CN115635243B - Replacing and repairing method for spoke type air inlet casing blade - Google Patents
Replacing and repairing method for spoke type air inlet casing blade Download PDFInfo
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- CN115635243B CN115635243B CN202211421134.1A CN202211421134A CN115635243B CN 115635243 B CN115635243 B CN 115635243B CN 202211421134 A CN202211421134 A CN 202211421134A CN 115635243 B CN115635243 B CN 115635243B
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- air inlet
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- inlet casing
- spoke type
- blade
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- 238000000034 method Methods 0.000 title claims abstract description 11
- 238000003466 welding Methods 0.000 claims abstract description 38
- 238000005520 cutting process Methods 0.000 claims abstract description 16
- 238000010894 electron beam technology Methods 0.000 claims abstract description 16
- 230000007547 defect Effects 0.000 claims abstract description 11
- 238000010438 heat treatment Methods 0.000 claims abstract description 11
- 238000001514 detection method Methods 0.000 claims abstract description 10
- 230000002950 deficient Effects 0.000 claims abstract description 9
- 238000004140 cleaning Methods 0.000 claims abstract description 7
- 238000012545 processing Methods 0.000 claims abstract description 7
- 238000003754 machining Methods 0.000 claims abstract description 4
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 24
- 229910052786 argon Inorganic materials 0.000 claims description 12
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 claims description 6
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims description 6
- 238000003801 milling Methods 0.000 claims description 6
- 238000005498 polishing Methods 0.000 claims description 6
- 229910000831 Steel Inorganic materials 0.000 claims description 3
- 238000012937 correction Methods 0.000 claims description 3
- 238000013461 design Methods 0.000 claims description 3
- 238000001035 drying Methods 0.000 claims description 3
- 238000000227 grinding Methods 0.000 claims description 3
- 229910052750 molybdenum Inorganic materials 0.000 claims description 3
- 239000011733 molybdenum Substances 0.000 claims description 3
- 230000035515 penetration Effects 0.000 claims description 3
- 230000002093 peripheral effect Effects 0.000 claims description 3
- 239000010959 steel Substances 0.000 claims description 3
- 230000000007 visual effect Effects 0.000 claims description 3
- 238000012423 maintenance Methods 0.000 abstract description 3
- 238000009966 trimming Methods 0.000 abstract 1
- 208000032825 Ring chromosome 2 syndrome Diseases 0.000 description 7
- 238000005336 cracking Methods 0.000 description 3
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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- Structures Of Non-Positive Displacement Pumps (AREA)
- Welding Or Cutting Using Electron Beams (AREA)
Abstract
A spoke type air inlet casing blade replacement and repair method comprises the following steps: calibrating the defective blade; removing defective blades by linear cutting; machining, trimming and removing the spoke type air inlet casing after the defective blade; performing pre-welding cleaning on the machined and trimmed spoke type air inlet casing; performing pre-welding assembly on the cleaned spoke type air inlet casing and the new blade; electron beam welding is carried out on the assembled spoke type air inlet casing and the new blade; carrying out vacuum heat treatment on the welded spoke type air inlet casing to eliminate residual stress of a welding line; and performing size detection and repair processing on the spoke type air inlet casing subjected to vacuum heat treatment. According to the spoke type air inlet casing blade replacement and repair method, when the blade has defects, the integrally scrapped maintenance mode of the air inlet casing is abandoned, the air inlet casing is repaired in a blade replacement mode, the spoke type air inlet casing after the blade replacement can be ensured to reach the assembly and use requirements of the aero-engine again, and the repair cost of the aero-engine is greatly reduced.
Description
Technical Field
The invention belongs to the technical field of repair of aero-engine parts, and particularly relates to a spoke type air inlet casing blade replacement and repair method.
Background
The spoke type air inlet casing is used as an important component of the aeroengine, is positioned at the forefront end of the aeroengine, is one of main bearing parts on the aeroengine, is formed by welding an outer casing, an inner ring and a plurality of cavity blades, and has the functions of air inlet, air flow adjustment, deicing and the like.
Because the spoke type air inlet casing has a complex structure, particularly the blades on the spoke type air inlet casing are of a complex thin-wall cavity structure, in the working process of the aeroengine, the spoke type air inlet casing is easily cracked, damaged and the like on the weak cavity blades due to the influence of factors such as airflow impact, vibration fatigue, residual stress and the like, and belongs to a titanium alloy welded structure component, so that the stress state of the component is complex, once the cavity blades of the spoke type air inlet casing are cracked, damaged and the like, the spoke type air inlet casing can only be scrapped at present, and when the aeroengine is maintained, the spoke type air inlet casing is replaced integrally, so that the repair cost of the aeroengine is greatly increased.
