CN115383395A - Method for repairing damage of threaded blind hole on aero-engine compressor casing - Google Patents
Method for repairing damage of threaded blind hole on aero-engine compressor casing Download PDFInfo
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- CN115383395A CN115383395A CN202210893083.6A CN202210893083A CN115383395A CN 115383395 A CN115383395 A CN 115383395A CN 202210893083 A CN202210893083 A CN 202210893083A CN 115383395 A CN115383395 A CN 115383395A
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- 238000000034 method Methods 0.000 title claims abstract description 60
- 238000003466 welding Methods 0.000 claims abstract description 138
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims abstract description 22
- 229910052786 argon Inorganic materials 0.000 claims abstract description 11
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims abstract description 11
- 229910052721 tungsten Inorganic materials 0.000 claims abstract description 11
- 239000010937 tungsten Substances 0.000 claims abstract description 11
- 238000005553 drilling Methods 0.000 claims abstract description 8
- 238000007689 inspection Methods 0.000 claims abstract description 6
- 238000010079 rubber tapping Methods 0.000 claims abstract description 5
- 239000000463 material Substances 0.000 claims description 24
- 230000008569 process Effects 0.000 claims description 21
- 238000003754 machining Methods 0.000 claims description 8
- 239000000758 substrate Substances 0.000 claims description 7
- 239000000919 ceramic Substances 0.000 claims description 6
- 230000008018 melting Effects 0.000 claims description 3
- 238000002844 melting Methods 0.000 claims description 3
- 230000001681 protective effect Effects 0.000 claims 2
- 239000011324 bead Substances 0.000 claims 1
- 239000010410 layer Substances 0.000 description 20
- 230000008439 repair process Effects 0.000 description 10
- 238000013021 overheating Methods 0.000 description 4
- 239000002356 single layer Substances 0.000 description 4
- 238000002485 combustion reaction Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 230000014759 maintenance of location Effects 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 230000033228 biological regulation Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 235000014121 butter Nutrition 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 239000013078 crystal Substances 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
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- 238000006748 scratching Methods 0.000 description 1
- 230000002393 scratching effect Effects 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
- 230000008023 solidification Effects 0.000 description 1
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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
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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
- B23K9/167—Arc welding or cutting making use of shielding gas and of a non-consumable electrode
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Abstract
The invention discloses a damage repairing method of a threaded blind hole on a compressor casing of an aircraft engine, which comprises the steps of firstly drilling and removing residual threads at the damaged threaded hole by adopting a drill bit with the same diameter as the threaded hole, then welding the threaded hole in a tungsten electrode argon arc mode to carry out small-hole multilayer surfacing welding until the surfacing welding position is higher than a workpiece mounting surface, then flattening the mounting surface, processing a new threaded bottom hole at the position of the original threaded hole, finally tapping threads at the threaded 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 method for repairing damage of a threaded blind hole in an aero-engine compressor casing.
Background
After parts of an aero-engine are used for a long time and are disassembled and installed for many times, threaded holes in a combustion adjustment installation surface of a compressor case are damaged frequently by abrasion, broken buttons, scratching buttons and the like. Because the material cost of the compressor case is high, the manufacturing difficulty is high, and the value of the case is high, a safe and reliable repairing method is required to save the compressor case and prolong the service life of the case. Specifically, as shown in fig. 1, a compressor casing mounting surface of an aircraft engine of a certain type 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 a small diameter, a deep depth and a thin wall thickness, specifically, the threaded holes are positioned in bosses of a combustion regulation 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 the repair of the casing of the compressor, the repaired threaded hole has enough strength.
