Aviation radiator corrugated plate lap joint structure and welding method

Abstract

The invention discloses an aviation radiator corrugated plate lap joint structure and a welding method, the lap joint structure comprises a first assembly and a second assembly, the first assembly is connected with the second assembly, the first assembly comprises a corrugated plate and a first shell, and the second assembly comprises a corrugated plate and a second shell. When the welding assembly structure of the corrugated plate, the first shell and the second shell is in lap joint argon arc welding, the assembly positions of the corrugated plate, the first shell and the second shell need to be manually provided with zigzag notches according to the waveform of the corrugated plate; a linear special-shaped welding seam of front lap joint argon arc welding in the prior art is improved into a curled edge argon arc welding linear welding seam, after the first connecting part and the second connecting part are additionally arranged and are changed into curled edge argon arc welding, secondary repairing and matching do not need to be conducted in the machining process of the first shell and the second shell any more, and the product machining period is shortened.

Description

Technical Field

[0001] The invention belongs to the technical field of curved cavity structures, and in particular relates to an aviation radiator corrugated plate overlap structure and a welding method. Background Art

[0002] The product structure of the annular aircraft is an annular cavity structure, and the product is mainly processed by resistance welding and argon arc welding. As a core functional part, the corrugated plate has the characteristics of large size and thin material thickness. Due to the thinning effect of sheet metal forming of parts, the material thickness will be thinner after the parts are formed. Therefore, the corrugated plate will burn through when it is welded with other parts after assembly, making it difficult to ensure the welding quality. The qualified rate of one-time welding is low, resulting in product scrapping and causing great waste and loss in the production process. Therefore, in order to improve the qualified rate of such corrugated plate welding and reduce production waste, measures are taken from the source of the structure to improve it by improving the welding structure between the corrugated plate and other parts.

[0003] The patent document with announcement number CN117419603A discloses an annular plate-fin heat sink and a processing method thereof. The invention adopts a corrugated plate structure that radiates radially outward uniformly. The main structure welding mode is an integrated brazing welding. When the core of the heat sink is welded, the annular fins and the inner and outer cylinders are interference fit. The corrugated plate is a rectangular serrated setting that radiates radially outward uniformly, and the two ends are respectively connected to the inner and outer cylinders. However, the corrugated plate does not need to be stretched to a large size, and its thickness is not thinned by the stretching. The welding method is not suitable for corrugated plates with thinner thickness. Summary of the invention

[0004] In order to solve the above technical problems, the present invention provides an aircraft radiator corrugated plate overlap structure and a welding method.

[0005] The present invention is achieved through the following technical solutions.

[0006] The present invention provides an aviation radiator corrugated plate overlap structure, comprising a first assembly and a second assembly, wherein the first assembly and the second assembly are connected, the first assembly comprising a corrugated plate and a first shell, and the second assembly comprising a corrugated plate and a second shell.

[0007] Preferably, the first shell includes a first connecting plate and a first fixing portion, both ends of the first connecting plate are respectively connected to the first fixing portion, both sides of the first connecting plate are connected to the corrugated plate, and the first fixing portion is connected to the corrugated plate.

[0008] Preferably, the first connecting plate is connected to the corrugated plate via a first connecting portion, and the first connecting portion is formed by bending an edge of the first connecting plate.

[0009] Preferably, a first slot and a second slot are provided on the first connecting plate.

[0010] Preferably, the second shell includes a second connecting plate and a second fixing portion, both ends of the second connecting plate are respectively connected to the second fixing portion, both sides of the second connecting plate are connected to the corrugated plate, and the second fixing portion is connected to the corrugated plate.

[0011] Preferably, the second connecting plate is connected to the corrugated plate via a second connecting portion, and the second connecting portion is formed by bending an edge of the second connecting plate.

[0012] Preferably, a third slot is provided on the second connecting plate.

