Helicopter tail nozzle assembly argon arc welding repair tool and process method

Abstract

The application discloses a kind of tooling and process method for argon arc welding repair of helicopter tail nozzle assembly, wherein the tooling includes support ring and briquetting piece;Support ring is clamped in the front end of the inner tube of the helicopter tail nozzle assembly to be repaired, and its outer peripheral wall is in contact with the inner peripheral wall of the front end of the inner tube to be repaired;Briquetting piece is arranged in support ring, and is used to fix the batten on the outer peripheral wall of support ring and align distribution with the repair area of the front end of the inner tube to be repaired.In this scheme, first, support ring is clamped in the front end of the inner tube to be repaired, and the outer peripheral wall of support ring is in contact with the inner peripheral wall of the front end of the inner tube to be repaired, then the batten is fixed on the outer peripheral wall of support ring and align distribution with the repair area by briquetting piece, in this way, the repair area of the front end of the inner tube to be repaired and the inner and outer surface of the argon arc welding of batten can be effectively controlled, thereby helping to prevent the repair area of the front end of the inner tube to be repaired from being deformed after argon arc welding repair.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of helicopter maintenance, in particular to a tool and process method for argon arc welding repair of a helicopter tail nozzle assembly. BACKGROUND

[0002] After long-term use, the front end of the inner tube port of the helicopter tail nozzle assembly will be worn thin or even broken and fail. The wear area is usually long arc rectangular, the arc length of the wear area is generally 175mm-230mm, the diameter is about 220mm, the width is about 15mm, and the thickness is about 1.5mm. Therefore, after cleaning the wear area, the existing treatment method is to use repair welding material to perform argon arc butt welding repair with the assembly base. However, since the helicopter tail nozzle assembly is a thin-walled cylindrical structure, if no deformation prevention measures are taken, post-welding deformation will easily occur. SUMMARY

[0003] Therefore, the present application provides an argon arc welding repair tool for a helicopter tail nozzle assembly. First, a support ring is clamped in the front end of the inner tube of the helicopter tail nozzle assembly to be repaired, and the outer peripheral wall of the support ring is in contact with the inner peripheral wall of the front end of the inner tube to be repaired. Then, the plate is fixed to the outer peripheral wall of the support ring by the pressing block and is aligned with the repair area of the front end of the inner tube to be repaired. In this way, the inner and outer profiles of the repair area of the front end of the inner tube to be repaired and the plate argon arc welding can be effectively controlled, thereby helping to prevent the repair area of the front end of the inner tube to be repaired from deforming after argon arc welding repair.

[0004] To achieve the above-mentioned purpose, the present application provides the following technical scheme:

[0005] An argon arc welding repair tool for a helicopter tail nozzle assembly, comprising: a support ring and a pressing block; the support ring is used for clamping in the front end of the inner tube of the helicopter tail nozzle assembly to be repaired, and the outer peripheral wall thereof is in contact with the inner peripheral wall of the front end of the inner tube to be repaired;

[0006] The pressing block is arranged on the support ring and is used for fixing the plate to the outer peripheral wall of the support ring and aligning the plate with the repair area of the front end of the inner tube to be repaired.

[0007] Preferably, the support ring is sequentially divided into a first section, a second section and a third section along the axial direction, and the inner diameters of the three sections are equal. The outer diameters of the second section and the third section are equal and larger than the outer diameter of the first section.

[0008] The second section and the third section are used to be clamped in the front end of the inner pipe to be repaired, and the outer peripheral wall of the second section and the third section is in contact with the inner peripheral wall of the front end of the inner pipe to be repaired, and the outer peripheral wall of the second section close to the end face is symmetrically provided with two limiting lugs about the axis, and is used to contact and match with the end face of the front end of the inner pipe to be repaired;

[0009] The pressing block is arranged on the outer peripheral wall of the first section between the two limiting lugs, and is used to fix the batten on the outer peripheral wall of the second section and align the distribution of the repaired area.

[0010] Preferably, the outer peripheral wall of the second section between the two limiting lugs is provided with a strip-shaped recess along the axial direction, and is aligned and distributed with the axial joint of the repaired area and the batten;

[0011] The groove bottom of the strip-shaped recess is provided with a first gas hole penetrating the inner wall of the second section;

[0012] The outer peripheral wall of the second section between the two limiting lugs and close to the third section is provided with an arc-shaped recess along the circumferential direction, and is used to align and distribute with the circumferential joint of the repaired area and the batten;

[0013] The groove bottom of the arc-shaped recess is provided with a second gas hole penetrating the inner wall of the second section;

[0014] The argon arc welding repair tool of the helicopter tail nozzle assembly further comprises a gas feeding mechanism;

[0015] The gas feeding mechanism is arranged on the inner wall of the second section, and the gas inlet is used to pass in argon, and the gas outlet is in communication with the first gas hole and the second gas hole.

[0016] Preferably, the number of the first gas holes is multiple, and is uniformly distributed along the axial direction of the second section on the groove bottom of the strip-shaped recess;

[0017] The number of the second gas holes is multiple, and is uniformly distributed along the circumferential direction of the second section on the groove bottom of the arc-shaped recess.

