CN108372387A - A kind of engine blade patching type restorative procedure - Google Patents
A kind of engine blade patching type restorative procedure Download PDFInfo
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- CN108372387A CN108372387A CN201710003786.6A CN201710003786A CN108372387A CN 108372387 A CN108372387 A CN 108372387A CN 201710003786 A CN201710003786 A CN 201710003786A CN 108372387 A CN108372387 A CN 108372387A
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- 238000000034 method Methods 0.000 title claims abstract description 54
- 238000003466 welding Methods 0.000 claims abstract description 96
- 230000008569 process Effects 0.000 claims abstract description 19
- 238000004088 simulation Methods 0.000 claims abstract description 13
- 230000008439 repair process Effects 0.000 claims description 17
- 238000003825 pressing Methods 0.000 claims description 7
- 238000002679 ablation Methods 0.000 claims description 5
- 230000003902 lesion Effects 0.000 claims description 4
- 230000007704 transition Effects 0.000 claims description 4
- 230000015572 biosynthetic process Effects 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 claims description 3
- 238000005476 soldering Methods 0.000 claims description 3
- 230000001360 synchronised effect Effects 0.000 claims description 3
- 238000003786 synthesis reaction Methods 0.000 claims description 3
- 244000228957 Ferula foetida Species 0.000 claims description 2
- 150000001875 compounds Chemical class 0.000 claims description 2
- 238000003754 machining Methods 0.000 claims description 2
- 238000003672 processing method Methods 0.000 claims description 2
- 230000008719 thickening Effects 0.000 claims description 2
- 230000008901 benefit Effects 0.000 claims 1
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 abstract description 6
- 230000007547 defect Effects 0.000 abstract description 5
- 229910052786 argon Inorganic materials 0.000 abstract description 3
- 230000004927 fusion Effects 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 4
- 238000010894 electron beam technology Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 238000011084 recovery Methods 0.000 description 2
- 230000008859 change Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000945 filler Substances 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 230000002441 reversible effect Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P6/00—Restoring or reconditioning objects
- B23P6/002—Repairing turbine components, e.g. moving or stationary blades, rotors
-
- 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
- B23P2700/00—Indexing scheme relating to the articles being treated, e.g. manufactured, repaired, assembled, connected or other operations covered in the subgroups
- B23P2700/01—Aircraft parts
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Arc Welding In General (AREA)
Abstract
The present invention relates to a kind of engine blade patching type restorative procedures.This method carries out the design of sticking patch according to the cross sectional shape of the blade after excision, processes a groove in sticking patch section, and design welding tooling according to the shape of sticking patch, and carry out Welding experiment to partial simulation blade, obtains best welding parameter；Then the welding of formal blade and sticking patch to be repaired is carried out.The type face of its further groove is corresponding with the upper and lower surface of blade, full coverage type and half mulching formula groove can be used, form the curved welding seam of a uniform thickness, the invention enables the welding procedure simplification for forming welding point, it can prevent front and rear edge from generating defect and deformation, in addition joint form is suitable for other fusion welding methods, such as argon arc welding, plasma weldering, Laser Welding, rehabilitation cost can be substantially reduced, joint quality and stability are improved.
Description
Technical field
The present invention relates to a kind of patching type restorative procedures, belong to welding technology field.
Background technology
Fan and compressor are the critical components of aviation turbojet engine, and main function is to improve to be used as engine
The pressure of the air of working media, wherein rotor blade are high-speed rotating dynamic component, quantity is more, body is thin, situation is harsh,
Working environment is complicated, one of highest parts of failure rate in making it use and test as engine always.To the leaf of damage
Piece reuses after being repaired, and can reduce engine life-cycle use cost.Especially used now with current blisk
The increase of demand, it is more urgent to the reparation demand of rotor blade, this is because blisk is integral structure so that damage
Blade is not easy to replace, therefore is necessarily required to corresponding recovery technique to reduce use cost.
