CN112207394B - Argon arc welding repair method for crack damage of high-temperature part of gas turbine - Google Patents
Argon arc welding repair method for crack damage of high-temperature part of gas turbine Download PDFInfo
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- CN112207394B CN112207394B CN202011312602.2A CN202011312602A CN112207394B CN 112207394 B CN112207394 B CN 112207394B CN 202011312602 A CN202011312602 A CN 202011312602A CN 112207394 B CN112207394 B CN 112207394B
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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
- B23K9/00—Arc welding or cutting
- B23K9/0026—Arc welding or cutting specially adapted for particular articles or work
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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
- B23K9/00—Arc welding or cutting
- B23K9/16—Arc welding or cutting making use of shielding gas
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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
- B23K9/00—Arc welding or cutting
- B23K9/235—Preliminary treatment
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Abstract
The invention belongs to the technical field of metallurgy, and discloses an argon arc welding repair method for crack damage of a high-temperature component of a gas turbine, which comprises the following steps: forming a V-shaped slotted hole along the crack of the workpiece to be repaired; a trapezoidal counter bore is formed in the end part of the first end of the V-shaped slotted hole; and fixing the workpiece to be repaired, and performing argon arc welding along the direction from the second end of the V-shaped slot hole to the trapezoidal counter bore until the welding of the trapezoidal counter bore is finished, so as to finish the crack damage repair of the workpiece to be repaired. The thickness of different high-temperature components of the gas turbine is considered to be different, and trapezoidal counter bores can be processed in the arc-closing area of the component to be welded, so that thick plate welding is changed into thin plate welding, smooth transition of molten drops is achieved, and finally the T-shaped nail head-shaped welding joint which is good in welding line forming, full in appearance and capable of meeting the requirements in performance is formed. The method is simple to operate, reliable, high in applicability and universality and high in economy, and can fully meet the repairing requirement of the crack damage of the high-temperature component of the gas turbine.
Description
Technical Field
The invention belongs to the technical field of metallurgy, and relates to an argon arc welding repair method for crack damage of a high-temperature component of a gas turbine.
Background
High-temperature components such as a gas turbine flame tube, a transition section, a turbine stator blade, a retaining ring and the like are used as core components of the gas turbine, and are the components with the worst working environment, the most complex structure, the most faults and the highest replacement cost. The high-temperature parts are in service under the conditions of long-time high temperature, high stress and frequent start and stop, and the high-temperature parts inevitably generate crack damage of different degrees, thereby seriously affecting the service safety of the high-temperature parts. In order to reduce the rejection rate of high-temperature components and ensure the economical and safe operation of gas turbine power generation equipment, the repairing method of the crack damage of the high-temperature components of the gas turbine has been paid attention by researchers at home and abroad.
At present, the reported methods for repairing the crack damage of the high-temperature component mainly comprise fusion welding such as argon arc welding, plasma arc welding and laser welding, and brazing methods such as activation diffusion and powder metallurgy. Before brazing, the surfaces of the defects need to be cleaned by a complex thermochemical process, pollutants are easy to remain, and moreover, a low-melting-point brittle phase is easy to generate in a weld zone to influence the brazing strength. Compared with brazing, the fusion welding method has stronger adaptability and plays a leading role in the high-temperature component repair technology. In fusion welding, the requirements of laser welding on welding operation environment are loose, the high-strength and high-toughness weld joint can be obtained, the application in the field of repairing hot channel parts is wide, but the requirements of laser welding on assembly gaps are strict. Argon arc welding and plasma arc welding and other traditional fusion welding methods are listed as a recommended method for welding repair of gas turbine hot channel components by the American Electric Power Research Institute (EPRI). The plasma arc welding has the advantages of high energy density, high penetrating capacity, high welding speed, high assembly gap adaptability, more welding parameters and high operation requirement. Compared with plasma welding and laser welding, the argon arc welding method has the advantages of wide range of applicable materials, wire filling, strong adaptability of assembly clearance, low cost, larger heat input amount, slower welding speed and easy welding deformation and cracking caused by generated residual stress. Aiming at crack damage repair, because of improper welding parameter selection and the surface tension action of the bottom surface of a molten pool, the front surface and the back surface of a welding seam are easy to dent, and the back surface of the welding seam is not filled and has insufficient strength. For the front surface depression of the welding seam in the arc-quenching area, some effective arc-quenching methods such as a welding current attenuation method, a welding speed increasing method, a multiple arc-quenching method, an arc-quenching plate application method and the like are formed.