[0018] Preferably, the number of the strip-shaped recesses is multiple, and is uniformly distributed along the outer peripheral wall of the second section between the two limiting lugs;

[0019] Each of the strip-shaped recesses is provided with multiple first gas holes;

[0020] The arc-shaped recesses are distributed on the outer peripheral wall of the second section between the two limiting lugs.

[0021] Preferably, the pressing block is an L-shaped pressing block;

[0022] The L-shaped pressing block is arranged on the end face and the peripheral wall of the second section, the horizontal part of the L-shaped pressing block is provided with a countersunk hole in the radial direction of the first section, the peripheral wall of the first section is provided with an internal thread hole in position with the countersunk hole of the L-shaped pressing block, and the countersunk hole and the internal thread hole are connected by a first screw, and the vertical part of the L-shaped pressing block is used for fixing the board to the peripheral wall of the second section and aligning with the repaired area.

[0023] Preferably, the number of internal thread holes is multiple, and the internal thread holes are uniformly distributed along the peripheral wall between the two limiting lugs of the first section.

[0024] Preferably, further comprising:

[0025] A positioning ring for sleeving and fixing the peripheral wall of the front end of the outer cylinder of the tail nozzle assembly of the helicopter;

[0026] A limiting strip arranged across the positioning ring and used for contact matching with the supporting ring.

[0027] Preferably, the positioning ring comprises a first half positioning ring and a second half positioning ring which can be assembled and connected;

[0028] One end of the limiting strip is connected to the end face of the first half positioning ring by a second screw, the other end is connected to the end face of the second half positioning ring by the second screw, and the middle part is used for contact matching with the supporting ring.

[0029] A process method for repairing the wear defect of the tail nozzle assembly of the helicopter by argon arc welding, which uses the argon arc welding repair tool for the tail nozzle assembly of the helicopter as described above to repair, comprising the following steps:

[0030] S1, measuring the size of the repaired area of the front end of the repaired inner tube of the tail nozzle assembly of the helicopter;

[0031] S2, cleaning the defect of the repaired area of the repaired inner tube by machining, and polishing the repaired area;

[0032] S3, selecting a board with a corresponding size and same material as the repaired inner tube according to the size of the repaired area, and rolling the board into a certain curvature;

[0033] S4, clamping the supporting ring in the front end of the repaired inner tube, and fixing the rolled board to the peripheral wall of the supporting ring and aligning with the repaired area of the front end of the repaired inner tube by the pressing block;

[0034] S5, positioning spot welding the fixed board by spot welding;

[0035] S6, the butt joint of the strip and the repaired area of the inner tube to be repaired is uniformly repaired by manual direct current argon arc welding.

[0036] Preferably, after the step S6, further comprising:

[0037] S7, polishing the front surface of the weld;

[0038] S8, local heat treatment after repairing the repaired area;

[0039] S9, disassembling the tooling, and polishing the back surface of the weld;

[0040] S10, metallurgical defect inspection is performed on the outer surface and the interior of the repaired area by visual inspection, fluorescent detection and X-ray detection.

[0041] From the above technical solution, the argon arc welding repair tooling of the helicopter tail nozzle assembly provided by the application firstly clamps the support ring in the front end of the inner tube of the helicopter tail nozzle assembly to be repaired, and the outer peripheral wall of the support ring is in contact with the inner peripheral wall of the front end of the inner tube to be repaired, then the strip is fixed on the outer peripheral wall of the support ring by the pressing block and aligned with the repaired area of the front end of the inner tube to be repaired, in this way, the inner and outer profiles of the repaired area of the front end of the inner tube to be repaired and the argon arc welding of the strip can be effectively controlled, thereby helping to prevent the repaired area of the front end of the inner tube to be repaired from deforming after argon arc welding repair.

[0042] The application also provides a process method for repairing the wear defect of the helicopter tail nozzle assembly by argon arc welding. Since the above-mentioned argon arc welding repair tooling of the helicopter tail nozzle assembly is used for repair, it also has corresponding beneficial effects, which can be referred to the foregoing description, and will not be described here. BRIEF DESCRIPTION OF DRAWINGS

[0043] In order to more clearly illustrate the technical solutions in the embodiments of the application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or the prior art description. Obviously, the drawings in the following description only some embodiments of the application, and for those skilled in the art, other drawings can also be obtained without creative labor on the basis of these drawings.

[0044] Figure 1 The tooling provided by the embodiment of the application and the assembly schematic diagram of the helicopter tail nozzle assembly;

[0045] Figure 2 The structure explosion diagram of the tooling provided by the embodiment of the application;

[0046] Figure 3 The structure schematic diagram of the support ring provided by the embodiment of the application;

[0047] Figure 4 The structural schematic diagram of the briquetting provided by the embodiment of the present application is shown.