Blade patching type reparation refers to using a piece of new local blade in fusion welding method repair welding by after lesion removal（It mends
Piece）, using processes such as subsequent processing, restore the use function of blade.This restorative procedure can meet most of foreign object damage
Hinder the needs repaired, is one of highest welding repair method of utilization rate.
Due to blade profile complexity, blade sectional thickness difference, the shape after excision damage are also irregular, on the other hand,
Sticking patch will meet following process requirement in design there are surplus, and the connector that Varying-thickness curved surface and thin and thick are arranged in pairs or groups makes subsequent molten
Welding is also more complex.
Blade profile after excision damage is very thin in front and rear edge, only a few tenths of a mm.Initial welding method, sticking patch are adopted
It is docked with blade with uniform thickness tablet, weld seam thickness of two sides difference is very big at front and rear edge, easily occurs burn-through, deformation in welding
The problems such as.This mode is improved in SNECMA patents, sticking patch thickness is become changing with vane thickness, and compares blade
Slightly thick, this method needs to change welding parameter with throat thickness in the welding process, and every section of weld seam, technique need to accurately be arranged
Process is more complex, more demanding to welding process, and standardization is difficult to complete.
Due to sticking patch than the two sides of prophyll piece it is thick go out it is a certain amount of, to meet the requirement of following process, material is thus formed
The weld seam front joint form low when height, this joint form are relatively suitble to use electron beam welding, and other methods are such as
Arc-welding, Laser Welding may be decreased welding quality it is not recommended that this connector, but electron beam welding cost is higher and need to be into vacuum chamber
Welding brings many limitations, therefore can be further improved from the aspect of flexible and cost.
Invention content
For above-mentioned repair process complex process, cost is higher the problems such as, the present invention proposes a kind of engine blade sticking patch
Formula restorative procedure, by designing special sticking patch geometry, in conjunction with corresponding technological measure so that form the weldering of welding point
Technique simplification is connect, can prevent front and rear edge from generating defect and deformation, in addition joint form is suitable for other fusion welding methods, such as argon arc
Weldering, plasma weldering, Laser Welding etc. can substantially reduce rehabilitation cost, improve joint quality and stability.
In order to realize the present invention, following technical solution is used：
A kind of engine blade patching type restorative procedure, this method specifically comprise the following steps：
The first step, the position knot occurred according to damage along linear ablation damage, excision position with rear from blade tip to blade inlet edge
The stress synthesis of hing straps is selected, and same position may include multiple damages；
Second step, the design that sticking patch is carried out according to the cross sectional shape of the blade after excision process a groove in sticking patch section；
Third step, the backing plate and pressing plate that welding tooling is designed according to the shape of sticking patch, the backing plate of welding tooling is by blade and sticking patch
It holds up, the position while welding back side provides protection gas, prevents from aoxidizing, and pressing plate compresses the front of blade and sticking patch；
4th step, when carrying out the manufacture of sticking patch and welding tooling, the synchronous processing for carrying out partial simulation blade and same position
The lesion removal of the blade of damage;
5th step marks position while welding according to sticking patch depth of groove in sticking patch upper surface, and partial simulation blade is packed into welded gasket
Plate, sticking patch are inserted in vane end faces, and progress parameter soldering test is compressed after assembling good position；
6th step, after staying in and obtaining satisfied welding parameter on partial simulation blade, by engine blade and sticking patch to be repaired
It is packed into welding tooling, REPAIR WELDING is carried out according to the welding parameter of partial simulation blade；
Processing is restored in carry out type face after the completion of 7th step, welding, completes to repair.
In a preferred technical solution, the upper and lower surface in the type face and blade to be repaired of the groove in the second step
Corresponding, the upper mo(u)ld bottom half face of groove covers the upper and lower surface of blade to be repaired, and blade to be repaired is inserted into sticking patch groove, shape before welding
At the weld seam of a uniform thickness, sticking patch thickens compensation to blade joint, and than weld seam, slightly long sticking patch covers blade and cuts
Face two-end-point.
