CN117464307A - In-situ brazing repair method for cracks of turbine guide vane - Google Patents
In-situ brazing repair method for cracks of turbine guide vane Download PDFInfo
- Publication number
- CN117464307A CN117464307A CN202311494819.3A CN202311494819A CN117464307A CN 117464307 A CN117464307 A CN 117464307A CN 202311494819 A CN202311494819 A CN 202311494819A CN 117464307 A CN117464307 A CN 117464307A
- Authority
- CN
- China
- Prior art keywords
- edge plate
- positioning block
- upper edge
- turbine guide
- plate
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000005219 brazing Methods 0.000 title claims abstract description 81
- 238000000034 method Methods 0.000 title claims abstract description 52
- 230000008439 repair process Effects 0.000 title claims abstract description 28
- 238000011065 in-situ storage Methods 0.000 title claims abstract description 19
- 238000007689 inspection Methods 0.000 claims abstract description 65
- 239000000945 filler Substances 0.000 claims abstract description 31
- 239000002184 metal Substances 0.000 claims abstract description 31
- 229910052751 metal Inorganic materials 0.000 claims abstract description 31
- 238000004140 cleaning Methods 0.000 claims abstract description 23
- 239000000843 powder Substances 0.000 claims abstract description 23
- 238000000576 coating method Methods 0.000 claims abstract description 21
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 14
- 239000000956 alloy Substances 0.000 claims abstract description 14
- 239000011248 coating agent Substances 0.000 claims abstract description 13
- 238000005498 polishing Methods 0.000 claims abstract description 13
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 30
- 238000004321 preservation Methods 0.000 claims description 24
- KRHYYFGTRYWZRS-UHFFFAOYSA-M Fluoride anion Chemical compound [F-] KRHYYFGTRYWZRS-UHFFFAOYSA-M 0.000 claims description 19
- 239000007789 gas Substances 0.000 claims description 18
- 230000007547 defect Effects 0.000 claims description 16
- 238000001035 drying Methods 0.000 claims description 15
- 229910052759 nickel Inorganic materials 0.000 claims description 15
- 230000004907 flux Effects 0.000 claims description 11
- 238000002156 mixing Methods 0.000 claims description 10
- 230000008569 process Effects 0.000 claims description 7
- 239000011230 binding agent Substances 0.000 claims description 5
- 230000001680 brushing effect Effects 0.000 claims description 5
- 238000011049 filling Methods 0.000 claims description 5
- 238000010438 heat treatment Methods 0.000 claims description 5
- 239000011159 matrix material Substances 0.000 claims description 5
- 239000000203 mixture Substances 0.000 claims description 5
- 229910000679 solder Inorganic materials 0.000 claims description 5
- 238000005476 soldering Methods 0.000 claims description 5
- 238000003756 stirring Methods 0.000 claims description 5
- 229910000601 superalloy Inorganic materials 0.000 claims description 5
- 230000007704 transition Effects 0.000 claims description 5
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 4
- 230000000149 penetrating effect Effects 0.000 claims description 3
- 229910052786 argon Inorganic materials 0.000 claims description 2
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 2
- 238000006243 chemical reaction Methods 0.000 claims description 2
- 230000002950 deficient Effects 0.000 claims description 2
- 229910001512 metal fluoride Inorganic materials 0.000 claims description 2
- 239000001301 oxygen Substances 0.000 claims description 2
- 229910052760 oxygen Inorganic materials 0.000 claims description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Chemical compound O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims 1
- 238000003466 welding Methods 0.000 abstract description 5
- 239000002131 composite material Substances 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 230000035515 penetration Effects 0.000 description 3
- 238000000227 grinding Methods 0.000 description 2
- 239000004576 sand Substances 0.000 description 2
- 238000002679 ablation Methods 0.000 description 1
- 239000011324 bead Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- 230000008021 deposition Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 239000002893 slag Substances 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
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P6/00—Restoring or reconditioning objects
- B23P6/002—Repairing turbine components, e.g. moving or stationary blades, rotors
- B23P6/007—Repairing turbine components, e.g. moving or stationary blades, rotors using only additive methods, e.g. build-up welding
-
- 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
- B23P6/04—Repairing fractures or cracked metal parts or products, e.g. castings
- B23P6/045—Repairing fractures or cracked metal parts or products, e.g. castings of turbine components, e.g. moving or stationary blades, rotors, etc.
Abstract
The invention relates to an in-situ brazing repair method for cracks of a turbine guide blade, which comprises the following steps: step one: removing the coating and crack oxide; step two: presetting mixed alloy powder; step three: presetting brazing filler metal; step four: vacuum brazing; step five: cleaning and polishing after welding; step six: performing X-ray inspection after welding; step seven: performing postweld fluorescent inspection; the method is not limited by crack positions, improves the oxide removal mode at the crack positions, avoids the problems of incomplete polishing of oxides and expansion of crack gaps, improves the brazing bonding strength, and realizes high-quality and high-efficiency repair of the turbine guide blade.
Description
Technical Field
The invention relates to the technical field of aero-engine blade repair, in particular to an in-situ brazing repair method for cracks of turbine guide blades.
