CN1883872A - Crack repair process for high-pressure turbine blade tip in gas turbine - Google Patents
Crack repair process for high-pressure turbine blade tip in gas turbine Download PDFInfo
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- CN1883872A CN1883872A CN 200510046729 CN200510046729A CN1883872A CN 1883872 A CN1883872 A CN 1883872A CN 200510046729 CN200510046729 CN 200510046729 CN 200510046729 A CN200510046729 A CN 200510046729A CN 1883872 A CN1883872 A CN 1883872A
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- 230000008439 repair process Effects 0.000 title claims abstract description 71
- 238000003466 welding Methods 0.000 claims abstract description 59
- 238000000034 method Methods 0.000 claims abstract description 40
- 239000000463 material Substances 0.000 claims abstract description 30
- 238000005498 polishing Methods 0.000 claims abstract description 19
- 230000008569 process Effects 0.000 claims abstract description 17
- 238000010438 heat treatment Methods 0.000 claims abstract description 15
- 208000037656 Respiratory Sounds Diseases 0.000 claims description 36
- 239000007789 gas Substances 0.000 claims description 32
- 238000000151 deposition Methods 0.000 claims description 17
- 239000000843 powder Substances 0.000 claims description 12
- 230000008021 deposition Effects 0.000 claims description 11
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 10
- 238000011049 filling Methods 0.000 claims description 9
- 239000000956 alloy Substances 0.000 claims description 8
- 229910045601 alloy Inorganic materials 0.000 claims description 7
- 239000000203 mixture Substances 0.000 claims description 7
- 239000001307 helium Substances 0.000 claims description 6
- 229910052734 helium Inorganic materials 0.000 claims description 6
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 claims description 6
- 239000011159 matrix material Substances 0.000 claims description 6
- 229910052786 argon Inorganic materials 0.000 claims description 5
- 239000000758 substrate Substances 0.000 claims description 5
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 4
- 238000001816 cooling Methods 0.000 claims description 4
- 238000003483 aging Methods 0.000 claims description 3
- 239000004744 fabric Substances 0.000 claims description 3
- 238000005728 strengthening Methods 0.000 claims description 3
- 238000000227 grinding Methods 0.000 claims description 2
- 239000003595 mist Substances 0.000 claims description 2
- 229910052757 nitrogen Inorganic materials 0.000 claims description 2
- 230000001681 protective effect Effects 0.000 claims description 2
- 229910052751 metal Inorganic materials 0.000 abstract description 14
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- 230000007774 longterm Effects 0.000 abstract description 2
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- 239000000945 filler Substances 0.000 description 7
- 238000011084 recovery Methods 0.000 description 7
- 239000011324 bead Substances 0.000 description 6
- 238000011161 development Methods 0.000 description 4
- 238000009413 insulation Methods 0.000 description 4
- 239000002737 fuel gas Substances 0.000 description 3
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 239000002131 composite material Substances 0.000 description 2
- 238000012937 correction Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000010892 electric spark Methods 0.000 description 2
- 239000007772 electrode material Substances 0.000 description 2
- 230000004927 fusion Effects 0.000 description 2
- 230000008520 organization Effects 0.000 description 2
- 239000002245 particle Substances 0.000 description 2
- 229910000601 superalloy Inorganic materials 0.000 description 2
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
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- 230000008859 change Effects 0.000 description 1
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- 239000000567 combustion gas Substances 0.000 description 1
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- 238000005260 corrosion Methods 0.000 description 1
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- 238000009792 diffusion process Methods 0.000 description 1
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- 239000000428 dust Substances 0.000 description 1
- 239000003546 flue gas Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
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- Welding Or Cutting Using Electron Beams (AREA)
- Butt Welding And Welding Of Specific Article (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention belongs to the metal surface crack repairing method, meaning the tip crack repairing method of a gas-turbine engine high-pressure turbine blade. The method comprises polishing apertures for complete crack removal based on the crack conditions of the gas-turbine engine high-pressure turbine blade tip, carrying out surfacing welding in the repair welding zone using low-heat input welding technology and implementing heat treatment process to the repaired blade. The present invention has the virtues of simple process, needing no vacuum or preheating, small damage to blade base materials, realizing loss-free repair to the high-pressure turbine blade tip cracks and reducing repair cost. The invention can be used to repair both the gas-turbine engine high-pressure turbine blade tip cracks and steam turbine, smoke turbine and other turbine mechanisms high-pressure or low-pressure blade tip cracks. And the aircraft engine high-pressure turbine blade repaired with the method has passes 368h long-term bench trial check.