[0048] Wherein, 1 is a support ring, 11 is a first section, 11.1 is an internal threaded hole, 12 is a second section, 12.1 is a strip-shaped recess, 12.2 is a first air hole, 12.3 is an arc-shaped recess, 12.4 is a second air hole, 13 is a third section, 14 is a limiting lug; 2 is a briquetting, 21 is a horizontal part, 21.1 is a countersunk hole, 22 is a vertical part; 3 is a gas feeding mechanism; 4 is a positioning ring, 41 is a first half positioning ring, 42 is a second half positioning ring; 5 is a limiting strip; 6 is a to-be-repaired inner tube, 61 is a to-be-repaired area; 7 is an outer cylinder; 8 is a first screw; 9 is a second screw, 10 is a third screw. DETAILED DESCRIPTION

[0049] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all the other embodiments obtained by a person of ordinary skill in the art without creative work fall within the protection scope of the present application.

[0050] The argon arc welding repair tooling of the helicopter tail nozzle assembly provided by the embodiment of the present application is shown in Figure 1 , which comprises a support ring 1 and a briquetting 2, the structures of which can be respectively referred to Figure 3 and Figure 4 .

[0051] The support ring 1 is used for clamping into the front end of the to-be-repaired inner tube 6 of the helicopter tail nozzle assembly, and the outer peripheral wall of the support ring 1 is in contact and cooperation with the inner peripheral wall of the front end of the to-be-repaired inner tube 6.

[0052] The briquetting 2 is arranged on the support ring 1, and is used for fixing the plate to the outer peripheral wall of the support ring 1 and aligning and distributing the to-be-repaired area 61 of the front end of the to-be-repaired inner tube 6.

[0053] It should be noted that, as Figure 1As shown, the part of the support ring 1 is used to be clamped in the front port of the inner pipe 6 of the helicopter tail nozzle assembly to be repaired, and the outer peripheral wall of the part of the support ring 1 is in contact with the inner peripheral wall of the front port of the inner pipe 6 to be repaired (clamping cooperation), the remaining part of the support ring 1 is exposed to the front port of the inner pipe 6 to be repaired, and the pressing block 2 is arranged on the exposed part of the support ring 1. In addition, the pressing block 2 is used to align and fix the repair strip to the repaired area 61 of the front port of the inner pipe 6 to be repaired, and a spacing of 0.5mm-1.0mm is reserved between the repair strip and the repaired area 61 of the front port of the inner pipe 6 to be repaired; wherein the failure mode of the repaired area 61 of the front port of the inner pipe 6 (inclined thin-walled pipe) to be repaired is the wear of the front port of the inner pipe 6 to be repaired, as shown in Figure 2 As shown, the shape of the repaired area 61 is a long arc-shaped rectangular shape. In addition, the materials of the repair strip and the welding wire are consistent with the material of the inner pipe 6 to be repaired, so as to avoid the inconsistent physical properties between dissimilar materials leading to post-welding deformation.

[0054] As can be seen from the above technical solutions, the argon arc welding repair tooling of the helicopter tail nozzle assembly provided by the embodiment of the present application first clamps the support ring 1 in the front port of the inner pipe 6 of the helicopter tail nozzle assembly to be repaired, and makes the outer peripheral wall of the support ring 1 in contact with the inner peripheral wall of the front port of the inner pipe 6 to be repaired, and then aligns and arranges the repair strip on the outer peripheral wall of the support ring 1 and the repaired area 61 of the front port of the inner pipe 6 to be repaired through the pressing block 2, so as to effectively control the inner and outer profiles of the repaired area 61 of the front port of the inner pipe 6 to be repaired and the argon arc welding of the repair strip, thereby helping to prevent the repaired area 61 of the front port of the inner pipe 6 to be repaired from being deformed after argon arc welding repair.

[0055] In the present scheme, as shown in Figure 3 The support ring 1 is sequentially divided into a first section 11, a second section 12 and a third section 13 along the axial direction, and the inner diameters of the three sections are equal, and the outer diameters of the second section 12 and the third section 13 are equal and greater than the outer diameter of the first section 11; wherein the first section 11, the second section 12 and the third section 13 are sequentially connected along the axial direction, and the three sections can be an integral structure;

[0056] As shown in Figure 1 The second section 12 and the third section 13 are used to be clamped in the front port of the inner pipe 6 to be repaired, and the outer peripheral walls of the second section 12 and the third section 13 are in contact with the inner peripheral wall of the front port of the inner pipe 6 to be repaired, that is, the outer peripheral walls of the second section 12 and the third section 13 are clamped (clamping) on the inner peripheral wall of the front port of the inner pipe 6 to be repaired, as shown in Figure 3 The outer peripheral wall of the second section 12 close to the end face is provided with two limiting lugs 14 symmetrically about the axis thereof, and is used to be in contact with the end face of the front port of the inner pipe 6 to be repaired (as shown in Figure 1That is, the present scheme can help to realize the clamping and axial limiting of the support ring 1 in the front port of the inner pipe 6 to be repaired through the second section 12, the third section 13 and the two limiting lugs 14;

[0057] As shown in Figure 1 The pressing block 2 is arranged on the outer peripheral wall of the first section 11 between the two limiting lugs 14, and is used to fix the board to the outer peripheral wall of the second section 12 and align the distribution with the repaired area 61. The present scheme is designed in this way, which not only facilitates the arrangement of the pressing block 2 on the support ring 1, but also makes the support ring 1 have the characteristics of simple structure, convenient clamping and limiting, etc.

