CN115383395B - Method for repairing damage of threaded blind hole on aeroengine compressor case - Google Patents
Method for repairing damage of threaded blind hole on aeroengine compressor case Download PDFInfo
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- CN115383395B CN115383395B CN202210893083.6A CN202210893083A CN115383395B CN 115383395 B CN115383395 B CN 115383395B CN 202210893083 A CN202210893083 A CN 202210893083A CN 115383395 B CN115383395 B CN 115383395B
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- 238000000034 method Methods 0.000 title claims abstract description 61
- 238000003466 welding Methods 0.000 claims abstract description 157
- 230000008439 repair process Effects 0.000 claims abstract description 22
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims abstract description 20
- 229910052786 argon Inorganic materials 0.000 claims abstract description 10
- 238000012545 processing Methods 0.000 claims abstract description 6
- 238000010079 rubber tapping Methods 0.000 claims abstract description 4
- 230000008569 process Effects 0.000 claims description 21
- 239000000463 material Substances 0.000 claims description 9
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims description 9
- 239000010937 tungsten Substances 0.000 claims description 9
- 229910052721 tungsten Inorganic materials 0.000 claims description 9
- 239000010953 base metal Substances 0.000 claims description 6
- 239000000919 ceramic Substances 0.000 claims description 6
- 238000005553 drilling Methods 0.000 claims description 6
- 239000011159 matrix material Substances 0.000 claims description 6
- 238000009966 trimming Methods 0.000 claims description 3
- 238000007689 inspection Methods 0.000 abstract description 4
- 239000010410 layer Substances 0.000 description 21
- 230000001681 protective effect Effects 0.000 description 5
- 238000002485 combustion reaction Methods 0.000 description 4
- 238000003754 machining Methods 0.000 description 4
- 238000013021 overheating Methods 0.000 description 4
- 239000002356 single layer Substances 0.000 description 4
- 238000009434 installation Methods 0.000 description 3
- 238000000137 annealing Methods 0.000 description 2
- 239000013078 crystal Substances 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 238000003303 reheating Methods 0.000 description 2
- 238000007711 solidification Methods 0.000 description 2
- 230000008023 solidification Effects 0.000 description 2
- NGONBPOYDYSZDR-UHFFFAOYSA-N [Ar].[W] Chemical compound [Ar].[W] NGONBPOYDYSZDR-UHFFFAOYSA-N 0.000 description 1
- 238000005299 abrasion Methods 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000007429 general method Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000012958 reprocessing Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
Classifications
-
- 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
- B23K9/16—Arc welding or cutting making use of shielding gas
- B23K9/167—Arc welding or cutting making use of shielding gas and of a non-consumable electrode
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Butt Welding And Welding Of Specific Article (AREA)
Abstract
The invention discloses a damage repair method for a threaded blind hole on an aeroengine compressor casing, which comprises the steps of firstly adopting a drill bit with the same diameter as a threaded hole to drill residual threads at the damaged threaded hole, then adopting argon tungsten-arc welding to carry out small-hole multilayer overlaying welding in the threaded hole until the overlaying welding position is higher than a workpiece mounting surface, then flattening the mounting surface, processing a new thread bottom hole at the original threaded hole position, tapping threads at the thread bottom hole, and carrying out appearance and size inspection.
Description
Technical Field
The invention relates to the technical field of threaded hole repair, in particular to a damage repair method for a threaded blind hole on an aero-engine compressor box.
Background
After the aeroengine parts are used for a long time and decomposed and installed for many times, the threaded holes on the combustion adjusting installation surface of the compressor box are frequently damaged by abrasion, broken buckles, scratch buckles and the like. Because the compressor casing has high material cost, high manufacturing difficulty and high casing value, the compressor casing must be saved by adopting a safe and reliable repairing method, and the service life of the compressor casing is prolonged. Specifically, as shown in fig. 1, the mounting surface of the compressor casing of a certain aeroengine is provided with a plurality of M8 threaded holes with the depth of about 17mm and the diameter of 8.2mm, the threaded holes are of a structure with small diameter, deep depth and thin wall thickness, and specifically, the threaded holes are positioned in bosses of a combustion adjusting mounting plate, and the thinnest wall thickness of the bosses at the threaded holes is only 2 mm. In order to improve the quality and reliability of repairing the compressor casing, the screw hole needs to have enough strength after repairing.