Description
Technical field
The invention belongs to the crack of metal surface restorative procedure, be specially a kind of high-pressure turbine blade tip in gas turbine method for repairing crack.
Background technology
Modern gas turbines is widely used on aero-engine and the ground electrical power combustion machine, and along with the raising of engine efficiency, the fuel gas temperature of engine is more and more higher, and the high-temperature fuel gas of engine combustion generation simultaneously also has very strong corrosivity and oxidisability.High-pressure turbine blade is in the turbine position of gas turbine; the highest combustion gas of temperature that discharge the combustion chamber directly acts near the turbo blade blade tip; because the start-stop of engine or state change suddenly; blade tip can produce very high thermal stress; blade high-temerature creep elongate blade is most advanced and sophisticated simultaneously weares and teares with outer casing; in corrosion that adds high-temperature fuel gas and oxidation; gas turbine; particularly early stage cracking phenomena can appear in aero-engine high-pressure turbine blade blade tip; prolongation along with the working time; the blade tip crackle shows a rising trend, and a lot of blades are scrapped in advance because of crackle is overproof.Because blade manufacturing expense costliness is repaired usefulness again to the blade that does not reach projected life as yet, is a thing highly significant.
On the other hand, because high-pressure turbine blade belongs to Al, nickel base superalloy that Ti content is very high, have very high fire check sensitiveness in welding and post weld heat treatment process, usually genus can not the wlding material, and this has brought very big difficulty with regard to the reparation to high-pressure turbine blade.
The initial failure of high-pressure turbine blade blade tip mainly is wearing and tearing and crackle, sees that with regard to failure mode the long more wearing and tearing of active time are outstanding more, and the high more crackle of operating temperature is outstanding more.Reparation at the wearing and tearing of high-pressure turbine blade blade tip, general fusion welding method such as argon arc welding, Laser Welding and the non-fusion welding method such as soldering, diffusion welding (DW) of adopting carries out, this respect all has document and patent report both at home and abroad, but high-pressure turbine blade tip Crack repair seldom has the open source literature report both at home and abroad.
Summary of the invention
The present invention is directed to above problem, propose a kind of crack repair process for high-pressure turbine blade tip in gas turbine, can repair the level that makes former blade be able to normally re-use high Al, Ti superalloy turbine vane tip crackle.
Technical scheme of the present invention is achieved in that
A kind of crack repair process for high-pressure turbine blade tip in gas turbine adopts corresponding micro-grinding machine opening thoroughly to remove crackle according to gas turbine high-pressure turbine blade tip crackle situation; Under gas shield, adopt low-heat input welding procedure to carry out built-up welding then at blade tip polishing open region; Again the blade after repairing is carried out restorability heat treatment.
Described openings of sizes is: the degree of depth is no more than 15% of blade height, and be advisable by the substrate loss minimum to remove crackle fully for width.
The repair materials employing solution strengthening that home or overseas is close with the matrix material composition, thermal coefficient of expansion is suitable, weldability is good of the present invention or the high temperature alloy of age-hardening, performance is better than being repaired material or close with being repaired material.
Described repair materials is that one of electrode and powder or two kinds of forms are used simultaneously, and electrode composition and powder composition are identical or different.
Described low-heat input welding procedure comprises: laser weld or high energy micro arc deposition or laser weld/high energy micro arc deposition combination process.
Material modes of emplacement of the present invention is: under gas shield, adopt the direct width of cloth of laser according to powder or high energy micro arc depositing electrode; Perhaps the two is compounded in the built-up welding of repair welding district, adopts earlier the high energy micro arc depositing electrode to preset bottom, then laser weld in the built-up welding layer by layer of repair welding district until filling up whole repair welding district.
Protective gas of the present invention is: nitrogen, helium, argon gas or its mist.
Described heat treatment is: 900 ℃～1300 ℃, be incubated 0～100 hour, air cooling.
Advantage of the present invention:
1, the present invention thoroughly removes crackle according to gas turbine high-pressure turbine blade tip crackle situation polishing opening, adopts low-heat input welding procedure to carry out built-up welding in the repair welding district then, and the blade after repairing is heat-treated.Its process is simple, does not need vacuum and preheating, and is little to the basic material of blade damage, realized the harmless reparation of high-pressure turbine blade blade tip crackle, reduced repair cost.
2, the present invention is by adopting the high temperature alloy filler; at room temperature use high energy micro arc (also being electric spark) and laser beam; under gas shield, the high-pressure turbine blade tip crackle of gas turbine is carried out repair welding and repair by set technique methods such as heat treatments; process is simple, processing ease.
3, the present invention is little to the high temperature alloy fire damage, and the heat affected area is narrow or do not have the heat affected area, has effectively avoided the generation of repair welding material and substrate interface crackle, and the high-temperature alloy material that can not weld is become can be welded, and this method need not preheating.
4, the inventive method not only can be used for repairing the high-pressure turbine blade tip in gas turbine crackle, can also be used to repairing steam turbine, flue gas turbine expander and other turbine mechanism high pressure and low pressure blade blade tip crackle.Examine by 368 hours long-term bench test drives with certain aero-engine high-pressure turbine blade that this process is repaired.
Description of drawings
Fig. 1 is high-pressure turbine blade and tip crackle schematic diagram thereof; Among the figure, the 1-high-pressure turbine blade; 2-tip crackle.
Fig. 2 is a crackle repair welding main technique schematic diagram, and technical process comprises: crackle → polishing opening → filler weldering → heat treatment.
Fig. 3 (a)-(b) is the actual crack repair tissue structure, and the repair welding district is finished by high energy micro arc deposition and laser weld composite overlaying; Fig. 3 (a) is a filler weldering tissue, and Fig. 3 (b) organizes after the heat treatment.
The specific embodiment
Aero-engine, the overproof form of ground electrical power combustion machine crackle is varied, there is single crackle that intensive crackle is also arranged, the invention is characterized in and to repair the crackle that high-pressure turbine blade tip length is not more than blade height 15%, crackle is removed by the opening polishing, the polishing open region is filled up by laser weld, high energy micro arc or the two combination process built-up welding are finished, repairing the district is the metallurgical binding flawless with matrix, repair and distinguish material therefor the high temperature alloy that is compatible and the good high-temperature mechanical property is arranged, will carry out recovery organization heat treatment the blade after the repair welding with matrix.Its process is:
1, adopt the opening form polishing to remove crackle according to high-pressure turbine blade blade tip crack length and dense degree, the opening degree of depth is no more than 15% of blade height, and be advisable by the substrate loss minimum to remove crackle fully for width.
2, repair materials: the repair materials employing solution strengthening that home or overseas is close with the matrix material composition, thermal coefficient of expansion is suitable, weldability is good or the high temperature alloy of age-hardening, performance are better than being repaired material or close with being repaired material.
3, under gas shield, adopt the direct width of cloth of laser to shine powder or high energy micro arc depositing electrode or the two and be compounded in the built-up welding layer by layer of repair welding district until filling up whole repair welding district and leaving the polishing surplus.
4, the repair welding district to high-pressure turbine blade carries out correction of the flank shape, rubbing down, bead.
5, blade is carried out recovery organization heat treatment, 900 ℃～1300 ℃ of temperature are incubated 0～100 hour, air cooling.
6, do not need to carry out preheating before the blade reparation.
7, reparation needs descale with metal electrode material, is machined to be fit to repair welding district size.Reparation need be carried out drying with metal powder material, sieves, and granularity is not more than 200 orders.Need carry out cleaning to restoring area, descale makes its surface-brightening.
Embodiment 1
Certain aero-engine high-pressure turbine blade blade tip crackle is repaired, and material is the K465 alloy, and concrete steps are as follows:
1, adopt the opening form polishing to remove crackle according to high-pressure turbine blade blade tip crack length and dense degree, the maximum 5mm of the opening degree of depth, be advisable by the substrate loss minimum to remove crackle fully for width.