In a preferred technical solution, the groove in the second step is the form of single side groove, when welding
Position is distinguished up and down, and the mo(u)ld bottom half face of commissure sticking patch has more 0.1~0.3mm than blade mo(u)ld bottom half to be repaired face, but does not cover to be repaired
Compound leaf piece mo(u)ld bottom half face, sticking patch mo(u)ld top half face is parallel with mo(u)ld bottom half face, covers blade mo(u)ld top half to be repaired face, forms the curve weldering of a uniform thickness
Seam, only has the compensation that there is thickness in mo(u)ld top half face, mo(u)ld bottom half face is uncompensated when using single side groove.
In a preferred technical solution, the sticking patch welding ends is the case where meeting surplus and containing blade to be repaired
Under it is thin as possible, weld seam distalmost end section transitions be rectangle, thickness is thicker than welded section, depth of groove be no more than 5mm,
It will process more shallow about 3mm than both ends in the middle part of weld seam.
In a preferred technical solution, the groove is processed together with recombinant respectively with sticking patch, the processing of groove
Method is mechanical processing or electric machining.
In a preferred technical solution, when carrying out backing plate and platen design in third step, can not exclusively according to
Prototype face is processed, but blade and sticking patch are carried out predeformation to negative direction, it is made to generate certain deflection in advance, with
Eliminate the deformation of welding process.
The technique effect of the present invention is as follows：
（1）It is designed by sticking patch, blade is inserted into suitable sticking patch groove, thickening is compensated to the thickness of commissure blade,
Make whole weld seam uniform thickness, realized using same parameters and repair welding, simplify the process of blade surgical repair, reduces repair process behaviour
The levels of precision of work improves and repairs success rate and repairing quality, while restorative procedure is extended to argon arc welding, plasma weldering, is swashed
The other methods such as flush weld, further reduce costs；
（2）The backing plate and pressing plate of welding tooling are designed processing in view of welding deformation amount, and welding deformation is reduced to minimum,
Improve the precision after blade is repaired.
Figure of description
Fig. 1 surgical repair assembling schematic diagrams；
Fig. 2 surgical repair joint form schematic diagrames；
The upper mo(u)ld bottom half face of Fig. 3 grooves covers the sticking patch schematic diagram of the upper and lower surface of blade to be repaired；
The mo(u)ld bottom half face of Fig. 4 grooves does not cover the sticking patch schematic diagram of the lower surface of blade to be repaired.
In figure, 1- blades, 2- sticking patch, 3- weld seams, 4- missing blades profiles, 5- grooves.
Specific implementation mode
The engine blade patching type restorative procedure of the present invention includes the following steps：
（1）Front/rear edge is damaged along linear ablation from blade tip to blade, which combines blade according to the position that damage occurs
Stress synthesis selected, same position may include multiple damages, be conducive to the standardization reparation for carrying out multiple blades.
（2）The design that sticking patch is carried out according to cross sectional shape processes a groove in sticking patch section, and depth of groove is no more than
The type face of 5mm, groove are corresponding with the upper and lower surface of blade, and blade to be repaired is inserted into sticking patch groove before welding, form one etc.
Thick weld seam, sticking patch thicken compensation to blade joint, and than weld seam, slightly long sticking patch covers blade section two-end-point.
It is welded using same welding parameter, when welding is not easy to slim vane burn-through, and positive compensation block functions simultaneously as welding
Filler makes it that will not generate undercut in the case that not filling silk, and simplifies arc welding gun head.Sticking patch blocks leaf at blade tip and front/rear edge
Piece plays the role of positioning.Sticking patch welding ends is thin as possible in the case where meeting surplus and containing missing blades, to reduce welding
When heat input, and the section of weld seam distalmost end can with transition be simple rectangle, thickness can be thicker than welded section,
Play the role of increasing sticking patch rigidly reduction sticking patch deformation.