There are generally two methods for repairing damage to a threaded hole: inlaying a thread bushing and increasing the thread specification. The method for embedding the threaded sleeve is to enlarge a damaged threaded hole, embed a plug, and rework a specified threaded hole in the middle of the plug to finish the repair. For example, an M8 threaded hole is repaired by using an insert method, at least one M14 plug needs to be inserted, as shown in fig. 2, the thinnest part between the insert position and the edge of the boss is only 0.6 mm, and the part of the compressor casing is a force bearing part, so that the method cannot meet the requirement on 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 specification of the thread is that if the specification of the thread of the M8 needs to be increased for repair, the repair can be realized only by increasing the threaded hole to M10, the wall thickness of the threaded hole from the edge of the boss is reduced from 4mm to 3mm, the strength is greatly weakened, the strength requirement of the mounting edge of the compressor casing is not met, and particularly, the thinnest wall thickness of the boss at the threaded hole is only 2mm, so that the strength is weakened more obviously. In addition, in the engine, other components need to be assembled at the threaded hole of the compressor casing, the threaded hole needs to be enlarged simultaneously for target parts, and bolts, gaskets and the like need to be specially assembled, so that the universality and interchangeability of engine parts are not met, and the use is not allowed. Therefore, the existing repair method for enlarging the thread specification cannot be applied to repair of the threaded hole of the structure.
Therefore, due to the special structure of the threaded hole of the compressor casing and the assembly requirements of the engine, the existing threaded hole damage repairing method is not suitable for repairing the threaded hole.
Disclosure of Invention
The invention provides a damage repairing method for a threaded blind hole on a compressor casing of an aero-engine, which aims to solve the technical problem that the existing threaded hole damage repairing method is not suitable for repairing damage of an M8 threaded hole on the compressor casing.
According to one aspect of the invention, a method for repairing damage to a threaded blind hole in a compressor casing of an aircraft engine is provided, which comprises the following steps:
drilling out residual threads at the damaged threaded hole by adopting a drill bit with the same diameter as the threaded hole;
carrying out small-hole multilayer surfacing in the threaded hole by adopting argon tungsten-arc welding until the surfacing position is higher than the workpiece mounting surface;
flattening the mounting surface, and processing a new thread bottom hole at the position of the original thread hole;
tapping at the threaded bottom hole and performing appearance and dimension inspection.
Further, the process of performing small-hole multilayer surfacing 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 the workpiece, arcing and melting the substrate material at the deepest part of the small hole, putting the substrate material into a welding wire section after the base material is melted, and solidifying to form a circular bead-shaped overlaying layer overlaying along the central line of the small hole after ensuring that the welding wire section and the substrate material at the bottom of the hole are completely fused;
adjusting the angle of a welding gun to form a first included angle with the workpiece, putting the next welding wire section, and rotating and swinging a tungsten electrode after the welding wire section is molten to ensure that the welding wire section is completely fused with a base material of the hole wall and then is solidified to form an annular overlaying layer overlaying along the hole wall;
alternately carrying out the operations until the height of the overlaying layer reaches half of the hole depth;
and adjusting the angle of the welding gun to form a second included angle with the workpiece, and adding a welding wire for surfacing until the surfacing part is higher than the workpiece mounting surface.
Further, the following is included before carrying out the small-hole multilayer overlay welding:
and machining a chamfer at the orifice.
Further, the process of machining the chamfer at the orifice specifically comprises:
and (3) processing a chamfer at the orifice by adopting a 60-degree chamfer cutter on a drilling machine.
Further, the processing depth of the chamfering processing was 7 mm.
Furthermore, a nozzle of the welding gun adopts a ceramic protection nozzle with the diameter of 9 mm, and the length of the tungsten electrode extending out of the ceramic protection 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 which is formed by cutting a welding wire with the diameter of 1.2 mm into a length of 5mm.
Further, the dimensions of the new threaded bottom hole were 6mm in diameter, 1 × 45 ° chamfered at the orifice and 14 mm deep.
The invention has the following effects:
the invention relates to a damage repair method of a threaded blind hole on a compressor casing of an aero-engine, which comprises the steps of firstly drilling residual threads at a damaged threaded hole by using a drill bit with the same diameter as the threaded hole, then carrying out small-hole multilayer surfacing welding in the threaded hole by using argon tungsten-arc welding until the surfacing welding position is higher than a workpiece mounting surface, then flattening the mounting surface, processing a new threaded bottom hole at the position of the original threaded hole, finally tapping threads at the threaded bottom hole, and carrying out appearance and size inspection.
