CN113579630A - Laser welding fixture and welding method for circular seam of exhaust funnel of aircraft engine - Google Patents
Laser welding fixture and welding method for circular seam of exhaust funnel of aircraft engine Download PDFInfo
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- CN113579630A CN113579630A CN202110850761.6A CN202110850761A CN113579630A CN 113579630 A CN113579630 A CN 113579630A CN 202110850761 A CN202110850761 A CN 202110850761A CN 113579630 A CN113579630 A CN 113579630A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K37/00—Auxiliary devices or processes, not specially adapted to a procedure covered by only one of the preceding main groups
- B23K37/04—Auxiliary devices or processes, not specially adapted to a procedure covered by only one of the preceding main groups for holding or positioning work
- B23K37/053—Auxiliary devices or processes, not specially adapted to a procedure covered by only one of the preceding main groups for holding or positioning work aligning cylindrical work; Clamping devices therefor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/14—Working by laser beam, e.g. welding, cutting or boring using a fluid stream, e.g. a jet of gas, in conjunction with the laser beam; Nozzles therefor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/20—Bonding
- B23K26/21—Bonding by welding
- B23K26/24—Seam welding
- B23K26/28—Seam welding of curved planar seams
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/70—Auxiliary operations or equipment
- B23K26/702—Auxiliary equipment
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K2101/00—Articles made by soldering, welding or cutting
- B23K2101/04—Tubular or hollow articles
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- Plasma & Fusion (AREA)
- Laser Beam Processing (AREA)
Abstract
The application discloses an aircraft engine exhaust funnel circumferential weld laser welding fixture and a welding method, wherein the welding fixture comprises a main shaft structure, an adjustable support, a positioning disc structure, a positioning disc driving mechanism and a gas protection device, one end of the main shaft structure is connected with a machine tool working turntable, the machine tool drives the main shaft structure to rotate, and the other end of the main shaft structure is connected with the adjustable support; the positioning disc structure is axially sleeved on the main shaft structure and is radially connected with the main shaft structure through a sliding block of a sliding rail; the positioning disk driving mechanism is arranged on the main shaft structure and drives the positioning disks with different diameters on the positioning disk structure to stretch along the radial direction; the gas protection device is arranged on the positioning disc structure and is connected with the main shaft structure to provide inert gas protection for the backs of different welding seams, and the exhaust funnel of the aircraft engine is sleeved and positioned on the positioning disc structure to be welded. The welding of annular welding seam is realized through the rotation of anchor clamps and by the welding work piece, forms the welding seam quality best and has the commonality.
Description
Technical Field
The application relates to the technical field of laser welding of airplane parts, in particular to a laser welding fixture and a welding method for an annular seam of an exhaust funnel of an airplane engine.
Background
The cylindrical exhaust funnel of the airplane is generally formed by a plurality of skins and then welded into a whole, and in order to obtain a high-strength, continuous and smooth welding seam, laser welding gradually becomes the first choice of a titanium alloy skin welding mode, and the welding of a circular welding seam is a difficult point. The titanium alloy skin of the exhaust funnel of the aircraft engine has the characteristics of thin wall thickness, large size, weak rigidity and the like, generally the thickness of the skin is about 1mm, the length is about 2000mm, the diameter of the section of the cylinder is phi 700 mm-phi 800mm, the whole section of the cylinder is weak in rigidity, and a special device is needed to position and support the inner diameter of the exhaust funnel of the aircraft engine during laser welding to ensure the rigidity of the exhaust funnel of the aircraft engine and determine the welding position of the exhaust funnel of the aircraft engine during welding. The requirement of laser girth welding on the butt joint precision of skins and the coaxiality between cylinder sections is extremely strict, and the poor butt joint precision can directly cause the skins to be burnt through or the welding cannot be finished. Titanium alloy is extremely easy to have harmful reaction with impurity gas in the air in the welding process, so the welding clamp also needs to have a gas protection function. The tubular structure girth welding is generally the last process, and its whole shape is the enclosed construction after the welding is accomplished, and because the influence of welding stress deformation and welding seam surplus height after the welding, the loading and unloading of aircraft engine aiutage on the frock is also very difficult.
