CN119216945A - An angular positioning tool and method for welding of aero-engine barrel casing - Google Patents
An angular positioning tool and method for welding of aero-engine barrel casing Download PDFInfo
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- CN119216945A CN119216945A CN202411544489.9A CN202411544489A CN119216945A CN 119216945 A CN119216945 A CN 119216945A CN 202411544489 A CN202411544489 A CN 202411544489A CN 119216945 A CN119216945 A CN 119216945A
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- positioning
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- welding
- fixing plate
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- 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
- B23K37/00—Auxiliary devices or processes, not specially adapted for a procedure covered by only one of the other main groups of this subclass
- B23K37/04—Auxiliary devices or processes, not specially adapted for a procedure covered by only one of the other main groups of this subclass for holding or positioning work
- B23K37/0426—Fixtures for other work
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- Optics & Photonics (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Butt Welding And Welding Of Specific Article (AREA)
Abstract
The invention relates to the field of combined welding of aero-engine barrel casing parts, in particular to an angular positioning tool and method for welding an aero-engine barrel casing. The angular positioning tool comprises a fixing plate and a positioning plate, clamping grooves are formed in the fixing plate, a first positioning column and two second positioning columns are arranged on the front face of the fixing plate, the first positioning column is used for being inserted into an angular hole of a middle mounting edge, the second positioning column is used for being inserted into a mounting hole of the middle mounting edge, the positioning plate is clamped in the clamping grooves, two ends of the positioning plate are respectively inclined downwards, limiting notch is respectively formed in two ends of the positioning plate and used for being clamped on reinforcing ribs of the front section of a casing body and the rear section of the casing body, and the symmetrical center faces of the limiting notch are coplanar with the center line of the first positioning column. The tool can rapidly and accurately realize the angular positioning of parts, ensure the consistency of the angular directions of each part after welding, and ensure the stability of the angular quality of the parts.
Description
Technical Field
The invention relates to the field of combined welding of aero-engine barrel casing parts, in particular to an angular positioning tool and method for welding an aero-engine barrel casing.
Background
The barrel casing parts are mainly connected by a front mounting edge, a casing shell front section, a middle mounting edge, a casing shell rear section and a rear mounting edge through a welding process, and the joint is in butt joint. The front section and the rear section of the casing are equal-wall-thickness cylinders, long-strip-shaped reinforcing ribs are uniformly distributed along the circumference, the number of the reinforcing ribs at the front section and the rear section is the same, the distribution angles are the same, and the trend of the reinforcing ribs is the axial direction of the casing. In the welding process, the special welding tool is generally used for restraining the butt joint to ensure the quality of the welding joint, and under the condition that the welding tool is inconvenient to design an angular positioning function, the positioning welding is generally carried out in a scribing mode.
Fig. 1 is a schematic view of a typical barrel casing part of an aeroengine, wherein the casing is in a barrel structure and is mainly formed by connecting a front mounting edge 1, a casing front section 2, a middle mounting edge 3, a casing rear section 4 and a rear mounting edge 5 through a welding process, and the joint is in butt joint. A, b, c, d in fig. 1 represent welds. The front section 2 and the rear section 4 of the casing are both equal-wall-thickness cylinders, long-strip-shaped reinforcing ribs are uniformly distributed along the circumference, the number of the reinforcing ribs at the front section and the rear section are the same, the distribution angles are the same, and the trend of the reinforcing ribs is the axial direction of the casing. The central line of the angular hole 3a on the middle mounting edge 3 is coplanar with the reinforcing ribs at the corresponding positions of the front section 2 of the casing and the rear section 4 of the casing respectively.
When the front section 2, the middle mounting edge 3 and the rear section 4 of the casing are welded, the problem is that the assembly angle requirement exists before the component combination welding, namely the central line of the angle hole 3a on the middle mounting edge 3 is required to be coplanar with the reinforcing ribs at the corresponding positions of the front section 2 and the rear section 4 of the casing respectively. During welding, the welding tool is used for expanding the welding part to meet the welding requirement, so that the welding quality is ensured. However, the currently used welding tool has no angular positioning function, the center line of the angular hole 3a, the reinforcing rib of the front section 2 of the casing body and the reinforcing rib of the rear section 4 of the casing body are generally located on the same plane through scribing during pre-welding assembly, different deviations are inevitably caused by the personal skill level of operators, the three parts deviate from the theoretical plane after welding, angular inconsistency can occur during mass production of parts, the quality of the parts is unstable, and the follow-up incapability of processing the parts is caused by serious deviation, so that the parts are scrapped.
