CN114713959A - Aero-engine cylinder assembly double-face forming welded joint and forming method thereof - Google Patents
Aero-engine cylinder assembly double-face forming welded joint and forming method thereof Download PDFInfo
- Publication number
- CN114713959A CN114713959A CN202210412097.1A CN202210412097A CN114713959A CN 114713959 A CN114713959 A CN 114713959A CN 202210412097 A CN202210412097 A CN 202210412097A CN 114713959 A CN114713959 A CN 114713959A
- Authority
- CN
- China
- Prior art keywords
- welding
- forming
- welded
- cylinder
- groove
- 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.)
- Granted
Links
- 238000000034 method Methods 0.000 title claims abstract description 34
- 238000003466 welding Methods 0.000 claims abstract description 83
- 238000001514 detection method Methods 0.000 claims abstract description 13
- 238000010894 electron beam technology Methods 0.000 claims abstract description 11
- 230000035515 penetration Effects 0.000 claims abstract description 7
- 239000000758 substrate Substances 0.000 claims abstract description 7
- 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
- 230000004907 flux Effects 0.000 claims description 2
- 210000001503 joint Anatomy 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 238000007689 inspection Methods 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
- 238000000465 moulding Methods 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
Images
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
Landscapes
- 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 method for forming a double-sided forming welding joint of an aircraft engine cylinder assembly, which comprises the following steps: s1, removing the original substrate part of the cylinder, prefabricating a welding spatter receiving groove, and extending one side of the welding spatter receiving groove to the outside of a welding seam to be welded; s2, prefabricating a boss on the cylinder; s3, processing a semi-arc groove at the root of the original weld of the cylinder, processing the other half of arc groove at the root of the original weld of the adapter stub, and forming a complete detection groove by the two half arc grooves; s4, preprocessing the areas to be welded of the cylinder and the adapter short pipe; s5, assembling the simple body and the adapter pipe stub; and S6, vacuumizing the electron beam welding machine and welding. The problem of stress concentration in the process of welding parts by adopting a non-penetration welding process 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 aircraft engine cylinder assembly and a forming method thereof.
Background
The cylinder assembly of the aircraft engine is formed by welding a part cylinder 1 and a short switching pipe 2 by electron beams by adopting an electron beam welding process. 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. Because the welded substrate cannot be processed, an unfused gap is easy to exist at the joint of the substrate and the short connecting pipe, so that stress concentration is caused, and cracks are generated in severe cases.
Disclosure of Invention
The invention aims to provide a double-sided forming welding joint of an aeroengine cylinder assembly and a forming method thereof, and solves the problem of stress concentration in the process of welding parts by adopting a non-penetration welding process.
The invention is realized by the following technical scheme:
a forming method for a double-sided forming welded joint of an aircraft engine cylinder assembly comprises a cylinder and a switching short pipe, and comprises the following steps:
s1, removing the original substrate part of the cylinder, prefabricating a welding spatter receiving groove, and extending one side of the welding spatter receiving groove to the outside of a welding seam to be welded;
s2, prefabricating a boss on the cylinder;
s3, processing a semi-arc groove at the root of the original welding line of the cylinder, processing the other half of arc groove at the root of the original welding line of the adapter stub, and forming a complete detection groove by the two half of arc grooves;
s4, preprocessing the areas to be welded of the cylinder and the adapter short pipe;
s5, assembling the barrel body and the adapter pipe stub;
and S6, vacuumizing the electron beam welding machine and welding.
Further, S1 specifically is: and cleaning the to-be-welded areas of the cylinder body and the short adapter 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 less than or equal to 5x10-4mbar。
Further, in S6, the welding specifically includes: and performing penetration welding on the positions of to-be-welded welding seams of the cylinder body and the adapter short pipe, forming the front surface and the back surface of the welding seams, and filling the detection grooves with welding flux to form the root residual height.
Further, in S5, assembling the cylinder and the adapter stub specifically includes: the outer circle surface of the boss is in interference fit with the inner circle of the adapter short pipe; and then the assembled cylinder body and the adapter short pipe are arranged on a rotary table of a vacuum electron beam welding machine.