Background
Aero-engines are engineering machines approaching the limit in classical mechanics and are known as "bright beads on crowns" in modern mechanical manufacturing. The technical level of the aeroengine is an important sign for measuring the comprehensive national force of a country. Turbine blades are an important component of an aircraft engine that converts thermal energy into mechanical energy that powers the flight of an aircraft. The turbine blade is in high temperature, high pressure and stress load conditions for a long time in the service process, and defects such as cracks, ablation, chipping and the like are extremely easy to generate, so that the blade is scrapped and cannot be used continuously. Because turbine blades are complex in manufacturing process and are typically manufactured from high temperature alloys, they are costly. The repair of the scrapped blades after service can prolong the service time of the turbine blades, reduce the number of new parts to be replaced, save the manufacturing cost of the aeroengine and have important economic benefits.
There are two existing methods for turbine guide vane repair: one is to adopt a photoelectric composite repairing method, namely removing cracks by a mechanical polishing method, then adopting micro-arc to deposit filling materials, and finally carrying out laser remelting treatment to finish blade repairing. Because the turbine guide vane is a triple vane, a welding gun unreachable area exists between the vanes, and micro-arc deposition filling welding flux cannot be adopted, namely, the unrepairable area is limited by the photoelectric composite repairing method. Another method is a mechanical polishing and vacuum brazing repair method, namely removing cracks by a mechanical polishing method, and then coating brazing filler metal on polished positions for vacuum brazing repair. The disadvantage of this method is that: because crack forms of each blade after service are different, the mechanical polishing method is low in polishing efficiency, high in difficulty and high in skill level requirement on operators, and the condition that oxide is not polished thoroughly easily occurs, so that defects such as air holes and no penetration are caused; in addition, the crack gap can be enlarged by adopting a mechanical polishing method, and can reach more than 0.5mm after the penetrating crack at the edge plate is polished, so that the brazing joint strength is seriously reduced, and even the defects of brazing filler metal loss, no brazing penetration and the like occur.
Disclosure of Invention
In order to solve the technical problems, the invention provides an in-situ brazing repair method for cracks of a turbine guide vane; the specific technical scheme is as follows:
an in-situ braze repair method for cracks of a turbine guide vane, comprising the steps of:
step one: coating and crack oxide removal
Removing coatings and oxides in cracks of turbine guide blades by adopting a fluoride ion cleaning method, putting the blades to be cleaned into fluoride ion cleaning equipment, generating metal fluoride gas and steam through chemical reaction of HF gas and the coatings and the oxides in the cracks at high temperature, intermittently introducing flowing argon gas, and taking away the fluoride gas and oxygen, thereby achieving the purpose of removing the coatings and the oxides;
step two: presetting mixed alloy powder
For cracks with the gap larger than 0.1mm, filling mixed alloy powder in the crack gap by using an applicator; mixing the mixed alloy powder according to the proportion of the nickel-based superalloy powder and the nickel-based brazing filler metal of 7:3, and fully stirring to uniformly mix the powder;
step three: preset solder
Mixing nickel-based brazing filler metal and binder according to the weight ratio of 10:1, preparing into paste, coating the paste brazing filler metal on a part to be welded along a crack shape by using a coater, brushing a layer of soldering flux on the outer side of the paste brazing filler metal, and finally placing the coated turbine guide vane into a drying box for drying;
step four: vacuum brazing
Placing one side of the dried lower edge plate of the turbine guide vane downwards in a vacuum furnace for vacuum brazing;
step five: post-weld cleaning and polishing
Removing the flux on the surface of the blade by adopting compressed air, and removing redundant brazing filler metal at the repairing position by using a sander so as to enable the repairing position to be in smooth transition with the blade matrix;
step six: post-weld X-ray inspection
The method comprises the steps of placing turbine guide blades on a special X-ray inspection tool in 4 modes of downward inlet edge of a blade, downward exhaust edge of an upper edge plate, outward edge of a lower edge plate, downward inlet edge of a lower edge plate and outward edge of a lower edge plate, fixing the turbine guide blades through locking screws and baffles, performing X-ray inspection according to HB20160-2014 standard, recording inspection results, and marking defective positions of unqualified parts;
step seven: post-weld fluorescent inspection
And (3) performing fluorescent inspection according to HB/Z61-1992 standard, recording inspection results, marking the defect positions of the unqualified parts, and repeating the steps two to eight for the X-ray and the unqualified parts subjected to fluorescent inspection.
The in-situ brazing repair method for the cracks of the turbine guide blade has the preferable scheme that in the first step, the technological parameters of fluoride ion cleaning are as follows: the heat preservation temperature is 930-1050 ℃, the heat preservation time is 120-240 min, the HF gas flow is 0.5-1L/min, and H 2 The gas flow is 4L/min-10L/min.
In the third step, the drying temperature is 150-200 ℃, and the heat preservation time is 1.5-2 h.
In the in-situ brazing repair method for the cracks of the turbine guide blade, in the preferred scheme, in the third step, brazing filler metal is arranged on one side of a runner surface for penetrating cracks at the edge plate.
