CN104493431B - A kind of method of aircraft fold mechanism stress corrosion resistant - Google Patents
A kind of method of aircraft fold mechanism stress corrosion resistant Download PDFInfo
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- CN104493431B CN104493431B CN201410664223.8A CN201410664223A CN104493431B CN 104493431 B CN104493431 B CN 104493431B CN 201410664223 A CN201410664223 A CN 201410664223A CN 104493431 B CN104493431 B CN 104493431B
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- welding
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- fold mechanism
- stress corrosion
- corrosion resistant
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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
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
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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
- 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)
- Welding Or Cutting Using Electron Beams (AREA)
Abstract
The invention belongs to aeronautic structure designing technique, is related to a kind of method of aircraft fold mechanism stress corrosion resistant.The method includes：Step 1, part select the manufacture of TA15 titanium alloy forgings, and the grain direction of forging is consistent with the primary load bearing direction of part；Step 2, using electron beam welding and matched post weld heat treatment technique, reduces the welding deformation of web structure, so as to reduce residualinternal stress；Edge strip and web surfaces externally and internally weld reinforcement up and down are removed after step 3 welding and is polishing to Ra1.6；Step 4, overall sand blasted surface processing is carried out after Finishing Parts Machining.
Description
Technical field
The invention belongs to aeronautic structure designing technique, is related to a kind of method of aircraft fold mechanism stress corrosion resistant.
Background technology
Fold mechanism is the important mechanism of aircraft, can change aircraft form by fold mechanism, and realizing improves pneumatic increase
Ascending effect, reduction aircraft park the effect such as area occupied.It is required that fold mechanism component part have high stretching, fatigue behaviour and
Stress corrosion performance.The material of selection is mainly strength titanium alloy in TA15, which has good stretching and fatigue behaviour, but
Al content limit on the upper side in alloy, adds the potential danger of stress corrosion.Therefore, fold mechanism is needed using stress corrosion resistant
Manufacture method.
The content of the invention
The technical problems to be solved by the invention are：For problem present in above-mentioned background technology, a kind of aircraft is proposed
The method of fold mechanism stress corrosion resistant.
The technical scheme is that：A kind of method of aircraft fold mechanism stress corrosion resistant, it is characterized in that the method
Comprise the steps of：
Step 1, part select the manufacture of TA15 titanium alloy forgings, the grain direction of forging and the primary load bearing direction one of part
Cause；
Step 2, using electron beam welding and matched post weld heat treatment technique, reduces the welding deformation of web structure, from
And residualinternal stress is reduced, welding parameter is shown in Table 1；
1 electro-beam welding process parameter of table
Edge strip and web surfaces externally and internally weld reinforcement up and down are removed after step 3 welding and is polishing to Ra1.6；
Step 4, overall sand blasted surface processing is carried out after Finishing Parts Machining：Corundum granularity：F90 (159 mesh), F60 (102
Mesh), F54 (60 mesh~9 mesh), 0.4~0.5MPa of air pressure, jet hole to being reinforced surface 80~120mm of spacing, nozzle with
By 70 °~90 ° of the inclination angle on spray surface.
The beneficial effects of the present invention are：Using the aircraft foldable structure Static Strength of Mechanical Parts and fatigue behaviour of the method design
It is satisfied by requiring, while there is excellent anti-stress corrosion performance.
Brief description of the drawings
Fig. 1 is part schematic diagram in the present invention.
Embodiment
1 the present invention will be further described below in conjunction with the accompanying drawings.
A kind of method of aircraft fold mechanism stress corrosion resistant of the present invention comprises the following steps：
Step 1, part select strong, high fatigue property and the manufacture of the TA15 titanium alloy forgings of improved corrosion performance, forging in tool
The grain direction of part is consistent with the primary load bearing direction of part.
Welding point, is processed smooth, bright and clean impulse- free robustness by step 2, and keeps corner angle, the scope away from welding point 20mm
Nipple surface roughness is not more than Ra3.2, and thickness to be welded is respectively 3.0 ± 0.1mm and 3.5 ± 0.1mm；Between guarantee weld seam
Gap is not more than 0.1mm, local (overall length：10% or 100mm of fusion length takes its small value) maximal clearance is not more than 0.2mm, and it is wrong
Position amount is not more than 0.2mm.
Argon arc welding positioning run-on tab and receipts arc plate by hand.The position of welding gun is adjusted, makes the cross hairs center of electron gun complete
Full alignment welding point, it is desirable to which the distance of electron gun prosopyle and weld seam keeps 190 ± 0.5mm.Welding booth gate is closed, starts to take out
Vacuum, vacuum chamber pressure are not more than 7.0 × 10- 4mbar。
Positioned using electron beam welding.Positioning welding program is called, split fix welding, first weld seam are carried out to weld seam
Tack welding electric current uses 5mA, and Article 2 tack welding electric current uses 8mA.During tack welding, one end tack welding first in weld seam
50mm, then split fix is welded since the other end is with larger line, welds 50mm, is spaced 50mm.
After tack welding is completed, electron gun is moved to weld seam initial position of the tack welding electric current using 5mA, is called formal
Welding procedure, formally welds first weld seam；Then electron gun is moved to tack welding electric current to rise using the weld seam of 8mA
Beginning position, call formal welding procedure, Article 2 weld seam formally welded.
Welding condition is shown in Table 2, table 3.
The welding parameter of electron beam of 2 web of table and edge strip
3 web of table, edge strip and the welding parameter of electron beam of termination side
Step 3, removes edge strip and web surfaces externally and internally weld reinforcement up and down and is polishing to Ra1.6 after welding.
