Angular positioning tool and method for welding of aero-engine cylinder casing

Abstract

The invention relates to the field of combined welding of aero-engine barrel and receiver parts, in particular to an angular positioning tool and method for welding of an aero-engine barrel and receiver. The angular positioning tool comprises a fixing plate and a positioning plate; a clamping groove is 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 the middle mounting edge; the second positioning column is used for being inserted into the mounting hole of the middle mounting edge; the positioning plate is clamped in the clamping groove; the two ends of the positioning plate incline downwards respectively, limiting notches are formed in the two ends of the positioning plate respectively, and the limiting notches are used for being clamped on reinforcing ribs of the front section and the rear section of the case shell. And the symmetric central plane of the limiting notch is coplanar with the central line of the first positioning column. The tool can quickly and accurately realize the angular positioning of the parts, ensures the consistency of the angular directions of all the parts after welding, and ensures the stability of the angular quality of the parts.

Description

Technical Field

[0001] The invention relates to the field of combined welding of aircraft engine barrel casing parts, and in particular to an angular positioning tool and method for welding of aircraft engine barrel casing. Background Art

[0002] The barrel casing parts are mainly connected by welding process, including the front mounting edge, the front section of the casing, the middle mounting edge, the rear section of the casing and the rear mounting edge, and the joint form is butt joint. The front section and the rear section of the casing are cylinders with equal wall thickness, and long strips of reinforcing ribs are evenly distributed along the circumference. The number of reinforcing ribs in the front section and the rear section are the same, and the distribution angle is the same. The direction of the reinforcing ribs is in the axial direction of the casing. During the welding process, special welding tools are usually used to constrain the butt joint to ensure the quality of the welded joint. When it is inconvenient to design the angular positioning function of the welding tool, the marking method is generally used for positioning welding.

[0003] Figure 1 The figure shows a schematic diagram of a typical cylinder casing part of an aircraft engine. The casing is a cylindrical structure, which is mainly connected by a front mounting edge 1, a casing shell front section 2, a middle mounting edge 3, a casing shell rear section 4 and a rear mounting edge 5 through a welding process, and the joint form is a butt joint. Figure 1 In the figure, a, b, c, and d represent welds. The front section 2 and the rear section 4 of the casing are both cylinders of equal wall thickness, and long strip reinforcement ribs are evenly distributed along the circumference. The number and distribution angle of the reinforcement ribs of the front section and the rear section are the same, and the direction of the reinforcement ribs is in the axial direction of the casing. The center lines of the angular holes 3a on the middle mounting edge 3 are coplanar with the reinforcement ribs at the corresponding positions of the front section 2 and the rear section 4 of the casing.

[0004] When welding the front section 2, the middle installation edge 3, and the rear section 4 of the casing, there is a problem that there is an assembly angle requirement before the parts are assembled and welded, that is, the center line of the angular hole 3a on the middle installation 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. During welding, a welding tool is used to expand and tighten the welding joint to meet the welding requirements and ensure the welding quality. However, the welding tool currently used does not have an angular positioning function. During assembly before welding, the center line of the angular hole 3a, the reinforcing rib of the front section 2 of the casing, and the reinforcing rib of the rear section 4 of the casing are generally ensured to be on the same plane by marking. It is inevitable that the marking will have different deviations due to the personal skill level of the operator, which will eventually lead to the above three deviations from the theoretical plane after welding. Angular inconsistency will occur during mass production of parts, and the quality of parts will be unstable. Severe deviation will cause the parts to be unable to be processed later and thus be scrapped. Summary of the invention

[0005] The main purpose of the invention is to provide an angular positioning tool and method for welding an aircraft engine barrel casing, so as to ensure that the front section of the casing shell, the rear section of the casing shell and the middle installation edge angular holes can meet the angular requirements after welding.

[0006] To achieve the above-mentioned purpose, on the one hand, the present invention proposes an angular positioning tool for welding an aircraft engine barrel casing, comprising a fixing plate and a positioning plate; a slot is provided on the fixing plate; a first positioning column and two second positioning columns are provided on the front side of the fixing plate; the first positioning column is used to be inserted into the angular hole of the middle mounting edge; the second positioning column is used to be inserted into the mounting hole of the middle mounting edge; the positioning plate is clamped in the slot; the two ends of the positioning plate are respectively inclined downward, and limiting slots are respectively provided at the two ends of the positioning plate, and the limiting slots are used to be clamped on the reinforcing ribs of the front section and the rear section of the casing shell; the symmetrical center plane of the limiting slot is coplanar with the center line of the first positioning column.