In the fourth step, the brazing heating rate of vacuum brazing is 8 ℃/min-12 ℃/min, the brazing temperature is 1110 ℃ -1150 ℃ and the heat preservation time is 15min-25min, after the heat preservation is finished, the furnace is cooled to below 80 ℃ and discharged, and the vacuum pressure in the brazing process is not more than 1 multiplied by 10 - 2 Pa。
In the sixth step, when the upper edge plate of the blade faces outwards towards the downward air inlet edge, an X-ray inspection special tool consisting of an exhaust positioning seat, an upper edge plate positioning block c, a lead plate and a baffle plate is adopted, wherein the upper edge plate positioning block c is arranged on a positioning surface of the exhaust positioning seat, the lead plate is arranged on the upper edge plate positioning block c, the baffle plate is locked by a screw to fix the turbine guide blade, and the upper edge plate is abutted against an attaching surface of the exhaust positioning seat;
when the lower edge plate faces downwards and the air inlet edge faces outwards, a special X-ray inspection tool consisting of an exhaust positioning seat, a lower edge plate positioning block b, a lead plate and a baffle plate is adopted, the lower edge plate positioning block b is arranged on a positioning surface of the exhaust positioning seat, the lead plate is arranged on the lower edge plate positioning block b, a turbine guide blade is fixed by locking the baffle plate through a screw, and the lower edge plate is abutted against an abutting surface of the exhaust positioning seat;
when the lower edge plate faces downwards and the exhaust edge faces outwards, a special X-ray inspection tool consisting of an air inlet positioning seat, a lower edge plate positioning block a, a lead plate and a baffle plate is adopted, the lower edge plate positioning block a is arranged on a positioning surface of the air inlet positioning seat, the lead plate is arranged on the lower edge plate positioning block a, a turbine guide blade is fixed by locking the baffle plate through a screw, and the lower edge plate is abutted against an abutting surface of the air inlet positioning seat;
when the upper edge plate is downward and the exhaust edge is outward, a special X-ray inspection tool consisting of an air inlet positioning seat, an upper edge plate positioning block a, an upper edge plate positioning block b, a lead plate and a baffle plate is adopted, the upper edge plate positioning block b is arranged on a positioning surface on the air inlet positioning seat, the upper edge plate positioning block a is vertically arranged with the upper edge plate positioning block b, the lead plate is arranged on the upper edge plate positioning block b, the turbine guide vane is fixed through a screw locking baffle plate, and the upper edge plate is abutted against an abutting surface of the exhaust positioning seat.
In the in-situ brazing repair method for the cracks of the turbine guide vane, the preferable scheme is that the positioning of the air inlet positioning seat and the air outlet side is L-shaped, and the inner profile is a positioning surface and an attaching surface;
the positioning profiles of the upper edge plate positioning block a, the upper edge plate positioning block b, the upper edge plate positioning block c, the lower edge plate positioning block a and the lower edge plate positioning block b correspond to the profile of the upper edge plate or the lower edge plate of the turbine guide vane.
Compared with the prior art, the invention has the following beneficial technical effects:
the method is not limited by crack positions, and a repair unreachable area of the photoelectric composite repair method does not exist;
the fluoride ion cleaning method is adopted to remove the coating, so that the defect of welding slag inclusion caused by the fact that sand grains enter crack gaps and cannot be removed in the sand blowing process can be avoided;
the fluoride ion cleaning method is adopted to remove oxides in cracks, so that the defects of incomplete grinding of the oxides or no brazing penetration, brazing filler metal loss and the like caused by the increase of crack gaps after grinding can be avoided, and the brazing bonding strength can be improved due to the reduction of the gaps;
the invention designs a special tool for X-ray inspection, which performs X-ray inspection on the repair piece from 4 directions, and avoids the influence of structural shielding on inspection result judgment.
Drawings
FIG. 1 is a front view of a turbine guide vane lower edge plate with its exhaust side facing outwardly on an X-test fixture;
FIG. 2 is a side view of the turbine guide vane lower edge plate with the exhaust side facing outwardly on the X-test tooling;
FIG. 3 is a schematic view of a turbine guide vane lower edge plate with a downward inlet edge facing outwardly positioned on an X-test fixture;
FIG. 4 is a schematic view of a turbine guide vane upper edge plate with a downward exhaust edge facing outwardly on an X-test fixture;
FIG. 5 is a schematic view of a turbine guide vane upper edge plate with a downward inlet edge facing outwardly on an X-test fixture.
In the figure: 1. a lower edge plate; 2. an upper edge plate; 3. an air inlet positioning seat; 4. a lower edge plate positioning block a;5. a baffle; 6. a screw; 7. a lead plate; 8. an exhaust edge; 9. an air inlet edge; 10. an exhaust positioning seat; 11. a lower edge plate positioning block b;12. an upper edge plate positioning block a;13. an upper edge plate positioning block b;14. and an upper edge plate positioning block c.
Detailed Description
The present invention will be described in detail with reference to fig. 1 to 5, but the scope of the present invention is not limited by the accompanying drawings.
An in-situ braze repair method for cracks of a turbine guide vane, comprising the steps of:
step one: coating and crack oxide removal
Removing coatings and oxides in cracks of the turbine guide vane by adopting a fluoride ion cleaning method, and putting the vane to be cleaned into fluoride ion cleaning equipment to perform fluoride ion cleaning; the heat preservation temperature is 950 ℃, the heat preservation time is 120min, the HF gas flow is 0.5L/min, and the H 2 Gas flowThe amount was 4L/min.