Since blade profile is hyperboloid, for convenience of processing, depth of groove too deep should not be usually no more than 5mm, while by weld seam
Middle part processes more shallow about 3mm than both ends.Mechanical processing or electric processing method processing can be used in groove, also can be by groove and sticking patch
The mode of processing recombinant together respectively.
For single side groove, pose when welding is distinguished up and down, and the mo(u)ld bottom half face of commissure sticking patch is more than blade mo(u)ld bottom half face
Go out 0.1~0.3mm, but do not cover blade, sticking patch mo(u)ld top half face is parallel with mo(u)ld bottom half face, and covering blade forms the curve weldering of a uniform thickness
Seam.The method only has and has the compensation of thickness above, below it is uncompensated.Thickness backwards face transition of the sticking patch below weld seam is more
Thickness, the method is easier to be machined and realize, and the throat depth formed is minimum.Back of weld does not have surplus, but postwelding is welding
The back side is stitched due to naturally forming reinforcement so that sealing run can meet follow-up recovery in the case where both sides are equal and add
The needs of work.At front and rear edge, the weld seam of blade is located at below entire weld seam, and heat input is also upper small.
（4）According to the shape of sticking patch, the backing plate of welding tooling is designed, the backing plate of welding tooling holds up blade and sticking patch,
The position while welding back side provides protection gas, prevents from aoxidizing.Front pressing plate compresses blade and sticking patch.Due to being possible to meeting when welding
It deforms, it is causing blade to generate micro torsional deflection to weld seam front, therefore the backing plate of tooling and pressing plate exist to lead to sticking patch
It when design, can be not exclusively processed according to prototype face, but blade and sticking patch are subjected to predeformation to negative direction, make it in advance
Certain deflection is generated, the deformation of welding process can be eliminated.
（5）When carrying out the manufacture of sticking patch and welding tooling, the synchronous processing for carrying out partial simulation blade and same position
The lesion removal of the blade of damage.All after the completion of work, the REPAIR WELDING of engine blade can be carried out.
（6）According to sticking patch depth of groove position while welding is marked in sticking patch upper surface.Partial simulation blade is packed into welded gasket
Plate, sticking patch are inserted in vane end faces, compress progress parameter soldering test after assembling good position, are realized and welded using same welding parameter
It connects.It is easy to operate without especially accurately carrying out centering since sticking patch itself is with positioning.It itself has carried and has received arc plate, will easily go out
The rising of existing defect is received an arc position and is drawn, and with blade tip and front/rear edge intersection non-notch, be less prone to defect.
（7）Stay in after obtaining satisfied welding parameter on partial simulation blade, by formal engine blade to be repaired and
Sticking patch be packed into specific welding assambly, weld seam be blade be inserted into sticking patch uniform thickness weld seam, according to simulation blade test parameters into
The actual REPAIR WELDING of row.Weld seam is shorter when due to melting welding surgical repair, and in the case that tooling is fixed well, deformable blade amount is very
It is small, blade and sticking patch are subjected to a small amount of reversible deformation and do not interfere with the total type face of blade and performance, but can be by final result
It controls more preferably, ensures the high-precision for repairing rear profile face.
To tenon head type blade, after being soldered a piece of blade, dismounting is packed into next blade and is directly welded using original program,
Welding parameter and path are constant, facilitate realization is automatic to repair.Reparation to blisk, after a blade is completed in welding,
It rotates by a certain angle, next reparation can be carried out, original program or fine tuning can be used in the program of welding gun, and the degree of automation is higher.
（8）After completing welding, then carries out type face and restore other technological processes completion blade reparations such as processing.
Specific implementation mode is as shown in embodiment 1 and embodiment 2.
Embodiment 1
Certain blisk multiple blade inlet edge leaves angle is damaged, and it includes maximum damage to select unified excision position, along blade tip
After being damaged to leading edge linear ablation, sticking patch design is carried out, forms single side groove.Welding tooling, type face tolerance are processed according to type face
It is processed by -0.3mm, blade and sticking patch is assembled on welding tooling, is welded using arc welding method.Use welding robot pair
Welding track carries out teaching, carries out reparation welding later.Postwelding sheds tooling, has the gap of very little between sticking patch and tooling, around here
Gap amount is suitable with predeformation amount.The defects of carrying out X-ray detection, there are no any stomata is welded to repairing.