In addition, the invention can reduce welding deformation, reduce welding seam stress and prevent welding seam overheating by a multilayer surfacing welding mode of alternately carrying out vertical welding and annular spin-swing welding. The welding current is usually larger during single-layer welding, the welding heat input is large, the welding deformation is large, but the heat input amount is smaller when multilayer overlaying welding is adopted than during single-layer welding, the heat affected zone of the welding seam is small, the high-temperature retention 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 meanwhile, as the subsequent welding seam reheats the previous welding seam, crystal grains of the previous welding seam are refined, the overall toughness of the welding seam is improved, and the welding quality is greatly improved. In addition, in the process of multilayer surfacing, the condition that welding wires cannot be added due to the limitation of the size of a small hole is considered, and the method effectively solves the problem that the welding wires cannot be added in the welding process due to the narrow bottom space of the threaded hole in the process of multilayer surfacing in a mode of throwing a welding wire section.
In addition to the above-described objects, features and advantages, the present invention has other objects, features and advantages. The present invention will be described in further detail below with reference to the drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
fig. 1 is a schematic view of a threaded hole structure on a combustion adjusting mounting plate of a compressor casing of an aircraft engine.
FIG. 2 is a schematic illustration of a threaded hole being repaired using a prior art insert repair method.
FIG. 3 is a schematic illustration of a prior art enlarged thread gage repair method for repairing a threaded hole.
Fig. 4 is a schematic flow chart of a method for repairing damage to a blind threaded hole in a compressor casing of an aircraft engine according to a preferred embodiment of the invention.
Fig. 5 is a schematic diagram of the structure of the present invention after the drill bit is used to drill the residual thread in the threaded hole.
Fig. 6 is a sub-flowchart of step S2 in fig. 4.
FIG. 7 is a schematic illustration of the formation of a layer of butter dots within the apertures in accordance with a preferred embodiment of the present invention.
FIG. 8 is a schematic view of the configuration of the annular weld overlay formed within the aperture in the preferred embodiment of the present invention.
FIG. 9 is a schematic diagram of a preferred embodiment of the present invention in which the spot weld and the annular weld are formed alternately in the small hole.
Fig. 10 is a schematic structural view of the inside of the small hole after the build-up welding is completed according to the preferred embodiment of the invention.
Fig. 11 is a schematic view of a torch according to a preferred embodiment of the invention.
Fig. 12 is a schematic flow chart illustrating a method for repairing damage to a blind threaded hole in a compressor casing of an aircraft engine according to another embodiment of the present invention.
Fig. 13 is a dimensional schematic diagram of an orifice chamfering process performed in another embodiment of the present invention.
FIG. 14 is a schematic representation of the dimensions of the new threaded bottom hole in the preferred embodiment of the present invention.
FIG. 15 is a dimensional schematic of the M8 thread at the new bottom hole of the preferred embodiment of the invention.
Detailed Description
The embodiments of the invention will be described in detail below with reference to the accompanying drawings, but the invention can be embodied in many different forms, which are defined and covered by the following description.
As shown in fig. 4, a preferred embodiment of the present invention provides a method for repairing damage to a blind threaded hole in a compressor casing of an aircraft engine, including the following steps:
step S1: drilling out residual threads at the damaged threaded hole by adopting a drill bit with the same diameter as the threaded hole;
step S2: carrying out small-hole multilayer surfacing in the threaded hole by adopting argon tungsten-arc welding until the surfacing position is higher than the workpiece mounting surface;
and step S3: flattening the mounting surface, and processing a new thread bottom hole at the position of the original thread hole;
and step S4: tapping at the threaded bottom hole and performing appearance and dimension inspection.