Disclosure of Invention
The laser welding device and the laser welding method for the circular seam of the exhaust funnel of the aircraft engine are designed, the laser welding device is accurate in positioning, convenient to clamp and capable of forming reliable gas protection for the circular seam in the welding process.
In order to achieve the above purpose, the following technical scheme is adopted to realize the purpose:
a laser welding fixture for circumferential seams of exhaust ducts of aircraft engines comprises a main shaft structure, an adjustable support, a positioning disc structure, a positioning disc driving mechanism and a gas protection device, wherein one end of the main shaft structure is connected with a machine tool working turntable, the machine tool drives the main shaft structure to rotate, and the other end of the main shaft structure is connected with the adjustable support; the positioning disc structure is axially sleeved on the main shaft structure and is radially connected with the main shaft structure through a sliding block of a sliding rail; the positioning disk driving mechanism is arranged on the main shaft structure and drives the positioning disks with different diameters on the positioning disk structure to stretch along the radial direction; the gas protection device is arranged on the positioning disc structure and is connected with the main shaft structure to provide inert gas protection for the backs of different welding seams, and the exhaust funnel of the aircraft engine is sleeved and positioned on the positioning disc structure to be welded.
The main shaft structure includes frock bearing capacity axle, end revolution mechanic, first supporting disk, the second supporting disk, the third supporting disk, a slide rail, six oil-free bush, the fixed frock bearing capacity axle one end of end revolution mechanic, first supporting disk, the second supporting disk, the suit of third supporting disk is fixed on frock bearing capacity is epaxial, 3 slide rails of equipartition installation are gone up to every supporting disk quotation, the three oil-free bush of equipartition in first supporting disk quotation, be provided with two oil-free bush of contained angle 120 degrees in the second supporting disk quotation, be provided with an oil-free bush on the third supporting disk, the third supporting disk is connected with the lathe revolving stage, adjustable support is connected with end revolution mechanic.
The end rotating structure comprises a rotating shaft, a rotating body and a locking device, the rotating shaft is connected with the adjustable support and can rotate, the rotating body is of a three-claw structure, the rotating body is sleeved on the rotating shaft, and each claw structure is provided with the locking device of the driving mechanism and a positioning support hole of the driving device.
The positioning disc structure comprises a first positioning disc, a second positioning disc and a third positioning disc which respectively comprise a large gear, a guide pin and three sector discs; the large gear is provided with an end face spiral groove, the guide pin is fixed on the fan-shaped discs and can slide in the end face spiral groove, three fan-shaped discs on each positioning disc are respectively connected with the slide rails on the corresponding supporting discs and can move along the radial direction of the supporting discs, the large gear rotationally drives each fan-shaped positioning disc to move in a telescopic manner along the radial direction, 3 fan-shaped positioning discs on each positioning disc can simultaneously stretch in the radial direction to realize the scaling of the diameter of the supporting disc, the middle parts of the outer diameters of the second positioning disc and the third positioning disc are provided with protective gas through grooves, the bottom parts of the grooves are provided with vent holes for the protective gas, and the outer diameters of the first positioning disc, the second positioning disc and the third positioning disc are matched with the inner diameter of the exhaust funnel.
Positioning disk actuating mechanism, including three hand wheel, first drive pivot, second drive pivot, third drive pivot, three pinion, first drive pivot passes first supporting disk in proper order, the second supporting disk, the oilless bush on the third supporting disk, first supporting disk is passed in proper order in the second drive pivot, the oilless bush on the second supporting disk, the oilless bush on the first supporting disk is passed in the third drive pivot, every drive pivot one end installation hand wheel, other end installation pinion, the pinion respectively with first supporting disk, the second supporting disk, the gear engagement on the third supporting disk.