Step two: presetting mixed alloy powder
Mixing the nickel-based superalloy powder and the nickel-based brazing filler metal in a ratio of 7:3, and fully stirring to uniformly mix the powder; filling the crack gap with the mixed alloy powder with an applicator;
step three: preset solder
Mixing nickel-based brazing filler metal and binder according to the weight ratio of 10:1, preparing into paste, coating the paste brazing filler metal on a part to be welded along a crack shape by using a coater, and brushing a layer of soldering flux on the outer side of the paste brazing filler metal. And (5) putting the coated blade into a drying box for drying. The drying temperature is 150 ℃ and the heat preservation time is 1.5 hours.
Step four: vacuum brazing
Placing one side of the dried turbine guide vane lower edge plate 1 downwards in a vacuum furnace for vacuum brazing; the brazing heating rate is 8 ℃/min: the brazing temperature is 1110 ℃, the heat preservation time is 15min, the brazing is carried out after the heat preservation is finished, the brazing is cooled to below 80 ℃ along with the furnace, and the vacuum pressure is not more than 1 multiplied by 10 in the brazing process -2 Pa。
Step five: post-weld cleaning and polishing
And removing the flux on the surface of the blade by adopting compressed air, and removing the redundant brazing filler metal at the repairing position by using a sander so as to enable the repairing position to be in smooth transition with the blade matrix.
Step six: post-weld X-ray inspection
The turbine guide blades are placed on a special X-ray inspection tool in four modes according to the conditions that the lower edge plate of the blade faces outwards in a downward exhaust mode, the lower edge plate faces outwards in a downward air inlet mode, the upper edge plate faces outwards in a downward exhaust mode and the upper edge plate faces outwards in a downward air inlet mode in figures 1-5, the turbine guide blades are fixed through locking screws 6 and baffles 5, X-ray inspection is carried out according to HB 201604 standard, inspection results are recorded, and the defect positions of unqualified parts are marked.
When the blade upper edge plate 2 faces downwards and the air inlet edge 9 faces outwards, a special X-ray inspection tool consisting of an exhaust positioning seat 10, an upper edge plate positioning block c14, a lead plate 7 and a baffle plate 5 is adopted, the upper edge plate positioning block c14 is arranged on a positioning surface of the exhaust positioning seat 10, the lead plate 7 is arranged on the upper edge plate positioning block c14, the baffle plate 5 is locked by a screw 6 to fix a turbine guide blade, and the upper edge plate 2 is abutted against an abutting surface of the exhaust positioning seat 10;
when the lower edge plate 1 faces downwards and the air inlet edge 9 faces outwards, a special X-ray inspection tool consisting of an exhaust positioning seat 10, a lower edge plate positioning block b11, a lead plate 7 and a baffle plate 5 is adopted, the lower edge plate positioning block b11 is arranged on a positioning surface of the exhaust positioning seat 10, the lead plate 7 is arranged on the lower edge plate positioning block b11, the baffle plate 5 is locked by a screw 6 to fix a turbine guide blade, and the lower edge plate 1 is abutted against an abutting surface of the exhaust positioning seat 10;
when the lower edge plate 1 faces downwards and the exhaust edge 8 faces outwards, a special X-ray inspection tool consisting of an air inlet positioning seat 3, a lower edge plate positioning block a4, a lead plate 7 and a baffle plate 5 is adopted, the lower edge plate positioning block a4 is arranged on a positioning surface of the air inlet positioning seat 3, the lead plate 7 is arranged on the lower edge plate positioning block a4, the baffle plate 5 is locked by a screw 6 to fix a turbine guide blade, and the lower edge plate 1 is abutted against an abutting surface of the air inlet positioning seat 3;
when the upper edge plate 2 faces downwards and the exhaust edge 8 faces outwards, a special X-ray inspection tool consisting of an air inlet positioning seat 3, an upper edge plate positioning block a12, an upper edge plate positioning block b13, a lead plate 7 and a baffle plate 5 is adopted, the upper edge plate positioning block b13 is arranged on a positioning surface on the air inlet positioning seat 3, the upper edge plate positioning block a12 and the upper edge plate positioning block b13 are vertically arranged, the lead plate 7 is arranged on the upper edge plate positioning block b13, a turbine guide vane is fixed by locking the baffle plate 5 through a screw 6, and the upper edge plate 2 is abutted to an attaching surface of the air inlet positioning seat 3.
The air inlet positioning seat 3 and the air outlet positioning seat 10 are both L-shaped, and the inner surfaces are positioning surfaces and bonding surfaces;
the positioning profiles of the upper edge plate positioning block a12, the upper edge plate positioning block b13, the upper edge plate positioning block c14, the lower edge plate positioning block a4 and the lower edge plate positioning block b11 are corresponding to the profile of the upper edge plate 2 or the lower edge plate 1 of the turbine guide vane.
Step seven: post-weld fluorescent inspection
Fluorescent inspection is carried out according to HB/Z61-1992 standard, the inspection result is recorded, and the defect position of the unqualified part is marked. Repeating the second step to the eighth step for the X-ray and fluorescent unqualified parts.