Step 4, overall sand blasted surface processing is carried out after Finishing Parts Machining.Corundum granularity：F90 (159 mesh), air pressure
0.4MPa, jet hole is to being reinforced surface spacing 80mm, nozzle and 90 ° of the inclination angle by spray surface.
Claims (1)
- A kind of 1. method of aircraft fold mechanism stress corrosion resistant, it is characterized in that the method comprises the steps of：Step 1, part select the manufacture of TA15 titanium alloy forgings, and the grain direction of forging is consistent with the primary load bearing direction of part；Step 2, using electron beam welding and matched post weld heat treatment technique, reduces the welding deformation of web structure, so as to drop Low residualinternal stress, welding parameter see the table below；Edge strip and web surfaces externally and internally weld reinforcement up and down are removed after step 3 welding and is polishing to Ra1.6；Step 4, overall sand blasted surface processing is carried out after Finishing Parts Machining：Corundum granularity：F90 (159 mesh), F60 (102 mesh), F54 (60 mesh~9 mesh), 0.4~0.5MPa of air pressure, jet hole is to surface 80~120mm of spacing is reinforced, and nozzle is with being sprayed 70 °~90 ° of the inclination angle on surface；Wherein, joint surface roughness is not more than Ra3.2, and electron beam welding in the range of step 2 middle-range welding point 20mm Split fix welding is carried out to weld seam, first weld and HAZ weldering electric current uses 5mA, and Article 2 tack welding electric current uses 8mA.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410664223.8A CN104493431B (en) | 2014-11-19 | 2014-11-19 | A kind of method of aircraft fold mechanism stress corrosion resistant |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410664223.8A CN104493431B (en) | 2014-11-19 | 2014-11-19 | A kind of method of aircraft fold mechanism stress corrosion resistant |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104493431A CN104493431A (en) | 2015-04-08 |
| CN104493431B true CN104493431B (en) | 2018-04-13 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410664223.8A Active CN104493431B (en) | 2014-11-19 | 2014-11-19 | A kind of method of aircraft fold mechanism stress corrosion resistant |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106442285A (en) * | 2016-09-07 | 2017-02-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Corrosion testing method for anti-corrosion protection capability of exposed part of lower surface of aircraft |
| CN106124395A (en) * | 2016-09-07 | 2016-11-16 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of corrosion tests |
| CN108098255B (en) * | 2017-11-30 | 2019-09-13 | 江西洪都航空工业集团有限责任公司 | A kind of TA15 titanium alloy frame class parts machining process |
Citations (6)
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| EP0616043A1 (en) * | 1993-03-18 | 1994-09-21 | Hitachi, Ltd. | Austenic steel for structural members having superior resistance to neutron irradiation embrittlement, and use of the steel in nuclear reactors |
| CN1729077A (en) * | 2001-11-02 | 2006-02-01 | 波音公司 | Apparatus and method for forming weld joints having compressive residual stress patterns |
| CN1762636A (en) * | 2004-10-22 | 2006-04-26 | 沈阳黎明航空发动机(集团)有限责任公司 | Vacuum electron beam welding method for thin-walled titanium alloy assembly |
| CN101913022A (en) * | 2010-09-10 | 2010-12-15 | 哈尔滨工业大学 | Method for welding dissimilar materials of TA15 titanium alloy and chromium bronze through electron beams |
| CN102953023A (en) * | 2011-08-29 | 2013-03-06 | 中国石油化工股份有限公司 | Surface treatment process of titanium alloy welded joint |
| CN104057198A (en) * | 2014-06-19 | 2014-09-24 | 哈尔滨东安发动机（集团）有限公司 | Vacuum electronic beam welding method for titanium-alloy rotor component |
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2014
- 2014-11-19 CN CN201410664223.8A patent/CN104493431B/en active Active
Patent Citations (6)
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|---|---|---|---|---|
| EP0616043A1 (en) * | 1993-03-18 | 1994-09-21 | Hitachi, Ltd. | Austenic steel for structural members having superior resistance to neutron irradiation embrittlement, and use of the steel in nuclear reactors |
| CN1729077A (en) * | 2001-11-02 | 2006-02-01 | 波音公司 | Apparatus and method for forming weld joints having compressive residual stress patterns |
| CN1762636A (en) * | 2004-10-22 | 2006-04-26 | 沈阳黎明航空发动机(集团)有限责任公司 | Vacuum electron beam welding method for thin-walled titanium alloy assembly |
| CN101913022A (en) * | 2010-09-10 | 2010-12-15 | 哈尔滨工业大学 | Method for welding dissimilar materials of TA15 titanium alloy and chromium bronze through electron beams |
| CN102953023A (en) * | 2011-08-29 | 2013-03-06 | 中国石油化工股份有限公司 | Surface treatment process of titanium alloy welded joint |
| CN104057198A (en) * | 2014-06-19 | 2014-09-24 | 哈尔滨东安发动机（集团）有限公司 | Vacuum electronic beam welding method for titanium-alloy rotor component |
Non-Patent Citations (2)
| Title |
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| TA15合金及其在飞机结构中的应用前景;李兴无等;《钛工业进展》;20031030;第20卷(第4-5期);第90页-第94页 * |
| TA15板与电子束焊接疲劳特性研究;王向明等;《北京航空航天大学学报》;20031030;第29卷(第9期);第807页-第811页 * |
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| CN104493431A (en) | 2015-04-08 |
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