Disclosure of Invention
The invention mainly aims to provide an angular positioning tool and an angular positioning method for welding an aeroengine barrel casing, which ensure that the angle requirements of the front section of the casing after welding, the rear section of the casing and middle mounting angle holes can be met.
In order to achieve the aim, on one hand, the invention provides an angular positioning tool for welding an aeroengine barrel casing, which comprises a fixing plate and a positioning plate, wherein a clamping groove is formed in the fixing plate, a first positioning column and two second positioning columns are arranged on the front surface of the fixing plate, the first positioning column is used for being inserted into an angular hole of a middle mounting edge, the second positioning column is used for being inserted into a mounting hole of the middle mounting edge, the positioning plate is clamped in the clamping groove, two ends of the positioning plate are respectively inclined downwards, two ends of the positioning plate are respectively provided with a limiting notch, the limiting notches are used for being clamped on reinforcing ribs of the front section of the casing and the rear section of the casing, and the symmetrical center faces of the limiting notches are coplanar with the center line of the first positioning column.
Preferably, the symmetrical center plane of the clamping groove is coplanar with the central line of the first positioning column, and the limiting notch is coplanar with the symmetrical center plane of the positioning plate.
Preferably, the two second positioning columns are respectively located at two sides of the first positioning column.
Preferably, the top surface of the positioning plate is integrally formed with a convex block, and the clamping groove is formed in the convex block of the positioning plate.
Preferably, the lower surface of the fixing plate is an arc surface, and when the fixing plate is assembled on the middle mounting edge through the first positioning column and the second positioning column, the lower surface of the fixing plate is attached to the outer peripheral surface of the middle mounting edge.
Preferably, the positioning plate is in transition fit with the clamping groove.
Preferably, the limit notch is in transition fit with the reinforcing ribs of the front section of the casing and the rear section of the casing.
Preferably, the first positioning column and the second positioning column are connected with the positioning plate in a welding mode, or the first positioning column and the second positioning column are of an integrated structure with the fixing plate.
Preferably, the first positioning column is in transition fit with the angular hole of the middle mounting edge, and the second positioning column is in transition fit with the mounting hole of the middle mounting edge.
On the other hand, the invention also provides an angular positioning method for welding the aeroengine cylinder casing, which adopts the angular positioning tool and comprises the following steps:
S1, sequentially placing a front mounting edge, a front section of a casing shell, a middle mounting edge, a rear section of the casing shell and a rear mounting edge on a welding tool;
s2, mounting the fixing plate on the middle mounting edge, so that the first positioning column is inserted into an angular hole of the middle mounting edge, and the second positioning column is inserted into a mounting hole of the middle mounting edge;
S3, clamping the positioning plate in the clamping groove of the fixing plate, rotating the front section of the casing body and the rear section of the casing body, enabling the reinforcing ribs on the front section of the casing body and the rear section of the casing body to be respectively clamped into the limiting notch of the positioning plate, and then completing angular positioning of the front section of the casing body, the middle mounting edge and the rear section of the casing body.
Due to the adoption of the technical scheme, the invention has the following beneficial effects:
(1) By adopting the angular positioning tool and the angular positioning method provided by the invention, when angular positioning is carried out, the fixed plate is mounted on the middle mounting edge, so that the first positioning column is inserted into the angular hole of the middle mounting edge, the second positioning column is inserted into the mounting hole of the middle mounting edge, the positioning plate is clamped in the clamping groove of the fixed plate, the front section of the casing shell and the rear section of the casing shell are rotated, and the reinforcing ribs on the front section of the casing shell and the rear section of the casing shell are respectively clamped into the limit notch of the positioning plate, so that the angular positioning of the front section of the casing shell, the middle mounting edge and the rear section of the casing shell can be completed.
(2) The angular positioning tool provided by the invention has the advantages of simple structure and convenient use process, can rapidly and accurately realize the angular positioning of parts, ensures the consistency of the angular directions of each part after welding, and ensures the stability of the angular quality of the parts.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to the structures shown in these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic illustration of a typical barrel casing part of an aircraft engine;
FIG. 2 is a schematic view of an angular positioning tool according to the present invention;
Fig. 3 is a schematic view of a use state of the angular positioning tool according to the present invention.