And repairing the cracks of the turbine guide vane according to the process steps and parameters, and performing X-ray and fluorescent inspection on the repaired vane to obtain the vane which is free of defects and can be put into use.
Example 2:
an in-situ braze repair method for cracks of a turbine guide vane, comprising the steps of:
step one: coating and crack oxide removal
Removing coatings and oxides in cracks of the turbine guide vane by adopting a fluoride ion cleaning method, and putting the vane to be cleaned into fluoride ion cleaning equipment to perform fluoride ion cleaning; the heat preservation temperature is 1000 ℃, the heat preservation time is 180min, the HF gas flow is 0.8L/min, and H 2 The gas flow rate was 8L/min.
Step two: presetting mixed alloy powder
Mixing the nickel-based superalloy powder and the nickel-based brazing filler metal in a ratio of 7:3, and fully stirring to uniformly mix the powder; the crack gap is filled with the mixed alloy powder using an applicator.
Step three: preset solder
Mixing nickel-based brazing filler metal and binder according to the weight ratio of 10:1, preparing into paste, coating the paste brazing filler metal on a part to be welded along a crack shape by using a coater, and brushing a layer of soldering flux on the outer side of the paste brazing filler metal. And (5) putting the coated blade into a drying box for drying. The drying temperature is 150 ℃, and the heat preservation time is 2 hours.
Step four: vacuum brazing
Placing one side of the dried lower edge plate of the turbine guide vane downwards in a vacuum furnace for vacuum brazing; the brazing heating rate is 10 ℃/min: the brazing temperature is 1150 ℃, the heat preservation time is 20min, the brazing is carried out after the heat preservation is finished, the brazing is cooled to below 80 ℃ along with the furnace, and the vacuum pressure is not more than 1 multiplied by 10 in the brazing process -2 Pa。
Step five: post-weld cleaning and polishing
And removing the flux on the surface of the blade by adopting compressed air, and removing the redundant brazing filler metal at the repairing position by using a sander so as to enable the repairing position to be in smooth transition with the blade matrix.
Step six: post-weld X-ray inspection
The turbine guide blades are placed on an X-ray inspection special tool in four modes according to the mode that the lower edge plate of the blade faces downwards and the exhaust edge faces outwards, the lower edge plate faces downwards and the air inlet edge faces outwards, the upper edge plate faces downwards and the air inlet edge faces outwards in the figures 1-5, the turbine guide blades are fixed through locking screws and baffles, X-ray inspection is carried out according to HB20160-2014 standard, inspection results are recorded, and the defect positions of unqualified parts are marked.
When the blade upper edge plate 2 faces downwards and the air inlet edge 9 faces outwards, a special X-ray inspection tool consisting of an exhaust positioning seat 10, an upper edge plate positioning block c14, a lead plate 7 and a baffle plate 5 is adopted, the upper edge plate positioning block c14 is arranged on a positioning surface of the exhaust positioning seat 10, the lead plate 7 is arranged on the upper edge plate positioning block c14, the baffle plate 5 is locked by a screw 6 to fix a turbine guide blade, and the upper edge plate 2 is abutted against an abutting surface of the exhaust positioning seat 10;
when the lower edge plate 1 faces downwards and the air inlet edge 9 faces outwards, a special X-ray inspection tool consisting of an exhaust positioning seat 10, a lower edge plate positioning block b11, a lead plate 7 and a baffle plate 5 is adopted, the lower edge plate positioning block b11 is arranged on a positioning surface of the exhaust positioning seat 10, the lead plate 7 is arranged on the lower edge plate positioning block b11, the baffle plate 5 is locked by a screw 6 to fix a turbine guide blade, and the lower edge plate 1 is abutted against an abutting surface of the exhaust positioning seat 10;
when the lower edge plate 1 faces downwards and the exhaust edge 8 faces outwards, a special X-ray inspection tool consisting of an air inlet positioning seat 3, a lower edge plate positioning block a4, a lead plate 7 and a baffle plate 5 is adopted, the lower edge plate positioning block a4 is arranged on a positioning surface of the air inlet positioning seat 3, the lead plate 7 is arranged on the lower edge plate positioning block a4, the baffle plate 5 is locked by a screw 6 to fix a turbine guide blade, and the lower edge plate 1 is abutted against an abutting surface of the air inlet positioning seat 3;
when the upper edge plate 2 faces downwards and the exhaust edge 8 faces outwards, a special X-ray inspection tool consisting of an air inlet positioning seat 3, an upper edge plate positioning block a12, an upper edge plate positioning block b13, a lead plate 7 and a baffle plate 5 is adopted, the upper edge plate positioning block b13 is arranged on a positioning surface on the air inlet positioning seat 3, the upper edge plate positioning block a12 and the upper edge plate positioning block b13 are vertically arranged, the lead plate 7 is arranged on the upper edge plate positioning block b13, a turbine guide vane is fixed by locking the baffle plate 5 through a screw 6, and the upper edge plate 2 is abutted to an attaching surface of the air inlet positioning seat 3.
