CN112059529A - Method for repairing abrasion of inner wall of thin-wall titanium alloy conduit joint for aircraft engine - Google Patents
Method for repairing abrasion of inner wall of thin-wall titanium alloy conduit joint for aircraft engine Download PDFInfo
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- CN112059529A CN112059529A CN202010926846.3A CN202010926846A CN112059529A CN 112059529 A CN112059529 A CN 112059529A CN 202010926846 A CN202010926846 A CN 202010926846A CN 112059529 A CN112059529 A CN 112059529A
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- welding
- titanium alloy
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P6/00—Restoring or reconditioning objects
-
- 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
- B23K9/00—Arc welding or cutting
- B23K9/04—Welding for other purposes than joining, e.g. built-up welding
-
- 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
- B23K9/00—Arc welding or cutting
- B23K9/16—Arc welding or cutting making use of shielding gas
-
- 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
- B23K9/00—Arc welding or cutting
- B23K9/235—Preliminary treatment
-
- 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
- B23K9/00—Arc welding or cutting
- B23K9/32—Accessories
- B23K9/325—Devices for supplying or evacuating shielding gas
- B23K9/326—Purge gas rings, i.e. devices for supplying or evacuating shielding gas inside of hollow or tubular articles, e.g. pipes, vessels
Abstract
A method for repairing the abrasion of the inner wall of a thin-wall titanium alloy conduit joint for an aircraft engine comprises the following steps: preparing before welding: measuring the wear depth of the inner wall of each fault joint, cleaning the guide pipe, and polishing the wear of the inner wall of each fault joint; repair welding and repair: screwing a welding protection tool onto the fault joint, sealing the pipe orifice of each joint of the guide pipe except the fault joint to be repaired, introducing argon gas into the pipe and the welding protection tool, and performing repair welding on the abrasion of the inner wall of the fault joint; and (3) post-welding inspection: x-ray inspection is carried out on each fault joint, and the subsequent mechanical finishing can be carried out only through the inspected thin-wall titanium alloy guide pipe; mechanical finishing: clamping the inspected thin-wall titanium alloy guide pipe into a machining positioning tool, moving the thin-wall titanium alloy guide pipe and the machining positioning tool into a boring machine, aligning inner holes of fault joints, removing redundant welding seams in each fault joint by using the boring machine, and grinding and polishing the inner holes of the joints; and (3) trial assembly verification: and (5) performing a compression test, and warehousing after passing.
Description
Technical Field
The invention belongs to the technical field of aero-engines, and particularly relates to a method for repairing abrasion of an inner wall of a thin-wall titanium alloy conduit joint for an aero-engine.
Background
The titanium alloy material has high mechanical property and excellent stamping property, and can be welded in various forms, so that the titanium alloy material is widely applied to the production and manufacture of large-diameter pipelines of aero-engines.
At present, technologies such as argon arc welding, laser welding and electron beam welding are generally adopted for repair welding of titanium alloy parts, and for large titanium alloy parts such as conventional castings and sheet metal parts, the welding technologies are generally used on planes or positions where repair welding is easy to perform, and welding protection at the positions is easy to achieve, so that the requirement on machining after repair welding is low.
However, when facing the thin-wall titanium alloy conduit, the traditional repair welding method is not applicable any more, because the inner wall of the thin-wall titanium alloy conduit is cylindrical, argon protection is difficult to realize during repair welding, the wall thickness of the thin-wall titanium alloy conduit is only 1 mm-2 mm usually, and welding deformation is also difficult to control. In addition, because the thin-wall titanium alloy conduit applied to the aeroengine generally has a complex spatial shape, the requirement on the surface quality of the conduit joint after the solder on the inner wall is removed is high, and the mechanical processing and positioning are very difficult.
Therefore, at the present stage, aiming at the condition that the inner wall of the thin-wall titanium alloy conduit with a complex space shape is abraded, only the worn old conduit can be replaced completely, and the replaced old conduit can be only disposed according to scrapping, so that the repair cost of the aircraft engine is increased.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides a method for repairing the abrasion of the inner wall of a thin-wall titanium alloy conduit joint for an aeroengine, which can provide good argon protection during repair welding, can better control welding deformation, provides good mechanical processing positioning for a welding flux removing procedure of the inner wall of the conduit joint, and ensures the quality of mechanical finishing.
