CN114713959B - Double-sided forming welding joint of aero-engine cylinder assembly and forming method thereof - Google Patents
Double-sided forming welding joint of aero-engine cylinder assembly and forming method thereof Download PDFInfo
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- CN114713959B CN114713959B CN202210412097.1A CN202210412097A CN114713959B CN 114713959 B CN114713959 B CN 114713959B CN 202210412097 A CN202210412097 A CN 202210412097A CN 114713959 B CN114713959 B CN 114713959B
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- short pipe
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- 238000003466 welding Methods 0.000 title claims abstract description 88
- 238000000034 method Methods 0.000 title claims abstract description 32
- 238000003860 storage Methods 0.000 claims abstract description 15
- 238000001514 detection method Methods 0.000 claims abstract description 13
- 238000010894 electron beam technology Methods 0.000 claims abstract description 11
- 239000000758 substrate Substances 0.000 claims abstract description 7
- 230000035515 penetration Effects 0.000 claims abstract description 6
- 238000007781 pre-processing Methods 0.000 claims abstract description 3
- 238000004140 cleaning Methods 0.000 claims description 9
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 claims description 6
- 238000000465 moulding Methods 0.000 claims description 5
- 230000004907 flux Effects 0.000 claims description 2
- 238000007493 shaping process Methods 0.000 claims 1
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000007598 dipping method Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 230000000149 penetrating effect Effects 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
-
- 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
- B23K15/06—Electron-beam welding or cutting within a vacuum chamber
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Welding Or Cutting Using Electron Beams (AREA)
Abstract
The invention belongs to the field of electron beam welding, and relates to a forming method of a double-sided formed welding joint of an aero-engine cylinder assembly, which comprises the following steps: s1, removing a part of an original substrate of a cylinder body, prefabricating a welding splash storage groove, and enabling one side of the welding splash storage groove to extend out of a welding seam to be welded; s2, prefabricating a boss on the cylinder; s3, processing a half arc-shaped groove at the root of an original welding line of the cylinder body, processing the other half arc-shaped groove at the root of the original welding line of the switching short pipe, and forming a complete detection groove by the two half arc-shaped grooves; s4, preprocessing the cylinder and the to-be-welded area of the switching short pipe; s5, assembling the simple body and the switching short pipe; and S6, vacuumizing the electron beam welding machine, and welding. The problem of stress concentration in the welding of parts by adopting a non-penetration welding process method is solved.
Description
Technical Field
The invention belongs to the field of electron beam welding, and relates to a double-sided forming welding joint of an aero-engine cylinder assembly and a forming method thereof.
Background
The certain aeroengine cylinder assembly is formed by adopting an electron beam welding process to weld the part cylinder 1 and the switching short pipe 2 through electron beams. The original welding structure is a butt joint with a substrate, and as shown in fig. 1, the welding of parts is realized by adopting a non-penetration welding process method. Because the welded substrate cannot be processed, an unfused gap is easy to exist at the joint of the substrate and the junction pipe, so that stress concentration is caused, and cracks can be generated when the stress concentration is serious.
Disclosure of Invention
The invention aims to provide a double-sided forming welding joint of an aero-engine cylinder assembly and a forming method thereof, which solve the problem of stress concentration in welding parts by adopting a non-penetration welding process.
The invention is realized by the following technical scheme:
the molding method of the double-sided formed welding joint of the aircraft engine barrel assembly comprises a barrel and a switching short pipe, and the molding method comprises the following steps:
s1, removing a part of an original substrate of a cylinder body, prefabricating a welding splash storage groove, and enabling one side of the welding splash storage groove to extend out of a welding seam to be welded;
S2, prefabricating a boss on the cylinder;
S3, processing a half arc-shaped groove at the root of an original welding line of the cylinder body, processing the other half arc-shaped groove at the root of the original welding line of the switching short pipe, and forming a complete detection groove by the two half arc-shaped grooves;
S4, preprocessing the cylinder and the to-be-welded area of the switching short pipe;
s5, assembling the simple body and the switching short pipe;
and S6, vacuumizing the electron beam welding machine, and welding.