The reference numerals are described as 1, front mounting edge, 2, front section of casing, 3, middle mounting edge, 3a, angle hole, 3b, mounting hole, 4, rear section of casing, 5, rear mounting edge, 6, fixing plate, 6a, protruding block, 6b, clamping groove, 7, locating plate, 7a, limit notch, 8, first locating column, 9, second locating column.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
It should be noted that all directional indicators (such as up, down, left, right, front, and rear are used in the embodiments of the present invention) are merely for explaining the relative positional relationship, movement conditions, and the like between the components in a certain specific posture (as shown in the drawings), and if the specific posture is changed, the directional indicators are changed accordingly.
Furthermore, the description of "first," "second," etc. in this disclosure is for descriptive purposes only and is not to be construed as indicating or implying a 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 at least one such feature. In addition, the technical solutions of the embodiments may be combined with each other, but it is necessary to base that the technical solutions can be realized by those skilled in the art, and when the technical solutions are contradictory or cannot be realized, the combination of the technical solutions should be considered to be absent and not within the scope of protection claimed in the present invention.
Referring to fig. 2, the embodiment of an angular positioning tool for welding an aeroengine barrel casing provided by the invention comprises a fixing plate 6 and a positioning plate 7, wherein a clamping groove 6b is formed in the fixing plate 6, a first positioning column 8 and two second positioning columns 9 are arranged on the front surface of the fixing plate 6, the first positioning column 8 is used for being inserted into an angular hole 3a of a middle mounting side 3, the second positioning column 9 is used for being inserted into a mounting hole 3b of the middle mounting side 3, the positioning plate 7 is clamped in the clamping groove 6b, two ends of the positioning plate 7 are respectively inclined downwards, limiting notch 7a are respectively formed at two ends of the positioning plate 7, the limiting notch 7a is used for being clamped on a reinforcing rib of a front section 2 of the casing and a rear section 4 of the casing, and the symmetrical center surface of the limiting notch 7a is coplanar with the center line of the first positioning column 8.
In this embodiment, the angular hole 3a on the mounting edge 3 and the aperture and circumferential distribution positions of the two mounting holes 3b around the angular hole are designed and manufactured in the positioning tools of the first positioning column 8 and the second positioning column 9, and the two second positioning columns 9 are respectively located at two sides of the first positioning column 8. In use, the second positioning posts 9 are inserted into the mounting holes 3b on the left and right sides of the angular hole 3 a.
Further, the symmetrical center plane of the clamping groove 6b is coplanar with the center line of the first positioning column 8, and the limit notch 7a is coplanar with the symmetrical center plane of the positioning plate 7.
As shown in fig. 2, a protruding block 6a is integrally formed on the top surface of the fixing plate 6, and the clamping groove 6b is formed on the protruding block 6a of the fixing plate 6. And the integral forming mode is adopted, so that the integral processing of the fixing plate 6 and the protruding block 6a is convenient.
In this embodiment, the lower surface of the fixing plate 6 is an arc surface, and when the fixing plate 6 is assembled on the middle mounting edge 3 through the first positioning column 8 and the second positioning column 9, the lower surface of the fixing plate 6 is attached to the outer peripheral surface of the middle mounting edge 3, so as to ensure that the fixing plate 6 can be stably mounted on the middle mounting edge 3, and prevent radial movement.
In this embodiment, the positioning plate 7 is in transition fit with the clamping groove 6 b. The limit notch 7a is in transition fit with the reinforcing ribs of the front section 2 and the rear section 4 of the casing. The first positioning column 8 is in transition fit with the angular hole 3a of the middle mounting edge 3, and the second positioning column 9 is in transition fit with the mounting hole 3b of the middle mounting edge 3. The transition fit is suitable for applications requiring precise positioning because it allows for both a certain clearance for ease of assembly and adjustment and a certain interference to ensure the robustness of the connection.
As shown in fig. 2, the first positioning column 8 and the second positioning column 9 are connected with the fixing plate 6 by adopting a welding mode. Or the first positioning column 8, the second positioning column 9 and the fixing plate 6 adopt an integrated structure.
Referring to fig. 3, this embodiment further provides an angular positioning method for welding an aero-engine barrel casing, and the angular positioning tool includes the following steps:
s1, sequentially placing a front mounting edge 1, a front section 2, a middle mounting edge 3, a rear section 4 and a rear mounting edge 5 of the casing on a welding tool, wherein the welding tool is conventional in the prior art, and no description is given here.