In order to achieve the purpose, the invention adopts the following technical scheme: a method for repairing the abrasion of the inner wall of a thin-wall titanium alloy conduit joint for an aircraft engine comprises the following steps:
the method comprises the following steps: preparation before welding
Firstly, measuring each fault joint on the thin-wall titanium alloy guide pipe by using calipers and an inside micrometer until the inner wall abrasion depth of all fault joints is measured, then, pressurizing and washing the thin-wall titanium alloy guide pipe by using lubricating oil and gasoline, and then, polishing the inner wall abrasion part of all fault joints by using an air drill and a grinding head to remove a surface oxidation layer and prepare for subsequent repair welding and repairing;
step two: repair welding repair
The method comprises the following steps: preparing welding protection tools with the same number as the fault joints, wherein the welding protection tools are of cylindrical structures, two-pole stepped holes are formed in the centers of the welding protection tools and are respectively a first stepped hole and a second stepped hole, the aperture of the first stepped hole is larger than that of the second stepped hole, an internal thread is formed in the inner hole wall of the second stepped hole, an argon gas access hole is formed in the hole wall of the first stepped hole, an argon gas nozzle is screwed in the argon gas access hole, and the argon gas nozzle is opposite to and communicated with the first stepped hole;
step two: the prepared welding protection tool is connected with the fault joint in a threaded mode through the internal thread of the second stepped hole, the first stepped hole is arranged inwards or outwards according to the distance between the inner wall abrasion part and the pipe orifice of the fault joint, and meanwhile the threaded connection distance between the fault joint and the second stepped hole is adjusted, so that the outer wall surface of the inner wall abrasion part of the fault joint is opposite to the gas outlet of the argon nozzle;
step three: except for the selected fault joint to be repaired, plugging other joint pipe orifices of the thin-wall titanium alloy conduit by using adhesive tapes, and then introducing argon into the thin-wall titanium alloy conduit through the reserved fault joint to be repaired; meanwhile, argon is introduced into the first stepped hole through an argon nozzle so as to form an annular cooling area on the outer wall surface at the worn part of the inner wall of the fault joint;
step IV: repairing and welding the inner wall abrasion of all fault joints by using an argon arc welding mode, and ensuring that the inner wall abrasion grooves are fully filled with welding flux;
step three: post weld inspection
After all fault joints on the thin-wall titanium alloy guide pipe are subjected to repair welding, X-ray inspection is carried out on all fault joints, and the subsequent mechanical finishing can be carried out only through the inspected thin-wall titanium alloy guide pipe;
step four: mechanical finishing
Clamping the checked thin-wall titanium alloy guide pipe into a machining positioning tool prepared in advance, then moving the machining positioning tool clamped with the thin-wall titanium alloy guide pipe into a boring machine, and then aligning an inner hole of a fault joint by using a dial indicator; after the alignment is finished, removing redundant welding seams in each fault joint by using a boring machine, and finally grinding and polishing an inner hole of the joint;
step five: trial verification
And trial assembling the repaired thin-wall titanium alloy guide pipe and a matched guide pipe, performing a compression test on the combined body, and storing the thin-wall titanium alloy guide pipe which passes the compression test for later use.
In the mechanical truing step, the mechanical processing location frock of adoption is modular structure, including the bottom plate, the locating pin post, screw rod clamp plate subassembly and V type piece clamp plate subassembly, the locating pin post, a plurality of and the size difference of quantity of screw rod clamp plate subassembly and V type piece clamp plate subassembly, the locating pin post, the mounted position and the quantity of screw rod clamp plate subassembly and V type piece clamp plate subassembly on the bottom plate are adjustable, the locating pin post is used for circumference location pipe mouth of pipe, screw rod clamp plate subassembly is used for compressing tightly the pipe outer wall perpendicularly, V type piece clamp plate subassembly is used for circumference to compress tightly the pipe outer wall.