[0013] Preferably, the assembly gap between the corrugated plate and the first shell and the second shell is no more than 1.5 mm.

[0014] A welding method for an aircraft radiator corrugated plate overlap structure comprises the following steps:

[0015] 1) Preparation: clean the dirt on the surface of the corrugated plate, the first shell and the second shell;

[0016] 2) Assembling the corrugated plate, the first shell and the second shell to obtain a first assembly and a second assembly;

[0017] 3) Use auxiliary tools to seal the assembly gaps between the corrugated plate and the first shell, and between the corrugated plate and the second shell;

[0018] 4) Insert the air pipe into the first assembly and the second assembly, and introduce protective gas into the first assembly and the second assembly;

[0019] 5) Turn on the argon arc welding equipment and perform test welding on the test plate according to the confirmed debugging parameters;

[0020] 6) After the test welding is qualified, the connection between the corrugated plate and the first shell, and the connection between the corrugated plate and the second shell are welded according to the qualified parameters;

[0021] 7) After welding, check whether there is oxidation on the back of the weld. If there is oxidation, clean it. The weld surface is qualified if there are no cracks, holes, burn-through, etc.

[0022] Preferably, the shielding gas in step 4) is argon, the argon flow rate is 15-30 L / min, and the duration is 1-8 min; and the welding current in step 6) is 25-35 A.

[0023] The beneficial effects of the present invention are:

[0024] 1) When the corrugated plate and the first shell and the second shell are welded and assembled by lap argon arc welding, the assembling positions of the corrugated plate and the first shell and the second shell need to be manually trimmed with serrated notches according to the waveform of the corrugated plate. The linear special-shaped weld of the front lap argon arc welding in the existing process is improved to a straight weld of the rolled argon arc welding, and the first connecting part and the second connecting part are added and changed to the rolled argon arc welding. It is no longer necessary to perform secondary trimming of the first shell and the second shell processing process, thereby shortening the product processing cycle.

[0025] 2) By setting the first connecting part and the second connecting part, a welding buffer area of ​​the corrugated plate is increased to avoid direct heat transfer to the corrugated plate body, thereby solving the quality problems of burn-through and thermal deformation of the corrugated plate during welding. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 is a schematic structural diagram of a first assembly of the present invention;

[0027] Figure 2 is a schematic AA cross-sectional view of the second assembly of the present invention;

[0028] Figure 3 It is a schematic diagram of the structure of region B of the present invention;

[0029] Figure 4 is a schematic structural diagram of a second assembly of the present invention;

[0030] Figure 5 is a schematic cross-sectional view taken along line BB of the second assembly of the present invention;

[0031] Figure 6 It is a schematic diagram of the structure of region A of the present invention;

[0032] In the figure: 1-corrugated plate, 2-first shell, 21-first connecting plate, 22-first fixing part, 23-first connecting part, 24-first slot, 25-second slot, 3-second shell, 31-second connecting plate, 32-second fixing part, 33-second connecting part, 34-third slot. DETAILED DESCRIPTION

[0033] The technical solution of the present invention is further described below, but the scope of protection claimed is not limited to the description.

[0034] Embodiment 1:

[0035] like Figures 1 to 6 As shown, a corrugated plate overlap structure of an aircraft radiator includes a first assembly and a second assembly, wherein the first assembly and the second assembly are connected, the first assembly includes a corrugated plate 1 and a first shell 2, and the second assembly includes a corrugated plate 1 and a second shell 3.

[0036] The corrugated plate 1 is formed of an integral sheet material and is close to a semicircular structure, and its cross section is wavy. The two ends of the corrugated plate 1 are bent into a J-shaped structure. The corrugated plate 1 is connected to the first shell 2 and the second shell 3 through the J-shaped structure end, and is used for air diversion. The matching quantity is set to 2;

[0037] The first shell 2 is assembled with the corrugated plate 1 by crimping welding;

[0038] The second shell 3 is assembled with the corrugated plate 1 by crimping welding;

[0039] Then, the first shell 2 and the second shell 3 are assembled with the corrugated plate 1 by crimping welding, respectively, to form a full-circle cavity with two corrugated plates 1 on the inner side.