It can be understood that the damage repairing method of the blind threaded hole on the aero-engine compressor casing of the embodiment is characterized in that the residual threads at the damaged threaded hole are drilled and removed by adopting the drill bit with the same diameter as the threaded hole, then the tungsten electrode argon arc welding is adopted to carry out small-hole multilayer surfacing in the threaded hole until the surfacing position is higher than the workpiece mounting surface, then the mounting surface is flattened, a new threaded bottom hole is processed at the position of the original threaded hole, finally the threads are tapped at the threaded bottom hole, and the appearance and the size are checked, 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 ensured, the thread strength after the repairing by adopting the surfacing method is high and is close to the base material strength, the newly processed threads are completely consistent with the original threads, special matching object pieces are not needed, the strength of the threaded hole mounting edge is reduced compared with the existing embedding and reaming methods, and the special matching object pieces need to be added in reaming repairing.
It can be understood that, in the step S1, as shown in fig. 5, for repairing the M8 threaded hole with a diameter of 8.2mm, the residual thread at the damaged threaded hole is drilled out by using a drill with a diameter of 8.2 mm. Of course, in other embodiments of the present invention, a drill bit with a diameter of 8mm, a diameter of 8.1 mm, a diameter of 8.3mm, a diameter of 8.4mm, etc. may be used to take into account machining tolerances.
It can be understood that, as shown in fig. 6, in the step S2, the process of performing the small-hole multilayer overlay welding in the threaded hole by using the 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, arcing and melting the substrate material at the deepest part of the small hole, feeding the base material into a welding wire section after the base material is melted, and solidifying to form a circular bead-shaped surfacing layer which is subjected to surfacing along the central line of the small hole after the welding wire section is completely fused with the substrate material at the bottom of the hole;
step S22: adjusting the angle of a welding gun to form a first included angle with the workpiece, putting the next welding wire section, and swinging a tungsten electrode after the welding wire section is melted to ensure that the welding wire section is completely fused with the base material of the hole wall and then is solidified to form an annular overlaying layer which is overlaid along the hole wall;
step S23: alternately carrying out the operations until the height of the overlaying layer reaches half of the hole depth;
step S24: and adjusting the angle of the welding gun to form a second included angle with the workpiece, and adding a welding wire for surfacing until the surfacing part is higher than the workpiece mounting surface.
It can be understood that the technical difficulty in the process of overlaying the small holes by adopting the argon tungsten-arc welding method is as follows: the diameter of a small hole at the position of surfacing is only 8.2mm, the depth of the hole is 17mm, the innermost space of the hole is too small, a welding wire cannot be added in the welding process, and the surfacing difficulty is high. Therefore, the invention adopts the overlaying mode of alternately carrying out the welding wire feeding section, the vertical welding and the annular swing welding in the overlaying process, thereby not only ensuring the welding operability, but also ensuring the welding quality. Specifically, as shown in fig. 7, the angle of the welding gun is adjusted to keep an included angle of 90 ° with the workpiece, the base material at the deepest portion of the small hole is melted by arcing, the base material is melted and then fed into the wire section, and after the wire section and the base material at the bottom of the hole are completely fused, the base material is solidified to form a circular bead-shaped overlay (i.e., the overlay 1 in fig. 7). Then, as shown in fig. 8, adjusting the angle of the welding gun to form a first included angle with the workpiece, putting the next welding wire segment, and swinging the welding gun in the direction indicated by the arrow after the welding wire segment is melted, so as to ensure that the base material of the hole wall can be sufficiently melted and sufficiently fused with the filling material (i.e., the melted welding wire segment), and forming an annular overlaying layer (i.e., the overlaying layer 2 in fig. 8) overlaying along the hole wall after solidification. And then, alternately carrying out dot-shaped overlaying and annular overlaying until the height of the overlaying layer reaches half of the hole depth and is about 8.5mm, and stopping feeding the welding wire section to form an overlaying layer structure as shown in fig. 9, wherein the overlaying layers 1, 3, 5, 7, 8230are odd overlaying layers, the like, of which the dot-shaped overlaying layers are overlaid along the center line of the small hole, and the overlaying layers 2, 4, 6, 8, 8230are even overlaying layers, of which the ring-shaped overlaying layers are overlaid along the hole wall. And then adjusting the angle of the welding gun to form a second included angle with the workpiece, directly adding the welding wire for surfacing, and gradually approaching the angle of the welding gun and the angle of the welding wire to the normal welding angle along with the continuous rising of the surfacing layer until the surfacing part is higher than the workpiece mounting surface by more than 1mm, as shown in figure 10.