[0058] Specifically, as shown in Figure 3 The outer peripheral wall of the second section 12 between the two limiting lugs 14 is axially provided with a strip-shaped recess 12.1, and is used to align the distribution of the axial weld joints of the repaired area 61 and the board; wherein the number of the strip-shaped recess 12.1 is at least two, and is used to align the distribution of the two axial weld joints of the repaired area 61 and the board one by one;

[0059] The groove bottom of the strip-shaped recess 12.1 is provided with a first gas hole 12.2 penetrating through the inner wall of the second section 12;

[0060] The outer peripheral wall of the second section 12 between the two limiting lugs 14 and close to the third section 13 is circumferentially provided with an arc-shaped recess 12.3, and is used to align the distribution of the circumferential weld joints of the repaired area 61 and the board;

[0061] The groove bottom of the arc-shaped recess 12.3 is provided with a second gas hole 12.4 penetrating through the inner wall of the second section 12;

[0062] As shown in Figure 1 The argon arc welding repair tool of the helicopter tail nozzle assembly further comprises a gas feeding mechanism 3, the structure of which can refer to Figure 2 ;

[0063] The gas feeding mechanism 3 is arranged on the inner wall of the second section 12, and the gas inlet thereof is used to pass in argon, and the gas outlets are in communication with the first gas hole 12.2 and the second gas hole 12.4. The present scheme is designed in this way to provide back argon protection for the axial weld joints and the circumferential weld joints of the repaired area 61 and the board, so that the repaired area 61 of the front port of the inner pipe 6 to be repaired can obtain better argon arc welding repair effect.

[0064] Further, in order to facilitate the provision of sufficient back argon protection for the axial weld joints and the circumferential weld joints of the repaired area 61 and the board, correspondingly, as shown in Figure 3 The number of the first gas hole 12.2 is multiple, and is uniformly distributed along the axial direction of the second section 12 at the groove bottom of the strip-shaped recess 12.1;

[0065] There are multiple second pores 12.4, which are evenly distributed around the bottom of the arc-shaped groove 12.3 along the circumference of the second section 12.

[0066] Furthermore, such as Figure 3 As shown, there are multiple strip-shaped grooves 12.1, which are evenly distributed along the outer peripheral wall of the second segment 12 between the two limiting ear pieces 14.

[0067] Each strip-shaped groove 12.1 is provided with multiple first air holes 12.2;

[0068] The arc-shaped grooves 12.3 are distributed on the outer peripheral wall of the second section 12 between the two limiting lugs 14. This design facilitates back-side argon gas protection for the welds between the repaired areas 61 and the strips of different arc lengths. It also helps enable single-person welding repair of the repaired areas 61 (wear defects) of different arc lengths at the front port of the inner tube 6, thereby improving the repair efficiency of the inner tube 6 and reducing deformation of the repaired areas 61 at the front port of the inner tube 6. Furthermore, it should be noted that after the support ring 1 is fitted into the front port of the inner tube 6, its mounting posture can be adjusted by rotating the support ring 1 so that the two axial welds of the repaired area 61 and the strip are respectively aligned with the two strip-shaped grooves 12.1. Additionally, to better provide sufficient back-side argon gas protection for the axial welds of the repaired area 61 and the strip, such as... Figure 3 As shown, the outer peripheral wall of the second segment 12, which is located between each pair of adjacent strip grooves 12.1, may also be provided with the aforementioned multiple first vents 12.2.

[0069] In this plan, such as Figure 4 As shown, pressure block 2 is an L-shaped pressure block;

[0070] like Figure 1 and Figure 4 As shown, the L-shaped pressure block is inverted and disposed on the end face and outer peripheral wall of the second section 12. The horizontal part 21 of the L-shaped pressure block has a countersunk through hole 21.1 along the radial direction of the first section 11, as shown. Figure 3 As shown, the outer peripheral wall of the first segment 11 has internally threaded holes 11.1 that are aligned with the countersunk through holes 21.1 of the L-shaped pressure block, and the countersunk through holes 21.1 and internally threaded holes 11.1 are connected by a first screw 8 (such as...). Figure 2 As shown, the vertical portion 22 of the L-shaped pressure block is used to adhere and fix the strip to the outer peripheral wall of the second section 12 and align it with the area to be repaired 61. The horizontal portion 21 of the L-shaped pressure block has an arc-shaped end face facing the first section 11 for better adhesion and installation to the outer peripheral wall of the first section 11. Similarly, the vertical portion 22 of the L-shaped pressure block also has an arc-shaped end face facing the second section 12 for better adhesion and fixation of the strip (with curvature) to the outer peripheral wall of the second section 12. Additionally, as shown... Figure 4As shown, there are two countersunk through holes 21.1, and at least two internal threaded holes 11.1, which are arranged in a one-to-one correspondence with the two countersunk through holes 21.1. Furthermore, the design of the pressure block 2 in this scheme features a simple structure and convenient alignment and fixing of the strips.