[0007] Preferably, the symmetric center plane of the slot is coplanar with the center line of the first positioning column; the limiting notch is coplanar with the symmetric center plane of the positioning plate.

[0008] Preferably, the two second positioning columns are respectively located on both sides of the first positioning column.

[0009] Preferably, a protruding block is integrally formed on the top surface of the positioning plate, and the clamping groove is provided on the protruding block of the positioning plate.

[0010] Preferably, the lower surface of the fixing plate is an arc surface, and when the fixing plate is assembled to the middle installation edge through the first positioning column and the second positioning column, the lower surface of the fixing plate is in contact with the outer peripheral surface of the middle installation edge.

[0011] Preferably, there is a transition fit between the positioning plate and the slot.

[0012] Preferably, the limiting groove forms a transition fit with the reinforcing ribs of the front section and the rear section of the receiver shell.

[0013] Preferably, the first positioning column and the second positioning column are connected to the positioning plate by welding, or the first positioning column, the second positioning column and the fixing plate are an integrally formed structure.

[0014] Preferably, the first positioning column is transitionally matched with the angular hole of the middle mounting edge; the second positioning column is transitionally matched with the mounting hole of the middle mounting edge.

[0015] On the other hand, the present invention also provides an angular positioning method for welding an aircraft engine barrel casing, using the above-mentioned angular positioning tool, comprising the following steps:

[0016] S1. Place the front mounting edge, the front section of the casing, the middle mounting edge, the rear section of the casing and the rear mounting edge on the welding tool in sequence;

[0017] S2, installing the fixing plate to the middle mounting edge, so that the first positioning column is inserted into the angular hole of the middle mounting edge, and the second positioning column is inserted into the mounting hole of the middle mounting edge;

[0018] S3. The positioning plate is clamped in the clamping groove of the fixing plate, and the front section and the rear section of the receiver shell are rotated so that the reinforcing ribs on the front section and the rear section of the receiver shell are respectively clamped in the limiting grooves of the positioning plate, thereby completing the angular positioning of the front section of the receiver shell, the middle installation edge, and the rear section of the receiver shell.

[0019] Due to the adoption of the above technical solution, the beneficial effects of the present invention are as follows:

[0020] (1) By adopting the angular positioning tool and method provided by the present invention, when performing angular positioning, the fixing plate is installed on the middle mounting edge, so that the first positioning column is inserted into the angular hole of the middle mounting edge, and 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 fixing plate, and the front section and the rear section of the receiver shell are rotated so that the reinforcing ribs on the front section and the rear section of the receiver shell are respectively clamped into the limiting grooves of the positioning plate, thereby completing the angular positioning of the front section of the receiver shell, the middle mounting edge, and the rear section of the receiver shell.

[0021] (2) The angular positioning tool provided by the present invention has a simple structure and is easy to use. It can quickly and accurately realize the angular positioning of parts, ensure the consistency of the angle of each part after welding, and ensure the stability of the angular quality of the parts. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying creative work.

[0023] Figure 1 This is a schematic diagram of a typical cylinder casing part of an aircraft engine;

[0024] Figure 2 This is a schematic diagram of the structure of the angular positioning tool provided by the present invention;

[0025] Figure 3 This is a schematic diagram of the angular positioning tool provided by the present invention in use.

[0026] Explanation of the accompanying figure numbers: 1. front mounting edge; 2. front section of the receiver shell; 3. middle mounting edge; 3a. angular hole; 3b. mounting hole; 4. rear section of the receiver shell; 5. rear mounting edge; 6. fixing plate; 6a. raised block; 6b. slot; 7. positioning plate; 7a. limiting notch; 8. first positioning column; 9. second positioning column. DETAILED DESCRIPTION