Disclosure of Invention
According to the spoke type air inlet casing blade replacement and repair method, when the hollow cavity blade has the defects of cracking, damage and the like, the maintenance mode of the aircraft engine, in which the spoke type air inlet casing is scrapped as a whole, is abandoned, the spoke type air inlet casing is repaired only by replacing the defect blade, the spoke type air inlet casing after replacing the blade can be ensured to reach the assembly and use requirements of the aircraft engine again, and accordingly the repair cost of the aircraft engine is greatly reduced.
In order to achieve the above purpose, the present invention adopts the following technical scheme: a spoke type air inlet casing blade replacement and repair method comprises the following steps:
Step one: calibrating defect blade
Determining the position of a defective blade on the spoke type air inlet casing by adopting a visual and penetration detection method, and checking and determining that the range of the cracked and damaged defect is not beyond the range of a cavity blade;
Step two: defect-removing blade
Firstly, rigidly fixing an outer casing and an inner ring of a spoke type air inlet casing by using a tool, then cutting a defective cavity blade from between the outer casing and the inner ring by using a wire cutting machine, and ensuring that molybdenum wires of the wire cutting machine are cut along an original argon arc welding seam of the cavity blade in the cutting process;
step three: machining finishing
Grinding the residual high parts on the front and back of the cut original argon arc welding seam in a manual clamping mode to enable the wall thickness of the original argon arc welding seam to meet the design requirement of a drawing, milling the cut end face by a milling machine, enabling the single-side removal amount to be not less than 0.5mm, ensuring that a remelting layer is completely removed, temporarily assembling a new blade to be replaced between an outer casing and an inner ring, checking an assembly gap by using a clearance gauge, ensuring that the assembly gap is not more than 0.05mm, and removing the new blade to be replaced after the checking is qualified;
Step four: cleaning of weld front
Firstly cleaning the spoke type air inlet casing after being inspected to be qualified to remove greasy dirt and surface dirt, then drying the cleaned spoke type air inlet casing, then polishing the cut end face and the peripheral part thereof by adopting a steel wire brush, wherein the polishing range is not less than 10mm, and finally wiping the polished part by utilizing acetone to ensure that the part to be welded is clean;
Step five: pre-weld assembly
Assembling the cleaned spoke type air inlet casing into a tool, rigidly fixing an outer casing and an inner ring of the spoke type air inlet casing through the tool, then assembling a new blade between the outer casing and the inner ring, checking an assembly gap by using a clearance gauge, ensuring that the assembly gap is not more than 0.05mm, and simultaneously ensuring the dislocation requirement of subsequent electron beam welding, wherein the dislocation is not more than 0.1mm;
step six: electron beam welding
Transferring the tool with the spoke type air inlet casing and the new blade to a rotary table of a vacuum electron beam welding machine, then sending the tool into a vacuum chamber and completing vacuumizing, and finally welding the new blade with an outer casing and an inner ring in an electron beam welding mode;
Step seven: post-weld treatment
Feeding the welded spoke type air inlet casing into a vacuum heat treatment furnace, and carrying out vacuum heat treatment on the spoke type air inlet casing to eliminate residual stress of an electron beam welding seam;
Step eight: size detection and repair processing
And transferring the spoke type air inlet casing subjected to vacuum heat treatment to a detection table, detecting the diameter, the circle jump and the end jump size of the matched position of the inner ring of the spoke type air inlet casing, ensuring that the deformation is not more than 0.05mm, and if the deformation exceeds the diameter tolerance, carrying out repair processing correction within the diameter tolerance range so that the repaired spoke type air inlet casing meets the assembly requirement of the aeroengine.
The invention has the beneficial effects that:
According to the spoke type air inlet casing blade replacement and repair method, when the hollow cavity blade has the defects of cracking, damage and the like, the maintenance mode of the aircraft engine in which the spoke type air inlet casing is scrapped as a whole is abandoned, and the spoke type air inlet casing is repaired only by replacing the defect blade, so that the spoke type air inlet casing after replacing the blade can be ensured to reach the assembly and use requirements of the aircraft engine again, and the repair cost of the aircraft engine is greatly reduced.
Drawings
FIG. 1 is a schematic view of a partial structure of a spoke type air intake casing;
in the figure, 1-an outer casing, 2-an inner ring, 3-cavity blades and 4-an original argon arc welding line.
Detailed Description
The invention will now be described in further detail with reference to the drawings and to specific examples.
