CN110732795B - Welding method for aero-engine exhaust casing - Google Patents
Welding method for aero-engine exhaust casing Download PDFInfo
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- CN110732795B CN110732795B CN201911135719.5A CN201911135719A CN110732795B CN 110732795 B CN110732795 B CN 110732795B CN 201911135719 A CN201911135719 A CN 201911135719A CN 110732795 B CN110732795 B CN 110732795B
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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
- B23K28/00—Welding or cutting not covered by any of the preceding groups, e.g. electrolytic welding
- B23K28/02—Combined welding or cutting procedures or apparatus
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
- B23Q15/00—Automatic control or regulation of feed movement, cutting velocity or position of tool or work
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Abstract
The invention discloses a method for welding an aero-engine exhaust casing, which solves the problems of high processing precision requirement, multiple welding seams and compact space of the exhaust casing, improves the welding quality and meets the requirement of subsequent machining by reasonably arranging the welding sequence, the welding mode, the assembly sequence, the reference selection and the like of an outer ring front mounting edge (1), a support plate (2), a barrel front section (3), a mounting seat (4), an inner ring mounting edge (5), a barrel rear section (6), a central cone inclined section (7), an outer ring rear mounting edge (8), an exhaust pipe (9) and a reinforcing ring (10) which form an inner ring and an outer ring.
Description
Technical Field
The invention belongs to the technical field of plate welding manufacturing of aero-engines, and particularly relates to a combined welding method for an aero-engine exhaust casing.
Background
As shown in figure 1, the exhaust casing is a key part of an engine, the shape of the exhaust casing is phi 300mm in diameter and 270mm in height, the exhaust casing is formed by combining and welding a plurality of sheet metal parts, mounting edges, mounting seats and other parts, the assembly is compact in space and has a plurality of welding seams, and two welding processes of argon arc welding and resistance welding are involved. The requirement on the machining precision of parts is high, the size precision of the mounting edge is 0.03mm, and the form and position tolerance precision is 0.01 mm. The state of the welded assembly is critical to whether the later machining can meet the design requirements.
The prior combined welding method of the exhaust casing is immature, the positioning precision is not high during assembly welding, and the deformation is large after the assembly welding, so that the exhaust casing after machining often has an out-of-tolerance condition, the design requirement cannot be met, and the later assembly of the aero-engine is directly influenced. In order to improve the quality of the combined welding and control the state of the welded part to meet the requirement of subsequent machining, an efficient, stable and reasonable welding process route needs to be found out, the product quality is ensured, and a solid foundation is laid for the rapid development of the aircraft engine.
Disclosure of Invention
The invention aims to provide a combined welding method of an aero-engine exhaust casing aiming at the exhaust casing, which effectively controls the deformation of a combined welding part of the exhaust casing so as to ensure that a final delivered product of the exhaust casing meets the design requirement.
The technical scheme adopted by the invention is as follows:
the structure of the aero-engine exhaust casing comprises an inner ring part, an outer ring part, a support plate and the like. The front mounting edge of the outer ring part is connected with the front section of the cylinder body through argon arc welding, the rear section of the cylinder body is connected with the front section of the cylinder body through argon arc welding, and the rear section of the cylinder body is connected with the rear mounting edge of the outer ring through resistance welding; the inner ring mounting edge of the inner ring part is connected with the central cone inclined section through argon arc welding, the central cone inclined section is connected with the exhaust pipe through argon arc welding, and the central cone inclined section is connected with the reinforcing ring through argon arc welding; the inner ring and the outer ring are connected through support plates by argon arc welding. The mounting seat is welded on the outer ring through argon arc welding, and a central exhaust hole machined in a part needs to extend through a support plate with a narrow space to penetrate through to the mounting edge of the inner ring.