2, under argon shield; adopt the metal surface enhanced reparation machine of 3H-ES-6 of Metal Inst., Chinese Academy of Sciences's development to carry out high energy micro arc (electric spark) deposition; electrode diameter Φ 1mm, electrode in the built-up welding layer by layer of repair welding district until filling up whole repair welding district and leaving the polishing surplus.
3, the high energy micro arc deposition materials is GH44.
4, the repair welding district to high-pressure turbine blade carries out correction of the flank shape, rubbing down, bead.
5, blade is heat-treated, 900 ℃ of temperature are incubated 2 hours, air cooling.
6, do not need to carry out preheating before the blade reparation.
7, reparation needs descale with metal electrode material, is machined to be fit to repair welding district size.
High-pressure turbine blade with this process reparation meets the recovery technique standard by X-ray, fluoroscopic examination.
Embodiment 2
Difference from Example 1 is:
Certain aero-engine high-pressure turbine blade blade tip crackle is repaired, and blade material is Rene80, adopts the weldering of opening filler to repair, the maximum 7mm of the opening degree of depth, and repair materials is the IN625 powder, particle mean size is about 270 orders.Under helium protection, adopt laser welding process in the built-up welding layer by layer of repair welding district until filling up whole repair welding district and leaving the polishing surplus.Grind afterwards repair, detect, polishing, bead, last blade carries out restorability heat treatment 1050 ℃, insulation 80 hours.
High-pressure turbine blade with this process reparation meets the recovery technique standard by X-ray, fluoroscopic examination.
Embodiment 3
Difference from Example 1 is:
Certain aero-engine high-pressure turbine blade blade tip crackle is repaired, and blade material is K24, adopts the weldering of opening filler to repair, the maximum 5mm of the opening degree of depth.Under the helium protection; adopting earlier the metal surface enhanced reparation machine of 3H-ES-6 of Metal Inst., Chinese Academy of Sciences's development to carry out the high energy micro arc deposition presets bottom (electrode diameter is Φ 3mm; the bottom height is 100um); adopt metal dust to carry out laser weld then; until filling up whole repair welding district and leaving the polishing surplus, electrode and powder are Haynes 230 in the built-up welding layer by layer of repair welding district.Grind afterwards repair, detect, polishing, bead, last blade carries out restorability heat treatment 1180 ℃, insulation 10 hours.
Present embodiment adopts the high energy micro arc depositing electrode to preset bottom earlier, and laser weld until filling up whole repair welding district, can reduce the fire damage of base material in the built-up welding layer by layer of repair welding district as far as possible then.
High-pressure turbine blade with this process reparation meets the recovery technique standard by X-ray, fluoroscopic examination.
Embodiment 4
Difference from Example 1 is:
Certain ground electric power combustion machine high-pressure turbine blade blade tip crackle is repaired, and blade material is IN738, adopts the weldering of opening filler to repair, and repair materials is the IN625 powder, and particle mean size is about 320 orders, the maximum 10mm of the opening degree of depth.Mixed gas protected down at helium and argon gas; adopt the built-up welding layer by layer of laser irradiation IN625 powder until filling up 90% of whole repair welding district, adopt the metal surface enhanced reparation machine of 3H-ES-D3000 of Metal Inst., Chinese Academy of Sciences's development to carry out high energy micro arc deposition NiCrAlY on IN625 sedimentary deposit surface and leave the polishing surplus then.Grind afterwards repair, detect, polishing, bead, last blade carries out restorability heat treatment 1210 ℃, insulation 24 hours.
Present embodiment adopts the mode of high energy micro arc and laser weld combination earlier, is because NiCrAlY fire check sensitiveness height needs high energy micro arc to deposit and improves surface oxidation-resistant.
Institutional framework after being depicted as an actual crack and repairing as Fig. 3 (a)-(b), the repair welding district is finished by high energy micro arc deposition and laser weld composite overlaying.Repair layer flawless and obvious metallurgical imperfection, with matrix be good metallurgical binding, with the combustion machine blade pass of this process reparation cross X-ray, fluoroscopic examination reparation district quality meets the recovery technique standard.