The repair welding technological parameters of argon arc welding are as follows: the current intensity is 30A-50A, the type of the tungsten electrode is WCe-20 phi 2.0mm, the type of the welding wire is TA15-1 or BT20 phi 1.2 mm-phi 1.6mm, and the argon flow of the welding gun is 8L/min-10L/min.
The invention has the beneficial effects that:
the method for repairing the abrasion of the inner wall of the thin-wall titanium alloy conduit joint for the aircraft engine can provide good argon protection during repair welding, can better control welding deformation, provides good machining positioning for a welding flux removing procedure of the inner wall of the conduit joint, and ensures the quality of mechanical fine repair.
Drawings
FIG. 1 is a schematic structural view of a thin-walled titanium alloy catheter in an example;
FIG. 2 is a schematic structural diagram of the welding protection tool of the present invention
FIG. 3 is a schematic view of the assembly of the welding protection tool and the failed joint of the present invention (with the first step hole disposed inward);
FIG. 4 is a schematic view of the assembly of the welding protection tool and the failed joint of the present invention (with the first step hole disposed outward);
FIG. 5 is a schematic structural diagram of a machining positioning tool in an embodiment;
FIG. 6 is a view taken along line A of FIG. 5;
FIG. 7 is a view taken along line B of FIG. 5;
in the figure, 1-a first stepped hole, 2-a second stepped hole, 3-an argon nozzle, 4-a bottom plate, 5-a positioning pin column, 6-a screw rod pressing plate component, 7-a V-shaped block pressing plate component, 8-a thin-wall titanium alloy conduit, 9-a fault joint and 10-inner wall abrasion.
Detailed Description
The invention is described in further detail below with reference to the figures and the specific embodiments.
A method for repairing the abrasion of the inner wall of a thin-wall titanium alloy conduit joint for an aircraft engine comprises the following steps:
the method comprises the following steps: preparation before welding
Firstly, measuring each fault joint on the thin-wall titanium alloy guide pipe shown in the figure 1 by using calipers and an inside micrometer until the inner wall abrasion depth of all the fault joints is measured, then, pressurizing and washing the thin-wall titanium alloy guide pipe by using lubricating oil and gasoline, and then, polishing the inner wall abrasion part of all the fault joints by using an air drill and a grinding head to remove surface oxide layers and prepare for subsequent repair welding and repairing;
step two: repair welding repair
The method comprises the following steps: preparing welding protection tools with the same number as the number of fault joints, wherein the welding protection tools are of a cylindrical structure, two-pole stepped holes, namely a first stepped hole 1 and a second stepped hole 2, are formed in the center of each welding protection tool, the aperture of the first stepped hole 1 is larger than that of the second stepped hole 2, internal threads are formed in the inner hole wall of the second stepped hole 2, an argon gas access hole is formed in the hole wall of the first stepped hole 1, an argon gas nozzle 3 is screwed in the argon gas access hole, and the argon gas nozzle 3 is opposite to and communicated with the first stepped hole 1;
step two: the prepared welding protection tool is connected with the fault joint in a threaded mode through the internal thread of the second stepped hole 2, the first stepped hole 1 is determined to be arranged inwards or outwards according to the distance between the inner wall abrasion part and the pipe orifice of the fault joint, and meanwhile the threaded connection distance between the fault joint and the second stepped hole 2 is adjusted, so that the outer wall surface of the inner wall abrasion part of the fault joint is opposite to the gas outlet of the argon nozzle 3;
step three: except for the selected fault joint to be repaired, plugging other joint pipe orifices of the thin-wall titanium alloy conduit by using adhesive tapes, and then introducing argon into the thin-wall titanium alloy conduit through the reserved fault joint to be repaired; meanwhile, argon is introduced into the first stepped hole 1 through an argon nozzle 3, so that an annular cooling area is formed on the outer wall surface at the worn part of the inner wall of the fault joint; the flow rate of argon is 6L/min-8L/min;
step IV: repairing and welding the inner wall abrasion of all fault joints by using an argon arc welding mode, and ensuring that the inner wall abrasion grooves are fully filled with welding flux; the repair welding technological parameters of argon arc welding are as follows: the current intensity is 30A-50A, the type of the tungsten electrode is WCe-20 phi 2.0mm, the type of the welding wire is TA15-1 or BT20 phi 1.2 mm-phi 1.6mm, and the argon flow of the welding gun is 8L/min-10L/min;