S2, the fixing plate 6 is mounted on the middle mounting side 3, so that the first positioning column 8 is inserted into the angular hole 3a of the middle mounting side 3, and the second positioning column 9 is inserted into the mounting hole 3b of the middle mounting side 3.
S3, the positioning plate 7 is clamped in the clamping groove 6a of the fixing plate 6, the front section 2 of the casing body and the rear section 4 of the casing body are rotated, so that the reinforcing ribs on the front section 2 of the casing body and the rear section 4 of the casing body are respectively clamped in the limit notch 7a of the positioning plate 7, and the angular positioning of the front section 2 of the casing body, the middle mounting edge 3 and the rear section 4 of the casing body can be completed.
After the angular positioning is finished by adopting the method, the casing can be welded normally.
The foregoing description is only of the preferred embodiments of the present invention, and is not intended to limit the scope of the invention, but rather, the equivalent structural changes made by the description of the present invention and the accompanying drawings or the direct/indirect application in other related technical fields are included in the scope of the invention.
Claims (10)
1. The angle positioning tool for welding the aeroengine barrel casing is characterized by comprising a fixing plate (6) and a positioning plate (7), wherein clamping grooves (6 b) are formed in the fixing plate (6), a first positioning column (8) and two second positioning columns (9) are arranged on the front face of the fixing plate (6), the first positioning column (8) is used for being inserted into an angle hole (3 a) of a middle mounting side (3), the second positioning column (9) is used for being inserted into a mounting hole (3 b) of the middle mounting side (3), the positioning plate (7) is clamped in the clamping grooves (6 b), two ends of the positioning plate (7) are respectively inclined downwards, limiting notch (7 a) are respectively formed in two ends of the positioning plate (7), the limiting notch (7 a) is used for being clamped on a reinforcing rib of a front section (2) of a casing body and a rear section (4) of the casing, and the symmetrical center face of the limiting notch (7 a) is coplanar with the center line of the first positioning column (8).
2. The angular positioning tool for welding an aeroengine barrel casing according to claim 1, wherein the symmetrical center plane of the clamping groove (6 b) is coplanar with the center line of the first positioning column (8), and the limiting notch (7 a) is coplanar with the symmetrical center plane of the positioning plate (7).
3. An aircraft engine barrel casing welded angular positioning tool according to claim 1, characterized in that two second positioning posts (9) are located on both sides of the first positioning post (8), respectively.
4. The angular positioning tool for welding an aeroengine barrel casing according to claim 1, wherein the protruding block (6 a) is integrally formed on the top surface of the fixing plate (6), and the clamping groove (6 b) is formed on the protruding block (6 a) of the fixing plate (6).
5. The angular positioning tool for welding an aeroengine barrel casing according to claim 1, wherein the lower surface of the fixing plate (6) is an arc surface, and when the fixing plate (6) is assembled on the middle mounting edge (3) through the first positioning column (8) and the second positioning column (9), the lower surface of the fixing plate (6) is attached to the outer peripheral surface of the middle mounting edge (3).
6. The angular positioning tool for welding an aeroengine barrel casing according to claim 1, wherein the positioning plate (7) is in transition fit with the clamping groove (6 b).
7. An aeroengine barrel casing welded angular positioning tool as claimed in claim 1, wherein the limit notch (7 a) is in transition fit with reinforcing ribs of a casing front section (2) and a casing rear section (4).
8. The angular positioning tool for welding an aeroengine cylinder casing according to claim 1, wherein the first positioning column (8) and the second positioning column (9) are connected with the fixing plate (6) in a welding mode, or the first positioning column (8) and the second positioning column (9) are integrally formed with the fixing plate (6).
9. An aeroengine barrel casing welded angular positioning tool as claimed in claim 1, wherein the first positioning column (8) is in transition fit with the angular hole (3 a) of the middle mounting edge (3), and the second positioning column (9) is in transition fit with the mounting hole (3 b) of the middle mounting edge (3).