The combined welding steps of the exhaust casing are as follows:
1.1, butting the front mounting edge of the outer ring with the welding edge of the front section of the cylinder, correcting to ensure that the gap of the butted part is less than or equal to 0.3mm and the misalignment amount is less than or equal to 0.3mm, and symmetrically positioning 25-30 points by using argon arc welding points;
1.2 welding the butt joint of the step 1.1 into an assembly I through argon arc welding;
1.3 installing an edge reference surface 1A in front of an outer ring of the vehicle repairing assembly I;
1.4 taking the 1A as a reference, and installing an edge reference surface 1B before the outer ring is lathed and repaired;
1.5 processing a welding process bottom hole 3A of the front section of the cylinder by using a numerical control machine tool by taking a reference surface 1B of the front mounting edge of the outer ring as a reference;
1.6 connecting the assembly I and the inner ring mounting edge into an assembly II through a support plate by argon arc welding, ensuring that the clearance between a first surface 2A on the support plate and a second surface 3B on the front section of the cylinder body and the clearance between a third surface 2B on the support plate and a fourth surface 5A on the inner ring mounting edge are less than or equal to 0.3 before the argon arc welding, and simultaneously inserting a core rod into a welding process bottom hole 3A on the front section of the cylinder body along the radial direction to ensure that the core rod passes through an inner cavity 2C of the support plate without interference;
1.7, carrying out related welding quality inspection on the assembly II;
1.8 butting the inclined section of the central cone with the welding edge of the exhaust pipe, and correcting to ensure that the gap at the butting position is less than or equal to 0.3 and the misalignment amount is less than or equal to 0.3;
1.9 connecting the butt joint of the step 1.8 into an assembly III through argon arc welding;
1.10 marking to ensure the relative position of the reinforcing ring on the assembly III, and connecting the reinforcing ring and the assembly III through argon arc welding;
1.11 butting the welding edges of the assembly III and the assembly II, and correcting to ensure that the gap of the butting position is less than or equal to 0.3 and the misalignment amount is less than or equal to 0.3;
1.12 connecting the butt joint of the step 1.11 into an assembly IV through argon arc welding;
1.13, carrying out welding quality inspection on the welding seam formed in the step 1.12;
1.14 butting the rear section of the cylinder with the welding edge of the assembly IV, and correcting to ensure that the gap at the butting position is less than or equal to 0.3 and the misalignment amount is less than or equal to 0.3;
1.15 connecting the butt joint of the step 1.14 by argon arc welding to form an assembly V;
1.16, carrying out welding quality inspection on the welding seam formed in the step 1.15;
1.17 tightly abutting the mounting seat on the outer surface of the front section of the cylinder body, fixing the mounting seat by using a rigid fixing device, ensuring that a central exhaust hole 4A of the mounting seat and the center of a welding process bottom hole 3A of the front section of the cylinder body are in the same radial direction, and ensuring that the gap at the joint part is less than or equal to 0.2;
1.18 connecting the mounting seat in the step 1.17 with the front section of the cylinder body through argon arc welding, overlapping the rear mounting edge of the outer ring with the assembly V, and connecting the overlapped part through resistance welding to finish the welding of parts;
1.19, carrying out welding quality inspection on the welding seam formed by the 1.18 lap joint;
1.20 the welding of the parts is finished.
Compared with the prior art, the invention provides the combined welding process method for the aero-engine exhaust casing, and the process method is high in efficiency, stable in quality and reasonable in welding through continuous exploration and summary. The invention improves the welding efficiency of the exhaust casing and saves the waste cost.
Drawings
FIG. 1 is a schematic illustration of a welding sequence for an exhaust casing;
FIG. 2 is a schematic illustration of an exhaust casing weld profile;
figure 3 is a cross-sectional view of the coupling device in two parts, inner and outer ring.
Detailed Description
The technical solution of the present invention is further explained below with reference to the accompanying drawings, but the claimed protection scope is not limited to the above.
Referring to fig. 1, the structure of the aero-engine exhaust casing is composed of an inner ring portion, an outer ring portion, a support plate and the like. The outer ring front mounting edge 1 of the outer ring part is connected with the barrel front section 3 through argon arc welding, the barrel rear section 6 is connected with the barrel front section 3 through argon arc welding, and the barrel rear section 6 is connected with the outer ring rear mounting edge 8 through resistance welding; the inner ring mounting edge 5 of the inner ring part is connected with the central cone inclined section 7 through argon arc welding, the central cone inclined section 7 is connected with the exhaust pipe 9 through argon arc welding, and the central cone inclined section 7 is connected with the reinforcing ring 10 through argon arc welding; the inner ring and the outer ring are connected through the support plate 2 in an argon arc welding mode. The mounting seat 4 is welded on the outer ring through argon arc welding, and a central exhaust hole processed on a part needs to extend through a support plate with a narrow space to penetrate through the inner ring mounting edge 5.