[0040] The first shell 2 includes a first connecting plate 21 and a first fixing portion 22. Both ends of the first connecting plate 21 are respectively connected to the first fixing portion 22. The length of the first fixing portion 22 is greater than the width of the first connecting plate 21. Both sides of the first connecting plate 21 are connected to the corrugated plate 1. The first fixing portion 22 is connected to the corrugated plate 1.

[0041] The first connecting plate 21 is connected to the corrugated plate 1 via a first connecting portion 23 , which is formed by bending the edge of the first connecting plate 21 , and a corresponding bent connecting portion is provided at the edge of the corrugated plate 1 for welding after being fitted with the first connecting portion 23 .

[0042] The first connecting plate 21 is provided with a first slot 24 and a second slot 25. The first slot 24 is provided at two locations, and the second slot 25 is extended along the length direction of the first connecting plate 21. The first slot 24 and the second slot 25 can be used for gas circulation and pipeline passage.

[0043] The second shell 3 includes a second connecting plate 31 and a second fixing portion 32. Both ends of the second connecting plate 31 are respectively connected to the second fixing portion 32. The length of the second fixing portion 32 is greater than the width of the second connecting plate 31. Both sides of the second connecting plate 31 are connected to the corrugated plate 1. The second fixing portion 32 is connected to the corrugated plate 1.

[0044] The second connecting plate 31 is connected to the corrugated plate 1 via a second connecting portion 33 , which is formed by bending the edge of the second connecting plate 31 , and a corresponding bent connecting portion is provided at the edge of the corrugated plate 1 for welding after being fitted with the second connecting portion 33 .

[0045] The second connecting plate 31 is provided with third slots 34, and the third slots 34 are provided in parallel at a plurality of locations. The third slots 34 can be used for gas circulation.

[0046] The assembly gap between the corrugated plate 1 and the first shell 2 and the second shell 3 is not greater than 1.5 mm to ensure that the assembly welding surface is flush.

[0047] A welding method for an aircraft radiator corrugated plate overlap structure comprises the following steps:

[0048] 1) Preparation: Use a rag to clean the dirt on the surface of the corrugated plate 1, the first shell 2 and the second shell 3;

[0049] 2) Assembling the corrugated plate 1, the first shell 2 and the second shell 3 to obtain a first assembly and a second assembly;

[0050] 3) Use auxiliary tool tape to seal the assembly gaps between the corrugated plate 1 and the first shell 2, and between the corrugated plate 1 and the second shell 3;

[0051] 4) Turn on the switch of the argon gas cylinder, insert the gas pipe deep into the first assembly and the second assembly, and introduce the protective gas into the first assembly and the second assembly;

[0052] 5) Turn on the argon arc welding equipment and perform test welding on the test plate according to the confirmed debugging parameters;

[0053] 6) After the test welding is qualified, the connection between the corrugated plate 1 and the first shell 2, and the connection between the corrugated plate 1 and the second shell 3 are welded according to the qualified parameters. Pay attention to the color of the weld during the welding process. The weld should be silvery white or light yellow to be qualified;

[0054] 7) After welding, use a borescope to penetrate into the first assembly and the second assembly to check whether there is oxidation on the back of the weld. If there is oxidation, it needs to be cleaned. The weld surface is qualified if there are no cracks, holes, burn-throughs, etc.

[0055] The shielding gas in step 4) is argon gas, the argon gas flow rate is 15L / min, and the duration is 1min; the welding current in step 6) is 25A, the welding wire brand is TA15-1, the welding wire diameter is Φ1.0, and the nozzle diameter is Φ10-Φ12.