[0027] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0028] It should be noted that all directional indications in the embodiments of the present invention (such as up, down, left, right, front, back, etc.) are only used to explain the relative position relationship, movement status, etc. between the components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0029] In addition, the descriptions of "first", "second", etc. in the present invention are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In addition, the technical solutions between the various embodiments can be combined with each other, but they must be based on the ability of ordinary technicians in the field to implement them. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such a combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0030] Combination Figure 2 As shown, a specific embodiment of an angular positioning tool for welding an aircraft engine barrel casing provided by the present invention is provided, the angular positioning tool comprises a fixing plate 6 and a positioning plate 7; a slot 6b is provided on the fixing plate 6; a first positioning column 8 and two second positioning columns 9 are provided on the front side of the fixing plate 6; the first positioning column 8 is used to be inserted into the angular hole 3a of the middle mounting edge 3; the second positioning column 9 is used to be inserted into the mounting hole 3b of the middle mounting edge 3; the positioning plate 7 is clamped in the slot 6b; the two ends of the positioning plate 7 are respectively inclined downward, and limiting notches 7a are respectively provided at the two ends of the positioning plate 7, the limiting notches 7a are used to be clamped on the reinforcing ribs of the front section 2 and the rear section 4 of the casing shell; the symmetrical center plane of the limiting notch 7a is coplanar with the center line of the first positioning column 8.

[0031] In this embodiment, the apertures and circumferential distribution positions of the angular hole 3a and the two mounting holes 3b around the angular hole 3a on the mounting edge 3 are designed and manufactured in the positioning tool of the first positioning column 8 and the second positioning column 9, and the two second positioning columns 9 are respectively located on both sides of the first positioning column 8. When in use, the second positioning columns 9 are inserted into the mounting holes 3b on the left and right sides of the angular hole 3a.

[0032] Furthermore, the symmetric center plane of the clamping slot 6 b is coplanar with the center line of the first positioning column 8 ; and the limiting notch 7 a is coplanar with the symmetric center plane of the positioning plate 7 .

[0033] Combination Figure 2 As shown, a protruding block 6a is integrally formed on the top surface of the fixing plate 6, and the clamping groove 6b is provided on the protruding block 6a of the fixing plate 6. The integral molding method is adopted to facilitate the overall processing of the fixing plate 6 and the protruding block 6a.

[0034] In this embodiment, the lower surface of the fixing plate 6 is an arc surface. When the fixing plate 6 is assembled to 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 in contact with the outer peripheral surface of the middle mounting edge 3 to ensure that the fixing plate 6 can be stably installed on the middle mounting edge 3 to avoid radial movement.

[0035] In this embodiment, the positioning plate 7 and the clamping slot 6b form a transition fit. The limiting notch 7a forms a transition fit with the reinforcing ribs of the front section 2 and the rear section 4 of the casing. The first positioning column 8 forms a transition fit with the angular hole 3a of the middle mounting edge 3; the second positioning column 9 forms a transition fit with the mounting hole 3b of the middle mounting edge 3. The transition fit is suitable for occasions requiring precise positioning, because it allows a certain amount of clearance for easy assembly and adjustment, and allows a certain amount of interference to ensure the stability of the connection.

[0036] Combination Figure 2 As shown, the first positioning column 8 and the second positioning column 9 are connected to the fixing plate 6 by welding. Alternatively, the first positioning column 8, the second positioning column 9 and the fixing plate 6 are integrally formed.

[0037] Combination Figure 3 As shown, this embodiment also provides an angular positioning method for welding an aircraft engine barrel casing, using the above-mentioned angular positioning tool, comprising the following steps:

[0038] S1. Place the front mounting edge 1, the front section 2 of the casing shell, the middle mounting edge 3, the rear section 4 of the casing shell and the rear mounting edge 5 on the welding tool in sequence; the welding tool is conventional prior art and will not be described in detail here.

[0039] S2, installing the fixing plate 6 to the middle mounting edge 3, so that the first positioning column 8 is inserted into the angular hole 3a of the middle mounting edge 3, and the second positioning column 9 is inserted into the mounting hole 3b of the middle mounting edge 3.

[0040] S3, clamp the positioning plate 7 in the clamping groove 6a of the fixing plate 6, rotate the front section 2 of the casing shell and the rear section 4 of the casing shell, so that the reinforcing ribs on the front section 2 of the casing shell and the rear section 4 of the casing shell are respectively clamped in the limiting notches 7a of the positioning plate 7, and the angular positioning of the front section 2 of the casing shell, the middle installation edge 3 and the rear section 4 of the casing shell can be completed.