However, no effective method is available for the back surface depression defect of the weld joint in the arc-ending region at present, and particularly for repairing the crack of a plate with larger thickness, the defect is particularly prominent and typical, and the workpiece is often scrapped because the back surface depression of the weld joint in the arc-ending region causes that the workpiece cannot meet the requirement. Therefore, the argon arc welding repairing method which is strong in applicability, relatively simple in operation and capable of effectively solving the problem of crack damage of the high-temperature part of the gas turbine with the sunken back of the welding line has important practical significance.
Disclosure of Invention
The invention aims to overcome the defect that a welding line often has a back surface depression after the existing argon arc welding repair method for the crack damage of the high-temperature component of the gas turbine in the prior art is repaired, and provides the argon arc welding repair method for the crack damage of the high-temperature component of the gas turbine.
In order to achieve the purpose, the invention adopts the following technical scheme to realize the purpose:
the argon arc welding repair method for the crack damage of the high-temperature component of the gas turbine comprises the following steps of:
s1: forming a V-shaped slotted hole along the crack of the workpiece to be repaired;
s2: a trapezoidal counter bore is formed in the end part of the first end of the V-shaped slotted hole;
s3: and fixing the workpiece to be repaired, and performing argon arc welding along the direction from the second end of the V-shaped slot hole to the trapezoidal counter bore until the welding of the trapezoidal counter bore is finished, so as to finish the crack damage repair of the workpiece to be repaired.
The invention further improves the following steps:
the gradient of the V-shaped slotted hole is 30-60 degrees, and the bottom surface gap of the V-shaped slotted hole is 1-3 mm.
And the end part of the second end of the V-shaped slotted hole is provided with an arc transition area.
And an arc transition area is arranged between the end part of the first end of the V-shaped slotted hole and the trapezoidal counter bore.
Before fixing the workpiece to be repaired, polishing the workpiece to be repaired to obtain metallic luster, and ultrasonically cleaning the workpiece in acetone and dilute hydrochloric acid.
When carrying out argon arc welding along the direction of V type slotted hole second end to trapezoidal counter bore, weld and cover welding including the backing weld that goes on in proper order to when welding trapezoidal counter bore, carry out a plurality of bead weldings along the marginal round of trapezoidal counter bore.
When carrying out argon arc welding along the direction of V type slotted hole second end to trapezoidal counter bore, including backing weld, filling welding and the facing weld that carries out in proper order to when welding trapezoidal counter bore, carry out a plurality of bead weldings along the marginal round of trapezoidal counter bore.
The current of the backing welding is 70-80A, and the current of the cover surface welding is 90A.
The distance between the bottom surface of the trapezoidal counter bore and the bottom surface of the workpiece to be repaired is 2-3 mm.
The diameter of the hole of the trapezoidal counter bore is 8-12 mm.
Compared with the prior art, the invention has the following beneficial effects:
according to the argon arc welding repair method for the crack damage of the high-temperature component of the gas turbine, the trapezoidal counter bore is formed in the end part of the first end of the V-shaped slotted hole, so that the argon arc welding repair method is suitable for both thin plate components and thick plate components, no matter how thick plates are, the residual thickness of the bottom surface can be within a certain range by forming the trapezoidal counter bore, and therefore thick plate welding repair is changed into thin plate welding repair, smooth transition of molten drops is achieved, the T-shaped nail head-shaped welding joint which is good in weld forming, full in appearance and capable of meeting the requirements is finally formed, and the problems that the back of an arc closing area is sunken when the thick plate welding repair is carried out by adopting traditional argon arc welding are solved. Meanwhile, for the high-temperature component, the crack damage is the main consideration factor for determining whether the component can be continuously used, so the method is used for repairing the high-temperature component, and can be continuously used for the next maintenance period after being repaired, thereby reducing the rejection rate of the component, bringing great economic benefit and having wide application prospect. The main procedures of the method comprise groove design and processing, part fixing and argon arc welding, the main welding repair processes of different high-temperature parts are basically the same, and the method is simple to operate, reliable, high in applicability and universality and convenient for flow operation. In conclusion, the argon arc welding repair method for the crack damage of the high-temperature component of the gas turbine is simple to operate, reliable, high in applicability and universality and high in economy, and can meet the repair requirement for the crack damage of the high-temperature component of the gas turbine.