Further, in S2, after the boss is prepared, an exhaust groove is opened in the boss, and the exhaust groove is communicated with the welding spatter collecting groove.
Further, after the welding is completed, the vacuum chamber is waited for at least 2 minutes and then aerated.
Further, one side of the welding spatter receiving groove, which extends to the position outside the position to be welded, is 1mm away from the position to be welded, and the other side of the welding spatter receiving groove is 3.5mm away from the position to be welded.
The invention also discloses a double-sided forming welding joint of the cylinder assembly of the aero-engine prepared based on the forming method.
Further, the cross section of the welding spatter collecting 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 aircraft engine cylinder assembly and a forming method thereof. Meanwhile, welding spatter can be stored, and the detection groove is favorable for nondestructive detection and evaluation of the welding line.
Furthermore, after the lug boss is prefabricated, an exhaust groove is formed in the lug boss and is communicated with the welding spatter containing groove, and when the vacuum chamber is vacuumized before welding, gas in the welding spatter containing groove is smoothly extracted through the exhaust groove, so that the internal and external pressure of a welding line is consistent during welding, and the welding spatter containing groove is easy to form.
Drawings
FIG. 1 is a schematic view of an original welded joint structure for welding parts by a non-penetration welding process;
FIG. 2 is a schematic view of a welded joint structure for welding parts by the process of the present invention;
FIG. 3 is a post-weld X-ray inspection view 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 and accomodates the groove, and 4 is the detection recess.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the following detailed description is made with reference to the accompanying drawings and embodiments. It should be understood that the detailed description and specific examples, while indicating the preferred embodiment of the invention, are intended for purposes of illustration only and are not intended to limit the scope of the invention.
The components illustrated and described in the figures and embodiments of the present invention may be arranged and designed in a wide variety of different configurations, and accordingly, the detailed description of the embodiments of the present invention provided in the figures that follow is not intended to limit the scope of the invention, as claimed, but is merely representative of a selected embodiment of the invention. All other embodiments obtained by those skilled in the art without making creative verbalization are within the protection scope of the present invention based on the drawings and the embodiments 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 used only for the purpose of better describing the present invention, but do not require that the devices, components or apparatuses shown have to have this particular orientation, and therefore, should not be construed as limiting the present invention.
The features and properties of the present invention are further described in detail below with reference to examples.
As shown in FIG. 2, the invention discloses a method for forming a double-sided forming welded joint of an aeroengine cylinder assembly, which comprises the following steps:
s1, removing the original substrate of the cylinder 1, prefabricating the welding spatter containing groove 3, and enabling one side of the welding spatter containing groove 3 to extend to the outside of the position to be welded, wherein the distance between the one side of the welding spatter containing groove 3 and the position to be welded is about 1mm, and the distance between the other side of the welding spatter containing groove 3 and the position to be welded is about 3.5 mm.
The cross-sectional shape of the welding spatter receiving groove 3 is a combination of a rectangular groove and a fan shape.
And S2, turning a boss on the barrel 1, wherein the outer diameter of the boss forms interference fit with the inner circle of the adapter stub 2.
S3, symmetrically forming 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 the exhaust groove is to smoothly extract the gas in the welding spatter receiving groove 3 through the exhaust groove when the vacuum chamber is vacuumized before welding, so that the internal and external pressure intensity of a welding seam is consistent during welding, and the welding seam is easy to form.
S4, processing a half of detection groove 4 on the root of the original welding line of the cylinder 1, processing the other half of detection groove 4 on the root of the original welding line of the adapter sleeve 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 adapter stub 2, removing impurities such as oxides and oil stains, and wiping and cleaning the to-be-welded areas by using a silk cloth dipped with acetone after cleaning.
And S6, assembling the simple body and the adapter pipe stub 2, wherein the gap of the butt joint surface is not more than 0.05 mm. The part is mounted on a turntable of a vacuum electron beam welder.
S7, performing vacuum pumping by an electron beam welding machine, wherein the vacuum degree of the vacuum chamber is required to be less than or equal to 5x10-4mbar；
And measuring points are carried out on the positions to be welded of the parts. Measuring the offset every 10 degrees, inputting the offset into a welding program, and verifying the welding program by adopting a small beam current (0.2-0.5) mA.