[0056] Embodiment 2:

[0057] An aircraft radiator corrugated plate overlap structure and a welding method thereof are basically the same as those in Example 1, except that the argon gas flow rate is 30 L / min, the welding time lasts for 8 minutes, and the medium welding current is 35A.

[0058] Embodiment 3:

[0059] An aircraft radiator corrugated plate overlap structure and a welding method thereof are basically the same as those in Example 1, except that the argon gas flow rate is 20 L / min, the welding time is 4 minutes, and the medium welding current is 30A.

Claims

1. An aircraft radiator corrugated plate overlap structure, characterized in that: The invention comprises a first assembly and a second assembly, wherein the first assembly and the second assembly are connected, the first assembly comprises a corrugated plate (1) and a first shell (2), and the second assembly comprises a corrugated plate (1) and a second shell (3).

2. The aircraft radiator corrugated plate overlap structure according to claim 1, characterized in that: The first shell (2) comprises a first connecting plate (21) and a first fixing portion (22), the two ends of the first connecting plate (21) are respectively connected to the first fixing portion (22), the two sides of the first connecting plate (21) are connected to the corrugated plate (1), and the first fixing portion (22) is connected to the corrugated plate (1).

3. The aircraft radiator corrugated plate overlap structure according to claim 2, characterized in that: The first connecting plate (21) is connected to the corrugated plate (1) via a first connecting portion (23), and the first connecting portion (23) is formed by bending an edge of the first connecting plate (21).

4. The aircraft radiator corrugated plate overlap structure according to claim 2, characterized in that: The first connecting plate (21) is provided with a first slot (24) and a second slot (25).

5. The aircraft radiator corrugated plate overlap structure according to claim 1, characterized in that: The second shell (3) comprises a second connecting plate (31) and a second fixing portion (32), the two ends of the second connecting plate (31) are respectively connected to the second fixing portion (32), the two sides of the second connecting plate (31) are connected to the corrugated plate (1), and the second fixing portion (32) is connected to the corrugated plate (1).

6. The aircraft radiator corrugated plate overlap structure according to claim 5, characterized in that: The second connecting plate (31) is connected to the corrugated plate (1) via a second connecting portion (33), and the second connecting portion (33) is formed by bending an edge of the second connecting plate (31).

7. The aircraft radiator corrugated plate overlap structure according to claim 5, characterized in that: The second connecting plate (31) is provided with a third slot (34).

8. The aircraft radiator corrugated plate overlap structure according to claim 1, characterized in that: The assembly gap between the corrugated plate (1) and the first shell (2) and the second shell (3) is no greater than 1.5 mm.

9. A welding method for the overlapping structure of the corrugated plate of an aircraft radiator according to any one of claims 1 to 8, characterized in that: The following steps are involved: 1) Preparation: clean the dirt on the surface of the corrugated plate (1), the first shell (2) and the second shell (3); 2) Assembling the corrugated plate (1), the first shell (2) and the second shell (3) to obtain a first assembly and a second assembly; 3) using auxiliary tools to seal the assembly gaps between the corrugated plate (1) and the first shell (2), and between the corrugated plate (1) and the second shell (3); 4) Insert the air pipe into the first assembly and the second assembly, and introduce protective gas into the first assembly and the second assembly; 5) Turn on the argon arc welding equipment and perform test welding on the test plate according to the confirmed debugging parameters; 6) After the test welding is qualified, welding is performed on the connection points between the corrugated plate (1) and the first shell (2), and between the corrugated plate (1) and the second shell (3) according to qualified parameters; 7) After welding, check whether there is oxidation on the back of the weld. If there is oxidation, clean it. The weld surface is qualified if there are no cracks, holes, burn-through, etc.

10. A welding method for an aircraft radiator corrugated plate overlap structure as claimed in claim 9, characterized in that: The shielding gas in step 4) is argon gas, the argon gas flow rate is 15-30 L / min, and the duration is 1-8 min; the welding current in step 6) is 25-35 A.

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