Referring to fig. 1-3, the method for welding the combination of the exhaust casings of the aircraft engines is implemented according to the following steps:
1.1, according to the figure 2, supporting a reference A, centering a reference B, tensioning a butt joint A1 of a welding line, pressing a 3 end face 3C of the front section of the cylinder body to clamp a part, and correcting to ensure that the gap of the butt joint of the welding line is less than or equal to 0.3mm and the misalignment amount is less than or equal to 0.3 mm;
1.2, after the welding device is checked to work normally, adjusting the parameters of the welding machine, and forming an assembly I by argon arc welding weld seam No. 1;
1.3, performing related inspection of the weld joint on the weld joint No. 1 in FIG. 2;
1.4, turning and repairing a reference surface 1A in the figure 1, taking the reference surface 1A as a reference, turning and repairing a mounting edge reference surface 1B before the outer ring, taking a surface 1B as a reference, drilling a welding process bottom hole 3A on the front section 3 of the spray pipe barrel, and enabling the size of the welding process bottom hole 3A to be consistent with that of a hole 2C in the figure 3;
1.5, fixing the assembly I by a supporting datum A, a centering datum B and a pressing end face B1, fixing the assembly I by a supporting datum C, a centering datum D and a pressing end face C1, and fixing the inner ring mounting edge 5 in the figure 1;
1.6, the support plate 2 in the figure 1 is arranged between the assembly I and the inner ring mounting edge 5 according to the position shown in the figure, according to the figure 3 (the section schematic diagram of the connecting part C-C of the inner ring and the outer ring), a support reference D1 and positioning references D2 and D3 are used for fixing and clamping the support plate 2, the central line of the section of the support plate and the axial direction of a part form an angle of 10 degrees, and meanwhile, the gap between the support plate 2 and the wall surface of a main body is not more than 0.3mm, and the support plate 2;
1.7, according to the figure 1, when the support plate 2 is welded in a positioning welding mode, a core rod needs to be inserted into a bottom hole 3A and a hole 2C of a welding process, the positions of the two holes are ensured to be in the same radial direction, meanwhile, the core rod cannot interfere when being inserted into the support plate 2, the hole 2C of the support plate 2 is corrected when the core rod is not satisfied, and the support plate 2 is not damaged when the bottom hole 3A of the subsequent drilling welding process penetrates through an inner ring installation edge 5 on the inner ring wall;
1.8, adjusting welding parameters, and symmetrically and uniformly positioning 6 points along the edge of the argon arc welding positioning support plate 2;
1.9, after the position of the support plate 2 is fixed, taking down the rigid clamping and positioning device, then welding the support plate 2 by formal argon arc welding, and forming an assembly II after welding;
1.10, carrying out related quality inspection on the welded seam No. 5;
1.11, butting the inclined section 7 of the central cone with the welding edge of an exhaust pipe 9, correcting to ensure that the gap at the butted position is less than or equal to 0.3mm and the misalignment amount is less than or equal to 0.3mm, symmetrically positioning 8 points by argon arc welding, and uniformly distributing welding points;
1.12, forming a butt joint surface in an argon arc welding step 1.11 to form an assembly III;
1.13, scribing lines at the positions of the reinforcing rings 10 on the assembly III, wherein the depth of the scribed lines is less than or equal to 0.2mm, correcting to ensure that the gap between the reinforcing rings 10 and the main body is less than or equal to 0.3mm, and uniformly positioning 4-6 points through argon arc welding;
1.14, welding the butt joint of the step 1.13 into an assembly III through argon arc welding;
1.15, carrying out welding quality inspection on the argon arc welding seam No. 4 and the argon arc welding seam No. 6 of the assembly III;
1.16, butting the welding edge of the assembly III with the welding edge of the assembly II, correcting to ensure that the gap of the butted part is less than or equal to 0.3mm and the misalignment amount is less than or equal to 0.3mm, and symmetrically positioning 10-14 points by argon arc welding;