Embodiment 2
Certain trailing edge is slipped up due to processing generates damage, after blade tip to rear linear ablation damages, carries out sticking patch design, cuts
Face curvature is larger, using arc panel form, reduces throat thickness.Welding tooling is processed according to type face tolerance -0.2mm, is being welded
After assembling blade and sticking patch in tooling, teaching is carried out to welding track using welding robot, is carried out using unified welding parameter
Welding.
Claims (6)
1. a kind of engine blade patching type restorative procedure, which is characterized in that this method specifically comprises the following steps：
The first step, the position knot occurred according to damage along linear ablation damage, excision position with rear from blade tip to blade inlet edge
The stress synthesis of hing straps is selected, and same position may include multiple damages；
Second step, the design that sticking patch is carried out according to the cross sectional shape of the blade after excision process a groove in sticking patch section；
Third step, the backing plate and pressing plate that welding tooling is designed according to the shape of sticking patch, the backing plate of welding tooling is by blade and sticking patch
It holds up, the position while welding back side provides protection gas, prevents from aoxidizing, and pressing plate compresses the front of blade and sticking patch；
4th step, when carrying out the manufacture of sticking patch and welding tooling, the synchronous processing for carrying out partial simulation blade and same position
The lesion removal of the blade of damage;
5th step marks position while welding according to sticking patch depth of groove in sticking patch upper surface, and partial simulation blade is packed into welded gasket
Plate, sticking patch are inserted in vane end faces, and progress parameter soldering test is compressed after assembling good position；
6th step, after staying in and obtaining satisfied welding parameter on partial simulation blade, by engine blade and sticking patch to be repaired
It is packed into welding tooling, REPAIR WELDING is carried out according to the welding parameter of partial simulation blade；
Processing is restored in carry out type face after the completion of 7th step, welding, completes to repair.
2. engine blade patching type restorative procedure according to claim 1, which is characterized in that recessed in the second step
The type face of slot is corresponding with the upper and lower surface of blade to be repaired, and the upper mo(u)ld bottom half face of groove covers the upper and lower surface of blade to be repaired, weldering
Blade to be repaired is inserted into sticking patch groove before connecing, forms the weld seam of a uniform thickness, sticking patch has blade joint in the work for thickening compensation
With than weld seam, slightly long sticking patch covers blade section two-end-point.
3. engine blade patching type restorative procedure according to claim 1, which is characterized in that recessed in the second step
Slot is the form of single side groove, and position when welding is distinguished up and down, and the mo(u)ld bottom half face of commissure sticking patch is than blade mo(u)ld bottom half to be repaired
Face has more 0.1~0.3mm, but does not cover blade mo(u)ld bottom half to be repaired face, and sticking patch mo(u)ld top half face is parallel with mo(u)ld bottom half face, covers compound leaf to be repaired
Piece mo(u)ld top half face forms the curved welding seam of a uniform thickness, there was only the compensation that there is thickness in mo(u)ld top half face when using single side groove, mo(u)ld bottom half face without
Compensation.
4. engine blade patching type restorative procedure according to any one of claims 1 to 3, which is characterized in that the benefit
Piece welding ends is thin as possible in the case where meeting surplus and containing blade to be repaired, is rectangular in the section transitions of weld seam distalmost end
Shape, thickness is thicker than welded section, and depth of groove is no more than 5mm, will process more shallow about 3mm than both ends in the middle part of weld seam.
5. engine blade patching type restorative procedure according to any one of claims 1 to 3, which is characterized in that described recessed
Slot is processed together with recombinant respectively with sticking patch, and the processing method of groove is mechanical processing or electric machining.