The air inlet positioning seat 3 and the air outlet positioning seat 10 are both L-shaped, and the inner surfaces are positioning surfaces and bonding surfaces;
the positioning profiles of the upper edge plate positioning block a12, the upper edge plate positioning block b13, the upper edge plate positioning block c14, the lower edge plate positioning block a4 and the lower edge plate positioning block b11 are corresponding to the profile of the upper edge plate 2 or the lower edge plate 1 of the turbine guide vane.
Step seven: post-weld fluorescent inspection
Fluorescent inspection is carried out according to HB/Z61-1992 standard, the inspection result is recorded, and the defect position of the unqualified part is marked. Repeating the second step to the eighth step for the X-ray and fluorescent unqualified parts.
And repairing the cracks of the turbine guide vane according to the process steps and parameters, and performing X-ray and fluorescent inspection on the repaired vane to obtain the vane which is free of defects and can be put into use.
Example 3:
an in-situ braze repair method for cracks of a turbine guide vane, comprising the steps of:
step one: coating and crack oxide removal
Removing coatings and oxides in cracks of the turbine guide vane by adopting a fluoride ion cleaning method, and putting the vane to be cleaned into fluoride ion cleaning equipment to perform fluoride ion cleaning; the heat preservation temperature is 1050 ℃, the heat preservation time is 240min, the HF gas flow is 1L/min, H 2 The gas flow rate was 10L/min.
Step two: presetting mixed alloy powder
Mixing the nickel-based superalloy powder and the nickel-based brazing filler metal in a ratio of 7:3, and fully stirring to uniformly mix the powder; the crack gap is filled with the mixed alloy powder using an applicator.
Step three: preset solder
Mixing nickel-based brazing filler metal and binder according to the weight ratio of 10:1, preparing into paste, coating the paste brazing filler metal on a part to be welded along a crack shape by using a coater, and brushing a layer of soldering flux on the outer side of the paste brazing filler metal. And (5) putting the coated blade into a drying box for drying. The drying temperature is 200 ℃, and the heat preservation time is 2 hours.
Step four: vacuum brazing
Placing one side of the dried lower edge plate of the turbine guide vane downwards in a vacuum furnace for vacuum brazing; the brazing heating rate is 12 ℃/min: the brazing temperature is 1150 ℃, the heat preservation time is 25min, the brazing is carried out after the heat preservation is finished, the brazing is cooled to below 80 ℃ along with the furnace, and the vacuum pressure is not more than 1 multiplied by 10 in the brazing process -2 Pa。
Step five: post-weld cleaning and polishing
And removing the flux on the surface of the blade by adopting compressed air, and removing the redundant brazing filler metal at the repairing position by using a sander so as to enable the repairing position to be in smooth transition with the blade matrix.
Step six: post-weld X-ray inspection
The turbine guide blades are placed on an X-ray inspection special tool in four modes according to the mode that the lower edge plate of the blade faces downwards and the exhaust edge faces outwards, the lower edge plate faces downwards and the air inlet edge faces outwards, the upper edge plate faces downwards and the air inlet edge faces outwards in the figures 1-5, the turbine guide blades are fixed through locking screws and baffles, X-ray inspection is carried out according to HB20160-2014 standard, inspection results are recorded, and the defect positions of unqualified parts are marked.
When the blade upper edge plate 2 faces downwards and the air inlet edge 9 faces outwards, a special X-ray inspection tool consisting of an exhaust positioning seat 10, an upper edge plate positioning block c14, a lead plate 7 and a baffle plate 5 is adopted, the upper edge plate positioning block c14 is arranged on a positioning surface of the exhaust positioning seat 10, the lead plate 7 is arranged on the upper edge plate positioning block c14, the baffle plate 5 is locked by a screw 6 to fix a turbine guide blade, and the upper edge plate 2 is abutted against an abutting surface of the exhaust positioning seat 10;
when the lower edge plate 1 faces downwards and the air inlet edge 9 faces outwards, a special X-ray inspection tool consisting of an exhaust positioning seat 10, a lower edge plate positioning block b11, a lead plate 7 and a baffle plate 5 is adopted, the lower edge plate positioning block b11 is arranged on a positioning surface of the exhaust positioning seat 10, the lead plate 7 is arranged on the lower edge plate positioning block b11, the baffle plate 5 is locked by a screw 6 to fix a turbine guide blade, and the lower edge plate 1 is abutted against an abutting surface of the exhaust positioning seat 10;
when the lower edge plate 1 faces downwards and the exhaust edge 8 faces outwards, a special X-ray inspection tool consisting of an air inlet positioning seat 3, a lower edge plate positioning block a4, a lead plate 7 and a baffle plate 5 is adopted, the lower edge plate positioning block a4 is arranged on a positioning surface of the air inlet positioning seat 3, the lead plate 7 is arranged on the lower edge plate positioning block a4, the baffle plate 5 is locked by a screw 6 to fix a turbine guide blade, and the lower edge plate 1 is abutted against an abutting surface of the air inlet positioning seat 3;
when the upper edge plate 2 faces downwards and the exhaust edge 8 faces outwards, a special X-ray inspection tool consisting of an air inlet positioning seat 3, an upper edge plate positioning block a12, an upper edge plate positioning block b13, a lead plate 7 and a baffle plate 5 is adopted, the upper edge plate positioning block b13 is arranged on a positioning surface on the air inlet positioning seat 3, the upper edge plate positioning block a12 and the upper edge plate positioning block b13 are vertically arranged, the lead plate 7 is arranged on the upper edge plate positioning block b13, a turbine guide vane is fixed by locking the baffle plate 5 through a screw 6, and the upper edge plate 2 is abutted to an attaching surface of the air inlet positioning seat 3.