There are two general methods for repairing damage to threaded holes: insert thread bush and increase the screw thread specification. The method for embedding the thread bush is to enlarge the damaged threaded hole, embed a screw plug, and finish repairing by reprocessing the specified threaded hole in the middle of the screw plug. For example, the M8 threaded hole is repaired by a bushing method, at least one M14 plug is required to be inserted, as shown in fig. 2, the thinnest part between the bushing and the boss edge is only 0.6 mm, and the part of the compressor casing is a bearing part, so that the method cannot meet the requirement of strength and is not suitable for repairing the threaded hole of the structure. In addition, as shown in fig. 3, the method for increasing the screw thread specification is that if the screw thread of the M8 needs to be increased to repair, the repair can be realized only by increasing the screw hole to M10, the wall thickness of the screw hole at the edge of the boss is reduced from 4mm to 3mm, the strength is greatly reduced, the strength requirement of the mounting edge of the compressor case is not met, and especially, the thinnest wall thickness of the boss at the screw hole is only 2mm, and the strength reduction is more obvious. In addition, in the engine, other components and parts are assembled at the threaded hole of the compressor box, the threaded hole is enlarged at the same time for the object part, and bolts, washers and the like are specially matched, so that the universality and interchangeability of the engine components are not met, and the use is not allowed. Therefore, the existing repairing method for enlarging the screw thread specification cannot be applied to repairing the screw hole with the structure.
Therefore, due to the special structure of the threaded hole of the compressor casing and the assembly requirement of the engine, the existing method for repairing the damage of the threaded hole is not suitable for repairing the threaded hole.
Disclosure of Invention
The invention provides a damage repair method for a threaded blind hole on an aeroengine compressor case, which aims to solve the technical problem that the existing damage repair method for a threaded hole is not suitable for damage repair of an M8 threaded hole on the compressor case.
According to one aspect of the invention, a damage repair method for a threaded blind hole on an aeroengine compressor case is provided, and comprises the following steps:
drilling out residual threads at the damaged threaded holes by adopting a drill bit with the same diameter as the threaded holes;
carrying out small-hole multilayer overlaying welding in the threaded hole by adopting argon tungsten-arc welding until the overlaying welding position is higher than the workpiece mounting surface;
trimming the mounting surface, and processing a new threaded bottom hole at the original threaded hole position;
tapping the thread at the thread bottom hole, and checking the appearance and the size.
Further, the process of carrying out small-hole multilayer overlaying welding in the threaded hole by adopting argon tungsten-arc welding specifically comprises the following steps:
adjusting the angle of a welding gun to form an included angle of 90 degrees with a workpiece, starting an arc to burn a matrix material at the deepest part of a small hole, putting a welding wire section after a base metal is melted, and solidifying to form a dot-shaped surfacing layer for surfacing along the center line of the small hole after the welding wire section and the matrix material at the bottom of the hole are completely fused;
adjusting the angle of a welding gun to form a first included angle with a workpiece, throwing a next welding wire section, and swinging a tungsten electrode after the welding wire section is melted, so as to ensure that the welding wire section and a hole wall base material are completely fused, and solidifying to form an annular surfacing layer for surfacing along the hole wall;
the operation is alternately carried out until the height of the build-up welding layer reaches half of the depth of the hole;
and adjusting the angle of the welding gun to form a second included angle with the workpiece, and adding welding wires for surfacing until the surfacing is higher than the workpiece mounting surface.
Further, the method also comprises the following steps before carrying out the small-hole multilayer surfacing:
a chamfer is machined at the orifice.
Further, the chamfering process at the orifice is specifically as follows:
on a drilling machine, a chamfer is machined at the orifice by adopting a 60-degree chamfer cutter.
Further, the machining depth of the chamfering was 7 mm.
Further, a ceramic protective nozzle with the diameter of 9 mm is adopted as a nozzle of the welding gun, and the length of the tungsten electrode extending out of the ceramic protective nozzle is 15mm.
Further, the first included angle is 70-80 degrees.
Further, the second included angle is 60-65 degrees.
Further, the welding wire section is a section of welding wire with a diameter of 1.2 mm cut into a length of 5mm.
Further, the size of the new threaded bottom hole is 6mm in diameter, 1×45 ° in orifice chamfer, and 14 mm in depth.
The invention has the following effects:
according to the damage repair method for the threaded blind hole on the aeroengine compressor casing, the residual threads at the damaged threaded hole are drilled by adopting the drill bit with the same diameter as the threaded hole, then small-hole multilayer overlaying is carried out in the threaded hole by adopting tungsten argon arc welding until the overlaying position is higher than a workpiece mounting surface, then the mounting surface is flattened, a new threaded bottom hole is processed at the original threaded hole position, finally threads are tapped at the threaded bottom hole, appearance and size inspection are carried out, the diameter of the threaded hole is not increased in the whole damage repair process, the strength of the mounting edge of the threaded hole is ensured, the strength of the threads repaired by adopting the overlaying method is high and is close to the strength of a base metal, the newly processed threads are completely consistent with the original threads, a special object is not needed, compared with the existing embedding and reaming methods, the problems that the strength of the mounting edge of the threaded hole is reduced, the special object is needed to be increased are solved, and the damage repair method disclosed by the invention can be well applied to the damage repair of the threaded hole on the combustion adjustment mounting plate boss of the aeroengine casing, and the repaired threads are indiscriminate.
In addition, the invention can reduce welding deformation, reduce welding line stress and prevent welding line overheating by adopting a multilayer overlaying mode of alternately carrying out vertical welding and annular rotary swing welding. The welding current is generally larger during single-layer welding, the welding heat input is larger, and the welding deformation is larger, but the heat input amount is smaller during multi-layer overlaying welding than that during single-layer welding, the heat affected zone of the welding seam is smaller, the high-temperature stay time of the welding seam is short, the overheating of the welding seam joint is prevented, and the metallographic structure of the welding seam joint is effectively improved. And the multilayer build-up welding mode can also play a role in post-welding heat treatment, when the vertical welding and the annular swing welding are alternately performed, the back-pass welding seam is subjected to annealing treatment on the front-pass welding seam, so that the stress of the front-pass welding seam is reduced, and meanwhile, due to the fact that the back-pass welding seam is used for reheating the front-pass welding seam, crystal grains of the front-pass welding seam are thinned, the overall toughness of the welding seam is improved, and the welding quality is greatly improved. In addition, in the multilayer overlaying process, the problem that welding wires cannot be added in the welding process due to the fact that the space at the bottom of a threaded hole is narrow is effectively solved by adopting a mode of adding welding wire segments in the multilayer overlaying process in consideration of the fact that the welding wires cannot be added due to the fact that the small hole size is limited.
In addition to the objects, features and advantages described above, the present invention has other objects, features and advantages. The present invention will be described in further detail with reference to the drawings.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention. In the drawings:
fig. 1 is a schematic view of a threaded hole in a combustion adjustment mounting plate of a compressor case of an aero-engine.
FIG. 2 is a schematic illustration of a repair of a threaded bore using a prior art insert repair method.
FIG. 3 is a schematic diagram of a threaded hole repaired using a prior art oversized thread specification repair method.
Fig. 4 is a flow chart of a method for repairing damage to a threaded blind hole in an aero-engine compressor case according to a preferred embodiment of the present invention.
Fig. 5 is a schematic view of the structure of the present invention after the residual threads in the threaded hole are removed by using a drill bit.
Fig. 6 is a schematic view of the sub-flow of step S2 in fig. 4.
FIG. 7 is a schematic view of a structure of forming a spot weld overlay in a small hole in a preferred embodiment of the invention.