The gas protection device comprises a ventilation pipeline and a gas pipeline joint; the gas pipeline joint is connected with the protective gas through holes on the second supporting disk and the third supporting disk, one end of the vent pipeline is connected with the gas pipeline joint, and the other end of the vent pipeline is connected with an external protective gas source.
The adjustable support comprises a base, a support shaft, a roller mounting seat and four rollers; the pedestal mounting is on the lathe mesa, and back shaft one end is connected with the base, and the other end is connected as a whole with the gyro wheel mount pad, and four gyro wheels are installed on the gyro wheel mount pad to be connected with the structural end revolution mechanic of main shaft.
The method for welding the exhaust cylinder of the aircraft engine by using the welding fixture comprises the following steps:
1. before laser welding, a hand wheel on a positioning disk driving mechanism is rotated anticlockwise to drive a first driving rotating shaft, a second driving rotating shaft and a third driving rotating shaft to drive pinions on the first driving rotating shaft, the second driving rotating shaft and the third driving rotating shaft to rotate respectively, and the pinions drive large gears on a first positioning disk, a second positioning disk and a third positioning disk to rotate so as to drive the diameters of the three positioning disks to be reduced; after the diameters of the three positioning disks are all reduced, the exhaust funnel of the aircraft engine is sleeved on the three positioning disks;
2. after the installation of the exhaust funnel of the aircraft engine is finished, a hand wheel on a clockwise rotation positioning disk driving mechanism drives a first driving rotating shaft, a second driving rotating shaft and a third driving rotating shaft to drive a pinion to rotate, the pinion drives a large gear on a first positioning disk, a second positioning disk and a third positioning disk to rotate, and the large gear drives the diameters of the three positioning disks to be amplified until the diameters of the three positioning disks are attached to the inner diameter of the exhaust funnel of the aircraft engine; after the diameters of the three positioning plates are accurately attached to the inner diameter of the exhaust funnel of the aircraft engine, the exhaust funnel of the aircraft engine is accurately positioned, and the coaxiality and the butt joint gap are ensured;
3. in the laser welding process, the laser beam is always kept right above a welding seam of a first positioning disc, the welding seam of the first positioning disc of the exhaust cylinder of the whole aircraft engine is completed by rotating the device and the exhaust cylinder of the aircraft engine by 360 degrees through the rotating table of the machine tool, after the welding is completed, the laser beam is translated to the position right above the welding seam of a second positioning disc, and the device and the exhaust cylinder of the aircraft engine rotate by 360 degrees together through rotating the rotating table of the machine tool again to complete the welding seam of the second positioning disc of the exhaust cylinder of the whole aircraft engine;
4. after laser welding is finished, a hand wheel on a positioning disc driving mechanism is rotated anticlockwise to drive a first driving rotating shaft, a second driving rotating shaft and a third driving rotating shaft to drive a pinion to rotate, the pinion drives a large gear on a first positioning disc, a second positioning disc and a third positioning disc to rotate, and the large gear drives the three positioning discs to reduce in diameter; and (4) after the diameters of the three positioning plates are reduced, removing the welded exhaust pipe of the aircraft engine from the welding fixture.
Has the advantages that: the welding fixture has the advantages that the main shaft structure and the positioning disc structure of the welding fixture provide reliable positioning support for the annular welding line of the exhaust funnel of the aircraft engine and the end head of the exhaust funnel, and the coaxiality and the butt joint precision of the annular welding line are guaranteed; the telescopic function of the diameter of the positioning disc is realized through the positioning disc driving structure and the positioning disc structure, and the smooth disassembly of the sealed cylindrical exhaust funnel on the clamp after welding is ensured; the gas protection system provides reliable inert gas protection for the welding line in the rotating process, and prevents the titanium alloy skin from generating harmful reaction with impurity gas in the air; the welding of the annular welding line is realized through the rotation of the welding fixture and the welded workpiece, and the formed welding line has the best quality; the welding fixture completes welding of multiple annular welding seams in a mode of rotating together with the exhaust pipe part of the aircraft engine for multiple times, and the fixture has universality for welding of parts with the same structure.