A spoke type air inlet casing blade replacement and repair method comprises the following steps:
Step one: calibrating defect blade
Determining the position of a defective blade on the spoke type air inlet casing shown in fig. 1 by adopting a visual and penetration detection method, and checking and determining that the defect range of cracking and damage does not exceed the range of the cavity blade 3;
Step two: defect-removing blade
Firstly, rigidly fixing an outer casing 1 and an inner ring2 of a spoke type air inlet casing by using a tool, and then cutting a defective cavity blade 3 from between the outer casing 1 and the inner ring2 by using a wire cutting machine, wherein in the cutting process, molybdenum wires of the wire cutting machine need to be cut along an original argon arc welding seam 4 of the cavity blade 3; in the embodiment, in order to ensure the accuracy of the cutting position of the molybdenum wire, an anti-icing hole on the cavity blade 3 adjacent to the original argon arc welding seam 4 can be used as a reference, and the molybdenum wire is offset by 5mm relative to the anti-icing Kong Zheyi reference, so that the molybdenum wire can be accurately moved to the original argon arc welding seam 4;
step three: machining finishing
Grinding the residual high parts on the front and back of the original argon arc welding seam 4 after cutting in a manual clamping mode to ensure that the wall thickness at the original argon arc welding seam 4 reaches the drawing design requirement of 1.8-2.2 mm, then milling the cutting end face by a milling machine to ensure that the single-side removal amount is not less than 0.5mm and the remelting layer is completely removed, then temporarily assembling a new blade to be replaced between the outer casing 1 and the inner ring2, checking an assembly gap by using a clearance gauge to ensure that the assembly gap is not more than 0.05mm, and removing the new blade to be replaced after the checking is qualified;
Step four: cleaning of weld front
Firstly cleaning the spoke type air inlet casing after being inspected to be qualified to remove greasy dirt and surface dirt, then drying the cleaned spoke type air inlet casing, then polishing the cut end face and the peripheral part thereof by adopting a steel wire brush, wherein the polishing range is not less than 10mm, and finally wiping the polished part by utilizing acetone to ensure that the part to be welded is clean;
Step five: pre-weld assembly
Assembling the cleaned spoke type air inlet casing into a tool, rigidly fixing an outer casing 1 and an inner ring 2 of the spoke type air inlet casing through the tool, then assembling new blades between the outer casing 1 and the inner ring 2, checking an assembly gap by using a clearance gauge, ensuring that the assembly gap is not more than 0.05mm, and simultaneously ensuring the dislocation requirement of subsequent electron beam welding, wherein the dislocation is not more than 0.1mm;
step six: electron beam welding
Transferring the tool with the spoke type air inlet casing and the new blade to a rotary table of a vacuum electron beam welding machine, then sending the tool into a vacuum chamber and completing vacuumizing, and finally welding the new blade with the outer casing 1 and the inner ring 2 in an electron beam welding mode; in this embodiment, the welding parameters are: the accelerating voltage is 150KV, the focusing current is 1888mA, the welding speed is 20mm/s, and the welding current is 9 mA-13 mA;
Step seven: post-weld treatment
Feeding the welded spoke type air inlet casing into a vacuum heat treatment furnace, and carrying out vacuum heat treatment on the spoke type air inlet casing to eliminate residual stress of an electron beam welding seam;
Step eight: size detection and repair processing
And transferring the spoke type air inlet casing subjected to vacuum heat treatment to a detection table, detecting the diameter, the circle jump and the end jump size of the matched position of the inner ring 2 of the spoke type air inlet casing, ensuring that the deformation is not more than 0.05mm, and if the deformation exceeds the diameter tolerance, carrying out repair processing correction within the diameter tolerance range so that the repaired spoke type air inlet casing meets the assembly requirement of the aeroengine.
The embodiments are not intended to limit the scope of the invention, but rather are intended to cover all equivalent implementations or modifications that can be made without departing from the scope of the invention.