[0071] Specifically, such as Figure 3 As shown, there are multiple internal threaded holes 11.1, which are evenly (equally spaced) distributed along the outer peripheral wall of the first segment 11 between the two limiting lugs 14. This design allows the L-shaped pressure block to align and fix the strip to the repaired areas 61 at different positions on the front end of the inner tube 6 to be repaired. Furthermore, it should be noted that if the arc length of the repaired area 61 is less than the arc length of the vertical part 22 of the L-shaped pressure block, the arc length of the repaired area 61 can be adjusted by grinding to make it approximately equal to the arc length of the vertical part 22 of the L-shaped pressure block; if the arc length of the repaired area 61 is greater than the arc length of the vertical part 22 of the L-shaped pressure block, multiple L-shaped pressure blocks can be used to sequentially press the two axial welds of the repaired area 61 and the strip together.

[0072] Furthermore, such as Figure 1 As shown, the argon arc welding repair fixture for the helicopter tail nozzle assembly provided in this embodiment of the invention further includes:

[0073] Positioning ring 4 is used to fit and fix the outer peripheral wall of the front port of the outer cylinder 7 of the helicopter tail nozzle assembly;

[0074] A limiting strip 5 is positioned across the positioning ring 4 and is used to contact and engage with the support ring 1. In other words, this solution uses the limiting strip 5 to contact and engage with the support ring 1, thereby achieving another axial limitation on the support ring 1. That is, this solution achieves axial limitation on the support ring 1 through the limiting action of the limiting strip 5 and the two limiting lugs 14, thus helping to ensure the proper mounting and positioning of the support ring 1.

[0075] Furthermore, such as Figure 2 As shown, since the outer peripheral wall of the front port of the outer cylinder 7 has a flange, in order to facilitate the positioning ring 4 to be fitted and fixed to the outer peripheral wall of the front port of the outer cylinder 7, the positioning ring 4 can adopt a segmented mating structure; correspondingly, as Figure 2 As shown, the positioning ring 4 includes: a first half-positioning ring 41 and a second half-positioning ring 42 that can be mated and assembled; wherein, as Figure 2 As shown, the first half-locating ring 41 and the second half-locating ring 42 can be connected by two third screws 10. The connection structure can be referred to Figure 2 As shown, it will not be elaborated further here;

[0076] like Figure 1As shown, one end of the limiting strip 5 is connected with the end face of the first half positioning ring 41 through the second screw 9, and the other end is connected with the end face of the second half positioning ring 42 through the second screw 9, and the middle part of the limiting strip 5 is used for contact matching with the support ring 1.

[0077] The embodiment of the present application also provides a process method for repairing wear defects of a helicopter tail nozzle assembly by argon arc welding.

[0078] S1, measuring the size of a to-be-repaired area 61 of a front end of a to-be-repaired inner tube 6 of the helicopter tail nozzle assembly;

[0079] S2, cleaning defects of the to-be-repaired area 61 of the to-be-repaired inner tube 6 in a machining mode, so that the to-be-repaired area 61 is trimmed into a regular to-be-repaired area, such as a long arc-shaped to-be-repaired area, and sandpaper is used to polish the to-be-repaired area 61;

[0080] S3, selecting a plate strip of a corresponding size and same material as the to-be-repaired inner tube 6 according to the size of the to-be-repaired area 61, and roll forming the plate strip to form a certain bending degree; wherein a metal straight plate strip of a certain length, width and thickness and same material as the to-be-repaired inner tube 6 is selected according to the size information of the to-be-repaired area obtained in step S1;

[0081] S4, clamping the support ring 1 in the front end of the to-be-repaired inner tube 6, and using the pressing block 2 to fix the roll-formed plate strip to the outer peripheral wall of the support ring 1 and align the distribution of the to-be-repaired area 61 of the front end of the to-be-repaired inner tube 6;

[0082] S5, positioning spot welding the aligned and fixed plate strip in a spot welding mode; that is, to realize the pre-welding of the plate strip and the to-be-repaired area 61;

[0083] S6, uniformly repairing the butt joint of the plate strip and the to-be-repaired area 61 of the to-be-repaired inner tube 6 by manual direct-current argon arc welding.

[0084] It should be noted that the process method for repairing wear defects of a helicopter tail nozzle assembly by argon arc welding provided by the present scheme is suitable for the field of helicopter maintenance, especially for repairing the wear defects of the helicopter tail nozzle assembly after long-term service, which can help to reduce the use and maintenance cost of the helicopter. In addition, since the present scheme uses the above-mentioned argon arc welding repair tool for the helicopter tail nozzle assembly for repair, it also has corresponding beneficial effects, which can be referred to the previous description, and will not be repeated here.

[0085] Further, after the step S6, the process method for repairing wear defects of a helicopter tail nozzle assembly by argon arc welding provided by the embodiment of the present application further comprises:

[0086] S7, polishing the front surface of the weld joint;

[0087] S8, local heat treatment after repairing the repair area;

[0088] S9, dismounting the tooling and polishing the back surface of the weld joint;

[0089] S10, using visual inspection, fluorescent detection and X-ray detection methods to check the metallurgical defects of the outer surface and the interior of the repair area.