step three: post weld inspection
After all fault joints on the thin-wall titanium alloy guide pipe are subjected to repair welding, X-ray inspection is carried out on all fault joints, and the subsequent mechanical finishing can be carried out only through the inspected thin-wall titanium alloy guide pipe;
step four: mechanical finishing
Clamping the inspected thin-wall titanium alloy guide pipe into a machining positioning tool which is prepared in advance and is shown in the figures 5-7, moving the machining positioning tool clamped with the thin-wall titanium alloy guide pipe into a boring machine, and then aligning an inner hole of a fault joint by using a dial indicator, wherein the point aligning error is required to be less than 0.05mm, and the end jump error is required to be less than 0.02 mm; after the alignment is finished, removing redundant welding seams in each fault joint by using a boring machine, wherein the rotating speed of a spindle of the boring machine is 300r/min, and the feeding amount is 16 mm/min; finally, grinding and polishing the inner hole of the joint by using a pneumatic drill, a grinding head, a diamond finishing pen, a rubber wheel, wool felt and grinding paste in sequence; the adopted machining positioning tool is of a modular structure and comprises a base plate 4, a positioning pin column 5, a screw pressing plate assembly 6 and a V-shaped block pressing plate assembly 7, the positioning pin column 5, the screw pressing plate assembly 6 and the V-shaped block pressing plate assembly 7 are different in quantity and size, the mounting positions and the number of the positioning pin column 5, the screw pressing plate assembly 6 and the V-shaped block pressing plate assembly 7 on the base plate 3 are adjustable, the positioning pin column 5 is used for circumferentially positioning a pipe orifice, the screw pressing plate assembly 6 is used for vertically pressing an outer wall of a pipe, and the V-shaped block pressing plate assembly 7 is used for circumferentially pressing the outer wall of the pipe.
Step five: trial verification
And trial assembling the repaired thin-wall titanium alloy guide pipe and a matched guide pipe, and performing a compression test on the combined body, wherein the medium of the compression test is kerosene, the compression pressure is 1.5Mpa, the compression time is 5min, and only the thin-wall titanium alloy guide pipe passing the compression test can be put in storage for standby.
The embodiments are not intended to limit the scope of the present invention, and all equivalent implementations or modifications without departing from the scope of the present invention are intended to be included in the scope of the present invention.
Claims (3)
1. A method for repairing the abrasion of the inner wall of a thin-wall titanium alloy conduit joint for an aircraft engine is characterized by comprising the following steps:
the method comprises the following steps: preparation before welding
Firstly, measuring each fault joint on the thin-wall titanium alloy guide pipe by using calipers and an inside micrometer until the inner wall abrasion depth of all fault joints is measured, then, pressurizing and washing the thin-wall titanium alloy guide pipe by using lubricating oil and gasoline, and then, polishing the inner wall abrasion part of all fault joints by using an air drill and a grinding head to remove a surface oxidation layer and prepare for subsequent repair welding and repairing;
step two: repair welding repair
The method comprises the following steps: preparing welding protection tools with the same number as the fault joints, wherein the welding protection tools are of cylindrical structures, two-pole stepped holes are formed in the centers of the welding protection tools and are respectively a first stepped hole and a second stepped hole, the aperture of the first stepped hole is larger than that of the second stepped hole, an internal thread is formed in the inner hole wall of the second stepped hole, an argon gas access hole is formed in the hole wall of the first stepped hole, an argon gas nozzle is screwed in the argon gas access hole, and the argon gas nozzle is opposite to and communicated with the first stepped hole;