It can be understood that, as shown in fig. 11, the nozzle of the argon tungsten-arc welding gun adopts a ceramic protection nozzle with a diameter of 9 mm, and the length of the tungsten electrode extending out of the ceramic protection nozzle is 15mm, which is 5mm longer than the length of the tungsten electrode extending out of the protection nozzle during normal welding, so as to facilitate the surfacing operation of the deep hole. The welding wire section is a section which is cut into a length of 5mm by a welding wire with the diameter of 1.2 mm, and the welding wire cannot be added in the welding process due to the narrow space at the bottom of the threaded hole.
Preferably, the first included angle is preferably 70-80 degrees, further preferably 75 degrees, so that the tip of the tungsten electrode (namely, an arc striking part) can be just in contact with the hole wall, other parts of the welding gun are not in contact with parts, the parts are prevented from being burned in the welding process, the tungsten electrode is conveniently swung to melt the hole wall, the welding wire section is favorably put in under the condition of no arc interruption, the continuity of the welding process is ensured, and the welding quality is improved. The second included angle is preferably 60 ° to 65 °, and more preferably 60 °, to facilitate the wire bonding operation.
It can be understood that the invention can reduce welding deformation, reduce welding seam stress and prevent welding seam overheating by a multilayer surfacing welding mode of alternately carrying out vertical welding and annular spin-swing welding. The welding current is usually larger during single-layer welding, the welding heat input is large, the welding deformation is large, the heat input amount is smaller during multi-layer surfacing than during single-layer welding, the heat affected zone of the welding seam is small, the high-temperature retention 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 surfacing mode can also play a role in postweld heat treatment, when vertical welding and annular spin-swing welding are alternately welded, the subsequent welding seam anneals the previous welding seam, so that the stress of the previous welding seam is reduced, and simultaneously, as the subsequent welding seam reheats the previous welding seam, grains of the previous welding seam are refined, the overall toughness of the welding seam is improved, and the welding quality is greatly improved. In addition, in the multilayer surfacing process, the condition that welding wires cannot be added due to the limitation of the size of a small hole is considered, and the welding wire feeding section is adopted in the multilayer surfacing process, so that the problem that the welding wires cannot be added in the welding process due to the narrow bottom space of the threaded hole is effectively solved.
Optionally, as shown in fig. 12, in another embodiment of the present invention, the method for repairing damage to a blind threaded hole on a compressor casing of an aircraft engine further includes the following steps before performing the multi-layer overlay welding of the small hole:
step S12: and machining a chamfer at the orifice.
Wherein, the process of processing the chamfer at the orifice specifically comprises the following steps:
specifically, as shown in fig. 13, on a drilling machine, a chamfer is machined at an orifice by using a 60 ° chamfer cutter, the machining depth of the chamfer machining is 7mm, and the diameter of the machined orifice is 16mm. The purpose of processing the chamfer is to facilitate the welding gun to swing a certain angle in the small hole surfacing process so as to ensure the welding quality, and simultaneously, facilitate an operator to observe the change of a molten pool in the small hole in the welding process.
It can be understood that in the step S3, the mounting surface is flattened by using a tool, and then a new threaded bottom hole is machined at the position of the original threaded hole, wherein the new threaded bottom hole has the size of 6mm in diameter, 1 × 45 ° chamfered at the hole opening and 14 mm in depth, as shown in fig. 14.
