket engine combustion chamber production method according to any one of claims 1-3, wherein the weld seam (4) has a weld depth less than the thickness of the combustion chamber outer wall (3).
5. A rocket engine combustion chamber manufacturing method according to claim 1, wherein before assembling the inner combustion chamber wall (2) with the throat filling ring (1) in the outer combustion chamber wall (3), further comprises:
cleaning the surfaces of the throat filling block (11), the inner wall convergence section (21) and the outer wall (3) of the combustion chamber;
a plurality of throat fillers (11) are welded outside the throat (23) of the inner wall convergence section (21) along the throat (23) of the inner wall convergence section (21) in the circumferential direction.
6. A method of manufacturing a rocket engine combustion chamber as recited in claim 1, further comprising:
and the inner wall (2) and the outer wall (3) of the combustion chamber are connected in a diffusion way to form the rocket engine combustion chamber with complete structure.
7. A method of manufacturing a rocket engine combustion chamber as recited in claim 6, further comprising:
performance testing of the structurally complete rocket engine combustion chamber obtained after diffusion bonding is performed by at least one of the following modes:
detecting the connection strength between the inner wall (2) and the outer wall (3) of the combustion chamber through a hydraulic test;
detecting the flow channel smoothness of a cooling medium between the inner wall (2) and the outer wall (3) of the combustion chamber through a liquid flow test;
and detecting the air tightness between the inner wall (2) of the combustion chamber and the outer wall (3) of the combustion chamber through an air tightness test.
8. A rocket engine combustion chamber produced by the rocket engine combustion chamber production method of any one of claims 1-7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410026202.7A CN117532131B (en) | 2024-01-09 | 2024-01-09 | Rocket engine combustion chamber and manufacturing method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410026202.7A CN117532131B (en) | 2024-01-09 | 2024-01-09 | Rocket engine combustion chamber and manufacturing method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN117532131A CN117532131A (en) | 2024-02-09 |
| CN117532131B true CN117532131B (en) | 2024-03-26 |
Family
ID=89792232
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202410026202.7A Active CN117532131B (en) | 2024-01-09 | 2024-01-09 | Rocket engine combustion chamber and manufacturing method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117532131B (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1118365A (en) * | 1966-07-29 | 1968-07-03 | Thiokol Chemical Corp | Variable thrust rocket motor |
| US4434614A (en) * | 1981-04-13 | 1984-03-06 | George Gill | Combustion chamber in a rocket propulsion system with multiple divergent portion |
| CN111997785A (en) * | 2020-07-17 | 2020-11-27 | 沈阳航天新光集团有限公司 | Rocket engine combustion chamber with regenerative cooling structure |
| CN112065606A (en) * | 2020-09-23 | 2020-12-11 | 航天科工火箭技术有限公司 | Outer wall of combustion chamber of liquid rocket engine and assembly process thereof |
| CN113153574A (en) * | 2021-04-22 | 2021-07-23 | 北京航天动力研究所 | Reusable quick-connection sandwich type combustion chamber |
| CN113915029A (en) * | 2021-12-14 | 2022-01-11 | 星河动力(北京)空间科技有限公司 | Test device for nozzle throat lining of rocket engine |
| CN114991998A (en) * | 2022-04-28 | 2022-09-02 | 北京航天动力研究所 | Diffusion welding body part structure of sectional type liquid rocket engine thrust chamber and welding method |
| CN115740965A (en) * | 2022-11-01 | 2023-03-07 | 北京智创联合科技股份有限公司 | Method for manufacturing rocket engine combustion chamber with integral structure |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6688100B1 (en) * | 2002-07-16 | 2004-02-10 | The Boeing Company | Combustion chamber having a multiple-piece liner and associated assembly method |
-
2024
- 2024-01-09 CN CN202410026202.7A patent/CN117532131B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1118365A (en) * | 1966-07-29 | 1968-07-03 | Thiokol Chemical Corp | Variable thrust rocket motor |
| US4434614A (en) * | 1981-04-13 | 1984-03-06 | George Gill | Combustion chamber in a rocket propulsion system with multiple divergent portion |
| CN111997785A (en) * | 2020-07-17 | 2020-11-27 | 沈阳航天新光集团有限公司 | Rocket engine combustion chamber with regenerative cooling structure |
| CN112065606A (en) * | 2020-09-23 | 2020-12-11 | 航天科工火箭技术有限公司 | Outer wall of combustion chamber of liquid rocket engine and assembly process thereof |
| CN113153574A (en) * | 2021-04-22 | 2021-07-23 | 北京航天动力研究所 | Reusable quick-connection sandwich type combustion chamber |
| CN113915029A (en) * | 2021-12-14 | 2022-01-11 | 星河动力(北京)空间科技有限公司 | Test device for nozzle throat lining of rocket engine |
| CN114991998A (en) * | 2022-04-28 | 2022-09-02 | 北京航天动力研究所 | Diffusion welding body part structure of sectional type liquid rocket engine thrust chamber and welding method |
| CN115740965A (en) * | 2022-11-01 | 2023-03-07 | 北京智创联合科技股份有限公司 | Method for manufacturing rocket engine combustion chamber with integral structure |
Also Published As
| Publication number | Publication date |
|---|---|
| CN117532131A (en) | 2024-02-09 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| RU2488470C2 (en) | Method of connecting tube plates and tube in making heat exchangers | |
| US6107596A (en) | Method for producing a welded-brazed combustion chamber | |
| US6945032B2 (en) | Method for manufacturing outlet nozzles for rocket engines | |
| US4063062A (en) | Electron beam welding technique for joining two workpieces together | |
| JP2004306084A (en) | Composite welding method of laser welding and arc welding | |
| US10603740B2 (en) | Method of joining by electron beam or laser welding a turbocharger turbine wheel to a shaft; corresponding turbocharger turbine wheel | |
| CN109079322A (en) | The engine jet pipe preparation method of space launch vehicle | |
| JP2006289500A (en) | Weld prep joint for electron beam or laser welding | |
| EP0758283B1 (en) | Fabrication of tubular wall thrust chambers for rocket engines using laser powder injection | |
| US20120074203A1 (en) | Enhanced welding device | |
| WO2008010748A1 (en) | Method for manufacturing a wall structure | |
| EP1484496B1 (en) | Rocket engine tubular combustion chamber with single piece jacket | |
| CN117532131B (en) | Rocket engine combustion chamber and manufacturing method thereof | |
| WO1995029785A9 (en) | Fabrication of tubular wall thrust chambers for rocket engines using laser powder injection | |
| Gradl et al. | Bimetallic Channel Wall Nozzle Development and Hot-fire Testing using Additively Manufactured Laser Wire Direct Closeout Technology | |
| CN107598373B (en) | A kind of driving motor sealing drum laser welding manufacturing method | |
| RU2158668C2 (en) | Welded joint forming method | |
| CN111347163A (en) | Y-shaped joint laser-TIG composite welding method | |
| CN114412667B (en) | Connecting system for engine combustion chamber and jet pipe extension section and processing method thereof | |
| RU2456146C1 (en) | Method of producing complex combined axially symmetric welded structures | |
| CN112846461B (en) | Welding method of polygonal structural member | |
| CN114248029A (en) | Method for manufacturing nozzle of combustion chamber of gas turbine | |
| CN110711938B (en) | Laser welding method for silencer and cylinder cover | |
| RU2668648C2 (en) | Method of electron beam welding | |
| CN210770630U (en) | Be applied to bellows subassembly welded structure of bellows stop valve |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |