CN104475959A - Aero-engine stator assembly vacuum electron beam welding technology - Google Patents
Aero-engine stator assembly vacuum electron beam welding technology Download PDFInfo
- Publication number
- CN104475959A CN104475959A CN201410589405.3A CN201410589405A CN104475959A CN 104475959 A CN104475959 A CN 104475959A CN 201410589405 A CN201410589405 A CN 201410589405A CN 104475959 A CN104475959 A CN 104475959A
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- welding
- stator assembly
- aero
- electron beam
- weld seam
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K15/00—Electron-beam welding or cutting
- B23K15/04—Electron-beam welding or cutting for welding annular seams
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K15/00—Electron-beam welding or cutting
- B23K15/0033—Preliminary treatment
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Welding Or Cutting Using Electron Beams (AREA)
- Laser Beam Processing (AREA)
- Butt Welding And Welding Of Specific Article (AREA)
- Manufacture Of Motors, Generators (AREA)
Abstract
The invention discloses an aero-engine stator assembly vacuum electron beam welding technology and belongs to the technical field of aero-engine part manufacturing. Formerly, an aero-engine stator assembly is welded through a brazing method, the brazing intensity is lower than the base metal intensity, the stator assembly performance stability is directly influenced, and a traditional welding method is excessively large in welding deformation. Compared with the prior art, after a large amount of soldering tests, the aero-engine stator assembly vacuum electron beam welding technology has the advantages that welding of the aero-engine stator assembly can be completely satisfied, brand new welding parameters are provided, the welding parameters are obtained after a large amount of welding parameter tests, welding of different thickness weld joints can be satisfied maximally, and thermal input is guaranteed uniform, the welding deformation is effectively controlled, and the requirement for stable postwelding performance of the stator assembly is satisfied due to sequence welding of the two weld joints at symmetrical positions.
Description
Technical field
The invention belongs to technical field of aircraft engine part manufacture, particularly relate to a kind of aero-engine stator assembly vacuum electron beam welding process.
Background technology
In the past, aero-engine stator assembly adopts the method for soldering to weld, the intensity of brazed seam will lower than the intensity of mother metal, this can directly affect stator assembly property stability, and adopts traditional fusion welding method to weld, and can there is again the excessive problem of welding deformation, in order to stator assembly postwelding stability can be realized, avoid the problem that welding deformation is excessive again, person skilled attempts adopting existing vacuum electron beam welding process, wants to meet the welding to stator assembly.
But, existing vacuum electron beam welding process the part that is suitable for be aero-engine inlet casing, and inlet casing is compared with stator assembly, and the weld seam quantity of inlet casing is few, and weld seam density also will well below stator assembly; The blade of inlet casing is away from weld seam, and the blade of stator assembly is close to weld seam; Compared with stator assembly, the welding protection difficulty of inlet casing is low; From welding line structure, inlet casing is equal thickness welding, and stator assembly is not equal thickness welding; Require for deflection, inlet casing also will lower than stator assembly to the requirement of deflection.
After trial adopts existing vacuum electron beam welding process to carry out welding processing to stator assembly, find that the method still cannot meet the processing request of stator assembly for postwelding stability, welding deformation.
Summary of the invention
For prior art Problems existing, the invention provides a kind of aero-engine stator assembly vacuum electron beam welding process, the requirement of stator assembly postwelding stability can be met, effectively can solve stator components welding and be out of shape excessive problem.
