Resistance spot welding clamp and method for aero-engine nozzle outer wall assembly

Abstract

The invention relates to the technical field of welding, in particular to a resistance spot welding clamp and method for an aero-engine nozzle outer wall assembly. The resistance spot welding clamp comprises a pull rod and a connecting rod. The connecting rod is mounted at the left end of the pull rod and is perpendicular to the pull rod; a nut is welded at the lower end of the connecting rod, and an ejector rod is screwed in the nut and is parallel to the pull rod; a sliding rod clamp is mounted on the pull rod; and a bolt is welded on the sliding rod clamp. The resistance spot welding method comprises the following steps that S1, scribing is conducted, specifically, scribing is conducted on a barrel and a rectifying ring; s2, preassembling: inserting a rectifying ring into an inner hole of a large end opening part of the barrel; s3, jacking and welding are conducted, specifically, a plug pin on a resistance spot welding clamp is inserted into an exhaust hole of the barrel, and spot welding of the first point position is conducted after a jacking rod is rotated to jack the rectifying ring in place; and S4, the ejector rod is loosened, the resistance spot welding clamp is taken down, the resistance spot welding clamp is installed at the position of the next exhaust hole, and the step S3 is repeated till welding of all welding spots is completed.

Description

Technical Field

[0001] The invention relates to the technical field of welding, and in particular to a resistance spot welding fixture and method for an outer wall component of an aero-engine nozzle. Background Art

[0002] Combination Figure 1 , Figure 2 As shown, the outer wall assembly of the aircraft engine nozzle is an assembly formed by connecting the two parts of the barrel 1 and the fairing ring 2 by resistance spot welding. The barrel 1 is a large-diameter tapered barrel structure, and the outer diameter of the large end of the barrel 1 is φ1050mm, and the taper is 10°. During welding, the fairing ring 2 is inserted into the inner hole of the large end of the barrel 1, and then welded by resistance spot welding. The fitting clearance between the fairing ring 2 and the barrel 1 is less than 0.25mm. The material of the barrel 1 and the fairing ring 2 is GH536, and the wall thickness of the welding part of the two is 1.0~1.2mm. There are multiple exhaust holes 1a evenly distributed in a ring near the large end of the barrel 1.

[0003] Usually, when spot welding is performed on the outer wall assembly of the aircraft engine nozzle, upper and lower pressure plate type tools with the same outer diameter as the large end of the cylinder 1 can be used to position the fairing ring 2 to ensure the depth of the fairing ring 2 inserted into the cylinder 1. However, because the tools are relatively large, the cost is high and the operation is inconvenient; or argon arc welding is used for positioning welding at a machinable position, but due to the requirements of key parts, argon arc welding positioning is not allowed at non-machining positions, and argon arc welding positioning is not suitable for the overlapping position of the part.

[0004] Since the cylinder 1 and the rectifying ring 2 have large diameters and heavy weight, and the cylinder 1 has a taper, how to ensure that the axial distance from the left end face T of the rectifying ring 2 to the spot weld is 30±0.8mm after welding, and the distance from the spot weld to the large end face of the cylinder 1 is 6±1mm, is a problem that needs to be solved urgently. Summary of the invention

[0005] The main purpose of the present invention is to provide a resistance spot welding fixture and method for an aircraft engine nozzle outer wall component, aiming to solve the above technical problems.

[0006] To achieve the above-mentioned purpose, on the one hand, the present invention proposes a resistance spot welding fixture for the outer wall assembly of an aircraft engine nozzle, comprising a pull rod and a connecting rod; the connecting rod is installed at the left end of the pull rod, and the connecting rod is perpendicular to the pull rod; a nut is welded at the lower end of the connecting rod, and a push rod is screwed into the nut, and the push rod is parallel to the pull rod; a sliding rod clamp is installed on the pull rod; and a pin is welded on the sliding rod clamp.

[0007] Preferably, the slide bar clamp is provided with a mounting hole, and the pull rod is inserted into the mounting hole; a slit is provided on the slide bar clamp, and the upper end of the slit is connected to the mounting hole; locking screws are screwed on the blocks formed on both sides of the slit.

[0008] Preferably, an anti-dropping nut is screwed on the right end of the pull rod.

[0009] Preferably, a limit stop plate is welded at the connection portion between the latch and the slide bar clamp.

[0010] Preferably, the upper portion of the connecting rod and the left end of the pull rod are connected by welding.

[0011] Preferably, a hand wheel is welded to the left end of the push rod.