The present application will be described in further detail with reference to the following drawings and examples.
Drawings
FIG. 1 is a schematic view of a laser welding jig
FIG. 2 is a schematic view of the main shaft structure
FIG. 3 is a schematic view of a rotating structure of the head
FIG. 4 is a schematic view of the installation of the puck structure
FIG. 5 is a schematic view of the puck
FIG. 6 puck drive mechanism
FIG. 7 is a schematic view of a gas shield apparatus
FIG. 8 is a schematic view of an adjustable support
The numbering in the figures illustrates: 1. a spindle structure; 2. an adjustable support; 3. a positioning plate structure; 4. a puck drive mechanism; 5. a gas protection device; 6. an aircraft engine exhaust stack; 7. a machine tool; 8. a bearing shaft of the tool; 9. an end head rotating structure; 10. a first support tray; 11. a second support disc; 12. a third support disc; 13. a slide rail slider; 14. an oilless bushing; 15. a rotating shaft; 16. a rotating body; 17. a locking device; 18. positioning the support hole; 19. a first positioning plate; 20. a second positioning plate; 21. a third positioning plate; 22. a bull gear; 23. a guide pin; 24. a sector disc; 25. an end face spiral groove; 26. passing a gas through the slots; 27. a gas passing hole; 28. a hand wheel; 29. a first drive shaft; 30. a second drive shaft; 31. a third drive shaft; 32. a pinion gear; 33. a vent line; 34. a gas line connection; 35. a base; 36. a support shaft; 37. a roller mounting seat; 38. and a roller.
Detailed Description
Referring to attached drawings 1-8, the laser welding fixture for the circular seam of the exhaust funnel of the aircraft engine comprises a main shaft structure 1, an adjustable support 2, a positioning disc structure 3, a positioning disc driving mechanism 4 and a gas protection device 5, wherein one end of the main shaft structure 1 is connected with a working turntable of a machine tool 7, the machine tool 7 drives the main shaft structure 1 to rotate, and the other end of the main shaft structure is connected with the adjustable support 2; the positioning disc structure 3 is axially sleeved on the main shaft structure 1 and is radially connected with the main shaft structure 1 through a sliding rail sliding block 12; the positioning disk driving mechanism 4 is arranged on the main shaft structure 1 and drives the positioning disks with different diameters on the positioning disk structure 3 to stretch; the gas protection device 5 is arranged on the positioning disc structure 3 and connected with the main shaft structure 1 to provide inert gas protection for the backs of different welding seams, and the exhaust funnel 6 of the aircraft engine is sleeved and positioned on the positioning disc structure 3 to be welded.
Spindle structure 1 includes frock bearing capacity axle 8, end revolution mechanic 9, first supporting disk 10, second supporting disk 11, third supporting disk 12, slide rail slider 13, six oilless bush 14, 8 one ends of the fixed frock bearing capacity axle of end revolution mechanic 9, first supporting disk 10, second supporting disk 11, 12 suits of third supporting disk are fixed on frock bearing capacity axle 8, 3 slide rail slider 13 of equipartition installation on every supporting disk quotation, three oilless bush 14 of equipartition on the 10 quotations of first supporting disk, be provided with two oilless bush 14 of contained angle 120 degrees on the 11 quotations of second supporting disk, be provided with an oilless bush 14 on the third supporting disk 12, third supporting disk 12 is connected with 7 revolving stages of lathe, adjustable support 2 is connected with end revolution mechanic 9.
The end head rotating structure 9 comprises a rotating shaft 12, a rotating body 16 and a locking device 17, the rotating shaft 15 is connected with the adjustable support 2 and can rotate, the rotating body 16 is of a three-claw structure, the rotating body 16 is sleeved on the rotating shaft 12, and each claw structure is provided with the locking device 17 of the driving mechanism and a positioning support hole 18 of the driving mechanism.
The positioning disc structure 3 comprises a first positioning disc 19, a second positioning disc 20 and a third positioning disc 21; each positioning disc comprises a large gear 22, a guide pin 23 and three sector discs 24; an end face spiral groove 25 is formed in the large gear 22, the guide pin 23 is fixed on the sector discs 24 and can slide in the end face spiral groove 25, three sector discs 24 on each positioning disc are respectively connected with the slide rail slide blocks 13 on the corresponding supporting discs and can move along the radial direction of the supporting discs, the large gear 22 rotates to drive the end face spiral groove 25 to rotate around the center of the large gear 22, the rotation of the large gear 25 in the spiral groove provides component force along the radial direction of the sector positioning discs 24 for the guide pin 23, each sector positioning disc 24 is driven to move in a telescopic mode along the radial direction, and 3 sector positioning discs 24 on each positioning disc can simultaneously stretch in the radial direction to achieve the scaling of the diameter of the positioning disc; the middle parts of the outer diameters of the second positioning disk 20 and the third positioning disk 21 are provided with protective gas passing grooves 26, the bottom parts of the grooves are provided with vent holes 27 of the protective gas, and the outer diameters of the first positioning disk 19, the second positioning disk 20 and the third positioning disk 21 are matched with the inner diameter of the exhaust funnel 7 of the aircraft engine.
Positioning disk actuating mechanism 4, including three hand wheel 28, first drive pivot 29, second drive pivot 30, third drive pivot 31, three pinion 32, first drive pivot 29 passes first supporting disk 10 in proper order, second supporting disk 11, oil free bush 14 on the third supporting disk 12, second drive pivot 30 passes first supporting disk 10 in proper order, oil free bush 14 of 11 on the second supporting disk, third drive pivot 30 passes oil free bush 14 of 11 on the first supporting disk, every drive pivot one end installation hand wheel 28, other end installation pinion 32, the pinion respectively with first supporting disk 10, second supporting disk 11, the gear wheel 22 meshing on the third supporting disk 12.
A gas protection device 5 comprising a ventilation line 33 and a gas line connection 34; the gas pipeline joint 33 is connected with the protective gas through holes 27 on the second supporting disk 11 and the third supporting disk 12, one end of the vent pipeline is connected with the gas pipeline joint 34, and the other end of the vent pipeline is connected with an external protective gas source.
The adjustable support 2 comprises a base 35, a support shaft 36, a roller mounting seat 37 and four rollers 38; the base 35 is installed on the machine tool table, one end of the supporting shaft 36 is connected with the base, the other end of the supporting shaft is connected with the roller mounting seat 37 into a whole, and the four rollers 38 are installed on the roller mounting seat 37 and are connected with the end rotating structure on the main shaft structure 9.
The method for welding the exhaust cylinder of the aircraft engine by using the welding fixture comprises the following steps:
1. before laser welding, a hand wheel 28 on the positioning disk driving mechanism 4 is rotated anticlockwise to drive a first driving rotating shaft 29, a second driving rotating shaft 30 and a third driving rotating shaft 31 to drive a pinion 32 thereon to rotate respectively, and the pinion 32 drives a bull gear 22 on a first positioning disk 10, a second positioning disk 11 and a third positioning disk 12 to rotate so as to drive the diameters of the three positioning disks to be reduced; after the diameters of the three positioning disks are all reduced, an exhaust funnel 6 of the aircraft engine is sleeved on the three positioning disks;
2. after the installation of the exhaust funnel of the aircraft engine is finished, a hand wheel 28 on a clockwise rotation positioning disk driving mechanism 4 drives a first driving rotating shaft 29, a second driving rotating shaft 30 and a third driving rotating shaft 31 to drive a pinion 32 to rotate, the pinion 32 drives a bull gear 22 on a first positioning disk 10, a second positioning disk 11 and a third positioning disk 12 to rotate, and the bull gear 22 drives the diameters of the three positioning disks to be amplified until the diameters of the three positioning disks are attached to the inner diameter of the exhaust funnel 6 of the aircraft engine; after the diameters of the three positioning plates are accurately attached to the inner diameter of the exhaust funnel 6 of the aircraft engine, the exhaust funnel of the aircraft engine is accurately positioned, and the coaxiality and the butt joint gap are ensured;
3. in the laser welding process, a laser beam is always kept right above a welding seam of the first positioning disc 19, the device and the aircraft engine exhaust funnel 6 rotate together for 360 degrees through the rotation of the rotary table of the machine tool 7 to complete the welding of the welding seam of the first positioning disc 19 of the whole aircraft engine exhaust funnel 6, after the welding is completed, the laser beam is translated to the position right above the welding seam of the second positioning disc 20, and the device and the aircraft engine exhaust funnel 6 rotate together for 360 degrees through the rotation of the rotary table of the machine tool 7 to complete the welding of the welding seam of the second positioning disc 20 of the whole aircraft engine exhaust funnel;
4. after laser welding is finished, a hand wheel 28 on the positioning disk driving mechanism 4 is rotated anticlockwise to drive a first driving rotating shaft 29, a second driving rotating shaft 30 and a third driving rotating shaft 31 to drive a pinion 32 to rotate, the pinion 32 drives a large gear 22 on a first positioning disk 10, a second positioning disk 11 and a third positioning disk 12 to rotate, and the large gear 22 drives the three positioning disks to reduce the diameters; and (4) after the diameters of the three positioning plates are reduced, removing the welded exhaust funnel 6 of the aircraft engine from the welding fixture.
Claims (8)
1. A laser welding fixture for circumferential seams of exhaust ducts of aircraft engines is characterized by comprising a main shaft structure, an adjustable support, a positioning disc structure, a positioning disc driving mechanism and a gas protection device, wherein one end of the main shaft structure is connected with a machine tool working turntable and driven by the machine tool to rotate, and the other end of the main shaft structure is connected with the adjustable support; the positioning disc structure is axially sleeved on the main shaft structure and is radially connected with the main shaft structure through a sliding block of a sliding rail; the positioning disk driving mechanism is arranged on the main shaft structure and drives the positioning disks with different diameters on the positioning disk structure to stretch along the radial direction; the gas protection device is arranged on the positioning disc structure and is connected with the main shaft structure to provide inert gas protection for the backs of different welding seams, and the exhaust funnel of the aircraft engine is sleeved and positioned on the positioning disc structure to be welded.
2. The aircraft engine exhaust funnel circumferential weld laser welding anchor clamps of claim 1, characterized in that the main shaft structure include frock bearing shaft, end revolution mechanic, first supporting disk, the second supporting disk, the third supporting disk, a slide rail, six oilless bushes, end revolution mechanic fixed frock bearing shaft one end, first supporting disk, the second supporting disk, the suit of third supporting disk is fixed on frock bearing shaft, three slide rails of equipartition installation on every supporting disk quotation, three oilless bushes of equipartition on the first supporting disk quotation, be provided with two oilless bushes of contained angle 120 degrees on the second supporting disk quotation, be provided with an oilless bush on the third supporting disk, the third supporting disk is connected with the lathe revolving stage, adjustable support is connected with end revolution mechanic.
3. The laser welding fixture for the circumferential seams of the exhaust funnel of the aircraft engine as claimed in claim 2, wherein the end rotating structure comprises a rotating shaft, a rotating body and a locking device, the rotating shaft is connected with the adjustable support and can rotate around the axial direction of the rotating shaft, the rotating body is of a three-jaw structure, the rotating body is sleeved on the rotating shaft, and each jaw structure is provided with the locking device of the driving mechanism and a positioning support hole of the driving mechanism.