10. An angular positioning method for welding an aeroengine barrel casing, characterized in that an angular positioning tool according to any one of claims 1 to 9 is used, comprising the following steps:
S1, sequentially placing a front mounting edge (1), a front section (2) of a casing shell, a middle mounting edge (3), a rear section (4) of the casing shell and a rear mounting edge (5) on a welding tool;
s2, mounting the fixing plate (6) on the middle mounting edge (3) so that the first positioning column (8) is inserted into the angular hole (3 a) of the middle mounting edge (3), and the second positioning column (9) is inserted into the mounting hole (3 b) of the middle mounting edge (3);
S3, the locating plate (7) is clamped in the clamping groove (6 a) of the fixing plate (6), the front section (2) and the rear section (4) of the casing body are rotated, so that reinforcing ribs on the front section (2) and the rear section (4) of the casing body are respectively clamped into limit notches (7 a) of the locating plate (7), and angular locating of the front section (2), the middle mounting edge (3) and the rear section (4) of the casing body can be completed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202411544489.9A CN119216945B (en) | 2024-10-31 | 2024-10-31 | An angular positioning tool and method for welding aircraft engine casing. |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202411544489.9A CN119216945B (en) | 2024-10-31 | 2024-10-31 | An angular positioning tool and method for welding aircraft engine casing. |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN119216945A true CN119216945A (en) | 2024-12-31 |
| CN119216945B CN119216945B (en) | 2026-03-24 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202411544489.9A Active CN119216945B (en) | 2024-10-31 | 2024-10-31 | An angular positioning tool and method for welding aircraft engine casing. |
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| FR2942854A1 (en) * | 2009-03-06 | 2010-09-10 | Snecma | REPAIR DEVICE FOR AERONAUTICAL MOTOR CASE FLANGE |
| CN210388977U (en) * | 2019-06-06 | 2020-04-24 | 浙江吉利控股集团有限公司 | A front cover lock installation and adjustment tool |
| CN212577880U (en) * | 2020-03-30 | 2021-02-23 | 江西昌河航空工业有限公司 | Steel wire cross welding positioning device |
| CN112894201A (en) * | 2020-12-29 | 2021-06-04 | 浙江合众新能源汽车有限公司 | Handheld tool for positioning and welding safety air bag controller bracket assembly |
| CN213730146U (en) * | 2020-09-24 | 2021-07-20 | 辽宁忠旺特种车辆制造有限公司 | Group welding tool for cross beam assembly in a skeleton car |
| CN114753534A (en) * | 2022-05-07 | 2022-07-15 | 吉林大学 | Connecting piece for splicing water heating type heat supply floor slabs |
| CN219254621U (en) * | 2023-02-27 | 2023-06-27 | 溧阳市飞跃机电有限公司 | Machining fixing device for direct-drive generator support for offshore wind power |
| CN219354064U (en) * | 2022-09-23 | 2023-07-18 | 湘潭市中医医院 | Auxiliary positioning tool for coracoid tunnel drilling |
| CN220612842U (en) * | 2023-08-23 | 2024-03-19 | 四川翔越电力线路构件有限公司 | Welding positioning fixture for reinforcing ribs of power tower connecting plates |
-
2024
- 2024-10-31 CN CN202411544489.9A patent/CN119216945B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2942854A1 (en) * | 2009-03-06 | 2010-09-10 | Snecma | REPAIR DEVICE FOR AERONAUTICAL MOTOR CASE FLANGE |
| CN210388977U (en) * | 2019-06-06 | 2020-04-24 | 浙江吉利控股集团有限公司 | A front cover lock installation and adjustment tool |
| CN212577880U (en) * | 2020-03-30 | 2021-02-23 | 江西昌河航空工业有限公司 | Steel wire cross welding positioning device |
| CN213730146U (en) * | 2020-09-24 | 2021-07-20 | 辽宁忠旺特种车辆制造有限公司 | Group welding tool for cross beam assembly in a skeleton car |
| CN112894201A (en) * | 2020-12-29 | 2021-06-04 | 浙江合众新能源汽车有限公司 | Handheld tool for positioning and welding safety air bag controller bracket assembly |
| CN114753534A (en) * | 2022-05-07 | 2022-07-15 | 吉林大学 | Connecting piece for splicing water heating type heat supply floor slabs |
| CN219354064U (en) * | 2022-09-23 | 2023-07-18 | 湘潭市中医医院 | Auxiliary positioning tool for coracoid tunnel drilling |
| CN219254621U (en) * | 2023-02-27 | 2023-06-27 | 溧阳市飞跃机电有限公司 | Machining fixing device for direct-drive generator support for offshore wind power |
| CN220612842U (en) * | 2023-08-23 | 2024-03-19 | 四川翔越电力线路构件有限公司 | Welding positioning fixture for reinforcing ribs of power tower connecting plates |
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| Publication number | Publication date |
|---|---|
| CN119216945B (en) | 2026-03-24 |
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