[0090] It should be noted that in the welding repair process, the metal strip and the welding wire material are consistent with the material of the inner tube 6 to be repaired, so as to avoid the deformation after welding caused by the inconsistent physical properties between different materials; from the beginning of the repair to the stress relief annealing after the repair, the repair area is clamped by the tooling, that is, from the beginning of the repair to the stress relief annealing after the repair, the repair area is clamped by the anti-deformation special tooling to prevent the weld joint from being warped and deformed due to thermal stress; at the same time, the stress relief annealing can also be used to eliminate the residual stress generated during the clamping process of the tooling, so as to prevent deformation after the tooling is removed. In addition, through the test and analysis of the welding test plate and the test repair of the parts, the argon arc welding repair method can prevent the post-weld deformation of the thin-walled cylindrical structure and realize the repair of the wear defect of the tail nozzle assembly of the helicopter.

[0091] The process method of the present scheme will be further introduced in combination with specific embodiments:

[0092] The process method for repairing the wear defect of the tail nozzle assembly of the helicopter by using argon arc welding provided by the present scheme adopts a manual argon arc welding equipment, uses a metal strip and a welding wire with the same material as the base material of the part as welding materials, aligns and fixes the strip and the processed annular thin-walled repair area on the part by using a special tooling during the repair process, and the process method comprises the following steps:

[0093] (1) measuring the size of the long arc-shaped rectangular repair area of the part (i.e., the inner tube 6 to be repaired, the same below), obtaining the arc length of the repair area as 178 mm, the diameter as 222 mm, the width as 15 mm and the thickness as 1.5 mm;

[0094] (2) cutting the wear part by using a wire cutting method, and polishing the area within 10 mm from the edge of the repair area by using No. 100 and No. 200 sandpaper until the polished area exposes a metallic luster under visual inspection;

[0095] (3) according to the size information of the repair area obtained in step (1), a GH3030 high-temperature alloy straight strip with a length of 178 mm, a width of 15 mm, a thickness of 1.5 mm and the same material as the part base material is selected, and the straight strip is roll-formed to form a certain degree of curvature, so as to better butt with the part base;

[0096] (4) the support ring 1 of the special tooling is placed into the inner tube 6 of the part to be repaired, the positioning ring 4 is fixed to the front end of the outer cylinder 7 of the part to be repaired, the limiting strip 5 is connected with the positioning ring 4 to fix the support ring 1, the repair strip roll-formed in step (3) is aligned and fixed with the part base by the pressing block 2, and a spacing of 0.5 mm to 1.0 mm is reserved between the strip and the part base;

[0097] (5) the gas supply mechanism 3 of the special tooling is supplied with argon, the gas flow rate is 10 L / min to 20 L / min (preferably 15 L / min), and the gas supply is maintained for 5 min to 7 min (preferably 5 min), so as to ensure that the air inside the tooling and between the tooling and the back of the repair area is exhausted;

[0098] (6) a GH3030 high-temperature alloy welding wire with a diameter of Φ0.8 mm to Φ1.5 mm (preferably Φ1.2 mm) and the same material as the part base material and a tungsten electrode with a diameter of Φ1.2 mm to Φ2.0 mm (preferably Φ1.6 mm) are selected, the surface of the welding wire is polished with No. 400 sandpaper until the metal luster is seen, the strip aligned in step (4) is spot-welded, argon is continuously supplied into the tooling, the argon flow rate is 10 L / min to 20 L / min (preferably 15 L / min), the front argon flow rate is 10 L / min to 20 L / min (preferably 15 L / min), the spot-welding current is 15 A to 30 A (preferably 20 A), and the spot-welding spacing is 20 mm to 80 mm (preferably 35 mm);

[0099] (7) Select HGH3030 high-temperature alloy welding wire with a diameter of Φ0.8mm~Φ1.5mm (preferably Φ1.2mm) that matches the base material of the part, and tungsten electrodes with a diameter of Φ1.2mm~Φ2.0mm (preferably Φ1.6mm). Grind the surface of the welding wire with 400-grit sandpaper until a metallic luster is visible. Use manual DC argon arc welding to uniformly repair the joint between the strip and the base material of the part, ensuring complete penetration. The welding repair parameters are: argon gas flow rate of the tooling 10L / min~2 0L / min (preferably 15L / min), front argon flow rate 10L / min~20L / min (preferably 15L / min), arc ignition current 15A~23A (preferably 20A), arc termination current 2A~7A (preferably 5A), arc ignition time 0.05s~0.5s (preferably 0.20s), arc termination time 3s~10s (preferably 6s), welding current 20A~50A (preferably 35A), welding voltage adapted to 7.5V~9.5V (preferably 8.0V);

[0100] (8) Keep the tooling in the clamping state and use an electric grinding gun to grind the front of the weld. After grinding, the surface is bright, without undercut, without surface cracks, without depressions lower than the base material, and smoothly transitions with the surrounding substrate.

[0101] (9) Keep the tooling in the clamped state and perform local heat treatment on the repaired area after repair; wherein, the heat treatment regime is: 400℃~600℃ (preferably 600℃), heat preservation for 2 hours, and cooling with the furnace;

[0102] (10) Remove the tooling and use an electric grinding gun to grind the back of the weld. After grinding, the surface is bright, without undercut, without surface cracks, without depressions lower than the base material, and flush with the surrounding substrate.

