CN101559538B - 通过高温钎焊连接的金属件的修整方法 - Google Patents
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- B23K1/00—Soldering, e.g. brazing, or unsoldering
- B23K1/005—Soldering by means of radiant energy
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- B23K35/00—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting
- B23K35/001—Interlayers, transition pieces for metallurgical bonding of workpieces
- B23K35/007—Interlayers, transition pieces for metallurgical bonding of workpieces at least one of the workpieces being of copper or another noble metal
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- B23K35/00—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting
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Abstract
本发明涉及方法金属件的钎焊,特别是钎焊的修整。通过高温钎焊连接金属件(2,3)的修整方法,其特征在于,通过一个小功率激光修整装置(10)修整该被钎焊的区域(5)。
Description
技术领域
本发明涉及金属件钎焊,尤其是钎焊修整。
背景技术
钎焊包括将两个金属件在一表面接触位置通过加热一供料金属进行固连,该供料金属的熔化温度低于待连接的金属件的熔化温度。
当两个金属件在一窑炉中通过钎焊进行连接时,在所述金属件上可能出现缺陷。因而需要对钎焊进行《修整》;也就是说,钎焊缺陷的修整。钎焊的修整在于熔化该钎焊连接点,用初始钎焊时使用的该供料金属填补材料缺失。
然而,在窑炉中钎焊的第二次循环不具有一定风险。有时,可发现该组件的几何变形,材料内在品质劣化或导致新的缺陷出现,如果出现这样的情形,钎焊件就成了废品。
特别是对于航空件的钎焊,重复经过高温窑炉减少构件的寿命。
另外,钎焊和钎焊修整时使用同样的窑炉会降低组装生产的节奏。由于加热窑炉只用于成批构件,在实施修整之前需要等待足够数量的缺陷件,这同样会延长生产周期。
已知还通过弧焊来修整缺陷。然而,这种大强度的加热会导致无法修整的变形,因而该组件会成为废品。
发明内容
为了克服上述缺陷,申请人提出一种通过高温钎焊连接的金属件的修整方法,在所述方法中借助一小功率的修整激光来修整钎焊区域。
借助一修整激光来修整金属件可局部限定该金属件的施热作用区域(ZAT),这种激光传统上用于焊接操作,特别是在珠宝领域用于小尺寸件焊接,或者用于模具的重整。
这种激光可以在高温下对钎焊金属件实施修整。
与需要较大能量的焊接激光相反,钎焊修整激光由具有局部能量的小功率激光构成。
钎焊区域的修整通过在该钎焊区域提供或不提供该供料金属实施。
为了填补该金属件的钎焊缺陷,与修整的激光束接触的该供料金属在该钎焊区域熔化,该供料金属为粉末状,膏状或丝状。该供料金属与初始钎焊使用的该供料金属相容。
优选的,该小功率修整激光以脉冲模式被使用,用于镍基或钴基的金属件的激光脉冲的上升时间小于激光脉冲的下降时间。
有选地,借助抗氧化气体保护装置保护所述连接的金属件避免被氧化。
采用脉冲模式的激光有利于限制该金属件的变形,在高压压缩机的整流器的情况下不会影响翼片的几何形状。不仅如此,与连续作用模式的激光相比,脉冲模式的激光能量消耗更小。
附图说明
图1为一高压(HP)压缩机整流器截面的一部分的示意图,其中可以观察到在整流器的一翼片和一内环之间的一待修整的钎焊区域;
图2为用一小功率修整激光修整图1所示的该钎焊区域的修整方法的示意图;
图3为由附图2所示的小功率修整激光发射的脉冲信号的波形示意图。
具体实施方式
本发明的方法的其它特点和优势将参照附图加以叙述,参照附图1,涡轮发动机的高压压缩机整流器1的一截面包括固定于一内环2和一外环3(参见附图2)之间的整流器翼片4。钎焊操作时将所述整流器翼片4连接至环2,3上。参照附图1,在翼片4和环2之间相接的钎焊区域上出现一材料缺陷5。一这类缺陷导致翼片4的空气动力学性能的改变,且该组件具有很大的折断风险。因此,需要钎焊修整。
参照附图2,通过Nd-YAG型修整或校正激光装置10对钎焊缺陷5进行修整以消除空洞和缺点,该激光装置包括由一光纤13连接至一激光源11的一发射端12。一这类光纤相对于激光源11更便于对该发射端12进行操作。
该发射端12手动置于该缺陷5的下方,以便由发射端12发出的激光束13使该钎焊熔化且使缺陷5消失。
为了填补材料的缺少,钎焊的修整此处由未示出的一供料金属实现,所述供料金属为丝状,其直径在03mm-0.8mm之间,其被置于该缺陷5上以便在修整激光装置10通过时被熔化。不言而喻,供料金属可为粉末状、膏状,且预成型的煅烧件同样适合。该第二种供料金属无需与初始钎焊采用的供料金属相同,只要该供料金属与该初始钎焊的供料金属相容即可。
同样,用于初始钎焊的供料金属可以是镍/铬基,镍/钯基金属或贵金属,第二种供料金属可以采用金/镍(铜-镍)丝或镍基丝。
每次修整操作之前,金属件应当清洁或去除油污以免该钎焊被污染或增加缺陷。
该激光修整装置10此处为半手动控制,一自动装置或一直角坐标装置使使用者远距离导引该激光装置的发射端12,而使用者控制该供料金属。不言而喻,手动操作或完全自动操作同样适合。
采用小功率激光,激光频率范围为4-8Hz之间,以限制金属件发热。参照附图3,激光10采用脉冲形式,等间隔发射功率峰值为1500W-3000W的激光脉冲40。所述激光40不对称,激光脉冲上升时间41小于激光脉冲下降时间42,上升时间41为2ms-5ms,下降时间42为10-12ms,整体脉冲时间为5ms-15ms。
迅速上升时间41和缓慢下降时间42可以限制该金属件内的热梯度,在两个邻近区域之间有大的温度差会增加裂缝危险。这种类型的脉冲40特别适宜镍基钎焊,这种钎焊不稳定,需要释放钎焊应力。
然而,不言而喻,可以选配适于其它合金的信号形式。因而,对于镍基合金NC22FeD,具有平缓的上升时间和快速下降时间的脉冲很适合。为了避免出现裂缝,以脉冲功率峰值优选出激光脉冲的持续时间。
该激光装置是在抗氧化保护气氛24下使用的,该抗氧化保护气氛24通过抗氧化气体保护装置20保持。抗氧化气体由气源21经中间的一气体导管23导入一扩散管22。
实施钎焊时该保护气氛24包围住待钎焊区域以便阻止该金属件氧化。氧化会造成该金属件寿命缩短。在此使用直径为20mm-30mm的大直径的扩散管22,与在弧光焊接TIG方法中使用的扩散管相同。与传统激光焊接中使用的保护软管相比较,这样的软管可使流体在相对大的区域流动。
Claims (11)
1.通过高温钎焊连接的金属件的修整方法,其特征在于,通过一个修整激光修整该被钎焊的区域,所述修整激光的功率峰值在1500W-3000W之间,频率在4Hz-8Hz之间,并且该修整激光以脉冲模式工作。
2.根据权利要求1所述的方法,在所述方法中该被钎焊区域的修整通过在该被钎焊区域设置一供料金属实现。
3.根据前述权利要求2所述的方法,在所述方法中该供料金属为粉末状,膏状,丝状或预烧结件的形状。
4.根据前述权利要求2所述的方法,在所述方法中该供料金属与金属件的初始钎焊时所使用的供料金属相容。
5.根据前述权利要求1所述的方法,在所述方法中该修整激光以半手动方式控制。
6.根据前述权利要求1所述的方法,在所述方法中所述金属件由镍基合金或铬基合金构成。
7.根据前述权利要求1所述的方法,在所述方法中该激光脉冲的上升时间小于其下降时间。
8.根据前述权利要求1所述的方法,在所述方法中所述金属件通过在窑炉中钎焊进行连接。
9.根据前述权利要求1所述的方法,在所述方法中该修整激光脉冲的时间在5ms-15ms之间。
10.根据前述权利要求7所述的方法,在所述方法中该修整激光脉冲的时间在5ms-15ms之间。
11.根据前述权利要求1所述的方法,在所述方法中通过一抗氧化气体保护装置保护被钎焊的金属件免于被氧化。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0707011 | 2007-10-05 | ||
FR0707011A FR2921856B1 (fr) | 2007-10-05 | 2007-10-05 | Procede de retouche de pieces metalliques |
Publications (2)
Publication Number | Publication Date |
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CN101559538A CN101559538A (zh) | 2009-10-21 |
CN101559538B true CN101559538B (zh) | 2013-09-11 |
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US (1) | US8119948B2 (zh) |
EP (1) | EP2045033B1 (zh) |
JP (1) | JP5395392B2 (zh) |
CN (1) | CN101559538B (zh) |
CA (1) | CA2640219C (zh) |
DE (1) | DE602008005079D1 (zh) |
FR (1) | FR2921856B1 (zh) |
RU (1) | RU2498888C2 (zh) |
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US8573949B2 (en) * | 2009-09-30 | 2013-11-05 | General Electric Company | Method and system for focused energy brazing |
RU2534025C1 (ru) * | 2013-06-03 | 2014-11-27 | Открытое акционерное общество "Российская корпорация ракетно-космического приборостроения и информационных системы" (ОАО "Российские космические системы") | Способ исправления дефектов узлов многослойных печатных плат с высокоинтегрированной элементной базой |
US11135677B2 (en) * | 2018-03-06 | 2021-10-05 | General Electric Company | Laser welding of component |