Claims (1)
1. A spoke type air inlet casing blade replacement and repair method is characterized by comprising the following steps:
Step one: calibrating defect blade
Determining the position of a defective blade on the spoke type air inlet casing by adopting a visual and penetration detection method, and checking and determining that the range of the cracked and damaged defect is not beyond the range of a cavity blade;
Step two: defect-removing blade
Firstly, rigidly fixing an outer casing and an inner ring of a spoke type air inlet casing by using a tool, then cutting a defective cavity blade from between the outer casing and the inner ring by using a wire cutting machine, and ensuring that molybdenum wires of the wire cutting machine are cut along an original argon arc welding seam of the cavity blade in the cutting process;
step three: machining finishing
Grinding the residual high parts on the front and back of the cut original argon arc welding seam in a manual clamping mode to enable the wall thickness of the original argon arc welding seam to meet the design requirement of a drawing, milling the cut end face by a milling machine, enabling the single-side removal amount to be not less than 0.5mm, ensuring that a remelting layer is completely removed, temporarily assembling a new blade to be replaced between an outer casing and an inner ring, checking an assembly gap by using a clearance gauge, ensuring that the assembly gap is not more than 0.05mm, and removing the new blade to be replaced after the checking is qualified;
Step four: cleaning of weld front
Firstly cleaning the spoke type air inlet casing after being inspected to be qualified to remove greasy dirt and surface dirt, then drying the cleaned spoke type air inlet casing, then polishing the cut end face and the peripheral part thereof by adopting a steel wire brush, wherein the polishing range is not less than 10mm, and finally wiping the polished part by utilizing acetone to ensure that the part to be welded is clean;
Step five: pre-weld assembly
Assembling the cleaned spoke type air inlet casing into a tool, rigidly fixing an outer casing and an inner ring of the spoke type air inlet casing through the tool, then assembling a new blade between the outer casing and the inner ring, checking an assembly gap by using a clearance gauge, ensuring that the assembly gap is not more than 0.05mm, and simultaneously ensuring the dislocation requirement of subsequent electron beam welding, wherein the dislocation is not more than 0.1mm;
step six: electron beam welding
Transferring the tool with the spoke type air inlet casing and the new blade to a rotary table of a vacuum electron beam welding machine, then sending the tool into a vacuum chamber and completing vacuumizing, and finally welding the new blade with an outer casing and an inner ring in an electron beam welding mode;
Step seven: post-weld treatment
Feeding the welded spoke type air inlet casing into a vacuum heat treatment furnace, and carrying out vacuum heat treatment on the spoke type air inlet casing to eliminate residual stress of an electron beam welding seam;
Step eight: size detection and repair processing
And transferring the spoke type air inlet casing subjected to vacuum heat treatment to a detection table, detecting the diameter, the circle jump and the end jump size of the matched position of the inner ring of the spoke type air inlet casing, ensuring that the deformation is not more than 0.05mm, and if the deformation exceeds the diameter tolerance, carrying out repair processing correction within the diameter tolerance range so that the repaired spoke type air inlet casing meets the assembly requirement of the aeroengine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211421134.1A CN115635243B (en) | 2022-11-14 | 2022-11-14 | Replacing and repairing method for spoke type air inlet casing blade |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211421134.1A CN115635243B (en) | 2022-11-14 | 2022-11-14 | Replacing and repairing method for spoke type air inlet casing blade |
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| Publication Number | Publication Date |
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| CN115635243A CN115635243A (en) | 2023-01-24 |
| CN115635243B true CN115635243B (en) | 2024-04-26 |
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| CN202211421134.1A Active CN115635243B (en) | 2022-11-14 | 2022-11-14 | Replacing and repairing method for spoke type air inlet casing blade |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106392462A (en) * | 2016-11-22 | 2017-02-15 | 沈阳黎明航空发动机(集团)有限责任公司 | Repairing method for cracks of spoke-type casing |
| CN106637187A (en) * | 2016-11-16 | 2017-05-10 | 中国人民解放军第五七九工厂 | Laser cladding restoration method for damage of stator blade of welding assembly of large fan casing of aeroengine |
| CN109590595A (en) * | 2018-11-23 | 2019-04-09 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of high inclination-angle electro-beam welding method of inlet casing hollow blade |
| CN112621103A (en) * | 2020-12-17 | 2021-04-09 | 中国民航大学 | Repair method for titanium alloy blade of aircraft engine compressor |
| CN113478167A (en) * | 2021-07-21 | 2021-10-08 | 中国航发航空科技股份有限公司 | Method for repairing blade shroud of working blade of high-pressure turbine of aircraft engine |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2871399B1 (en) * | 2004-06-15 | 2006-09-22 | Snecma Moteurs Sa | PROCESS FOR REPAIRING A DAWN ELEMENT |
| KR102278830B1 (en) * | 2021-04-12 | 2021-07-19 | 주식회사 성일터빈 | Method of repairing gas turbine blade tip using high frequency welding |
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- 2022-11-14 CN CN202211421134.1A patent/CN115635243B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106637187A (en) * | 2016-11-16 | 2017-05-10 | 中国人民解放军第五七九工厂 | Laser cladding restoration method for damage of stator blade of welding assembly of large fan casing of aeroengine |
| CN106392462A (en) * | 2016-11-22 | 2017-02-15 | 沈阳黎明航空发动机(集团)有限责任公司 | Repairing method for cracks of spoke-type casing |
| CN109590595A (en) * | 2018-11-23 | 2019-04-09 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of high inclination-angle electro-beam welding method of inlet casing hollow blade |
| CN112621103A (en) * | 2020-12-17 | 2021-04-09 | 中国民航大学 | Repair method for titanium alloy blade of aircraft engine compressor |
| CN113478167A (en) * | 2021-07-21 | 2021-10-08 | 中国航发航空科技股份有限公司 | Method for repairing blade shroud of working blade of high-pressure turbine of aircraft engine |
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| CN115635243A (en) | 2023-01-24 |
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