[0012] Preferably, a tightening head is rotatably mounted on the right end of the push rod, and a rubber skin is pasted on the right end surface of the tightening head.

[0013] Preferably, a rotating shaft is inserted into the end surface of the right end of the push rod, and a stopper is integrally formed at the right end of the rotating shaft; the tightening head is rotatably mounted on the rotating shaft, and the stopper of the rotating shaft is arranged in the countersunk hole at the right end of the tightening head.

[0014] On the other hand, the present invention also provides a resistance spot welding method for an aircraft engine nozzle outer wall component, using the above-mentioned resistance spot welding fixture, comprising the following steps:

[0015] S1. Marking: Mark the cylinder and the rectifying ring respectively;

[0016] S2. Pre-assembly: insert the rectifying ring into the inner hole of the large end of the cylinder;

[0017] S3, tighten and weld: insert the pin on the resistance spot welding fixture into the exhaust hole of the cylinder, rotate the push rod so that the right end of the push rod presses against the left end surface of the rectifier ring, continue to rotate the push rod, tighten the rectifier ring into place, and then perform spot welding at the first point;

[0018] S4, loosen the ejector pin, remove the resistance spot welding fixture, install the resistance spot welding fixture at the next exhaust hole position, and repeat step S3 until all welding points are completed.

[0019] Preferably, in step S1, when marking, a first annular marking line is drawn on the outer circumferential surface of the large end portion of the cylinder; a second annular marking line is drawn on the outer circumferential surface of the right end of the rectifying ring; the first marking line is 6±1 mm away from the end face of the large end of the cylinder; the second marking line is 24 mm away from the left end face of the rectifying ring; in step S3, when the rectifying ring is tightened by using a push rod, when the second marking line is flush with the end face of the large end of the cylinder, it indicates that the tightening is in place; when spot welding is performed, the welding point position falls on the first marking line.

[0020] Due to the adoption of the above technical solution, the beneficial effects of the present invention are as follows:

[0021] (1) By adopting the resistance spot welding fixture and method provided by the present invention, the relative position of the cylinder and the rectifier ring after welding can be guaranteed, the position of the spot welding and the quality requirements of the spot welding can be guaranteed, and at the same time, the operation is convenient, the cost is reduced, and the efficiency is improved to meet the product use requirements.

[0022] (2) The resistance spot welding fixture provided by the present invention has a simple structure and a light weight, which is convenient for operators to operate. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] 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.

[0024] Figure 1 It is a structural schematic diagram of the outer wall assembly of an aircraft engine nozzle;

[0025] Figure 2 for Figure 1 A magnified view of the structure at center A;

[0026] Figure 3 This is a schematic diagram of the overall structure of the resistance spot welding fixture provided by the present invention;

[0027] Figure 4 This is a structural diagram of an assembly formed by a pull rod, a connecting rod, and a nut in the present invention;

[0028] Figure 5 It is a structural diagram of the assembly formed by the slide bar clamp, the latch, the limit baffle and the locking screw in the present invention;

[0029] Figure 6 It is a schematic diagram of the assembly structure formed by the ejector rod and the hand wheel in the present invention;

[0030] Figure 7 for Figure 6 The enlarged view of point B in the middle;

[0031] Figure 8 This is a schematic diagram of the rectifying ring when it is about to be inserted into place.

[0032] Explanation of the accompanying symbols: 1. Cylinder; 1a. Exhaust hole; 1b. First identification line; 2. Rectifier ring; 2a. Second identification line; 3. Pull rod; 4. Connecting rod; 5. Nut; 6. Push rod; 7. Slide rod clamp; 7a. Mounting hole; 7b. Split; 8. Latch; 9. Locking screw; 10. Limit baffle; 11. Anti-slip nut; 12. Handwheel; 13. Tightening head; 14. Rubber skin; 15. Rotating shaft; 15a. Stop head. DETAILED DESCRIPTION

[0033] 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.

[0034] 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.

[0035] 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.

[0036] Combination Figures 3 to 7 As shown, on the one hand, this embodiment provides a resistance spot welding fixture for an outer wall assembly of an aircraft engine nozzle, comprising a tie rod 3 and a connecting rod 4; the connecting rod 4 is installed at the left end of the tie rod 3, and the connecting rod 4 is perpendicular to the tie rod 3; a nut 5 is welded at the lower end of the connecting rod 4, and a push rod 6 is screwed into the nut 5, and the push rod 6 is parallel to the tie rod 3; a slide bar clamp 7 is installed on the tie rod 3; and a plug 8 is welded on the slide bar clamp 7. The diameter of the plug 8 matches the diameter of the exhaust hole 1a on the cylinder 1.