Fig. 8 is a schematic view of the structure of forming an annular weld overlay in a small hole in a preferred embodiment of the invention.
FIG. 9 is a schematic illustration of the alternate dot and annular weld overlay configuration within a small hole in accordance with a preferred embodiment of the present invention.
FIG. 10 is a schematic view of the structure of the hole in the preferred embodiment of the present invention after build-up welding is completed.
Fig. 11 is a schematic structural view of a welding gun according to a preferred embodiment of the present invention.
Fig. 12 is a flow chart of a method for repairing a blind threaded hole in an aeroengine compressor case according to another embodiment of the present invention.
Fig. 13 is a schematic dimensional view of an orifice chamfering process in accordance with another embodiment of the invention.
Fig. 14 is a schematic view of the size of a new threaded bottom hole in a preferred embodiment of the present invention.
FIG. 15 is a schematic illustration of the dimensions of an M8 thread tapped at a new thread pilot in a preferred embodiment of the invention.
Detailed Description
Embodiments of the invention are described in detail below with reference to the attached drawing figures, but the invention can be practiced in a number of different ways, as defined and covered below.
As shown in fig. 4, a preferred embodiment of the present invention provides a method for repairing damage to a threaded blind hole on an aeroengine compressor case, comprising the following steps:
step S1: drilling out residual threads at the damaged threaded holes by adopting a drill bit with the same diameter as the threaded holes;
step S2: carrying out small-hole multilayer overlaying welding in the threaded hole by adopting argon tungsten-arc welding until the overlaying welding position is higher than the workpiece mounting surface;
step S3: trimming the mounting surface, and processing a new threaded bottom hole at the original threaded hole position;
step S4: tapping the thread at the thread bottom hole, and checking the appearance and the size.
It can be understood that in the method for repairing the damaged blind hole on the aeroengine compressor casing, the drill bit with the same diameter as the threaded hole is adopted to drill the residual thread at the damaged threaded hole, then argon tungsten-arc welding is adopted to conduct small-hole multilayer surfacing in the threaded hole until the surfacing position is higher than the mounting surface of a workpiece, then the mounting surface is flattened, a new thread bottom hole is machined at the original threaded hole position, finally threads are tapped at the thread bottom hole, appearance and size inspection are conducted, the diameter of the threaded hole is not increased in the whole damage repairing process, the strength of the mounting edge at the threaded hole is guaranteed, the strength of the threads repaired by the surfacing method is high and is close to the strength of a base metal, the newly machined threads are completely consistent with the original threads, no special object is needed, compared with the existing embedding and reaming methods, the strength of the mounting edge of the threaded hole is reduced, the special object is also needed to be increased in reaming, and the like.
It will be appreciated that in step S1, as shown in fig. 5, for the repair of an M8 threaded hole having a diameter of 8.2mm, a drill having a diameter of 8.2mm is used to drill out the residual thread at the damaged threaded hole. Of course, in other embodiments of the present invention, drills of 8mm diameter, 8.1 mm diameter, 8.3mm diameter, 8.4mm diameter, etc. may also be used in view of machining errors.
It will be understood that, as shown in fig. 6, in the step S2, the process of performing the small-hole multilayer build-up welding in the threaded hole by using argon tungsten-arc welding specifically includes the following steps:
step S21: adjusting the angle of a welding gun to form an included angle of 90 degrees with a workpiece, starting an arc to burn a matrix material at the deepest part of a small hole, putting a welding wire section after a base metal is melted, and solidifying to form a dot-shaped surfacing layer for surfacing along the center line of the small hole after the welding wire section and the matrix material at the bottom of the hole are completely fused;
step S22: adjusting the angle of a welding gun to form a first included angle with a workpiece, throwing a next welding wire section, and swinging a tungsten electrode after the welding wire section is melted, so as to ensure that the welding wire section and a hole wall base material are completely fused, and solidifying to form an annular surfacing layer for surfacing along the hole wall;
step S23: the operation is alternately carried out until the height of the build-up welding layer reaches half of the depth of the hole;
step S24: and adjusting the angle of the welding gun to form a second included angle with the workpiece, and adding welding wires for surfacing until the surfacing is higher than the workpiece mounting surface.