Drawings
FIG. 1 is a flowchart of an argon arc welding repair method for crack damage of a high-temperature component of a gas turbine according to an embodiment of the invention;
FIG. 2 is a schematic diagram of a design of a V-groove hole according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of the design of the thickness of the bottom surface of the trapezoidal counterbore of the embodiment of the invention.
Wherein: 1-V type slotted hole; 2-molten dripping; 3-trapezoidal counter bore bottom surface.
Detailed Description
In order to make the technical solutions of the present invention better understood, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that the terms "first," "second," and the like in the description and claims of the present invention and in the drawings described above are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used is interchangeable under appropriate circumstances such that the embodiments of the invention described herein are capable of operation in sequences other than those illustrated or described herein. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed, but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
The invention is described in further detail below with reference to the accompanying drawings:
referring to fig. 1, the embodiment of the invention provides an argon arc welding repair method for crack damage of a high-temperature component of a gas turbine, which combines groove design processing, multilayer welding and multi-pass surfacing, considers the different thicknesses of different gas turbine components, can process a trapezoidal counter bore in an arc-ending area of the component to be repaired, and controls the thickness of the bottom surface of the trapezoidal counter bore to be 2-3 mm, so that thick plate welding repair is changed into a thin plate welding repair problem, thereby realizing smooth transition of a molten drop 2, and finally forming a T-shaped nail head-shaped welding joint with good welding seam forming, full appearance and meeting the requirements in performance. The high-temperature components of the gas turbine comprise main high-temperature components of the gas turbine, such as a gas turbine flame tube, a transition section, a turbine stator blade, a retaining ring and the like. The component materials comprise nickel-based and cobalt-based high-temperature alloy materials commonly used for high-temperature components of modern gas turbines, including Hastelloy X, Nimonic263, HS-188, FSX414, GTD222, MGA1400, IN738, IN939 and the like. Specifically, the argon arc welding repair method for the crack damage of the high-temperature component of the gas turbine comprises the following steps.
S1: and forming a V-shaped slotted hole 1 along the crack of the workpiece to be repaired.
Specifically, the workpiece is ground into a V-shaped groove along the cracks of the workpiece by a mechanical grinding method, the gap between the bottom surfaces of the V-shaped groove is about 1-3 mm, two ends of the V-shaped groove 1 need to be in smooth transition, and the slope is smaller and is about 30-60 degrees.
S2: the end part of the first end of the V-shaped slotted hole 1 is provided with a trapezoidal counter bore.
Specifically, according to part thickness, the arc closing area is processed into a trapezoidal counter bore, the circular arc transition area is arranged at the center of the bottom surface of the trapezoidal counter bore and on the bottom surface of the V-shaped groove hole 1 to perform smooth transition, the diameter of the upper end of the trapezoidal counter bore is about 10-14 mm, the diameter of the bottom surface of the lower end of the trapezoidal counter bore is about 6-8 mm, the distance between the bottom surface of the trapezoidal counter bore and the bottom surface of the part is kept at 2-3 mm, and the bottom surface of the trapezoidal counter bore and the wall surface of the trapezoidal counter bore are in smooth transition.
S3: and fixing the workpiece to be repaired, and performing argon arc welding in the direction from the second end of the V-shaped groove hole 1 to the trapezoidal counter bore until the welding of the trapezoidal counter bore is finished, thereby completing the crack damage repair of the workpiece to be repaired.
Specifically, a workpiece to be repaired is fixed by a special welding tool clamp, so that the workpiece to be repaired is accurately positioned and clamped, and the workpiece to be repaired is prevented from deforming in the welding process.