Embodiment 5
Difference from Example 1 is:
Certain ground electric power combustion machine high-pressure turbine blade blade tip crackle is repaired, and blade material is K24, adopts the weldering of opening filler to repair, the maximum 12mm of the opening degree of depth, and repair materials is the K24 electrode, electrode diameter Φ 5mm.Under helium protection, adopt the metal surface enhanced reparation machine of 3H-ES-D3000 of Metal Inst., Chinese Academy of Sciences's development to carry out the high energy micro arc deposition, in the built-up welding layer by layer of repair welding district until filling up whole repair welding district and leaving the polishing surplus.Grind afterwards repair, detect, polishing, bead, last blade carries out restorability heat treatment 1210 ℃, insulation 50 hours.
Combustion machine blade pass with this process reparation is crossed X-ray, fluoroscopic examination meets the recovery technique standard.
Claims (8)
1, a kind of crack repair process for high-pressure turbine blade tip in gas turbine is characterized in that, adopts corresponding micro-grinding machine opening thoroughly to remove crackle according to gas turbine high-pressure turbine blade tip crackle situation; Under gas shield, adopt low-heat input welding procedure to carry out built-up welding then at blade tip polishing open region; Again the blade after repairing is carried out restorability heat treatment.
According to the described crack repair process for high-pressure turbine blade tip in gas turbine of claim 1, it is characterized in that 2, described openings of sizes is: the degree of depth is no more than 15% of blade height, and be advisable by the substrate loss minimum to remove crackle fully for width.
3, according to the described crack repair process for high-pressure turbine blade tip in gas turbine of claim 1, it is characterized in that, the repair materials employing solution strengthening that home or overseas is close with the matrix material composition, thermal coefficient of expansion is suitable, weldability is good or the high temperature alloy of age-hardening, performance are better than being repaired material or close with being repaired material.
According to the described crack repair process for high-pressure turbine blade tip in gas turbine of claim 3, it is characterized in that 4, described repair materials is that one of electrode and powder or two kinds of forms are used simultaneously, electrode composition and powder composition are identical or different.
5, according to the described crack repair process for high-pressure turbine blade tip in gas turbine of claim 1, it is characterized in that described low-heat input welding procedure comprises: laser weld or high energy micro arc deposition or laser weld/high energy micro arc deposition combination process.
6, according to claim 1,3,4 or 5 described crack repair process for high-pressure turbine blade tip in gas turbine, it is characterized in that the material modes of emplacement is: under gas shield, adopt the direct width of cloth of laser according to powder or high energy micro arc depositing electrode; Perhaps the two is compounded in the built-up welding of repair welding district, adopts earlier the high energy micro arc depositing electrode to preset bottom, then laser weld in the built-up welding layer by layer of repair welding district until filling up whole repair welding district.
According to the described crack repair process for high-pressure turbine blade tip in gas turbine of claim 1, it is characterized in that 7, protective gas is: nitrogen, helium, argon gas or its mist.
According to the described crack repair process for high-pressure turbine blade tip in gas turbine of claim 1, it is characterized in that 8, described heat treatment is: 900 ℃～1300 ℃, be incubated 0～100 hour, air cooling.
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| CNB2005100467293A CN100402223C (en) | 2005-06-22 | 2005-06-22 | Crack repair process for high-pressure turbine blade tip in gas turbine |
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| CNB2005100467293A CN100402223C (en) | 2005-06-22 | 2005-06-22 | Crack repair process for high-pressure turbine blade tip in gas turbine |
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| CN1883872A true CN1883872A (en) | 2006-12-27 |
| CN100402223C CN100402223C (en) | 2008-07-16 |
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Assignee: Guangdong Huizhou LNG Power Co., Ltd. Assignor: Institute of metal research, Chinese Academy of Sciences Contract fulfillment period: 2008.10.8 to 2013.10.8 contract change Contract record no.: 2009440000829 Denomination of invention: Crack repair process for high-pressure turbine blade tip in gas turbine Granted publication date: 20080716 License type: Exclusive license Record date: 2009.7.24 |
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Free format text: EXCLUSIVE LICENSE; TIME LIMIT OF IMPLEMENTING CONTACT: 2008.10.8 TO 2013.10.8; CHANGE OF CONTRACT Name of requester: GUANGDONG HUIZHOU LNG POWER CO., LTD. Effective date: 20090724 |
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