To achieve these goals, the present invention adopts following technical scheme: a kind of aero-engine stator assembly vacuum electron beam welding process, comprises the steps:
Step one: before weldering, distortion allowance selection is carried out to stator component part
The axis of mounting edge appearance time 1. in order to reduce to weld and radial deformation, improve mounting edge rigidity, leaves 2mm surplus respectively in mounting edge axis and radial direction;
2. because stator assembly is welds with different thickness, ensureing smooth welded seam degree to reduce thickness difference, leave 1.5mm surplus thick section of weld seam, and between thick section to light filling bar, employing seamlessly transitting structure;
Step 2: in first 120 hours of weldering, carry out pickling to stator component part, removes the oxide layer of piece surface;
Step 3: tool locating is carried out to stator component part
1. in the root of blade position of stator component part, blade protection baffle plate is installed;
2. the locating piece after utilizing oil removing to clean positions assembling to stator component part, and orientation assemble gap is less than or equal to 0.1mm;
Step 4: the stator component part after being completed by orientation assemble and positioning tool thereof are together lifted on the floral disc of electron beam welding, and utilize pressing plate to be fixed, the gap of positioning tool and floral disc is less than or equal to 0.1mm, adjust the angle of stator component part again, ensure that weld interface is parallel with electronic beam current;
Step 5: input welding instruction in vacuum electron beam welder, welding instruction takes relative coordinate to programme, and runs welding instruction, and adopts the small area analysis of 0.1mA to scan, and ensures that electronic beam current aims at weld seam, and checking welding instruction is accurate;
Step 6 a: first weld seam is welded, its welding process is divided into formal weldering and modifies weldering, when formally welding, its welding parameter is: accelerating potential is 150kV, and focus current is surperficial focus, welding line is 7mA, speed of welding is 10mm/s, and sweep waveform is circle ripple, and scan frequency is 50Hz, scan amplitude is 0.5mm, and during welding, the pressure of vacuum chamber is less than or equal to 4 × 10
-4mbar; When carrying out modification weldering, its welding parameter is: accelerating potential is 150kV, and focus current is upper focus, welding line is 1.8mA, and speed of welding is 8mm/s, and sweep waveform is triangular wave, scan frequency is 20Hz, and scan amplitude is 1mm, and during welding, the pressure of vacuum chamber is less than or equal to 4 × 10
-4mbar;
Step 7: after completing the welding of an above-mentioned weld seam, opens vacuum chamber and checks weldquality, after qualified, carry out the welding of other weld seam; Because all weld seams are in circumference distribution, according to weld seam quantity, two weld seams choosing circumferentially symmetric position carry out order welding, the like, complete the welding of residue symmetric position weld seam.
The weld seam overall length of stator assembly is little, receives arc distance from short, adopts segmentation to receive arc, the high-energy section of decay is lengthened, low-yield decay section shortened, and can solve short distance welding and receive arc and to subside problem.
Described blade protection baffle plate is bayonet type structure; be divided into left and right two panels; profile is fastened identical with the blade profile of blade joint place between two panels; during blade protection baffle plate original state; its one end is connected and fixed by iron wire; the other end is opening-like; by its opening part, blade protection baffle plate is fitted to blade surface; be connected and fixed with the openend of iron wire by blade protection baffle plate again; finally by iron clamp, blade protection baffle plate is fixed on blade, prevents welding process Leaf from protecting baffle plate to be subjected to displacement.
Beneficial effect of the present invention:
The present invention compared with prior art, through a large amount of soldering tests, a kind of brand-new vacuum electron beam welding process is provided, the welding of aero-engine stator assembly can be met completely, additionally provide brand-new welding parameter simultaneously, this welding parameter has also been through a large amount of welding parameter tests and has obtained, at utmost can meet the welding of welds with different thickness, and adopt two weld seams of symmetric position to carry out order welding, ensure heat input evenly, effectively can control welding deformation, meet the requirement of stator assembly postwelding stability.
Accompanying drawing explanation
Fig. 1 is stator modular construction schematic diagram;
Fig. 2 is seam track schematic diagram;
In figure, 1-outer casing, 2-blade, 3-inner ring, 4-weld seam.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, the present invention is described in further detail.
Stator assembly for welding is TC4 titanium alloy material, its weld seam is welds with different thickness, weld seam running orbit is approximate parallelogram, the length of side is 28.2mm × 9.1mm, weld seam is 16 ° relative to the inclination angle of stator assembly central axis, weld seam quantity is 138, and welding machine used is vacuum electron beam welder.