[0037] On the other hand, this embodiment also provides a method for resistance spot welding of an aircraft engine nozzle outer wall assembly, wherein the resistance spot welding fixture comprises the following steps:

[0038] S1, marking: marking the cylinder 1 and the rectifying ring 2 respectively;

[0039] S2, pre-assembly: insert the rectifying ring 2 into the inner hole of the large end portion of the cylinder 1;

[0040] S3, tighten and weld: insert the pin 8 on the resistance spot welding fixture into the exhaust hole 1a of the cylinder 1, rotate the push rod 6, so that the right end of the push rod 6 is pressed against the left end surface of the rectifying ring 2, continue to rotate the push rod 6, tighten the rectifying ring 2 into place, and then perform spot welding at the first point;

[0041] S4, loosen the ejector pin 6, remove the resistance spot welding fixture, install the resistance spot welding fixture at the next exhaust hole 1a, and repeat step S3 until all welding points are completed.

[0042] Combination Figure 5 As shown, the slide bar clamp 7 is provided with a mounting hole 7a, and the pull rod 3 is inserted in the mounting hole 7a; a split slit 7b is provided on the slide bar clamp 7, and the upper end of the split slit 7b is connected to the mounting hole 7a; and locking screws 9 are screwed on the blocks formed on both sides of the split slit 7b. By adopting this structure, before performing step S3, firstly adjust the axial position of the slide bar clamp 7 on the pull rod 3 according to the distance from the exhaust hole 1a to the left end face of the rectifying ring 2, and after the position is adjusted to the right position, tighten the locking screw 9 to close the split slit 7b, and then the slide bar clamp 7 can be locked.

[0043] Combination Figure 3 , Figure 4 As shown, an anti-drop nut 11 is screwed on the right end of the pull rod 3. By providing the anti-drop nut 11, the sliding bar clamp 7 can be prevented from falling off from the pull rod 3.

[0044] Combination Figure 3 , Figure 5 As shown, a limit baffle 10 is welded at the connection portion between the latch pin 8 and the slide bar clamp 7. In the step S3, when the latch pin 8 is inserted into the exhaust hole 1a of the cylinder 1, the limit baffle 10 abuts against the outer peripheral surface of the cylinder 1 to limit the insertion depth of the latch pin 8 and play an axial limiting role on the latch pin 8.

[0045] In this embodiment, the upper portion of the connecting rod 4 is connected to the left end of the pull rod 3 by welding. The welding connection is simple and reliable.

[0046] Combination Figure 3 , Figure 6 As shown, a hand wheel 12 is welded on the left end of the push rod 6 , and the hand wheel 12 is provided for the convenience of rotating the push rod 6 .

[0047] Combination Figure 6 , Figure 7As shown, in step S3, in order to prevent the push rod 6 from damaging the fairing ring 2, a tightening head 13 is rotatably mounted on the right end of the push rod 6, and a rubber skin 14 is pasted on the right end surface of the tightening head 13. Since the tightening head 13 is rotatably mounted on the push rod 6, the tightening head 13 does not rotate with the push rod 6 during tightening, so the tightening head 13 and the rubber skin 14 can effectively prevent the fairing ring 2 from being damaged. Furthermore, a rotating shaft 15 is inserted into the end surface of the right end of the push rod 6, and a stopper 15a is integrally formed at the right end of the rotating shaft 15; the tightening head 13 is rotatably mounted on the rotating shaft 15, and the stopper 15a of the rotating shaft 15 is set in the countersunk hole at the right end of the tightening head 13.

[0048] Combination Figure 8 As shown, in step S1, when marking, a first circular marking line 1b is marked on the outer circumference of the large end of the cylinder 1; a second circular marking line 2a is marked on the outer circumference of the right end of the rectifying ring 2; the distance between the first marking line 1b and the large end face of the cylinder 1 is 6±1mm; the distance between the second marking line 2a and the left end face T of the rectifying ring 2 is 24mm; when pre-assembling in step S2, when the rectifying ring 2 is inserted, the second marking line 2a is as close to the large end face of the cylinder 1 as possible. In step S3, when the rectifying ring 2 is tightened with the push rod 6, when the second marking line 2a is flush with the large end face of the cylinder 1, it means that the tightening is in place; when spot welding is performed, the welding point position falls on the first marking line 1b. By using the first identification line 1b and the second identification line 2a, it can be well ensured that the axial distance from the left end face T of the rectifying ring 2 after welding to the spot weld is 30±0.8mm, and the distance from the spot weld to the large end face of the cylinder 1 is 6±1mm.