The air inlet positioning seat 3 and the air outlet positioning seat 10 are both L-shaped, and the inner surfaces are positioning surfaces and bonding surfaces;
the positioning profiles of the upper edge plate positioning block a12, the upper edge plate positioning block b13, the upper edge plate positioning block c14, the lower edge plate positioning block a4 and the lower edge plate positioning block b11 are corresponding to the profile of the upper edge plate 2 or the lower edge plate 1 of the turbine guide vane.
Step seven: post-weld fluorescent inspection
Fluorescent inspection is carried out according to HB/Z61-1992 standard, the inspection result is recorded, and the defect position of the unqualified part is marked. Repeating the second step to the eighth step for the X-ray and fluorescent unqualified parts.
And repairing the cracks of the turbine guide vane according to the process steps and parameters, and performing X-ray and fluorescent inspection on the repaired vane to obtain the vane which is free of defects and can be put into use.
Claims (7)
1. An in-situ braze repair method for cracks of turbine guide vanes, which is characterized by comprising the following steps: the method comprises the following steps:
step one: coating and crack oxide removal
Removing coatings and oxides in cracks of turbine guide blades by adopting a fluoride ion cleaning method, putting the blades to be cleaned into fluoride ion cleaning equipment, generating metal fluoride gas and water vapor through chemical reaction of HF gas and the coatings and the oxides in the cracks at high temperature, intermittently introducing flowing argon gas, and taking away the fluoride gas and oxygen;
step two: presetting mixed alloy powder
For cracks with the gap larger than 0.1mm, filling mixed alloy powder in the crack gap by using an applicator; mixing the mixed alloy powder according to the proportion of the nickel-based superalloy powder and the nickel-based brazing filler metal of 7:3, and fully stirring to uniformly mix the powder;
step three: preset solder
Mixing nickel-based brazing filler metal and binder according to the weight ratio of 10:1, preparing into paste, coating the paste brazing filler metal on a part to be welded along a crack shape by using a coater, brushing a layer of soldering flux on the outer side of the paste brazing filler metal, and finally placing the coated turbine guide vane into a drying box for drying;
step four: vacuum brazing
Placing one side of the dried lower edge plate of the turbine guide vane downwards in a vacuum furnace for vacuum brazing;
step five: post-weld cleaning and polishing
Removing the flux on the surface of the blade by adopting compressed air, and removing redundant brazing filler metal at the repairing position by using a sander so as to enable the repairing position to be in smooth transition with the blade matrix;
step six: post-weld X-ray inspection
The method comprises the steps of respectively placing turbine guide blades on an X-ray inspection special tool according to four modes of a blade upper edge plate facing downwards, an air inlet edge facing outwards, an upper edge plate facing downwards, an air outlet edge facing outwards, a lower edge plate facing downwards, an air outlet edge facing outwards, fixing the turbine guide blades through locking screws and baffles, performing X-ray inspection according to HB 201604 standard, recording inspection results, and marking defective parts;
step seven: post-weld fluorescent inspection
And (3) performing fluorescent inspection according to HB/Z61-1992 standard, recording inspection results, marking the defect positions of the unqualified parts, and repeating the steps two to eight for the X-ray and the unqualified parts subjected to fluorescent inspection.
2. The method for in-situ braze repair of a crack in a turbine guide vane of claim 1, wherein: in the first step, the technological parameters of fluoride ion cleaning are as follows: the heat preservation temperature is 930-1050 ℃, the heat preservation time is 120-240 min, the HF gas flow is 0.5-1L/min, and H 2 The gas flow is 4L/min-10L/min.
3. The method for in-situ braze repair of a crack in a turbine guide vane of claim 1, wherein: in the third step, the drying temperature is 150-200 ℃ and the heat preservation time is 1.5-2 h.
4. The method for in-situ braze repair of a crack in a turbine guide vane of claim 1, wherein: and thirdly, arranging the brazing filler metal on one side of the flow passage surface for penetrating cracks at the edge plate.
5. The method for in-situ braze repair of a crack in a turbine guide vane of claim 1, wherein: in the fourth step, the brazing heating rate of vacuum brazing is 8 ℃/min-12 ℃/min, the brazing temperature is 1110 ℃ -1150 ℃, the heat preservation time is 15min-25min, the vacuum brazing is cooled to below 80 ℃ along with a furnace and discharged, and the vacuum pressure in the brazing process is not more than 1 multiplied by 10 < -2 > Pa.