It can be understood that the technical difficulty of overlaying the small holes by adopting the argon tungsten-arc welding method is as follows: the diameter of the small hole at the surfacing is only 8.2mm, the depth of the small hole is 17mm, the space at the deepest part of the small hole is too small, welding wires cannot be added in the welding process, and the surfacing difficulty is high. Therefore, the invention adopts a build-up welding mode of alternately carrying out welding wire segment throwing, vertical welding and annular swing welding in the build-up welding process, thereby ensuring the operability of welding and the welding quality. Specifically, as shown in fig. 7, the angle of the welding gun is adjusted to keep an included angle of 90 degrees with the workpiece, the base material at the deepest part of the small hole is burned and melted by arc starting, the welding wire section is put into after the base material is melted, and after the welding wire section and the base material at the bottom of the hole are completely fused, a dot-shaped surfacing layer (namely, the surfacing layer 1 in fig. 7) is formed after solidification. Then, as shown in fig. 8, the welding gun angle is adjusted to form a first included angle with the workpiece, the next welding wire section is put into, the welding gun is rotated and swung along the arrow indication direction after the welding wire section is melted, the hole wall base material is ensured to be fully melted and fully fused with the filling material (namely the melted welding wire section), and an annular surfacing layer (namely the surfacing layer 2 in fig. 8) for surfacing along the hole wall is formed after solidification. Then, dot-shaped surfacing and annular surfacing are alternately performed until the height of the surfacing layer reaches half of the hole depth, about 8.5mm, the feeding of welding wire segments is stopped, and the formed surfacing layer structure is shown in fig. 9, wherein the odd surfacing layers such as surfacing layers 1, 3, 5, 7 and … are dot-shaped surfacing layers for surfacing along the center line of the hole, and the even surfacing layers such as surfacing layers 2, 4, 6 and 8 … are annular surfacing layers for surfacing along the wall of the hole. And then adjusting the angle of the welding gun to form a second included angle with the workpiece, directly adding a welding wire for surfacing, and gradually approaching the normal welding angle along with the continuous rising of the surfacing layer until the surfacing position is higher than the workpiece mounting surface by more than 1mm, as shown in figure 10.
It will be understood that as shown in fig. 11, the nozzle of the argon tungsten-arc welding gun adopts a ceramic protective nozzle with the diameter of 9 mm, and the length of the tungsten electrode extending out of the ceramic protective nozzle is 15mm and 5mm longer than the length of the tungsten electrode extending out of the protective nozzle in normal welding so as to facilitate the surfacing operation of the deep hole. The welding wire section is a section with the diameter of 1.2 mm and is cut into the length of 5mm, and the welding wire cannot be added in the welding process due to the small space at the bottom of the threaded hole.
Preferably, the first included angle is preferably 70-80 degrees, and more preferably 75 degrees, so that the tip (namely the arcing part) of the tungsten electrode can be just contacted with the hole wall, other parts of the welding gun are not contacted with the part, the part is prevented from being burnt in the welding process, the tungsten electrode is convenient to swing to melt the hole wall, the welding wire section is put in under the condition of continuous arc breaking, the continuity of the welding process is ensured, and the welding quality is improved. In addition, the second included angle is preferably 60-65 degrees, more preferably 60 degrees, so as to facilitate the welding operation of the welding wire.