1.17, forming an assembly IV at the butt joint (the argon arc welding seam No. 3 position) of the step 1.16 by argon arc welding;
1.18, carrying out welding quality inspection on a welding seam No. 3 of the assembly IV;
1.19, butting the welding edge of the rear section 6 of the cylinder with the welding edge of the assembly IV, correcting to ensure that the gap is less than or equal to 0.3mm and the misalignment amount is less than or equal to 0.3mm, and positioning 10-12 points by argon arc welding;
1.20, carrying out argon arc welding on the butt joint (the argon arc welding seam No. 2 position) in the step 1.19 to form an assembly V;
1.21, carrying out welding quality inspection on the argon arc welding weld joint No. 2;
1.22, machining an outer ring front mounting edge 1, an inner ring mounting edge 5 and a mounting seat 4 in a numerical control manner to meet the requirements of a design drawing;
1.23, turning and repairing an end surface 6A of the rear section 6 of the cylinder body;
1.24, scribing lines at the position of the rear mounting edge 8 of the outer ring on the rear section 6 of the cylinder;
1.25, correcting to ensure that the gap between the rear mounting edge 8 of the outer ring and the rear section 6 of the cylinder body is less than or equal to 0.3mm, and connecting the two through resistance welding;
and 1.26, finishing the welding process of the parts.
Claims (10)
1. A welding method for an aero-engine exhaust casing comprises an inner ring part, an outer ring part and a support plate, wherein the outer ring front mounting edge (1) of the outer ring part is connected with a cylinder front section (3), a cylinder rear section (6) is connected with the cylinder front section (3), and the cylinder rear section (6) is connected with an outer ring rear mounting edge (8); the utility model discloses a section of building up the gas turbine, including inner ring part inner ring installation limit (5) and central awl inclined segment (7) are connected, and central awl inclined segment (7) are connected with blast pipe (9), and central awl inclined segment (7) are connected with strengthening ring (10), and two parts of inner ring, outer loop pass through the extension board and connect, its characterized in that includes following step:
1.1, butting the front mounting edge (1) of the outer ring with the welding edge of the front section (3) of the cylinder body;
1.2 welding the butt joint of the step 1.1 into an assembly I through argon arc welding;
1.3 repairing the outer ring front mounting edge (1) of the assembly I by a vehicle to form a datum plane (1A);
1.4 taking the reference surface (1A) as a reference to vehicle repair the front end surface reference surface (1B) of the outer ring front mounting edge (1);
1.5 processing a welding process bottom hole (3A) of the front section (3) of the cylinder by taking a reference surface (1B) of the front end surface of the outer ring front mounting edge (1) as a reference;
1.6 connecting the assembly I and the inner ring mounting edge (5) into an assembly II through argon arc welding by a support plate (2);
1.8 butting the welding edges of the central cone inclined section (7) and the exhaust pipe (9);
1.9 connecting the butt joint of the step 1.8 into an assembly III through argon arc welding;
1.10 ensuring the relative position of the reinforcing ring (10) on the assembly III and connecting the reinforcing ring and the assembly III through argon arc welding;
1.11 butting the welding edges of the assembly III and the assembly II;
1.12 connecting the butt joint of the step 1.11 into an assembly IV through argon arc welding;
1.14 butting the rear section (6) of the cylinder body with the welding edge of the assembly IV;
1.15 connecting the butt joint of the step 1.14 by argon arc welding to form an assembly V;
1.17 tightly abutting the mounting seat (4) on the outer surface of the front barrel section (3), fixing the mounting seat (4) and ensuring that a central exhaust hole (4A) of the mounting seat (4) and the center of a welding process bottom hole (3A) of the front barrel section (3) are in the same radial direction;
1.18 connecting the mounting seat (4) in the step 1.17 with the front section (3) of the cylinder body through argon arc welding;
1.19, overlapping the rear mounting edge (8) of the outer ring with the assembly V;
1.20 the lap joint of step 1.19 is connected by resistance welding to complete the welding of the parts.