Described a kind of aero-engine stator assembly vacuum electron beam welding process, comprises the steps:
Step one: before weldering, distortion allowance selection is carried out to stator component part
The axis of mounting edge appearance time 1. in order to reduce to weld and radial deformation, improve mounting edge rigidity, leaves 2mm surplus respectively in mounting edge axis and radial direction;
2. because stator assembly is welds with different thickness, ensureing smooth welded seam degree to reduce thickness difference, leave 1.5mm surplus thick section of weld seam, and between thick section to light filling bar, employing seamlessly transitting structure;
Step 2: in first 120 hours of weldering, carry out pickling to stator component part, removes the oxide layer of piece surface;
Step 3: tool locating is carried out to stator component part
1. in the root of blade position of stator component part, blade protection baffle plate is installed;
2. the locating piece after utilizing oil removing to clean positions assembling to stator component part, and orientation assemble gap is less than or equal to 0.1mm;
Step 4: the stator component part after being completed by orientation assemble and positioning tool thereof are together lifted on the floral disc of electron beam welding, and utilize pressing plate to be fixed, the gap of positioning tool and floral disc is less than or equal to 0.1mm, adjust the angle of stator component part again, ensure that weld interface is parallel with electronic beam current;
Step 5: input welding instruction in vacuum electron beam welder, welding instruction takes relative coordinate to programme, and runs welding instruction, and adopts the small area analysis of 0.1mA to scan, and ensures that electronic beam current aims at weld seam, and checking welding instruction is accurate;
Step 6 a: first weld seam is welded, its welding process is divided into formal weldering and modifies weldering, when formally welding, its welding parameter is: accelerating potential is 150kV, and focus current is surperficial focus, welding line is 7mA, speed of welding is 10mm/s, and sweep waveform is circle ripple, and scan frequency is 50Hz, scan amplitude is 0.5mm, and during welding, the pressure of vacuum chamber is less than or equal to 4 × 10
-4mbar; When carrying out modification weldering, its welding parameter is: accelerating potential is 150kV, and focus current is upper focus, welding line is 1.8mA, and speed of welding is 8mm/s, and sweep waveform is triangular wave, scan frequency is 20Hz, and scan amplitude is 1mm, and during welding, the pressure of vacuum chamber is less than or equal to 4 × 10
-4mbar;
Step 7: after completing the welding of an above-mentioned weld seam, opens vacuum chamber and checks weldquality, after qualified, carry out the welding of other weld seam; Because all weld seams are in circumference distribution, according to weld seam quantity, two weld seams choosing circumferentially symmetric position carry out order welding, the like, complete the welding of residue symmetric position weld seam.
The weld seam overall length of stator assembly is little, receives arc distance from short, adopts segmentation to receive arc, the high-energy section of decay is lengthened, low-yield decay section shortened, and can solve short distance welding and receive arc and to subside problem.
Described blade protection baffle plate is bayonet type structure; be divided into left and right two panels; profile is fastened identical with the blade profile of blade joint place between two panels; during blade protection baffle plate original state; its one end is connected and fixed by iron wire; the other end is opening-like; by its opening part, blade protection baffle plate is fitted to blade surface; be connected and fixed with the openend of iron wire by blade protection baffle plate again; finally by iron clamp, blade protection baffle plate is fixed on blade, prevents welding process Leaf from protecting baffle plate to be subjected to displacement.
Scheme in embodiment is also not used to limit scope of patent protection of the present invention, and the equivalence that all the present invention of disengaging do is implemented or changed, and is all contained in the scope of the claims of this case.
Claims (3)
1. an aero-engine stator assembly vacuum electron beam welding process, is characterized in that comprising the steps:
Step one: before weldering, distortion allowance selection is carried out to stator component part
The axis of mounting edge appearance time 1. in order to reduce to weld and radial deformation, improve mounting edge rigidity, leaves 2mm surplus respectively in mounting edge axis and radial direction;
2. because stator assembly is welds with different thickness, ensureing smooth welded seam degree to reduce thickness difference, leave 1.5mm surplus thick section of weld seam, and between thick section to light filling bar, employing seamlessly transitting structure;
Step 2: in first 120 hours of weldering, carry out pickling to stator component part, removes the oxide layer of piece surface;
Step 3: tool locating is carried out to stator component part
1. in the root of blade position of stator component part, blade protection baffle plate is installed;
2. the locating piece after utilizing oil removing to clean positions assembling to stator component part, and orientation assemble gap is less than or equal to 0.1mm;
Step 4: the stator component part after being completed by orientation assemble and positioning tool thereof are together lifted on the floral disc of electron beam welding, and utilize pressing plate to be fixed, the gap of positioning tool and floral disc is less than or equal to 0.1mm, adjust the angle of stator component part again, ensure that weld interface is parallel with electronic beam current;
Step 5: input welding instruction in vacuum electron beam welder, welding instruction takes relative coordinate to programme, and runs welding instruction, and adopts the small area analysis of 0.1mA to scan, and ensures that electronic beam current aims at weld seam, and checking welding instruction is accurate;
Step 6 a: first weld seam is welded, its welding process is divided into formal weldering and modifies weldering, when formally welding, its welding parameter is: accelerating potential is 150kV, and focus current is surperficial focus, welding line is 7mA, speed of welding is 10mm/s, and sweep waveform is circle ripple, and scan frequency is 50Hz, scan amplitude is 0.5mm, and during welding, the pressure of vacuum chamber is less than or equal to 4 × 10
-4mbar; When carrying out modification weldering, its welding parameter is: accelerating potential is 150kV, and focus current is upper focus, welding line is 1.8mA, and speed of welding is 8mm/s, and sweep waveform is triangular wave, scan frequency is 20Hz, and scan amplitude is 1mm, and during welding, the pressure of vacuum chamber is less than or equal to 4 × 10
-4mbar;
Step 7: after completing the welding of an above-mentioned weld seam, opens vacuum chamber and checks weldquality, after qualified, carry out the welding of other weld seam; Because all weld seams are in circumference distribution, according to weld seam quantity, two weld seams choosing circumferentially symmetric position carry out order welding, the like, complete the welding of residue symmetric position weld seam.