It can be understood that the invention can reduce welding deformation, reduce welding stress and prevent welding from overheating by adopting a multilayer overlaying mode of alternately carrying out vertical welding and annular rotary swing welding. The welding current is generally larger during single-layer welding, the welding heat input is larger, and the welding deformation is larger, but the heat input amount is smaller during multi-layer overlaying welding than that during single-layer welding, the heat affected zone of the welding seam is smaller, the high-temperature stay time of the welding seam is short, the overheating of the welding seam joint is prevented, and the metallographic structure of the welding seam joint is effectively improved. And the multilayer build-up welding mode can also play a role in post-welding heat treatment, when the vertical welding and the annular swing welding are alternately performed, the back-pass welding seam is subjected to annealing treatment on the front-pass welding seam, so that the stress of the front-pass welding seam is reduced, and meanwhile, due to the fact that the back-pass welding seam is used for reheating the front-pass welding seam, crystal grains of the front-pass welding seam are thinned, the overall toughness of the welding seam is improved, and the welding quality is greatly improved. In addition, in the multilayer overlaying process, the problem that welding wires cannot be added in the welding process due to the fact that the space at the bottom of a threaded hole is narrow is effectively solved by adopting a mode of adding welding wire segments in the multilayer overlaying process in consideration of the fact that the welding wires cannot be added due to the fact that the small hole size is limited.
Optionally, as shown in fig. 12, in another embodiment of the present invention, the method for repairing damage to a threaded blind hole on an aeroengine compressor case further includes the following before performing the small hole multilayer build-up welding:
step S12: a chamfer is machined at the orifice.
Wherein, the process of processing the chamfer at the orifice is specifically as follows:
specifically, as shown in fig. 13, on a drilling machine, a chamfer was machined at the orifice by using a 60 ° chamfer cutter, the machining depth of the chamfer machining was 7mm, and the diameter of the machined orifice was 16mm. The chamfering processing aims to facilitate the rotation and swinging of the welding gun by a certain angle in the small hole surfacing process so as to ensure the welding quality, and simultaneously, facilitate operators to observe the change of a molten pool in the small hole in the welding process.
It will be appreciated that in step S3, the mounting surface is flattened with a tool, and then a new threaded bottom hole is machined at the original threaded hole location, the new threaded bottom hole having a diameter of 6mm, a chamfer of 1×45 ° of the hole, and a depth of 14 mm, as shown in fig. 14.
It will be appreciated that in step S4, as shown in fig. 15, the M8 thread is tapped at the newly machined thread pilot, and the associated appearance and size inspection is completed, so far, the repair of the damaged threaded hole is completed.
It can be understood that the damage repair method for the threaded blind hole on the aeroengine compressor case can be well applied to damage repair of the threaded hole on the compressor case boss, the repair of the threaded hole can not affect the strength of the installation edge of the threaded hole, the strength requirement of the installation edge of the compressor case can be met, the strength of the thread repaired by adopting the surfacing method is high and is close to that of a base metal, the newly machined thread is completely consistent with the original thread, a special object is not needed, and the service life of the compressor case is greatly prolonged.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. The damage repair method for the threaded blind hole on the aeroengine compressor box is characterized by comprising the following steps of:
drilling out residual threads at the damaged threaded holes by adopting a drill bit with the same diameter as the threaded holes;
carrying out small-hole multilayer overlaying welding in the threaded hole by adopting argon tungsten-arc welding until the overlaying welding position is higher than the workpiece mounting surface;
trimming the mounting surface, and processing a new threaded bottom hole at the original threaded hole position;
tapping the thread at the thread bottom hole, and checking the appearance and the size;
the process of carrying out small-hole multilayer overlaying welding in the threaded hole by adopting argon tungsten-arc welding specifically comprises the following steps of:
adjusting the angle of a welding gun to form an included angle of 90 degrees with a workpiece, starting an arc to burn a matrix material at the deepest part of a small hole, putting a welding wire section after a base metal is melted, and solidifying to form a dot-shaped surfacing layer for surfacing along the center line of the small hole after the welding wire section and the matrix material at the bottom of the hole are completely fused;
adjusting the angle of a welding gun to form a first included angle with a workpiece, throwing a next welding wire section, and swinging a tungsten electrode after the welding wire section is melted, so as to ensure that the welding wire section and a hole wall base material are completely fused, and solidifying to form an annular surfacing layer for surfacing along the hole wall;
the operation is alternately carried out until the height of the build-up welding layer reaches half of the depth of the hole;
and adjusting the angle of the welding gun to form a second included angle with the workpiece, and adding welding wires for surfacing until the surfacing is higher than the workpiece mounting surface.