Further, S1 is specifically: and cleaning the to-be-welded areas of the cylinder and the switching short pipe, and wiping and cleaning the to-be-welded areas by using acetone after cleaning.
Further, in S6, the vacuum degree of the vacuum chamber is required to be 5x10 -4 mbar or less.
Further, in S6, the welding specifically includes: and carrying out penetration welding on the to-be-welded seam between the cylinder body and the switching short pipe, forming on the front and back surfaces of the seam, and filling the detection groove with welding flux to form the residual height of the root.
Further, in S5, the assembling of the cylinder and the adapting short pipe is specifically: the outer circular surface of the boss is in interference fit with the inner circle of the switching short pipe; and then the assembled cylinder and the switching short pipe are mounted on a turntable of a vacuum electron beam welding machine.
In S2, after the boss is prefabricated, an air exhaust groove is opened in the boss, and the air exhaust groove is communicated with the welding spatter storage groove.
Further, after the welding is completed, the vacuum chamber is inflated again while waiting for at least 2 minutes.
Further, one side of the welding spatter receiving groove extending to the outside of the to-be-welded position is 1mm away from the to-be-welded position, and the other side of the welding spatter receiving groove is 3.5mm away from the to-be-welded position.
The invention also discloses a double-sided formed welding joint of the aero-engine cylinder assembly prepared based on the forming method.
Further, the cross-sectional shape of the welding spatter receiving groove is a combination of a rectangular groove and a fan shape.
Compared with the prior art, the invention has the following beneficial technical effects:
the invention discloses a double-sided forming welding joint of an aeroengine cylinder component and a forming method thereof. Meanwhile, the welding spatter can be stored, and the detection groove is beneficial to nondestructive detection and assessment of the welding seam.
Further, after prefabricating the boss, open the exhaust groove on the boss, the exhaust groove link up with welding and splash the storage tank, and when the aim at of exhaust groove was to the vacuum chamber evacuation before the welding, take out the gas in the storage tank that splashes with the welding smoothly through the exhaust groove, make the welding seam inside and outside pressure unanimous during the welding, easily take shape.
Drawings
FIG. 1 is a schematic diagram of an original welded joint for part welding by a non-penetrating welding process;
FIG. 2 is a schematic diagram of a welded joint for part welding using the process of the present invention;
FIG. 3 is a graph of a post-weld X-ray inspection corresponding to the molding method of the present invention.
Wherein, 1 is the barrel, 2 is the switching nozzle stub, 3 is the welding and splashes the storage tank, and 4 is the detection recess.
Detailed Description
The objects, technical solutions and advantages of the present invention will be more apparent from the following detailed description with reference to the accompanying drawings and examples. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the invention, i.e., the embodiments described are merely some, but not all, of the embodiments of the invention.
The components illustrated in the figures and described and shown in the embodiments of the invention may be arranged and designed in a wide variety of different configurations, and thus the detailed description of the embodiments of the invention provided in the figures below is not intended to limit the scope of the invention as claimed, but is merely representative of selected ones of the embodiments of the invention. All other embodiments, which can be made by those skilled in the art without making any inventive series of claims, are intended to be within the scope of the present invention.
It should be noted that: the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, element, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, element, method, article, or apparatus. Furthermore, the terms "horizontal" and "vertical" are based on the orientation and positional relationship of the devices or components shown in the drawings, and are merely used to better describe the present invention, and do not require that the devices, components or apparatus shown must have this particular orientation and therefore should not be construed as limiting the present invention.
The features and properties of the present invention are described in further detail below with reference to examples.
As shown in fig. 2, the invention discloses a molding method of a double-sided molded welding joint of an aero-engine cylinder assembly, which comprises the following steps:
s1, removing the original substrate of the cylinder body 1, prefabricating a welding splash storage groove 3, enabling one side of the welding splash storage groove 3 to extend out of a to-be-welded position, enabling the distance between the welding splash storage groove 3 and the to-be-welded position to be about 1mm, and enabling the other side of the welding splash storage groove 3 to be approximately 3.5mm away from the to-be-welded position.
The cross section of the welding spatter receiving groove 3 is a combination of a rectangular groove and a fan shape.