Argon arc welding is carried out along the direction from the second end of the V-shaped groove hole 1 to the trapezoid counter bore, protective gas is introduced into the back face, welding current is properly adjusted and wires are filled according to the thickness of the thin plate, the back face of a welding line is fully formed, welding of the trapezoid counter bore is completed, and crack damage repairing of a workpiece to be repaired is completed.
When argon arc welding is carried out along the direction from the second end of the V-shaped slotted hole 1 to the trapezoidal counter bore, the argon arc welding comprises backing welding and cover surface welding which are sequentially carried out, and when the trapezoidal counter bore is welded, a plurality of bead welding are carried out along one circle of the edge of the trapezoidal counter bore. During backing welding, the welding current is properly adjusted and the wire is filled according to the thickness of a workpiece to be repaired, the welding current is properly increased between 60A and 90A along with the increase of the plate thickness of the workpiece to be repaired from 2mm to 3mm, and the welding speed is reduced and the wire is continuously filled when the welding is carried out to the arc transition region from the V-shaped slotted hole 1 to the trapezoidal counter bore, so that the back surface of an arc closing region can be effectively prevented from sinking, and the back surface of the whole welding seam is ensured to be formed fully.
Preferably, whether an intermediate filling layer is needed or not is selected according to the thickness of the workpiece to be repaired, the thickness of the workpiece to be repaired is generally between 3mm and 12mm, when the thickness of a repair area of the workpiece to be repaired is larger than 4mm, an intermediate filling welding procedure is needed, and the filling welding can increase current properly, so that the filling amount of welding materials is increased. When the thickness of the repair area of the workpiece to be repaired is less than or equal to 4mm, the middle filling welding procedure is not considered. The cover welding can increase the current properly, increase the welding speed, and reduce the welding heat input as much as possible on the premise of ensuring the proper weld reinforcement.
Preferably, before fixing the workpiece to be repaired, the workpiece to be repaired is polished to have metallic luster, the crack and the surface area of the part nearby are polished to have metallic luster by using sand paper, and dirt, oil stain, dust and the like are removed by ultrasonic cleaning in acetone and dilute hydrochloric acid.
The basic principle of the invention is as follows: referring to fig. 2 and 3, the groove of the arc-ending area of the welding of the workpiece to be repaired is designed to be thin plate welding, the trapezoid counter bore is processed to the V-shaped groove hole 1 in the arc-ending area of the thick plate welding, the V-shaped groove hole 1 and the bottom surface of the trapezoid counter bore are in smooth transition, and when the V-shaped groove hole 1 and the bottom surface of the trapezoid counter bore are welded to an interface, the molten drop 2 is also in smooth transition, so that the phenomenon that the depth of a single V-shaped groove is large, the impact force of electric arc on a molten pool is small, and the molten drop 2 is contracted under the action of the surface tension of the liquid level of the molten pool to cause the inner concave of the molten drop 2 is avoided. According to the groove design, when the molten drop 2 reaches the bottom surface 3 of the trapezoidal counter bore, the base metal is subjected to self-melting to form the molten drop 2 with larger mass, and due to the impact of electric arcs and the gravity of the molten drop 2, the traction effect of two sides of the V-shaped slotted hole 1 on the molten drop 2 is lost, so that a full welding seam is formed on the back surface of the molten drop 2 in the solidification process. Taking the Nimonic263 deformed high-temperature alloy material used in the service transition section and the FSX414 cast high-temperature alloy material used in the turbine stationary blade as examples, the front side and the back side of the argon arc welding seam arc-receiving area of the Nimonic263 deformed high-temperature alloy material used in the transition section and the FSX414 cast cobalt-based high-temperature alloy material used in the turbine stationary blade obtained by the argon arc welding repair method for the crack damage of the high-temperature component of the gas turbine are slightly convex and full.