2. The method for repairing damage to a threaded blind hole in an aeroengine compressor case of claim 1, further comprising, prior to the performing of the small hole multilayer overlay welding:
a chamfer is machined at the orifice.
3. The method for repairing damage to a threaded blind hole in an aeroengine compressor case as defined in claim 2, wherein the chamfering process at the orifice is specifically:
on a drilling machine, a chamfer is machined at the orifice by adopting a 60-degree chamfer cutter.
4. A method for repairing a blind threaded hole in an aeroengine compressor case as defined in claim 3, wherein the chamfer is machined to a depth of 7 mm.
5. The method for repairing damage to a threaded blind hole in an aeroengine compressor case according to claim 1, wherein a nozzle of a welding gun is a ceramic protection nozzle with the diameter of 9 mm, and the length of a tungsten electrode extending out of the ceramic protection nozzle is 15mm.
6. The method for repairing a blind threaded hole in an aeroengine compressor case according to claim 1, wherein the first included angle is 70 ° to 80 °.
7. The method for repairing a blind threaded hole in an aeroengine compressor case according to claim 1, wherein the second included angle is 60 ° to 65 °.
8. The method for repairing damage to a blind threaded bore in an aeroengine compressor case of claim 1, wherein the wire segment is a segment of 1.2 mm diameter wire cut to a length of 5mm.
9. The method for repairing damage to a threaded blind hole in an aeroengine compressor case according to claim 1, wherein the size of the new threaded bottom hole is 6mm in diameter, 1 x 45% in chamfer angle of the orifice and 14 mm in depth.
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| CN202210893083.6A CN115383395B (en) | 2022-07-27 | 2022-07-27 | Method for repairing damage of threaded blind hole on aeroengine compressor case |
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| CN202210893083.6A CN115383395B (en) | 2022-07-27 | 2022-07-27 | Method for repairing damage of threaded blind hole on aeroengine compressor case |
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| CN105562890A (en) * | 2016-03-01 | 2016-05-11 | 中国兵器科学研究院宁波分院 | Welding method applicable to small-diameter deep blind hole |
| CN108907374A (en) * | 2018-08-10 | 2018-11-30 | 常州博瑞电力自动化设备有限公司 | A kind of through hole whorl restorative procedure |
| CN112453825A (en) * | 2020-11-19 | 2021-03-09 | 中车大连机车车辆有限公司 | C-grade steel thin-wall threaded hole repairing method |
| CN214393059U (en) * | 2020-12-30 | 2021-10-15 | 柳州机车车辆有限公司 | Device for repairing transverse threaded hole of railway passenger car bogie |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8601663B2 (en) * | 2012-02-13 | 2013-12-10 | Honeywell International Inc. | Methods for structural repair of components having damaged internally threaded openings and components repaired using such methods |
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| FR1369342A (en) * | 1963-01-14 | 1964-08-14 | New process for repairing or reinforcing cracked cast iron parts, using plates welded with studs | |
| CN202726410U (en) * | 2012-06-29 | 2013-02-13 | 江阴市振江钢结构有限公司 | Mechanism for repairing internal threads of threaded holes |
| CN104209624A (en) * | 2013-06-05 | 2014-12-17 | 中国石油天然气股份有限公司 | Special connector crack repair process method |
| CN105562890A (en) * | 2016-03-01 | 2016-05-11 | 中国兵器科学研究院宁波分院 | Welding method applicable to small-diameter deep blind hole |
| CN108907374A (en) * | 2018-08-10 | 2018-11-30 | 常州博瑞电力自动化设备有限公司 | A kind of through hole whorl restorative procedure |
| CN112453825A (en) * | 2020-11-19 | 2021-03-09 | 中车大连机车车辆有限公司 | C-grade steel thin-wall threaded hole repairing method |
| CN214393059U (en) * | 2020-12-30 | 2021-10-15 | 柳州机车车辆有限公司 | Device for repairing transverse threaded hole of railway passenger car bogie |
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