And (3) performing penetration welding on the positions to be welded of the cylinder body 1 and the adapter tube 2 according to the process parameters of the table 1. As shown in figure 3, the front and back sides of the welding seam are formed in a double-sided mode, the welding seam is full and attractive, and the detection groove 4 is filled with molten metal to form root residual height.
TABLE 1 barrel Assembly welding Process parameters
After welding, the vacuum chamber is aerated after waiting for at least 2 minutes to prevent the high-temperature oxidation of parts.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solutions of the present invention and not for limiting the same, and although the present invention is described in detail with reference to the above embodiments, those of ordinary skill in the art should understand that: modifications and equivalents may be made to the embodiments of the invention without departing from the spirit and scope of the invention, which is to be covered by the claims.
Claims (10)
1. A forming method for a double-sided forming welded joint of an aeroengine cylinder assembly is characterized in that the aeroengine cylinder assembly comprises a cylinder (1) and a switching short pipe (2), and the forming method comprises the following steps:
s1, removing the original substrate part of the cylinder (1), prefabricating a welding spatter containing groove (3), and extending one side of the welding spatter containing groove (3) to the outside of a welding seam to be welded;
s2, prefabricating a boss on the cylinder body (1);
s3, processing a semi-arc groove at the root of the original welding line of the cylinder body (1), processing the other half of arc groove at the root of the original welding line of the adapter stub (2), and forming a complete detection groove (4) by the two half of arc grooves;
s4, preprocessing the areas to be welded of the cylinder (1) and the adapter pipe stub (2);
s5, assembling the simple body and the adapter pipe stub (2);
and S6, vacuumizing the electron beam welding machine and welding.
2. The method for forming the double-sided forming welded joint of the aero-engine cylinder assembly as claimed in claim 1, wherein S1 specifically comprises: 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 as claimed in claim 1, wherein in S6, the vacuum degree of the vacuum chamber is required to be less than or equal to 5x10-4mbar。
4. The method for forming the double-sided formed welded joint of the aero-engine cylinder assembly as claimed in claim 1, wherein in S6, the welding is specifically: and (3) performing penetration welding on the positions of to-be-welded welding seams of the cylinder body (1) and the adapter short pipe (2), forming the front and back surfaces of the welding seams, and filling the detection groove (4) with welding flux to form the root residual height.
5. The method for forming the double-sided forming welded joint of the cylinder assembly of the aircraft engine according to claim 1, wherein in the step S5, the assembling of the cylinder (1) and the adapter stub (2) is specifically as follows: the outer circle surface of the boss is in interference fit with the inner circle of the adapter short pipe (2); and then the assembled cylinder body (1) and the adapter short pipe (2) are arranged on a rotary table of a vacuum electron beam welding machine.
6. The method for forming a double-sided formed welded joint of an aircraft engine barrel assembly according to claim 1, wherein in S2, after the boss is prefabricated, an exhaust groove is formed in the boss, and the exhaust groove is communicated with the weld spatter receiving groove (3).
7. The method of forming a double-sided formed weld joint for an aircraft engine barrel assembly as defined in claim 1, wherein after welding is completed, the vacuum chamber is charged again after waiting at least 2 minutes.
8. The forming method of the double-sided formed welded joint of the barrel assembly of the aircraft engine as claimed in claim 1, wherein one side of the weld spatter receiving groove (3) extending beyond the position to be welded is 1mm away from the position to be welded, and the other side of the weld spatter receiving groove (3) is 3.5mm away from the position to be welded.
9. An aircraft engine barrel assembly double-sided formed weld joint prepared based on the method of any one of claims 1 to 8.
10. The aero-engine cylinder assembly double-sided profiled weld joint as set forth in claim 9, wherein the weld spatter receiving groove (3) has a cross-sectional shape of a combination of a rectangular groove and a fan shape.