Example 1
A V-shaped slotted hole 1 is formed in a Nimonic263 high-temperature alloy test plate material used in a transition section with the thickness of 4mm, the V-shaped slotted hole 1 comprises an arc transition area of an arc striking area, a middle V-shaped slotted hole 1 and a trapezoidal counter bore of an arc ending area, and the designed bottom surface of the trapezoidal counter bore is thinned to 2 mm; sanding the V-shaped slotted hole 1 and the surface area of the material nearby the V-shaped slotted hole with sand paper to form metallic luster, and then ultrasonically cleaning the V-shaped slotted hole in acetone and dilute hydrochloric acid to remove dirt, oil stains, dust and the like; fixing the test plate by using a flat plate tool with a cooling system; protective gas is introduced to the back, the backing welding current is 70A, and when the welding is carried out to the transition area between the V-shaped groove hole 1 and the bottom surface of the trapezoidal counter bore, the welding speed is reduced and two drops of welding materials are filled at the same time; the middle part does not need to be filled and welded, cover surface welding is directly carried out, the current is 90A, the welding is carried out to the trapezoidal counter bore area along the edge of the trapezoidal counter bore area for multi-pass surfacing, the surfacing speed is properly increased, the heat input and the heat deformation are reduced, and finally, a welding seam which is good in forming and full in filling is obtained.
Example 2
A V-shaped slotted hole 1 is formed in an FSX414 high-temperature alloy test plate material used for a turbine stationary blade with the thickness of 6mm, the V-shaped slotted hole 1 comprises an arc transition area of an arc striking area, a middle V-shaped slotted hole 1 and a trapezoidal counter bore of an arc ending area, and the designed bottom surface of the trapezoidal counter bore is thinned to 2 mm; sanding the V-shaped slotted hole 1 and the surface area of the material nearby the V-shaped slotted hole with sand paper to form metallic luster, and then ultrasonically cleaning the V-shaped slotted hole in acetone and dilute hydrochloric acid to remove dirt, oil stains, dust and the like; fixing the test plate by using a flat plate tool with a cooling system; protective gas is introduced to the back, the backing welding current is 80A, and when the welding is carried out to the transition region of the V-shaped groove hole 1 and the bottom surface of the trapezoidal counter bore, the welding speed is reduced and two drops of welding materials are filled at the same time; the filling current and the cover welding current are respectively 90A, and the welding current is welded to the trapezoidal counter bore area along the edge of the trapezoidal counter bore area for one circle of multi-pass surfacing, so that the surfacing speed is properly increased, and the heat input and the heat deformation are reduced. Finally, the welding line which is well formed and fully filled is obtained.
Comparing the front and back shapes of a transition section material (Nimonic263) argon arc welding seam closed zone obtained by adopting a common groove and an improved groove, adopting a common V-shaped groove hole 1 groove, wherein the front shape of the argon arc welding seam closed zone is slightly convex and is similar to a slender nail shape, and the back shape of the arc welding seam closed zone is seriously concave; in contrast, by adopting the improved groove form of the invention, the front surface of the welding line in the arc-closing area of argon arc welding is slightly convex and is similar to a T-shaped nail head; the back of the welding line of the arc-closing area is slightly convex in shape and is fully filled. Comparing the front and back shapes of a welding line of the turbine stationary blade material (FSX414) obtained by argon arc welding in the form of a common groove and an improved groove, adopting a common V-shaped groove hole 1 groove, wherein the front shape of the welding line of the argon arc welding arc closing area is slightly convex and is similar to a slender nail shape, and the back shape of the welding line of the arc closing area is seriously concave; in contrast, by adopting the improved groove form of the invention, the front surface of the welding line in the arc-closing area of argon arc welding is slightly convex and is similar to a T-shaped nail head; the back of the welding line of the arc-closing area is slightly convex in shape and is fully filled.