step two: the prepared welding protection tool is connected with the fault joint in a threaded mode through the internal thread of the second stepped hole, the first stepped hole is arranged inwards or outwards according to the distance between the inner wall abrasion part and the pipe orifice of the fault joint, and meanwhile the threaded connection distance between the fault joint and the second stepped hole is adjusted, so that the outer wall surface of the inner wall abrasion part of the fault joint is opposite to the gas outlet of the argon nozzle;
step three: except for the selected fault joint to be repaired, plugging other joint pipe orifices of the thin-wall titanium alloy conduit by using adhesive tapes, and then introducing argon into the thin-wall titanium alloy conduit through the reserved fault joint to be repaired; meanwhile, argon is introduced into the first stepped hole through an argon nozzle so as to form an annular cooling area on the outer wall surface at the worn part of the inner wall of the fault joint;
step IV: repairing and welding the inner wall abrasion of all fault joints by using an argon arc welding mode, and ensuring that the inner wall abrasion grooves are fully filled with welding flux;
step three: post weld inspection
After all fault joints on the thin-wall titanium alloy guide pipe are subjected to repair welding, X-ray inspection is carried out on all fault joints, and the subsequent mechanical finishing can be carried out only through the inspected thin-wall titanium alloy guide pipe;
step four: mechanical finishing
Clamping the checked thin-wall titanium alloy guide pipe into a machining positioning tool prepared in advance, then moving the machining positioning tool clamped with the thin-wall titanium alloy guide pipe into a boring machine, and then aligning an inner hole of a fault joint by using a dial indicator; after the alignment is finished, removing redundant welding seams in each fault joint by using a boring machine, and finally grinding and polishing an inner hole of the joint;
step five: trial verification
And trial assembling the repaired thin-wall titanium alloy guide pipe and a matched guide pipe, performing a compression test on the combined body, and storing the thin-wall titanium alloy guide pipe which passes the compression test for later use.
2. The method for repairing the abrasion of the inner wall of the thin-wall titanium alloy conduit joint for the aircraft engine as claimed in claim 1, wherein the method comprises the following steps: in the mechanical truing step, the mechanical processing location frock of adoption is modular structure, including the bottom plate, the locating pin post, screw rod clamp plate subassembly and V type piece clamp plate subassembly, the locating pin post, a plurality of and the size difference of quantity of screw rod clamp plate subassembly and V type piece clamp plate subassembly, the locating pin post, the mounted position and the quantity of screw rod clamp plate subassembly and V type piece clamp plate subassembly on the bottom plate are adjustable, the locating pin post is used for circumference location pipe mouth of pipe, screw rod clamp plate subassembly is used for compressing tightly the pipe outer wall perpendicularly, V type piece clamp plate subassembly is used for circumference to compress tightly the pipe outer wall.
3. The method for repairing the abrasion of the inner wall of the thin-wall titanium alloy conduit joint for the aircraft engine as claimed in claim 1, wherein the method comprises the following steps: the repair welding technological parameters of argon arc welding are as follows: the current intensity is 30A-50A, the type of the tungsten electrode is WCe-20 phi 2.0mm, the type of the welding wire is TA15-1 or BT20 phi 1.2 mm-phi 1.6mm, and the argon flow of the welding gun is 8L/min-10L/min.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010926846.3A CN112059529B (en) | 2020-09-07 | 2020-09-07 | Method for repairing abrasion of inner wall of thin-wall titanium alloy conduit joint for aircraft engine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010926846.3A CN112059529B (en) | 2020-09-07 | 2020-09-07 | Method for repairing abrasion of inner wall of thin-wall titanium alloy conduit joint for aircraft engine |
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| CN112059529B CN112059529B (en) | 2021-08-10 |
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Cited By (1)
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| CN115338594A (en) * | 2022-07-01 | 2022-11-15 | 中国航发南方工业有限公司 | Air tightness repairing method for conduit in combined cavity of rear support shell |
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| CN115338594B (en) * | 2022-07-01 | 2024-02-20 | 中国航发南方工业有限公司 | Air tightness repairing method for catheter in combined cavity of rear bearing shell |
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| CN112059529B (en) | 2021-08-10 |
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