[0049] 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. A resistance spot welding fixture for an aircraft engine nozzle outer wall assembly, characterized in that: It comprises a pull rod (3) and a connecting rod (4); the connecting rod (4) is installed at the left end of the pull rod (3), and the connecting rod (4) is perpendicular to the pull rod (3); a nut (5) is welded at the lower end of the connecting rod (4), a push rod (6) is screwed into the nut (5), and the push rod (6) is parallel to the pull rod (3); a sliding rod clamp (7) is installed on the pull rod (3); and a latch (8) is welded on the sliding rod clamp (7).

2. A resistance spot welding fixture for an aircraft engine nozzle outer wall assembly as claimed in claim 1, characterized in that: The slide bar clamp (7) is provided with a mounting hole (7a), and the pull rod (3) is inserted into the mounting hole (7a); a slit (7b) is provided on the slide bar clamp (7), and the upper end of the slit (7b) is connected to the mounting hole (7a); and locking screws (9) are screwed on blocks formed on both sides of the slit (7b).

3. A resistance spot welding fixture for an aircraft engine nozzle outer wall assembly as claimed in claim 2, characterized in that: An anti-drop nut (11) is screwed onto the right end of the pull rod (3).

4. The resistance spot welding fixture for an aircraft engine nozzle outer wall assembly according to claim 1, characterized in that: A limit stop plate (10) is welded to the connection portion between the latch pin (8) and the slide bar clamp (7).

5. The resistance spot welding fixture for an aircraft engine nozzle outer wall assembly according to claim 1, characterized in that: The upper part of the connecting rod (4) and the left end of the pull rod (3) are connected by welding.

6. The resistance spot welding fixture for an aircraft engine nozzle outer wall assembly according to claim 1, characterized in that: A hand wheel (12) is welded to the left end of the push rod (6).

7. The resistance spot welding fixture for an aircraft engine nozzle outer wall assembly according to claim 1, characterized in that: A tightening head (13) is rotatably mounted on the right end of the push rod (6), and a rubber skin (14) is pasted on the right end surface of the tightening head (13).

8. The resistance spot welding fixture for the outer wall assembly of the nozzle of an aircraft engine according to claim 7, characterized in that: A rotating shaft (15) is inserted into the end surface of the right end of the push rod (6), and a stopper (15a) is integrally formed at the right end of the rotating shaft (15); the tightening head (13) is rotatably mounted on the rotating shaft (15), and the stopper (15a) of the rotating shaft (15) is arranged in a countersunk hole at the right end of the tightening head (13).

9. A resistance spot welding method for an aircraft engine nozzle outer wall assembly, characterized in that: The resistance spot welding fixture according to any one of claims 1 to 8 comprises the following steps: S1, marking: marking the cylinder (1) and the rectifying ring (2) respectively; S2, pre-assembly: insert the rectifying ring (2) into the inner hole of the large end portion of the cylinder (1); S3, tightening and welding: insert the pin (8) on the resistance spot welding fixture into the exhaust hole (1a) of the cylinder (1), rotate the push rod (6) so that the right end of the push rod (6) presses against the left end surface of the rectifying ring (2), continue to rotate the push rod (6), tighten the rectifying ring (2) into place, and then perform spot welding at the first point position; S4, loosen the ejector pin (6), remove the resistance spot welding fixture, install the resistance spot welding fixture at the next exhaust hole (1a) position, and repeat step S3 until all welding points are completed.

10. The resistance spot welding method for an aircraft engine nozzle outer wall assembly according to claim 1, characterized in that: In the step S1, when marking, a first annular marking line (1b) is marked on the outer circumference of the large end portion of the cylinder (1); a second annular marking line (2a) is marked on the outer circumference of the right end of the rectifying ring (2); the distance between the first marking line (1b) and the end surface of the large end of the cylinder (1) is 6±1 mm; the distance between the second marking line (2a) and the left end surface of the rectifying ring (2) is 24 mm; In step S3, when the push rod (6) is used to push the rectifying ring (2), when the second marking line (2a) is flush with the large end surface of the cylinder (1), it indicates that the pushing is in place; when spot welding is performed, the welding point position falls on the first marking line (1b).

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