The argon arc welding repair method for the crack damage of the high-temperature part of the gas turbine, disclosed by the invention, combines groove design and processing, multilayer and multi-pass surfacing, takes the recess defect existing in the actual crack damage welding repair of the service part into consideration, overcomes the outstanding problems of the traditional groove design and welding, has a good effect on the crack welding repair problem commonly existing in the high-temperature parts of the existing service E-grade, F-grade and even H-grade gas turbines, is generally suitable for the welding repair of the crack damage of the main high-temperature static parts of the gas turbines, such as flame tubes, transition sections, turbine stator blades and the like of the in-service heavy gas turbines, and has strong universality. The adopted groove designing and processing, multilayer and multi-channel surfacing methods are suitable for both thin plate parts and thick plate parts, theoretically, no matter how thick plates are, as long as the trapezoidal counter bore is processed when the groove is prepared in the arc-closing area, and the residual thickness of the bottom surface is kept within a certain range, the problem of back surface depression in the welding process can be solved through the method, and the method has strong applicability. The method can effectively repair the crack damage of the high-temperature component of the gas turbine, and for the high-temperature component, the crack damage is the main consideration factor for determining whether the component can be continuously used, so the method is used for repairing the high-temperature component, and can be continuously used to the next maintenance cycle after being repaired, thereby reducing the rejection rate of the component and bringing great economic benefit, and has wide application prospect. Meanwhile, the main procedures of the method comprise groove design and processing, part fixing, backing welding, filling, cover surface welding and multi-pass surfacing welding and the like, and the main welding and repairing processes of different high-temperature parts are basically the same. Therefore, the welding repair method provided by the invention is simple to operate, reliable, high in applicability and universality and convenient for flow operation.
In conclusion, the method is simple to operate, reliable, high in applicability and universality and high in economy, and can meet the requirement of repairing the crack damage of the high-temperature component of the gas turbine.
The above-mentioned contents are only for illustrating the technical idea of the present invention, and the protection scope of the present invention is not limited thereby, and any modification made on the basis of the technical idea of the present invention falls within the protection scope of the claims of the present invention.
Claims (7)
1. The argon arc welding repair method for the crack damage of the high-temperature component of the gas turbine is characterized by comprising the following steps of:
s1: forming a V-shaped slotted hole along the crack of the workpiece to be repaired;
s2: a trapezoidal counter bore is formed in the end part of the first end of the V-shaped slotted hole;
s3: fixing the workpiece to be repaired, and performing argon arc welding along the direction from the second end of the V-shaped slot hole to the trapezoidal counter bore until the welding of the trapezoidal counter bore is finished, so as to finish the crack damage repair of the workpiece to be repaired;
an arc transition area is arranged at the end part of the second end of the V-shaped slotted hole, and an arc transition area is arranged between the end part of the first end of the V-shaped slotted hole and the trapezoidal counter bore;
when carrying out argon arc welding along the direction of V type slotted hole second end to trapezoidal counter bore, weld and cover welding including the backing weld that goes on in proper order to when welding trapezoidal counter bore, carry out a plurality of bead weldings along the marginal round of trapezoidal counter bore.
2. The argon arc welding repair method for the crack damage of the high-temperature component of the gas turbine as claimed in claim 1, wherein the gradient of the V-shaped groove hole is 30-60 degrees, and the bottom gap of the V-shaped groove hole is 1-3 mm.
3. The argon arc welding repair method for the crack damage of the high-temperature component of the gas turbine as claimed in claim 1, wherein before the workpiece to be repaired is fixed, the workpiece to be repaired is polished to have metallic luster and is ultrasonically cleaned in acetone and dilute hydrochloric acid.
4. The argon arc welding repair method for the crack damage of the high-temperature component of the gas turbine as claimed in claim 1, wherein the argon arc welding along the direction from the second end of the V-shaped slot to the trapezoidal counter bore comprises backing welding, filling welding and cover surface welding which are sequentially performed, and a plurality of overlaying welding processes are performed along one circle of the edge of the trapezoidal counter bore when the trapezoidal counter bore is welded.
5. The argon arc welding repair method for the crack damage of the high-temperature component of the gas turbine as claimed in claim 1 or 4, wherein the current of the backing welding is 70-80A, and the current of the cover surface welding is 90A.
6. The argon arc welding repair method for the crack damage of the high-temperature component of the gas turbine as claimed in claim 1, wherein the distance between the bottom surface of the trapezoidal counter bore and the bottom surface of the workpiece to be repaired is 2-3 mm.
7. The argon arc welding repairing method for the crack damage of the high-temperature component of the gas turbine as claimed in claim 1, wherein the hole diameter of the trapezoidal counter bore is 8-12 mm.
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