S2, turning a boss on the cylinder body 1, wherein the outer diameter of the boss is in interference fit with the inner circle of the switching short pipe 2.
S3, symmetrically opening 2 exhaust grooves on the boss, wherein the groove depth is 0.5mm, and the groove width is equal to the boss width. The purpose of this exhaust groove is when vacuumizing the vacuum chamber before the welding, take out the gas in the welding splash receiving groove 3 smoothly through the exhaust groove, make the welding seam inside and outside pressure unanimous when welding, easily take shape.
S4, processing half of detection grooves 4 at the root of the original welding line of the cylinder body 1, processing the other half of detection grooves 4 at the root of the original welding line of the switching short pipe 2, and forming a complete detection groove 4 when the two half of detection grooves 4 are combined together.
S5, mechanically cleaning the to-be-welded areas of the cylinder body 1 and the switching short pipe 2, removing impurities such as oxides and greasy dirt, and wiping and cleaning the to-be-welded areas by dipping acetone in silk after cleaning.
S6, assembling the simple body and the junction pipe 2, wherein the gap between the junction surfaces is not more than 0.05mm. The part is mounted to a turntable of a vacuum electron beam welder.
S7, vacuumizing by an electron beam welding machine, wherein the vacuum degree of a vacuum chamber is required to be less than or equal to 5x10 -4 mbar;
and measuring points are carried out on the parts to be welded. The offset was measured every 10 degrees and input into the welding program, which was verified using a small beam (0.2-0.5) mA.
And performing penetration welding on the positions to be welded of the cylinder body 1 and the switching short pipe 2 according to the technological parameters in table 1. As shown in fig. 3, the front and back surfaces of the weld joint are formed in double surfaces, the weld joint is full and beautiful, and the detection groove 4 is filled with molten metal, so that the root is formed to be high.
TABLE 1 barrel assembly welding process parameters
After the welding is finished, the vacuum chamber is inflated after waiting for at least 2 minutes, so that the high-temperature oxidation of the parts is prevented.
Finally, it should be noted that: the above embodiments are only for illustrating the technical aspects of the present invention and not for limiting the same, and although the present invention has been described in detail with reference to the above embodiments, it should be understood by those of ordinary skill in the art that: modifications and equivalents may be made to the specific embodiments of the invention without departing from the spirit and scope of the invention, which is intended to be covered by the claims.
Claims (8)
1. The molding method of the double-sided molded welding joint of the aircraft engine barrel assembly is characterized in that the aircraft engine barrel assembly comprises a barrel (1) and a switching short pipe (2), and comprises the following steps:
S1, removing the original substrate part of a cylinder body (1), prefabricating a welding splash storage groove (3), and enabling one side of the welding splash storage groove (3) to extend out of a welding seam to be welded; the cross section of the welding splash storage groove (3) is a combination of a rectangular groove and a fan shape;
s2, prefabricating a boss on the cylinder body (1);
s3, processing a half arc-shaped groove at the root of an original welding line of the cylinder body (1), processing the other half arc-shaped groove at the root of the original welding line of the switching short pipe (2), and forming a complete detection groove (4) by the two half arc-shaped grooves;
s4, preprocessing the to-be-welded areas of the cylinder body (1) and the switching short pipe (2);
S5, assembling the simple body and the switching short pipe (2);
S6, vacuumizing an electron beam welding machine, and welding;
in S6, the welding is specifically as follows: and (3) carrying out penetration welding on the to-be-welded welding seam of the cylinder body (1) and the switching short pipe (2), forming the front and back surfaces of the welding seam, and filling the detection groove (4) with welding flux to form the residual height of the root.
2. The method for forming a double-sided formed welded joint of an aircraft engine cylinder assembly according to claim 1, wherein S1 specifically comprises: and cleaning the to-be-welded areas of the cylinder body (1) and the switching short pipe (2), and wiping and cleaning the to-be-welded areas by using acetone after cleaning.
3. The method for forming a double-sided formed welded joint of an aircraft engine cylinder assembly according to claim 1, wherein in S6, the vacuum degree of the vacuum chamber is required to be less than or equal to 5x10 -4 mbar.
