CN110732795A - aircraft engine exhaust casing welding method - Google Patents
aircraft engine exhaust casing welding method Download PDFInfo
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- CN110732795A CN110732795A CN201911135719.5A CN201911135719A CN110732795A CN 110732795 A CN110732795 A CN 110732795A CN 201911135719 A CN201911135719 A CN 201911135719A CN 110732795 A CN110732795 A CN 110732795A
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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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- Butt Welding And Welding Of Specific Article (AREA)
- Exhaust Silencers (AREA)
Abstract
The invention discloses a aeroengine exhaust casing welding method, which overcomes the problems of high processing precision requirement, more welding seams and compact space of an 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 cylinder front section (3), a mounting seat (4), an inner ring mounting edge (5), a cylinder 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 aeroengine sheet welding manufacturing, and particularly relates to a combined welding method for aeroengine exhaust casings.
Background
As shown in FIG. 1, the exhaust casing is a key part of engines, and the shape of the exhaust casing is a diameter
The height is 270mm, and the welding assembly is formed by combining and welding a plurality of sheet metal parts, mounting edges, mounting seats and other parts, has compact space and more welding seams, and relates to two welding processes of argon arc welding and resistance welding. 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.
In order to improve the quality of the combined welding and control the state of the welded parts to meet the requirements of subsequent machining, efficient, stable and reasonable welding process routes need to be found out to ensure the product quality and lay a solid foundation for the rapid development of the aircraft engine.
Disclosure of Invention
The invention aims to provide combination welding methods of an aeroengine exhaust casing aiming at the exhaust casing, which effectively control the deformation of a combination welding part of the exhaust casing so as to ensure that the 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 aeroengine 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 1A as a reference to vehicle repair reference surface 1B;
1.5 machining a welding process bottom hole 3A of a mounting seat and a support plate on the assembly I by using a numerical control machine tool by taking the reference surface 1B 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 a gap between the th surface 2A on the support plate and the second surface 3B on the front section of the cylinder body as well as a gap between the third surface 2B on the support plate and the fourth surface 5A on the inner ring mounting edge is 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 the 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, fixing the mounting seat by using a rigid fixing device, ensuring that the center exhaust hole 4A of the mounting seat and the center of the welding process bottom hole 3A of the front section of the cylinder are in the same radial direction of , and ensuring that the gap at the joint part is less than or equal to 0.2;
1.18, connecting the lap joint in the step 1.17 by argon arc welding, lapping the rear mounting edge of the outer ring and the assembly V, and connecting the lap joint by 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 a combined welding process method for aeroengine exhaust casings, which is a process method with high efficiency, stable quality and reasonable welding of types formed by continuous groping and summarization.
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 illustrated in below with reference to the drawings, but the scope of protection claimed is not limited to the above.
Referring to fig. 1, the structure of the exhaust casing of the aircraft engine comprises an inner ring part, an outer ring part and a support plate. The outer ring front mounting edge 1 of the outer ring part is connected with the cylinder front section 3 through argon arc welding, the cylinder rear section 6 is connected with the cylinder front section 3 through argon arc welding, and the cylinder 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, turning and repairing a reference surface 1B by taking the reference surface 1A as a reference, drilling a welding process bottom hole 3A on the front section 3 of the spray pipe barrel by taking a surface 1B as a reference, and enabling the size of the welding process bottom hole 3A to be equal to that of a hole 2C in the figure 3 to be ;
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 installation 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 angles of 10 degrees, 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 is corrected;
1.7, according to the figure 1, when the support plate 2 is welded in a positioning welding mode, core rods need to be inserted into bottom holes 3A and holes 2C of the welding process, the positions of the two holes are ensured to be in radial directions, meanwhile, the core rods cannot interfere when being inserted into the support plate 2, the holes 2C of the support plate 2 are corrected when the positions are not met, and the support plate 2 is not damaged when the bottom holes 3A of the subsequent drilling welding process penetrate through an inner ring mounting 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, aeroengine exhaust casing welding method, characterized by, including the 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 vehicle repairing reference surface (1B);
1.5 processing a mounting seat (4) and a welding process bottom hole (3A) of a support plate (2) on the assembly I by taking a reference surface (1B) 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 the center exhaust hole (4A) of the mounting seat (4) and the center of the welding process bottom hole (3A) of the front barrel section (3) are in the same radial direction of ;
1.18 connecting the lap joints in the step 1.17 by 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 method for welding the aero-engine exhaust casing according to claim 1, wherein in 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 to ensure that the gap at the butted position is less than or equal to 0.3mm and the misalignment is less than or equal to 0.3mm, and the argon arc welding points are used for symmetrically positioning 25 to 30 points.
3. The method for welding the exhaust casing of aircraft engine according to claim 1, wherein step 1.5 is performed by machining a welding bottom hole (3A) with a numerically controlled machine.
4. The method for welding the aero-engine exhaust casing according to claim 1, wherein in step 1.6, before argon arc welding, it is ensured that a gap between the surface (2A) on the support plate (2) and the second surface (3B) on the front barrel section (3) and a gap between the third surface (2B) on the support plate (2) and the fourth surface (5A) on the inner ring mounting edge (5) are less than or equal to 0.3mm, and simultaneously, a mandrel needs to be inserted into a welding process bottom hole (3A) of the front barrel section (3) along a radial direction, so that the mandrel is ensured to pass through the inner cavity (2C) of the support plate (2) without interference.
5. The method for welding the aero-engine exhaust casing according to claim 1, wherein in step 1.8, after the welding edges of the central cone inclined section (7) and the exhaust pipe (9) are butted, correction is needed to ensure that the gap at the butted position is less than or equal to 0.3mm and the misalignment is less than or equal to 0.3 mm.
6. The method of claim 1, wherein the relative position of the stiffener ring (10) on the assembly III is ensured by scribing in step 1.10.
7. The method for welding the aero-engine exhaust casing according to claim 1, wherein in step 1.11, after the welding edges of the assembly III and the assembly II are butted, the welding edges need to be corrected to ensure that the gap at the butted position is less than or equal to 0.3mm and the misalignment is less than or equal to 0.3 mm.
8. The method for welding the aero-engine exhaust casing according to claim 1, wherein in 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 to ensure that the gap at the butted position is less than or equal to 0.3mm and the misalignment is less than or equal to 0.3 mm.
9. The method for welding the aero-engine exhaust casing according to claim 1, wherein in step 1.17, the mounting seat (4) is fixed by a rigid fixing device, and a gap between the mounting seat (4) and the joint of the cylinder front section (3) is less than or equal to 0.2 mm.
10. The method of welding an aircraft engine exhaust casing according to claim 1, wherein:
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.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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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| Application Number | Priority Date | Filing Date | Title |
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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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| CN110732795A true CN110732795A (en) | 2020-01-31 |
| CN110732795B CN110732795B (en) | 2021-04-06 |
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Cited By (3)
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| CN113664456A (en) * | 2021-08-10 | 2021-11-19 | 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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| 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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| Publication number | Publication date |
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| WO2021098035A1 (en) | 2021-05-27 |
| CN110732795B (en) | 2021-04-06 |
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