4. The laser welding fixture for the circular seam of the exhaust funnel of the aircraft engine as claimed in claim 1, wherein the positioning plate structure comprises a first positioning plate, a second positioning plate and a third positioning plate, each positioning plate comprises a gearwheel, a guide pin and three sector plates; the large gear is provided with an end face spiral groove, the guide pin is fixed on the fan-shaped discs and can slide in the end face spiral groove, three fan-shaped discs on each positioning disc are respectively connected with the slide rails on the corresponding supporting discs and can move along the radial direction of the supporting discs, the large gear rotationally drives each fan-shaped positioning disc to move in a telescopic manner along the radial direction, 3 fan-shaped positioning discs on each positioning disc can simultaneously stretch in the radial direction to realize the scaling of the diameter of the supporting disc, the middle parts of the outer diameters of the second positioning disc and the third positioning disc are provided with protective gas through grooves, the bottom parts of the grooves are provided with vent holes for the protective gas, and the outer diameters of the first positioning disc, the second positioning disc and the third positioning disc are matched with the inner diameter of an exhaust funnel of an aircraft engine.
5. The aircraft engine aiutage circumferential weld laser welding anchor clamps of claim 1, characterized in that positioning disk actuating mechanism, including three hand wheel, first drive pivot, second drive pivot, third drive pivot, three pinion, first drive pivot passes first supporting disk in proper order, the second supporting disk, the oilless bush on the third supporting disk, the first supporting disk is passed in proper order in the second drive pivot, the oilless bush on the second supporting disk, the third drive pivot passes the oilless bush on the first supporting disk, every drive pivot one end installation hand wheel, other end installation pinion, the pinion respectively with first supporting disk, the second supporting disk, the gear wheel meshing on the third supporting disk.
6. The laser welding jig for the circumferential seams of the exhaust funnel of the aircraft engine as claimed in claim 1, wherein the gas protection device comprises a vent line and a gas line joint; the gas pipeline joint is connected with the protective gas through holes on the second supporting disk and the third supporting disk, one end of the vent pipeline is connected with the gas pipeline joint, and the other end of the vent pipeline is connected with an external protective gas source.
7. The laser welding fixture for the circular seam of the exhaust funnel of the aircraft engine as claimed in claim 1, wherein the adjustable support comprises a base, a support shaft, a roller mounting seat and four rollers; the pedestal mounting is on the lathe mesa, and back shaft one end is connected with the base, and the other end is connected as a whole with the gyro wheel mount pad, and four gyro wheels are installed on the gyro wheel mount pad to be connected with the structural end revolution mechanic of main shaft.
8. The method for welding by using the circular seam laser welding fixture for the exhaust funnel of the aircraft engine as claimed in claim 1, is characterized by comprising the following steps:
8-1. before laser welding, a hand wheel on a positioning disk driving mechanism is rotated anticlockwise to drive a first driving rotating shaft, a second driving rotating shaft and a third driving rotating shaft to drive pinions on the first driving rotating shaft, the second driving rotating shaft and the third driving rotating shaft to rotate respectively, and the pinions drive large gears on a first positioning disk, a second positioning disk and a third positioning disk to rotate so as to drive the diameters of the three positioning disks to be reduced; after the diameters of the three positioning disks are all reduced, the exhaust funnel of the aircraft engine is sleeved on the three positioning disks;