[0103] (11) Visual inspection, fluorescence inspection and X-ray inspection methods shall be used to inspect the metallurgical defects on the outer surface and inside of the repair area. The inspection area of ​​visual inspection, fluorescence inspection and X-ray inspection shall not be less than twice the area of ​​the repair area. Fluorescence inspection shall be carried out in accordance with the requirements of HB / Z61 standard and X-ray inspection shall be carried out in accordance with the requirements of HB20160 standard. The surface shall be free of inclusions, cracks, lack of fusion and other defects, and the inside shall be free of lack of fusion, flaky or sharp-angled inclusions and cracks. Pores with sharp corners or a diameter greater than 1 mm are not allowed.

[0104] Furthermore, the process method for repairing wear defects in helicopter tail nozzle components using argon arc welding provided in this solution has the following beneficial effects:

[0105] The argon arc welding repair test is carried out on the tail nozzle assembly base in the early stage, and the welding repair quality and the organization performance are researched. The research results show that the welding seam is well formed, and the surface and the inside are free of inclusion, crack, incomplete fusion, pore and other defects; the welding seam is combined closely with the base, the organization is dense, and there is no defect; after stress relief annealing, the tensile strength reaches 94% of the base material, and the performance is good.

[0106] The repair area is free of inclusion, crack, incomplete fusion, pore and other defects; the repaired part restores the use performance. The helicopter tail nozzle assembly repaired by the application has passed the pre-installation identification, and has successfully realized the installation use.

[0107] Therefore, the achievement of the application can be directly used for repairing the wear defects of the helicopter tail nozzle assembly, solves the urgent research problem of the current helicopter tail nozzle assembly repair technology, greatly shortens the maintenance cycle of the part, reduces the maintenance cost, and also provides technical support for similar problems on the helicopter or airplane.

[0108] In summary, the application belongs to the field of welding technology, and particularly relates to a process method for repairing wear defects of a helicopter tail nozzle assembly by argon arc welding, and is particularly suitable for the field of helicopter maintenance, and repairs the wear defects of the helicopter tail nozzle assembly after long-term service. The method is aimed at the wear defects of the front end of the inclined thin-walled pipe of the helicopter tail nozzle assembly, adopts a strip formed by roll forming and same as the base material of the part, and adopts reasonable argon arc welding process parameters to butt weld and repair the part base, and a special anti-deformation tool is used to clamp the repair area from the beginning of the repair to the stress relief annealing after the repair, so that one person can weld and repair the wear defects of the inclined thin-walled pipe of different lengths, the repair efficiency is improved, the post-weld deformation caused by the residual stress of the thin-walled pipe structure after welding is effectively reduced, the repair area is free of inclusion, crack, incomplete fusion, pore and other defects, and the repaired workpiece restores the use performance. The helicopter tail nozzle assembly repaired by the application has passed the pre-installation identification, and has successfully realized the installation use.

[0109] The embodiments in the specification are described in a progressive manner, and each embodiment focuses on the difference from other embodiments, and the same or similar parts between the embodiments can be referred to each other.

[0110] The above description of the disclosed embodiments enables a person skilled in the art to implement or use the application. Various modifications to the embodiments will be apparent to those skilled in the art, and the general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the application. Therefore, the application will not be limited to the embodiments shown herein, but will conform to the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. An argon arc welding repair tooling for a tail rotor exhaust assembly of a helicopter, characterized in that, The application relates to a repair tool for an argon arc welding of a tail nozzle assembly of a helicopter, which comprises a supporting ring (1) and a pressing block (2). The supporting ring (1) is used for being clamped into a front port of a to-be-repaired inner pipe (6) of the tail nozzle assembly of the helicopter, and the outer peripheral wall of the supporting ring (1) is in contact with the inner peripheral wall of the front port of the to-be-repaired inner pipe (6). The pressing block (2) is arranged on the supporting ring (1) and is used for fixing a batten on the outer peripheral wall of the supporting ring (1) and aligning the batten with a to-be-repaired area (61) of the front port of the to-be-repaired inner pipe (6). The supporting ring (1) is sequentially divided into a first section (11), a second section (12) and a third section (13) along an axial direction, and the inner diameters of the three sections are equal; the outer diameters of the second section (12) and the third section (13) are equal and larger than that of the first section (11).

2. The TIG repair tooling for a helicopter tail rotor assembly as defined in Claim 1 wherein, The second section (12) and the third section (13) are used for being clamped into the front port of the to-be-repaired inner pipe (6), and the outer peripheral walls of the second section (12) and the third section (13) are in contact with the inner peripheral wall of the front port of the to-be-repaired inner pipe (6); the outer peripheral wall of the second section (12) close to an end face is symmetrically provided with two limiting lugs (14) about an axis, and is used for being in contact with the end face of the front port of the to-be-repaired inner pipe (6). The pressing block (2) is arranged on the outer peripheral wall of the first section (11) between the two limiting lugs (14), and is used for fixing the batten on the outer peripheral wall of the second section (12) and aligning the batten with the to-be-repaired area (61). The outer peripheral wall of the second section (12) between the two limiting lugs (14) is provided with a strip-shaped recess (12.1) along the axial direction, and is aligned with the to-be-repaired area (61) and the batten along the axial direction.