2. a kind of aero-engine stator assembly vacuum electron beam welding process according to claim 1, it is characterized in that: the weld seam overall length of stator assembly is little, receive arc distance from short, segmentation is adopted to receive arc, the high-energy section of decay is lengthened, low-yield decay section is shortened, short distance welding can be solved and receive arc and to subside problem.
3. a kind of aero-engine stator assembly vacuum electron beam welding process according to claim 1, it is characterized in that: described blade protection baffle plate is bayonet type structure, be divided into a left side, right two panels, profile is fastened identical with the blade profile of blade joint place between two panels, during blade protection baffle plate original state, its one end is connected and fixed by iron wire, the other end is opening-like, by its opening part, blade protection baffle plate is fitted to blade surface, be connected and fixed with the openend of iron wire by blade protection baffle plate again, finally by iron clamp, blade protection baffle plate is fixed on blade, prevent welding process Leaf from protecting baffle plate to be subjected to displacement.
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105414733A (en) * | 2015-11-25 | 2016-03-23 | 北京航星机器制造有限公司 | Method for welding heterogenous system aluminum alloy through electron beams |
| CN106513972A (en) * | 2016-11-23 | 2017-03-22 | 沈阳黎明航空发动机(集团)有限责任公司 | Vacuum electronic beam welding method of brush sealing ring assemblies |
| CN107160025A (en) * | 2017-05-15 | 2017-09-15 | 中国船舶重工集团公司第七二五研究所 | A kind of thin-wall barrel high energy beam precision welding manufacture method |
| CN108941875A (en) * | 2018-09-05 | 2018-12-07 | 中国航发动力股份有限公司 | A kind of processing method controlling annular Thin-Wall Outer Casing welding deformation amount |
| CN109590595A (en) * | 2018-11-23 | 2019-04-09 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of high inclination-angle electro-beam welding method of inlet casing hollow blade |
| CN112475581A (en) * | 2020-11-18 | 2021-03-12 | 中国兵器科学研究院宁波分院 | Vacuum electron beam welding method for large-size aircraft engine tail cone assembly |
| CN117655573A (en) * | 2024-01-29 | 2024-03-08 | 沈阳长之琳航空制造有限公司 | Welding method for rear section of aero-engine casing |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105414733A (en) * | 2015-11-25 | 2016-03-23 | 北京航星机器制造有限公司 | Method for welding heterogenous system aluminum alloy through electron beams |
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| CN106513972A (en) * | 2016-11-23 | 2017-03-22 | 沈阳黎明航空发动机(集团)有限责任公司 | Vacuum electronic beam welding method of brush sealing ring assemblies |
| CN107160025A (en) * | 2017-05-15 | 2017-09-15 | 中国船舶重工集团公司第七二五研究所 | A kind of thin-wall barrel high energy beam precision welding manufacture method |
| CN108941875A (en) * | 2018-09-05 | 2018-12-07 | 中国航发动力股份有限公司 | A kind of processing method controlling annular Thin-Wall Outer Casing welding deformation amount |
| CN109590595A (en) * | 2018-11-23 | 2019-04-09 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of high inclination-angle electro-beam welding method of inlet casing hollow blade |
| CN109590595B (en) * | 2018-11-23 | 2020-09-25 | 中国航发沈阳黎明航空发动机有限责任公司 | Large-inclination-angle electron beam welding method for hollow blade of air inlet casing |
| CN112475581A (en) * | 2020-11-18 | 2021-03-12 | 中国兵器科学研究院宁波分院 | Vacuum electron beam welding method for large-size aircraft engine tail cone assembly |
| CN112475581B (en) * | 2020-11-18 | 2022-05-20 | 中国兵器科学研究院宁波分院 | Vacuum electron beam welding method for large-size aircraft engine tail cone assembly |
| CN117655573A (en) * | 2024-01-29 | 2024-03-08 | 沈阳长之琳航空制造有限公司 | Welding method for rear section of aero-engine casing |
| CN117655573B (en) * | 2024-01-29 | 2024-05-17 | 沈阳长之琳航空制造有限公司 | Welding method for rear section of aero-engine casing |
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Address after: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee after: Chinese Hangfa Shenyang Liming Aero engine limited liability company Address before: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee before: Liming Aeroplane Engine (Group) Co., Ltd., Shenyang City |