8-2. after the installation of the exhaust funnel of the aircraft engine is finished, a hand wheel on a clockwise rotation positioning disk driving mechanism drives a first driving rotating shaft, a second driving rotating shaft and a third driving rotating shaft to drive a pinion to rotate, the pinion drives a large gear on a first positioning disk, a second positioning disk and a third positioning disk to rotate, and the large gear drives the diameters of the three positioning disks to be amplified until the diameters of the three positioning disks are attached to the inner diameter of the exhaust funnel of the aircraft engine; after the diameters of the three positioning plates are accurately attached to the inner diameter of the exhaust funnel of the aircraft engine, the exhaust funnel of the aircraft engine is accurately positioned, and the coaxiality and the butt joint gap are ensured;
8-3. in the laser welding process, the laser beam is always kept right above a welding seam of a first positioning disc, the welding seam of the first positioning disc of the exhaust cylinder of the whole aircraft engine is completed by rotating the device and the exhaust cylinder of the aircraft engine by 360 degrees through the rotating table of the machine tool, after the welding is completed, the laser beam is translated to the position right above the welding seam of a second positioning disc, and the device and the exhaust cylinder of the aircraft engine rotate by 360 degrees together through rotating the rotating table of the machine tool again to complete the welding seam of the second positioning disc of the exhaust cylinder of the whole aircraft engine;
8-4. after laser welding is finished, a hand wheel on a positioning disc driving mechanism is rotated anticlockwise to drive a first driving rotating shaft, a second driving rotating shaft and a third driving rotating shaft to drive a pinion to rotate, the pinion drives a large gear on a first positioning disc, a second positioning disc and a third positioning disc to rotate, and the large gear drives the three positioning discs to reduce in diameter; and (4) after the diameters of the three positioning plates are reduced, removing the welded exhaust pipe of the aircraft engine from the welding fixture.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110850761.6A CN113579630B (en) | 2021-07-27 | 2021-07-27 | Laser welding fixture and welding method for circular seam of exhaust funnel of aircraft engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110850761.6A CN113579630B (en) | 2021-07-27 | 2021-07-27 | Laser welding fixture and welding method for circular seam of exhaust funnel of aircraft engine |
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| CN113579630A true CN113579630A (en) | 2021-11-02 |
| CN113579630B CN113579630B (en) | 2023-04-14 |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201702524U (en) * | 2010-05-20 | 2011-01-12 | 什邡市明日宇航工业股份有限公司 | Titanium alloy girth welding fixture |
| CN103753082A (en) * | 2013-12-24 | 2014-04-30 | 华东理工大学 | Weld centring and gas protecting device for furnace tube |
| CN103978340A (en) * | 2014-05-12 | 2014-08-13 | 西北工业大学 | Girth welding device and girth welding method for aircraft pipeline component |
| CN105873718A (en) * | 2015-07-29 | 2016-08-17 | 洛阳德平科技股份有限公司 | Gas shielded welding internal welding machine for pipelines |
| CN207087406U (en) * | 2017-07-20 | 2018-03-13 | 湖北三江航天万峰科技发展有限公司 | A kind of thin-walled cone bay section housing Quick self-centering positioner |
| CN112958925A (en) * | 2021-01-29 | 2021-06-15 | 江苏师范大学 | Major diameter thin wall pipe precision laser welding modular fixture |
| WO2021144303A2 (en) * | 2020-01-13 | 2021-07-22 | Saipem S.P.A. | Internal line-up clamp and methods of welding pipe sections |
-
2021
- 2021-07-27 CN CN202110850761.6A patent/CN113579630B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201702524U (en) * | 2010-05-20 | 2011-01-12 | 什邡市明日宇航工业股份有限公司 | Titanium alloy girth welding fixture |
| CN103753082A (en) * | 2013-12-24 | 2014-04-30 | 华东理工大学 | Weld centring and gas protecting device for furnace tube |
| CN103978340A (en) * | 2014-05-12 | 2014-08-13 | 西北工业大学 | Girth welding device and girth welding method for aircraft pipeline component |
| CN105873718A (en) * | 2015-07-29 | 2016-08-17 | 洛阳德平科技股份有限公司 | Gas shielded welding internal welding machine for pipelines |
| CN207087406U (en) * | 2017-07-20 | 2018-03-13 | 湖北三江航天万峰科技发展有限公司 | A kind of thin-walled cone bay section housing Quick self-centering positioner |
| WO2021144303A2 (en) * | 2020-01-13 | 2021-07-22 | Saipem S.P.A. | Internal line-up clamp and methods of welding pipe sections |
| CN112958925A (en) * | 2021-01-29 | 2021-06-15 | 江苏师范大学 | Major diameter thin wall pipe precision laser welding modular fixture |
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| CN113579630B (en) | 2023-04-14 |
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