3. The repair tooling for argon arc welding of a helicopter tail boom assembly according to claim 2, wherein, The groove bottom of the strip-shaped recess (12.1) is provided with a first gas hole (12.2) penetrating the inner wall of the second section (12). The outer peripheral wall of the second section (12) between the two limiting lugs (14) and close to the third section (13) is provided with an arc-shaped recess (12.3) along the circumferential direction, and is used for aligning the to-be-repaired area (61) and the batten along the circumferential direction. The groove bottom of the arc-shaped recess (12.3) is provided with a second gas hole (12.4) penetrating the inner wall of the second section (12). The repair tool further comprises a gas feeding mechanism (3). The gas feeding mechanism (3) is arranged on the inner wall of the second section (12), and the gas inlet is used for feeding argon gas, and the gas outlets are communicated with the first gas hole (12.2) and the second gas hole (12.4). The number of the first gas holes (12.2) is multiple, and the first gas holes (12.2) are uniformly distributed on the groove bottom of the strip-shaped recess (12.1) along the axial direction of the second section (12).

4. The argon arc welding repair tooling for a helicopter tail rotor assembly according to claim 3, wherein, The number of the second gas holes (12.4) is multiple, and the second gas holes (12.4) are uniformly distributed on the groove bottom of the arc-shaped recess (12.3) along the circumferential direction of the second section (12). The number of the strip-shaped recesses (12.1) is multiple, and the strip-shaped recesses (12.1) are uniformly distributed on the outer peripheral wall of the second section (12) between the two limiting lugs (14).

5. The TIG repair tooling for a helicopter tail rotor assembly as defined in Claim 4 wherein, ​ Each of the strip-shaped concave grooves (12.1) is provided with a plurality of the first air holes (12.2); The arc-shaped concave grooves (12.3) are distributed on the outer peripheral wall of the second section (12) between two limiting lugs (14).

6. The TIG repair tooling for a helicopter tail rotor assembly of claim 5, wherein, The pressing block (2) is an L-shaped pressing block. The L-shaped pressing block is arranged in reverse on the end face and the outer peripheral wall of the second section (12), the horizontal part (21) of the L-shaped pressing block is provided with a countersunk hole (21.1) along the radial direction of the first section (11), the outer peripheral wall of the first section (11) is provided with an internal thread hole (11.1) which is in alignment with the countersunk hole (21.1) of the L-shaped pressing block, and the countersunk hole (21.1) and the internal thread hole (11.1) are connected by a first screw (8), and the vertical part (22) of the L-shaped pressing block is used for fixing the strip to the outer peripheral wall of the second section (12) and aligning with the to-be-repaired area (61).

7. The TIG repair tooling for a helicopter tail rotor assembly of claim 6, wherein, The number of the internal thread holes (11.1) is multiple, and they are uniformly distributed along the outer peripheral wall of the first section (11) between two limiting lugs (14).

8. The TIG repair tooling for a helicopter tail rotor assembly of claim 1 wherein, Further comprising: A positioning ring (4) for sleeving and fixing on the outer peripheral wall of the front end of the outer cylinder (7) of the helicopter tail nozzle assembly; A limiting strip (5) which is arranged across the positioning ring (4) and is used for contact matching with the supporting ring (1).

9. The TIG repair tooling for a helicopter tail rotor assembly of claim 8, wherein, The positioning ring (4) comprises a first half positioning ring (41) and a second half positioning ring (42) which can be assembled and connected; One end of the limiting strip (5) is connected with the end face of the first half positioning ring (41) by a second screw (9), the other end is connected with the end face of the second half positioning ring (42) by the second screw (9), and the middle part is used for contact matching with the supporting ring (1).

10. A process for repairing wear defects in a tail boom exhaust assembly of a helicopter using argon arc welding, characterized in that, The argon arc welding repair tool of the helicopter tail nozzle assembly is repaired by the following steps: S1, measuring the size of the to-be-repaired area (61) of the front end of the to-be-repaired inner tube (6) of the helicopter tail nozzle assembly; S2, cleaning the defects of the to-be-repaired area (61) of the to-be-repaired inner tube (6) by machining, and polishing the to-be-repaired area (61); S3, selecting a strip with a corresponding size and same material as the to-be-repaired inner tube (6) according to the size of the to-be-repaired area (61), and rolling and shaping the strip to form a certain degree of curvature; S4, clamping the supporting ring (1) in the front end of the to-be-repaired inner tube (6), and fixing the rolled and shaped strip to the outer peripheral wall of the supporting ring (1) by the pressing block (2) and aligning with the to-be-repaired area (61) of the front end of the to-be-repaired inner tube (6); S5, positioning spot welding the fixed and aligned strip by spot welding; S6, uniformly repairing the butt joint between the strip and the to-be-repaired area (61) of the to-be-repaired inner tube (6) by manual direct current argon arc welding.

11. The process for repairing the wear defects of the tail boom exhaust assembly of a helicopter by means of argon arc welding according to claim 10, characterized in that, After the step S6, further comprising: S7, polishing the front surface of the weld; S8, local heat treatment after repairing the repair area; S9, disassembling the tool and polishing the back surface of the weld; S10, using visual detection, fluorescence detection, X-ray detection method, the outer surface and internal of the repair area are checked for metallurgical defects.

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