2. The aircraft engine exhaust casing welding method according to claim 1, characterized in that: in the step 1.1, after the front mounting edge (1) of the outer ring is butted with the welding edge of the front section (3) of the cylinder body, correction is needed, the gap of the butted part is ensured to be less than or equal to 0.3mm, the misalignment amount is ensured to be less than or equal to 0.3mm, and 25-30 points are symmetrically positioned by argon arc welding points.
3. The aircraft engine exhaust casing welding method according to claim 1, characterized in that: and in the step 1.5, a bottom hole (3A) of the welding process is machined by a numerical control machine.
4. The aircraft engine exhaust casing welding method according to claim 1, characterized in that: in the step 1.6, before argon arc welding, the gap between the first surface (2A) on the support plate (2) and the second surface (3B) on the barrel front section (3) and the gap between the third surface (2B) on the support plate (2) and the fourth surface (5A) on the inner ring mounting edge (5) are ensured to be less than or equal to 0.3mm, and meanwhile, a core rod is required to be inserted into a welding process bottom hole (3A) of the barrel front section (3) along the radial direction, so that the core rod is ensured to pass through the inner cavity (2C) of the support plate (2) and is not interfered.
5. The aircraft engine exhaust casing welding method according to claim 1, characterized in that: in the step 1.8, after the welding edges of the central cone inclined section (7) and the exhaust pipe (9) are butted, correction is needed, the gap of the butted part is ensured to be less than or equal to 0.3mm, and the misalignment amount is less than or equal to 0.3 mm.
6. The aircraft engine exhaust casing welding method according to claim 1, characterized in that: the relative position of the reinforcing ring (10) on the assembly III is ensured in step 1.10 by scribing.
7. The aircraft engine exhaust casing welding method according to claim 1, characterized in that: in the step 1.11, after the welding edges of the assembly III and the assembly II are butted, correction is needed, the gap of the butted part is less than or equal to 0.3mm, and the misalignment amount is less than or equal to 0.3 mm.
8. The aircraft engine exhaust casing welding method according to claim 1, characterized in that: in the step 1.14, after the rear section (6) of the cylinder body is butted with the welding edge of the assembly IV, correction is needed, the gap of the butted part is ensured to be less than or equal to 0.3mm, and the misalignment amount is less than or equal to 0.3 mm.
9. The aircraft engine exhaust casing welding method according to claim 1, characterized in that: in the step 1.17, the mounting seat (4) is fixed by a rigid fixing device, and meanwhile, the gap between the joint of the mounting seat (4) and the front section (3) of the cylinder body is ensured to be less than or equal to 0.2 mm.
10. The aircraft engine exhaust casing welding method according to claim 1, characterized in that:
the step 1.7 is also included between the step 1.6 and the step 1.8: carrying out welding quality inspection on the assembly II;
step 1.13 is also included between step 1.12 and step 1.14: carrying out welding quality inspection on the welding seam formed in the step 1.12;
step 1.16 is also included between step 1.15 and step 1.17: carrying out welding quality inspection on the welding seam formed in the step 1.15;
and after the step 1.18, performing welding quality inspection on the welding seam formed by the 1.18 lap joint.
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| CN201911135719.5A CN110732795B (en) | 2019-11-19 | 2019-11-19 | Welding method for aero-engine exhaust casing |
| PCT/CN2020/072231 WO2021098035A1 (en) | 2019-11-19 | 2020-01-15 | Aircraft engine exhaust casing welding method |
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| CN201911135719.5A CN110732795B (en) | 2019-11-19 | 2019-11-19 | Welding method for aero-engine exhaust casing |
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| CN110732795B true CN110732795B (en) | 2021-04-06 |
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| CN113664456B (en) * | 2021-08-10 | 2022-09-06 | 西安远航真空钎焊技术有限公司 | Combustion chamber barrel repairing method based on compensation structure |
| CN114654052A (en) * | 2022-05-05 | 2022-06-24 | 中国航发航空科技股份有限公司 | Welding process for thin-wall metal plate welding large casing |
| CN115475969A (en) * | 2022-09-29 | 2022-12-16 | 中国航发动力股份有限公司 | Machining method for combined turning of gas turbine case |
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| WO2021098035A1 (en) | 2021-05-27 |
| CN110732795A (en) | 2020-01-31 |
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