6. The method for in-situ braze repair of a crack in a turbine guide vane of claim 1, wherein: in the sixth step, when the upper edge plate of the blade faces downwards and the air inlet edge faces outwards, a special X-ray inspection tool consisting of an exhaust positioning seat, an upper edge plate positioning block c, a lead plate and a baffle plate is adopted, the upper edge plate positioning block c is arranged on a positioning surface of the exhaust positioning seat, the lead plate is arranged on the upper edge plate positioning block c, the baffle plate is locked by a screw to fix the turbine guide blade, and the upper edge plate is abutted against an abutting surface of the exhaust positioning seat;
when the lower edge plate faces downwards and the air inlet edge faces outwards, a special X-ray inspection tool consisting of an exhaust positioning seat, a lower edge plate positioning block b, a lead plate and a baffle plate is adopted, the lower edge plate positioning block b is arranged on a positioning surface of the exhaust positioning seat, the lead plate is arranged on the lower edge plate positioning block b, a turbine guide blade is fixed by locking the baffle plate through a screw, and the lower edge plate is abutted against an abutting surface of the exhaust positioning seat;
when the lower edge plate faces downwards and the exhaust edge faces outwards, a special X-ray inspection tool consisting of an air inlet positioning seat, a lower edge plate positioning block a, a lead plate and a baffle plate is adopted, the lower edge plate positioning block a is arranged on a positioning surface of the air inlet positioning seat, the lead plate is arranged on the lower edge plate positioning block a, a turbine guide blade is fixed by locking the baffle plate through a screw, and the lower edge plate is abutted against an abutting surface of the air inlet positioning seat;
when the upper edge plate is downward and the exhaust edge is outward, a special X-ray inspection tool consisting of an air inlet positioning seat, an upper edge plate positioning block a, an upper edge plate positioning block b, a lead plate and a baffle plate is adopted, the upper edge plate positioning block b is arranged on a positioning surface on the air inlet positioning seat, the upper edge plate positioning block a is vertically arranged with the upper edge plate positioning block b, the lead plate is arranged on the upper edge plate positioning block b, the turbine guide vane is fixed through a screw locking baffle plate, and the upper edge plate is abutted against an abutting surface of the air inlet positioning seat.
7. The method for in-situ braze repair of a crack in a turbine guide vane of claim 6, wherein: the air inlet positioning seat and the air outlet side are positioned in an L shape, and the inner surface is a positioning surface and a bonding surface;
the positioning profiles of the upper edge plate positioning block a, the upper edge plate positioning block b, the upper edge plate positioning block c, the lower edge plate positioning block a and the lower edge plate positioning block b correspond to the profile of the upper edge plate or the lower edge plate of the turbine guide vane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311494819.3A CN117464307A (en) | 2023-11-10 | 2023-11-10 | In-situ brazing repair method for cracks of turbine guide vane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311494819.3A CN117464307A (en) | 2023-11-10 | 2023-11-10 | In-situ brazing repair method for cracks of turbine guide vane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117464307A true CN117464307A (en) | 2024-01-30 |
Family
ID=89636074
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311494819.3A Pending CN117464307A (en) | 2023-11-10 | 2023-11-10 | In-situ brazing repair method for cracks of turbine guide vane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117464307A (en) |
-
2023
- 2023-11-10 CN CN202311494819.3A patent/CN117464307A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA1079043A (en) | Method of refurbishing turbine components and the like | |
| US5972424A (en) | Repair of gas turbine engine component coated with a thermal barrier coating | |
| US6172327B1 (en) | Method for laser twist welding of compressor blisk airfoils | |
| JP5322371B2 (en) | How to repair a disk with an integrated blade, test piece at the start and end of work | |
| US7810237B2 (en) | Method for repairing and/or modifying component parts of a gas turbine | |
| CN105149597B (en) | The reparation of metal or alloy component or connecting method and component that is repaired or being coupled | |
| US20090026182A1 (en) | In-situ brazing methods for repairing gas turbine engine components | |
| CN102107306B (en) | Repairing method for defects of turbine guide blade | |
| CN106493507B (en) | A kind of vacuum brazing repair method of aero-engine supersonic speed adjustment sheet crackle | |
| US20060248718A1 (en) | Superalloy repair methods and inserts | |
| CN106493506B (en) | A kind of aero-engine cobalt base superalloy component failure soldering repair method | |
| CN107723699B (en) | Method for repairing heat-resistant alloy | |
| JP2003155935A (en) | Method for repairing apertured gas turbine component | |
| KR102278830B1 (en) | Method of repairing gas turbine blade tip using high frequency welding | |
| CN108032033B (en) | A kind of restorative procedure of turborotor cold air hole crackle | |
| CN1943973A (en) | Method for producing aluminum plate-fin heat exchanger | |
| US20130326877A1 (en) | Method of working an airfoil using elevated temperature cmt welding | |
| JP2003507613A (en) | Laser cladding of turbine engine blade base plate | |
| CN111001808A (en) | Composite additive manufacturing method of large-size In718 high-temperature alloy component | |
| WO2019037410A1 (en) | Method for repairing abraded bearing | |
| JP2005349478A (en) | Homogeneous welding method for superalloy article | |
| CA2651142A1 (en) | Methods of repairing engine components | |
| CN106521487A (en) | Remanufacturing method for blade of titanium alloy gas compressor in middle service period | |
| US20130004320A1 (en) | Method of rotated airfoils | |
| CN113478167A (en) | Method for repairing blade shroud of working blade of high-pressure turbine of aircraft engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |