CN1990149A - Welding method of titanium alloy framework and covering variable cross-section element - Google Patents
Welding method of titanium alloy framework and covering variable cross-section element Download PDFInfo
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- CN1990149A CN1990149A CN 200510135350 CN200510135350A CN1990149A CN 1990149 A CN1990149 A CN 1990149A CN 200510135350 CN200510135350 CN 200510135350 CN 200510135350 A CN200510135350 A CN 200510135350A CN 1990149 A CN1990149 A CN 1990149A
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Abstract
A titanium alloy frame and covering variable cross-section components welding methods, it presets the titanium alloy foiling solder between the frame and covering to weld surface, uses thermal expansion assembly equipments or face pressurized thermal expansion assembly equipments clamping, heats the overall unit in vacuum environment to melting solder and covering entire surface welding, completes solder welding connection through diffusing treatment after solidifying, it also provides the structural components of face pressurized thermal expansion assembly equipments which can be used below 950 degree C repeatedly, the equipment structure is simple, woke reliable, cost low and easy to use, maintenance and repairs. And it reveals the innovative composite art parameters of high temperature solder welding and diffusing treatment using FTI high strength titanium alloy solder.
Description
Technical field
The present invention relates to a kind of welding method, refer to adopt the titanium alloy foil-shaped brazing material especially, clamp with profile adding pressure type thermal expansion assembly tooling, whole in a vacuum heating is carried out titanium alloy framework and is connected with covering variable cross-section element is large-area.
Background technology
The member solder technology of variable cross-section still be in conceptual phase at present at home for being connected with covering by skeleton and being, external similar technology report is not seen in data-searching.The characteristics of this class A of geometric unitA are: 1, member mainly is made up of skeleton and covering, is distributed with a large amount of reinforcements on the skeleton, and both side surface and covering link together.2, member is a variable cross-section body, the physical dimension became uneven.3, there are many complicated factors that are different from common components in this member in welding process, and the sweating heat expansion that internal stress that processing causes as the part preceding working procedure and the structural complexity of workpiece own cause is asymmetric etc., makes that welding deformation control is very difficult.Therefore the welding that solves this class A of geometric unitA belongs to large tracts of land labyrinth interconnection technique.
The domestic research of once carrying out methods such as argon arc welding, Laser Welding.But said method all belongs to local heat molten solder technology, and welding interior stress is big, post welding distortion is serious, and welding deformation is all greater than 0.5mm, and is difficult to reach skeleton and is connected with the large tracts of land of covering.
Summary of the invention
According to background technology, the object of the present invention is to provide a kind of at the titanium alloy member of forming by skeleton and covering, and member is the variable cross-section body, the physical dimension became uneven, a large amount of reinforcements distributes on the skeleton, need realization skeleton is connected with all contacts area of covering, for this reason, be preset between skeleton and the covering contact-making surface with the titanium alloy foil-shaped brazing material, utilize the assembly tooling of thermal expansion profile adding pressure type, under vacuum condition, it is carried out the integral body heating, make the solder fusing and be covered with the whole soldering welding method that is connected face.
To achieve these goals, the present invention is achieved through the following technical solutions:
A kind of titanium alloy framework and covering variable cross-section element welding method, its concrete steps are as follows:
(1) the part pickling after at first will detecting is clean, and FTI high strength titanium alloy foil-shaped brazing material is preset between skeleton and the covering surface to be welded;
(2) adopt thermal expansion assembly tooling or profile adding pressure type thermal expansion assembly tooling to clamp, under vacuum environment, it is carried out the integral body heating;
(3) by suitable vacuum brazing parameter, make solder fusing take place and be covered with whole surface to be welded, and carry out solid-state diffusion being lower than under the brazing temperature insulation at high temperature, connect thereby finish soldering;
(4) finish product welding after, the dismounting frock is checked scantling and welding quality.
Profile adding pressure type thermal expansion assembly tooling is mainly by location fastening cap (1), liner plate (2), pressure-regulating device (3), clamping plate (4), member (5), locating piece (6), following securing member (7) and base (8) are formed, wherein, location fastening cap (1) suit is positioned clamping plate (4) end, and locating piece (6) is connected with clamping plate (4), liner plate (2) contacts with member (5) and pressure-regulating device (3), and following securing member (7) is connected with base (8) with clamping plate (4).Frock is the vertical pressuring method of monosymmetric profile, adjustable multiple spot active force is vertically put on the superalloy liner plate, by liner plate with the power stepless action on covering, frock can reused below 950 ℃.
Frock can adopt thermal coefficient of expansion to make less than the exotic material of titanium alloy, as Mo or Mo alloy, WMo alloy, TZM alloy etc.
Adopt following welding parameter can realize being connected of titanium alloy framework and covering variable cross-section element.
Brazing process variables: 870～950 ℃, insulation 2～60min;
Diffusion parameter: 700～850 ℃ of insulations, 30～120min.
Wherein:
1, member is reduced to 850 ℃ of insulation 30min after being warming up to 900 ℃ of insulation 10min, cools off with stove;
2, member is reduced to 700 ℃ of insulation 60min after being warming up to 950 ℃ of insulation 5min, cools off with stove;
3, member is reduced to 800 ℃ of insulation 100min after being warming up to 870 ℃ of insulation 40min, cools off with stove.
Owing to adopted technique scheme, the present invention to have following advantage and effect:
1, the present invention is in order to reduce welding deformation, the realization skeleton is connected with all contact-making surfaces of covering, provide employing titanium alloy foil-shaped brazing material to be preset between skeleton and the covering contact-making surface and utilize the thermal expansion frock to clamp, under vacuum condition, it is carried out the integral body heating, make the solder fusing and be covered with the whole face that is connected, solidify after DIFFUSION TREATMENT forms firm soldered fitting, realized being connected of titanium alloy framework and covering variable cross-section complex component through practice of construction.
2, the invention provides soldering thermal expansion pressurization and deformed Control Technology, solved the technical barrier of member flatness and the serious welding deformation of symmetry.
3, the invention provides high temperature brazing and DIFFUSION TREATMENT innovative technology technology, finally make structural member obtain the good mechanical performance.
4, profile adding pressure type thermal expansion assembly tooling provided by the invention, simple in structure, cost is low, reliable operation, working service is repaired simple and easy.
Description of drawings
Fig. 1 is a member vacuum brazing schematic flow sheet of the present invention
Fig. 2 is a profile adding pressure type thermal expansion assembly tooling general structure cross-sectional schematic of the present invention
The specific embodiment
A kind of titanium alloy look skeleton and covering variable cross-section element welding method:
By Fig. 1 member vacuum brazing flow process is shown, part pickling after at first will detecting is clean, FTI high strength foil-shaped brazing material is contained in the skeleton surface to be welded in advance, carrying out vacuum brazing by thermal expansion assembly tooling or profile adding pressure type thermal expansion assembly tooling clamping fed to boiler, by suitable vacuum brazing parameter, as the high temperature brazing parameter: 870～950 ℃, insulation 2～60min; Diffusion parameter: 700～850 ℃ of insulations, 30～120min makes solder fusing take place and be lower than to be incubated under the brazing temperature to carry out solid-state diffusion at high temperature, diffusion makes the further homogenising of joint microstructure composition, after finishing the product welding, the dismounting frock is checked scantling and welding quality.
The overall cross-sectional schematic of profile adding pressure type thermal expansion assembly tooling is shown by Fig. 2.
Profile adding pressure type thermal expansion assembly tooling is mainly by location fastening cap 1, liner plate 2, pressure-regulating device 3, clamping plate 4, member 5, locating piece 6, following securing member 7 and base 8 are formed, wherein, location fastening cap 1 suit is positioned clamping plate 4 ends, and locating piece 6 is connected with clamping plate 4, liner plate 2 contacts with member 5 and pressure-regulating device 3, and following securing member 7 is connected with base 8 with clamping plate 4.Frock can reused below 950 ℃.
As can be known, utilize the difference of member and frock clamp material thermal expansion coefficient, adopt thermal coefficient of expansion to make frock less than the exotic material of titanium alloy, make the swell increment of member swell increment at high temperature greater than anchor clamps, thereby make covering in the soldering temperature-rise period and solder still can be subjected to the effect of thermal expansion thrust after melting and be close to skeleton, guaranteed the large-area brazing quality.Because element structure complexity, became uneven, so imposing on the thrust of two side skins must be even, symmetrical, otherwise very easily cause the consequence of member flatness and symmetry gross distortion, therefore adopted the vertical pressuring method of monosymmetric profile in the frock design: be about to adjustable multiple spot active force and vertically put on the superalloy liner plate, by liner plate (consistent) with skin-covering face with the power stepless action on covering, solved the technical barrier of member flatness and the serious welding deformation of symmetry.
The material of assembly tooling can adopt the metal or alloy of the coefficient of expansion less than titanium alloy.As Mo or Mo alloy, WMo alloy, TZM alloy etc.
Know again, in actual production process, adopt following technological parameter:
(1) member is reduced to 850 ℃ of insulation 30min after being warming up to 900 ℃ of insulation 10min, cools off with stove.
(2) member is reduced to 700 ℃ of insulation 60min after being warming up to 950 ℃ of insulation 5min, cools off with stove.
(3) member is reduced to 800 ℃ of insulation 100min after being warming up to 870 ℃ of insulation 40min, cools off with stove.
Claims (8)
1, a kind of titanium alloy framework and covering variable cross-section element welding method, its concrete steps are as follows:
(1) the part pickling after at first will detecting is clean, and the titanium alloy foil-shaped brazing material is preset between skeleton and the covering surface to be welded;
(2) adopt the thermal expansion assembly tooling to clamp, under vacuum environment, it is carried out the integral body heating;
(3) by suitable vacuum brazing parameter, make solder fusing take place and be covered with whole surface to be welded, and carry out solid-state diffusion being lower than under the brazing temperature insulation at high temperature, connect thereby finish soldering;
(4) finish product welding after, the dismounting frock is checked scantling and welding quality.
2, titanium alloy framework according to claim 1 and covering variable cross-section element welding method is characterized in that: adopt profile adding pressure type thermal expansion assembly tooling to clamp.
3, titanium alloy framework according to claim 2 and covering variable cross-section element welding method, it is characterized in that: profile adding pressure type thermal expansion assembly tooling, mainly by location fastening cap (1), liner plate (2), pressure-regulating device (3), clamping plate (4), member (5), locating piece (6), following securing member (7) and base (8) are formed, wherein, location fastening cap (1) suit is positioned clamping plate (4) end, locating piece (6) is connected with clamping plate (4), and liner plate (2) contacts with member (5) and pressure-regulating device (3), and following securing member (7) is connected with base (8) with clamping plate (4).
4, titanium alloy framework according to claim 3 and covering variable cross-section element welding method is characterized in that: adopt thermal coefficient of expansion to make frock less than the exotic material of titanium alloy, as Mo or Mo alloy, WMo alloy, TZM alloy etc.
5, titanium alloy framework according to claim 3 and covering variable cross-section element welding method, it is characterized in that: frock is the vertical pressuring method of monosymmetric profile, adjustable multiple spot active force is vertically put on the superalloy liner plate, by liner plate with the power stepless action on covering, frock can reused below 950 ℃.
6, titanium alloy framework according to claim 1 and covering variable cross-section element welding method is characterized in that: solder is a FTI high strength foil-shaped brazing material.
7, titanium alloy framework according to claim 1 and covering variable cross-section element welding method is characterized in that: the high temperature brazing parameter is 870～950 ℃, insulation 2～60min; Diffusion parameter is 700～850 ℃ of insulations, 30～120min.
8, titanium alloy framework according to claim 1 and covering variable cross-section element welding method is characterized in that: member is reduced to 850 ℃ of insulation 30min after being warming up to 900 ℃ of insulation 10min, cools off with stove; Member is reduced to 700 ℃ of insulation 60min after being warming up to 950 ℃ of insulation 5min, cools off with stove; Member is reduced to 800 ℃ of insulation 100min after being warming up to 870 ℃ of insulation 40min, cools off with stove.
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| CN102009272A (en) * | 2010-12-28 | 2011-04-13 | 哈尔滨工业大学 | Laser welding jig of triangular titanium alloy covering and skeleton weld assembly |
| CN105057990A (en) * | 2015-08-21 | 2015-11-18 | 北京星航机电装备有限公司 | Forming method of lightweight missile wing with integral diffusion bonding structure of envelope and framework |
| CN105904161A (en) * | 2016-05-24 | 2016-08-31 | 湖北三江航天红阳机电有限公司 | Double-cone rhombic titanium alloy overall cabin manufacturing method |
| CN106002088A (en) * | 2016-05-24 | 2016-10-12 | 湖北三江航天红阳机电有限公司 | Manufacturing method for integral wing-body-fused cabin |
| CN108225120A (en) * | 2018-01-09 | 2018-06-29 | 北京航空航天大学 | Frame-covering structure missile wing |
| CN109500145A (en) * | 2018-11-08 | 2019-03-22 | 北京星航机电装备有限公司 | A kind of titanium alloy thin wall aerofoil class part hot sizing method |
| CN110014217A (en) * | 2019-05-16 | 2019-07-16 | 江苏博联硕焊接技术有限公司 | A kind of diffusion welding method of diffusion welding (DW) fixture and turbo-molecular pump rotor |
| CN110899896A (en) * | 2019-12-10 | 2020-03-24 | 哈尔滨工业大学 | Welding fixture and method for brazing large-size aluminum alloy curved surface skin and ribbed framework structure |
| CN111168221A (en) * | 2019-12-13 | 2020-05-19 | 航天海鹰(哈尔滨)钛业有限公司 | Diffusion connection process method for K417 high-temperature alloy skin skeleton structure |
| CN111360399A (en) * | 2018-12-26 | 2020-07-03 | 航天海鹰(哈尔滨)钛业有限公司 | Laser welding forming method for titanium alloy control surface |
| CN111872508A (en) * | 2020-06-23 | 2020-11-03 | 上海航天精密机械研究所 | Diffusion brazing connection method for honeycomb structure |
| CN112743188A (en) * | 2020-12-29 | 2021-05-04 | 航天海鹰(哈尔滨)钛业有限公司 | Centre gripping formula frock of brazing |
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| GB394289A (en) * | 1933-02-23 | 1933-06-22 | Adolf Sambraus | Improvements in and relating to the manufacture of forcetransmitting constructional parts for aircraft more particularly for aeroplanes |
| CN87104456B (en) * | 1987-06-25 | 1988-11-02 | 吉林工业大学 | Stress coating process for coach and its apparatus |
| CN2360320Y (en) * | 1997-06-04 | 2000-01-26 | 陈作式 | Side surrounding tension reinforced covering equipment for passenger carriage |
| RU2179096C1 (en) * | 2000-07-26 | 2002-02-10 | Семенов Виктор Никонорович | Method for making complex-profile articles with lattice envelope |
| DE50113472D1 (en) * | 2001-02-13 | 2008-02-21 | Deutsch Zentr Luft & Raumfahrt | Method for producing a workpiece connection, in particular a connection of a fin outer skin with a stringer |
| CN1181944C (en) * | 2002-04-18 | 2004-12-29 | 南京工业大学 | Manufacture of fine-type stainless steel plate heat exchanger |
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| CN102009272A (en) * | 2010-12-28 | 2011-04-13 | 哈尔滨工业大学 | Laser welding jig of triangular titanium alloy covering and skeleton weld assembly |
| CN102009272B (en) * | 2010-12-28 | 2013-06-12 | 哈尔滨工业大学 | Laser welding jig of triangular titanium alloy covering and skeleton weld assembly |
| CN105057990A (en) * | 2015-08-21 | 2015-11-18 | 北京星航机电装备有限公司 | Forming method of lightweight missile wing with integral diffusion bonding structure of envelope and framework |
| CN105057990B (en) * | 2015-08-21 | 2017-08-25 | 北京星航机电装备有限公司 | A kind of lightweight covering skeleton missile wing integrally spreads joint forming method |
| CN105904161A (en) * | 2016-05-24 | 2016-08-31 | 湖北三江航天红阳机电有限公司 | Double-cone rhombic titanium alloy overall cabin manufacturing method |
| CN106002088A (en) * | 2016-05-24 | 2016-10-12 | 湖北三江航天红阳机电有限公司 | Manufacturing method for integral wing-body-fused cabin |
| CN106002088B (en) * | 2016-05-24 | 2018-07-06 | 湖北三江航天红阳机电有限公司 | A kind of blended wing-body entirety bay section manufacturing method |
| CN108225120A (en) * | 2018-01-09 | 2018-06-29 | 北京航空航天大学 | Frame-covering structure missile wing |
| CN109500145A (en) * | 2018-11-08 | 2019-03-22 | 北京星航机电装备有限公司 | A kind of titanium alloy thin wall aerofoil class part hot sizing method |
| CN111360399A (en) * | 2018-12-26 | 2020-07-03 | 航天海鹰(哈尔滨)钛业有限公司 | Laser welding forming method for titanium alloy control surface |
| CN111360399B (en) * | 2018-12-26 | 2022-01-04 | 航天海鹰(哈尔滨)钛业有限公司 | Laser welding forming method for titanium alloy control surface |
| CN110014217A (en) * | 2019-05-16 | 2019-07-16 | 江苏博联硕焊接技术有限公司 | A kind of diffusion welding method of diffusion welding (DW) fixture and turbo-molecular pump rotor |
| CN110899896A (en) * | 2019-12-10 | 2020-03-24 | 哈尔滨工业大学 | Welding fixture and method for brazing large-size aluminum alloy curved surface skin and ribbed framework structure |
| CN110899896B (en) * | 2019-12-10 | 2021-11-02 | 哈尔滨工业大学 | Welding fixture and method for brazing large-size aluminum alloy curved surface skin and ribbed framework structure |
| CN111168221A (en) * | 2019-12-13 | 2020-05-19 | 航天海鹰(哈尔滨)钛业有限公司 | Diffusion connection process method for K417 high-temperature alloy skin skeleton structure |
| CN111872508A (en) * | 2020-06-23 | 2020-11-03 | 上海航天精密机械研究所 | Diffusion brazing connection method for honeycomb structure |
| CN112743188A (en) * | 2020-12-29 | 2021-05-04 | 航天海鹰(哈尔滨)钛业有限公司 | Centre gripping formula frock of brazing |
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