4. The method for forming a double-sided formed welded joint of an aircraft engine barrel assembly according to claim 1, wherein in S5, the assembly of the barrel (1) and the junction pipe (2) is specifically: the outer circular surface of the boss is in interference fit with the inner circle of the switching short pipe (2); and then the assembled cylinder body (1) and the switching short pipe (2) are mounted on a turntable of a vacuum electron beam welding machine.
5. The method for forming a double-sided formed welded joint of an aircraft engine cylinder assembly according to claim 1, wherein in S2, after the boss is prefabricated, an exhaust groove is opened in the boss, and the exhaust groove is communicated with the welding spatter receiving groove (3).
6. A method of forming a double sided formed weld joint for an aircraft engine barrel assembly according to claim 1, wherein after the welding is completed, the vacuum chamber is inflated after waiting at least 2 minutes.
7. The method for forming the double-sided formed welding joint of the aircraft engine cylinder assembly according to claim 1, wherein one side of the welding spatter receiving groove (3) extending beyond the to-be-welded position is 1mm away from the to-be-welded position, and the other side of the welding spatter receiving groove (3) is 3.5mm away from the to-be-welded position.
8. An aero-engine barrel assembly double-sided shaped welded joint prepared based on the shaping method of any one of claims 1-7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210412097.1A CN114713959B (en) | 2022-04-19 | 2022-04-19 | Double-sided forming welding joint of aero-engine cylinder assembly and forming method thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210412097.1A CN114713959B (en) | 2022-04-19 | 2022-04-19 | Double-sided forming welding joint of aero-engine cylinder assembly and forming method thereof |
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| Publication Number | Publication Date |
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| CN114713959A CN114713959A (en) | 2022-07-08 |
| CN114713959B true CN114713959B (en) | 2024-07-23 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202210412097.1A Active CN114713959B (en) | 2022-04-19 | 2022-04-19 | Double-sided forming welding joint of aero-engine cylinder assembly and forming method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115502537B (en) * | 2022-10-18 | 2024-05-17 | 哈尔滨工业大学 | Electron beam lap welding and sealing method for prefabricated boss structure |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103506751A (en) * | 2012-06-20 | 2014-01-15 | 上海新力动力设备研究所 | Method for welding vacuum electron beam of stainless steel cylinder body |
| CN206029007U (en) * | 2016-08-29 | 2017-03-22 | 中航动力股份有限公司 | Electron -beam welding connects lap joint structure |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| DE10346072A1 (en) * | 2003-09-26 | 2005-04-21 | Erlas Erlanger Lasertechnik Gm | Welding process, composite body and use of a laser system for producing the composite body |
| CN104551376A (en) * | 2014-12-25 | 2015-04-29 | 重庆泽田汽车部件有限责任公司 | Welding positioning tooling with detection structure |
| CN106624321B (en) * | 2016-11-30 | 2019-05-17 | 中航动力股份有限公司 | A kind of double-layer barrel structural gap conduit electron beam welding banjo fixing butt jointing structure |
| CN108488006A (en) * | 2018-03-20 | 2018-09-04 | 北京宇航系统工程研究所 | It is a kind of to weld ultra-thin-wall tank entirely and be suitable for all-welded welding structure |
| CN111283315A (en) * | 2020-03-30 | 2020-06-16 | 沈阳富创精密设备有限公司 | Vacuum electron beam welding method for single-side welding and double-side forming of titanium alloy cylinder |
| CN112059394B (en) * | 2020-08-04 | 2022-03-22 | 西安航天发动机有限公司 | Electron beam welding method for lock bottom butt joint of large-size thin-wall titanium alloy storage box |
| CN112338601A (en) * | 2020-10-29 | 2021-02-09 | 陕西长羽航空装备有限公司 | Cylindrical thin-wall part machining and forming tool and method |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103506751A (en) * | 2012-06-20 | 2014-01-15 | 上海新力动力设备研究所 | Method for welding vacuum electron beam of stainless steel cylinder body |
| CN206029007U (en) * | 2016-08-29 | 2017-03-22 | 中航动力股份有限公司 | Electron -beam welding connects lap joint structure |
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| CN114713959A (en) | 2022-07-08 |
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