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 |
Applications Claiming Priority (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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114713959A true CN114713959A (en) | 2022-07-08 |
| CN114713959B CN114713959B (en) | 2024-07-23 |
Family
ID=82244727
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| 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 |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114713959B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115502537A (en) * | 2022-10-18 | 2022-12-23 | 哈尔滨工业大学 | Prefabricated boss structure electron beam lap welding and sealing method |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1518633A1 (en) * | 2003-09-26 | 2005-03-30 | Erlas Erlanger Lasertechnik GmbH | Welding process, assembled bodies and use of a laser to manufacture the assembled body |
| 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 |
| 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 |
| 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 |
| CN106624321A (en) * | 2016-11-30 | 2017-05-10 | 中航动力股份有限公司 | Double-layer tube structure air conduit electron beam welding butt joint 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 |
| CN112059394A (en) * | 2020-08-04 | 2020-12-11 | 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 |
-
2022
- 2022-04-19 CN CN202210412097.1A patent/CN114713959B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1518633A1 (en) * | 2003-09-26 | 2005-03-30 | Erlas Erlanger Lasertechnik GmbH | Welding process, assembled bodies and use of a laser to manufacture the assembled body |
| 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 |
| 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 |
| 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 |
| CN106624321A (en) * | 2016-11-30 | 2017-05-10 | 中航动力股份有限公司 | Double-layer tube structure air conduit electron beam welding butt joint 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 |
| CN112059394A (en) * | 2020-08-04 | 2020-12-11 | 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 |
Non-Patent Citations (1)
| Title |
|---|
| 方连军: "GH536高温合金薄壁结构件焊接工艺研究", 中国优秀硕士学位论文全文数据库, no. 08, 31 August 2020 (2020-08-31), pages 1 - 49 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115502537A (en) * | 2022-10-18 | 2022-12-23 | 哈尔滨工业大学 | Prefabricated boss structure electron beam lap welding and sealing method |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114713959B (en) | 2024-07-23 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101444871B (en) | Method for deeply repairing scrap with local defects by utilizing electron beam bonding | |
| CN102294541B (en) | Electron beam welding method for ultra supercritical partition plates | |
| CN108788410A (en) | T-steel full penetration exempts from back chipping welding method | |
| CN107052517B (en) | Automatic butt welding process for low-alloy steel and nickel-based alloy dissimilar steel heat exchange tubes | |
| CN107999950B (en) | A kind of middle pressure high-velocity electron beam welding method of titanium alloy thin wall casing | |
| CN106392292A (en) | Electron beam welding method of thin-walled part | |
| CN105880815B (en) | A kind of tube sheet corner joint auxiliary welding device and welding method | |
| CN114713959A (en) | Aero-engine cylinder assembly double-face forming welded joint and forming method thereof | |
| CN108057952A (en) | A kind of electron beam soldering method of big L/D ratio thin-walled parts | |
| CN113500279A (en) | Electric resistance welding process for end plugs of ODS-FeCrAl alloy cladding tube fuel rods | |
| CN106695104B (en) | It is a kind of for eliminating the ventilation lock bottom structure of annular element electron beam weld stomata | |
| CN105750717A (en) | Welding process used for connecting plates and cylinder body | |
| CN106001971A (en) | Automatic 2G-welding-position narrow-gap welding method for steam turbine valve thick-wall connection tube | |
| CN111702317A (en) | Electron beam welding method for double-sided planet weld joint structure | |
| CN105290575A (en) | Electron beam welding method of titanium alloy material and CVDNb | |
| CN111112952A (en) | Integral forming process for pipe seat of boiler header | |
| CN101332529B (en) | Welding process of thin-wall hexagonal tube | |
| CN108857033A (en) | The electron beam single face welding and double face shaping process of class component is led in a kind of 1Cr18Ni9Ti, TA2 space flight | |
| CN106624278B (en) | A kind of change wall thickness aluminium welding method | |
| CN104889544A (en) | Stainless steel cavity preheating transmission cavity welding process | |
| CN101745735B (en) | Electric heating plug welding technique for engine | |
| CN104526155B (en) | A kind of preparation method of armouring thermode | |
| CN114248029A (en) | Method for manufacturing nozzle of combustion chamber of gas turbine | |
| CN113664342A (en) | Process for welding through strength welding joint between heat exchange tube and tube plate of reactor or heat exchanger | |
| CN101839498A (en) | Turbine singlet nozzle assembly with radial stop and narrow groove |
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 |