6. engine blade patching type restorative procedure according to any one of claims 1 to 3, which is characterized in that described
Backing plate is carried out in three steps and when platen design, can be not exclusively processed according to prototype face, but by blade and sticking patch to negative side
To predeformation is carried out, it is set to generate certain deflection in advance, to eliminate the deformation of welding process.
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109175881A (en) * | 2018-09-28 | 2019-01-11 | 中国人民解放军第五七九工厂 | A kind of vacuum brazing method of aero-turbine stator blade surgical repair |
| CN109500496A (en) * | 2018-11-23 | 2019-03-22 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of aero-engine titanium alloy blade injure after repair method |
| CN110052777A (en) * | 2018-09-30 | 2019-07-26 | 上海吴泾电力工程有限责任公司 | Suitable for cheating the field repairing method of cavity space |
| CN110853439A (en) * | 2018-08-20 | 2020-02-28 | 联合工艺公司 | Fan blade renovation training device |
| CN110936101A (en) * | 2019-11-26 | 2020-03-31 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for restoring dimension of blade tip or blade shroud of turbine blade |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4822248A (en) * | 1987-04-15 | 1989-04-18 | Metallurgical Industries, Inc. | Rebuilt shrouded turbine blade and method of rebuilding the same |
| JP2002361523A (en) * | 2001-06-11 | 2002-12-18 | Mitsubishi Heavy Ind Ltd | Method for repairing plate-like body having flow passage inside thereof |
| CN1684790A (en) * | 2002-09-30 | 2005-10-19 | 焊接研究院 | Workpiece structure modification |
| CN1903494A (en) * | 2005-07-29 | 2007-01-31 | 斯奈克玛 | Method for repairing a blade of a one-piece bladed disc of aturbine engine and a test piece for implementing the method |
| CN101092012A (en) * | 2006-06-19 | 2007-12-26 | 斯奈克玛 | Part-holding device |
| CN101108453A (en) * | 2006-07-18 | 2008-01-23 | 联合工艺公司 | Process for repairing turbine engine components |
| CN205129170U (en) * | 2015-10-26 | 2016-04-06 | 西安航空动力股份有限公司 | Back of weld that prevents to polish makes electron -beam welding joint of wall thickness reduction |
| CN107511567A (en) * | 2017-08-10 | 2017-12-26 | 燕山大学 | A kind of welding plate stamping and forming end socket welding heat affected zone wall thickness control method |
-
2017
- 2017-01-04 CN CN201710003786.6A patent/CN108372387A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4822248A (en) * | 1987-04-15 | 1989-04-18 | Metallurgical Industries, Inc. | Rebuilt shrouded turbine blade and method of rebuilding the same |
| JP2002361523A (en) * | 2001-06-11 | 2002-12-18 | Mitsubishi Heavy Ind Ltd | Method for repairing plate-like body having flow passage inside thereof |
| CN1684790A (en) * | 2002-09-30 | 2005-10-19 | 焊接研究院 | Workpiece structure modification |
| CN1903494A (en) * | 2005-07-29 | 2007-01-31 | 斯奈克玛 | Method for repairing a blade of a one-piece bladed disc of aturbine engine and a test piece for implementing the method |
| CN101092012A (en) * | 2006-06-19 | 2007-12-26 | 斯奈克玛 | Part-holding device |
| CN101108453A (en) * | 2006-07-18 | 2008-01-23 | 联合工艺公司 | Process for repairing turbine engine components |
| CN205129170U (en) * | 2015-10-26 | 2016-04-06 | 西安航空动力股份有限公司 | Back of weld that prevents to polish makes electron -beam welding joint of wall thickness reduction |
| CN107511567A (en) * | 2017-08-10 | 2017-12-26 | 燕山大学 | A kind of welding plate stamping and forming end socket welding heat affected zone wall thickness control method |
Non-Patent Citations (1)
| Title |
|---|
| 李淑华: "《典型难焊接材料焊接技术》", 31 March 2015 * |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
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