RU2686499C1 (ru) * | 2018-05-04 | 2019-04-29 | Акционерное общество "ОДК-Авиадвигатель" | Способ ремонта охлаждаемой лопатки из жаропрочного суперсплава турбины газотурбинного двигателя |
FR3101560B1 (fr) | 2019-10-07 | 2022-06-24 | Safran Aircraft Engines | Procede de rechargement d’une piece metallique de turbomachine |
CN115026511B (zh) * | 2022-05-07 | 2023-10-13 | 金川集团股份有限公司 | 一种大、中型球磨机大齿圈轮齿断裂修理方法 |
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- 2008-10-03 DE DE602008005079T patent/DE602008005079D1/de active Active
- 2008-10-03 CA CA2640219A patent/CA2640219C/fr active Active
- 2008-10-03 RU RU2008139469/02A patent/RU2498888C2/ru not_active Application Discontinuation
- 2008-10-03 US US12/245,131 patent/US8119948B2/en active Active
- 2008-10-03 EP EP08165849A patent/EP2045033B1/fr active Active
- 2008-10-06 CN CN2008101847486A patent/CN101559538B/zh active Active
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CN1063906A (zh) * | 1991-02-07 | 1992-08-26 | 清华大学 | 造粒模具激光合金化涂敷方法 |
CN1074160A (zh) * | 1992-05-20 | 1993-07-14 | 中国科学院金属腐蚀与防护研究所 | 航空叶片表面激光仿形熔铸加工之工艺方法 |
US5889254A (en) * | 1995-11-22 | 1999-03-30 | General Electric Company | Method and apparatus for Nd: YAG hardsurfacing |
CN1392023A (zh) * | 2001-06-15 | 2003-01-22 | 沈阳大陆激光技术有限公司 | 烟气轮机损伤叶片激光仿形修复工艺 |
EP1424158A1 (en) * | 2002-11-29 | 2004-06-02 | Alstom Technology Ltd | A method for fabricating, modifying or repairing of single crystal or directionally solidified articles |
WO2007012338A1 (de) * | 2005-07-22 | 2007-02-01 | Siemens Aktiengesellschaft | Verfahren zum reparieren eines mit einer gerichteten mikrostruktur umfassenden bauteils, durch einstellung während der laser-wärmeeinwirkung ein temperaturgradient; ein mit einem solchen verfahren hergestellter bauteil |
Also Published As
Publication number | Publication date |
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CA2640219C (fr) | 2015-02-17 |
CA2640219A1 (fr) | 2009-04-05 |
EP2045033B1 (fr) | 2011-02-23 |
FR2921856A1 (fr) | 2009-04-10 |
FR2921856B1 (fr) | 2011-12-09 |
US20090090701A1 (en) | 2009-04-09 |
JP2009090370A (ja) | 2009-04-30 |
US8119948B2 (en) | 2012-02-21 |
RU2498888C2 (ru) | 2013-11-20 |
RU2008139469A (ru) | 2010-04-10 |
DE602008005079D1 (de) | 2011-04-07 |
JP5395392B2 (ja) | 2014-01-22 |
EP2045033A1 (fr) | 2009-04-08 |
CN101559538A (zh) | 2009-10-21 |
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