[0041] After completing the angular positioning by using the above method, the casing can be welded normally.

[0042] The above description is only a preferred embodiment of the present invention, and does not limit the patent scope of the present invention. All equivalent structural changes made by using the contents of the present invention specification and drawings under the inventive concept of the present invention, or directly / indirectly applied in other related technical fields are included in the patent protection scope of the present invention.

Claims

1. An angular positioning tool for welding an aircraft engine barrel casing, characterized in that: The invention comprises a fixing plate (6) and a positioning plate (7); a slot (6b) is provided on the fixing plate (6); a first positioning column (8) and two second positioning columns (9) are provided on the front side of the fixing plate (6); the first positioning column (8) is used to be inserted into the angular hole (3a) of the middle mounting edge (3); the second positioning column (9) is used to be inserted into the mounting hole (3b) of the middle mounting edge (3); the positioning plate (7) is clamped in the slot (6b); the two ends of the positioning plate (7) are respectively inclined downward, and limiting notches (7a) are respectively provided at the two ends of the positioning plate (7), and the limiting notches (7a) are used to be clamped on the reinforcing ribs of the front section (2) and the rear section (4) of the casing; the symmetric center plane of the limiting notch (7a) is coplanar with the center line of the first positioning column (8).

2. An angular positioning tool for welding an aircraft engine barrel casing as claimed in claim 1, characterized in that: The symmetrical center plane of the clamping slot (6b) is coplanar with the center line of the first positioning column (8); and the limiting notch (7a) is coplanar with the symmetrical center plane of the positioning plate (7).

3. The angular positioning tool for welding an aircraft engine barrel casing according to claim 1, characterized in that: The two second positioning columns (9) are respectively located on both sides of the first positioning column (8).

4. The angular positioning tool for welding an aircraft engine barrel casing according to claim 1, characterized in that: A protruding block (6a) is integrally formed on the top surface of the fixing plate (6), and the clamping groove (6b) is provided on the protruding block (6a) of the fixing plate (6).

5. The angular positioning tool for welding an aircraft engine barrel casing according to claim 1, characterized in that: The lower surface of the fixing plate (6) is an arc surface. When the fixing plate (6) is assembled onto 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 in contact with the outer peripheral surface of the middle mounting edge (3).

6. The angular positioning tool for welding an aircraft engine barrel casing according to claim 1, characterized in that: The positioning plate (7) and the clamping groove (6b) are in transitional fit.

7. The angular positioning tool for welding an aircraft engine barrel casing according to claim 1, characterized in that: The limiting notch (7a) forms a transition fit with the reinforcement ribs of the front section (2) and the rear section (4) of the casing shell.

8. The angular positioning tool for welding an aircraft engine barrel casing according to claim 1, characterized in that: The first positioning column (8) and the second positioning column (9) are connected to the fixing plate (6) by welding, or the first positioning column (8), the second positioning column (9) and the fixing plate (6) are an integrally formed structure.

9. The angular positioning tool for welding an aircraft engine barrel casing according to claim 1, characterized in that: The first positioning column (8) is transitionally matched with the angular hole (3a) of the middle installation edge (3); the second positioning column (9) is transitionally matched with the installation hole (3b) of the middle installation edge (3).

10. An angular positioning method for welding of an aircraft engine barrel casing, characterized in that: The angular positioning tool according to any one of claims 1 to 9 is used, comprising the following steps: S1, placing the front mounting edge (1), the front section of the casing (2), the middle mounting edge (3), the rear section of the casing (4) and the rear mounting edge (5) on a welding tool in sequence; S2, installing the fixing plate (6) to the middle mounting edge (3), so that the first positioning column (8) is inserted into the angular hole (3a) of the middle mounting edge (3), and the second positioning column (9) is inserted into the mounting hole (3b) of the middle mounting edge (3); S3, the positioning plate (7) is clamped in the clamping groove (6a) of the fixing plate (6), and the front section (2) and the rear section (4) of the casing are rotated so that the reinforcing ribs on the front section (2) and the rear section (4) of the casing are respectively clamped in the limiting grooves (7a) of the positioning plate (7), thereby completing the angular positioning of the front section (2), the middle mounting edge (3) and the rear section (4) of the casing.

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