It can be understood that in the step S4, as shown in fig. 15, M8 threads are tapped at the newly machined thread bottom hole, and the related appearance and size inspection is completed, so that the damaged threaded hole is repaired.
The damage repairing method of the threaded blind hole on the aero-engine compressor casing can be well suitable for repairing the damage of the threaded hole on the boss of the compressor casing, the repairing of the threaded hole cannot influence the strength of the mounting edge of the threaded hole, the strength requirement of the mounting edge of the compressor casing can be met, the strength of the thread repaired by the surfacing method is high and is close to that of a base material, the newly machined thread is completely consistent with the original thread, a special object part is not needed, and the service life of the compressor casing is greatly prolonged.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A damage repairing method for a threaded blind hole on a compressor casing of an aero-engine is characterized by comprising the following steps:
drilling out residual threads at the damaged threaded hole by adopting a drill bit with the same diameter as the threaded hole;
carrying out small-hole multilayer surfacing in the threaded hole by adopting argon tungsten-arc welding until the surfacing part is higher than the workpiece mounting surface;
flattening the mounting surface, and processing a new thread bottom hole at the position of the original thread hole;
tapping at the threaded bottom hole and performing appearance and dimension inspection.
2. The method for repairing damage to a blind threaded hole in a compressor casing of an aircraft engine according to claim 1, wherein the step of performing multi-layer bead welding of the small hole in the threaded hole by 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, arcing and melting the substrate material at the deepest part of the small hole, feeding the base material into a welding wire section after the base material is melted, and solidifying to form a circular bead-shaped surfacing layer which is subjected to surfacing along the central line of the small hole after the welding wire section is completely fused with the substrate material at the bottom of the hole;
adjusting the angle of a welding gun to form a first included angle with the workpiece, putting the next welding wire section, and swinging a tungsten electrode after the welding wire section is melted to ensure that the welding wire section is completely fused with the base material of the hole wall and then is solidified to form an annular overlaying layer which is overlaid along the hole wall;
alternately carrying out the operations until the height of the overlaying layer reaches half of the hole depth;
and adjusting the angle of the welding gun to form a second included angle with the workpiece, and adding a welding wire for surfacing until the surfacing part is higher than the workpiece mounting surface.
3. A method of repairing damage to a blind threaded bore in a compressor casing of an aircraft engine as defined in claim 2, further comprising, prior to applying the small bore multi-layer weld deposit:
a chamfer is machined at the orifice.
4. The method for repairing damage to the blind threaded hole in the compressor casing of the aircraft engine as claimed in claim 3, wherein the process of machining the chamfer at the orifice specifically comprises:
and (3) processing a chamfer at the orifice by adopting a 60-degree chamfer cutter on a drilling machine.
5. The method for repairing damage to a blind threaded hole in a compressor casing of an aircraft engine as defined in claim 4, wherein the chamfer machining depth is 7 mm.
6. The method of repairing damage to a blind threaded hole in a compressor case of an aircraft engine of claim 2, wherein a 9 mm diameter ceramic protective nozzle is used as a nozzle of the welding gun, and the length of the tungsten electrode extending beyond the ceramic protective nozzle is 15mm.
7. A method of repairing damage to a blind threaded bore in a compressor case of an aircraft engine as defined in claim 2, wherein the first included angle is from 70 ° to 80 °.
8. The method of repairing damage to a blind threaded hole in a compressor case of an aircraft engine of claim 2, wherein the second included angle is 60 ° to 65 °.
9. The method of repairing damage to a blind threaded hole in a compressor case of an aircraft engine of claim 2, wherein said wire segment is a 5mm length segment of 1.2 mm diameter wire.
10. A method of repairing damage to a blind threaded bore in an aircraft engine compressor case as defined in claim 1 in which the new threaded bore has dimensions of 6mm diameter, 1 x 45 ° chamfer and 14 mm 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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- 2022-07-27 CN CN202210893083.6A patent/CN115383395B/en active Active
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