CN101397662A - 复原涡轮机元件的方法 - Google Patents
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Abstract
本发明公开了一种复原涡轮机元件的方法,该涡轮机元件由基质和粘接基质的保护涂层构成,该基质形成元件的主体。该方法包括:涡轮机元件的控制,以精确定点保护涂层和基质之间具有接合缺陷的区域;以及,保护涂层和基质之间接合缺陷的排除。通过向具有接合缺陷的每个区域上引导激光束,以引起保护涂层和下面的基质的局部熔化以在停止激光束后,在所述区域的水平上,在保护涂层和基质之间能够得到可靠的接合,来排除接合缺陷。
Description
技术领域
本发明涉及一种复原涡轮机元件的方法。
使用“复原”意指给新部件带来配合性,该新部件在制造结束时具有一个或几个缺陷,该缺陷可以危及它的正常使用。
背景技术
在涡轮机构造中使用的元件必须具有非常仔细准备的精加工条件,并且这适用于最小的细节。
涡轮机元件,特别是可动部件附近的部件的元件或元件,设有保护涂层,其性质取决于这些元件的作用和它们的等级。例如,涡轮机的叶片通常设有涂层,该涂层用作热阻挡和对构成叶片的金属的扩散形成阻挡。并且,例如,在由焊接在一起的部件形成转子的情况下,转子的迷宫式刀口密封设有耐磨涂层,其中所述刀口密封在相对面设有与固定叶片一体的耐磨材料。
通常,通过等离子沉积或激光淀积获得保护涂层。其中主体部分(或基质)是基于镍、钴、铁或钛的金属的叶片可以具有例如,氧化铝、氧化锆、氧化钇、碳化钛、碳化钨等的涂层。例如,该涂层的厚度在0.05mm和0.5mm之间。
涂层操作后,有时可以观察到元件基质上的涂层没有接合或剥离。通过表面处理的方法,即,化学溶解(通过酸的方法)可以复原缺陷的部件,能够排除有缺陷的涂层。一旦进行这种操作,就得进行新的沉积。必须依次检查该新的沉积。除了延长生产周期外,现有技术的复原方法也有健康、安全和环境方面的缺陷。
而且,使用激光束局部地处理金属部件已经成为公开出版物的主题。
美国专利4960611公开了一种可以改正机械部件的涂层中小缺陷的方法,所述缺陷明显地是由于尘粒或油滴。这种方法特别地为车辆的电动机架设计,所述的电动机架涂覆有几层保护层:接合层,中间层和成品外部涂层。为了改正影响成品外部涂层的缺陷(尘粒、油滴),建议通过激光束辐照成品外部涂层的缺陷区,以升华尘粒或油滴以及成品外部涂层的相邻区以在成品外部涂层中形成细微的孔穴。然后,用修复组合物填充该孔穴,例如,通过激光束硬化它。
文献EP-A-0 504 095公开了一种用于修复燃气轮机的元件的方法,特别地是一种修复使用中损坏的叶片的方法。在使用中,叶片受到了氧化、裂隙和金属腐蚀现象,这些现象是由于气流中所包含的磨擦剂和腐蚀剂打击叶片。然后,高温时气流循环的高压引起了叶片的变形。这篇文献推荐了通过向待修复的叶片表面区域上引导激光束而修复叶片的方法。该激光束局部地熔化叶片的薄表面层,然后进行固化。固化引起了处理层下面材料中的牵力,使叶片的这部分产生了凹形结构。通过沿着确定的路径应用激光束,可以改装叶片。
文献DE-A-33 25 251描述了一种复原涡轮机元件的方法,该涡轮机元件包括陶瓷层涂覆的基质,该陶瓷层通过粘合层粘接基质。该方法包括部件的控制以精确定点具有陶瓷层接合缺陷的区域。通过能量射束,优选地电子束的方法,扫描涡轮机元件来精确定点缺陷。能量束引起了每个缺陷区域中陶瓷层的剥落。通过剥落区域的精磨和陶瓷材料的添加完成了缺陷的排除。
美国专利5 576 069公开了通过激光的再熔化方法,通过等离子体,氧化锆层溅射到涂覆有接合层的金属元件上。为了处理氧化锆层中的缺陷,表面再熔化该层。然后,应用陶瓷的悬浮液。然后,再次地表面再熔化陶瓷层。在该方法中,没有基质或接合层的再熔化。
发明内容
本发明设计为用于克服目前所用的复原涡轮机元件的方法的缺陷。
本发明涉及一种复原涡轮机元件的方法,该涡轮机元件由基质和粘接基质的保护涂层构成,该基质形成了元件的主体,其中该方法包括:
-涡轮机元件的控制,以精确定点保护涂层和基质之间具有接合缺陷的区域;
-保护涂层和基质之间接合缺陷的排除;
其特征在于通过向具有接合缺陷的每个区域上引导激光束,并且引起保护涂层和下面的基质的局部熔化以在停止激光束后,在所述区域的水平上,在每个区域冷却后,在保护涂层和基质之间能够得到可靠的接合,来排除接合缺陷。
根据特定的实施方式,在三维中,用几何学分析具有缺陷的、在涡轮机元件控制期间被精确定点的区域,并且记录,以给激光束提供确定的路径,并且以给激光束提供一些特征以使它能够排除每个接合缺陷。
特别地,可以尽可能快地确定涡轮机元件上激光束的路径。
根据另一个实施方式,在惰性或还原环境下,进行通过激光束引起的局部熔化。
有利地,通过光纤向具有接合缺陷的区域引导激光束。
可以通过YAG激光器发射激光束。
该方法可以包括接合缺陷排除后涡轮机元件的新控制,以检查是否接合缺陷存在于保护涂层和基质之间。
例如,该方法适于涡轮机的叶片或刀口密封的复原。
附图说明
通过阅读下面的描述和参考附图可以更好地理解本发明,并且其它优点及特征将变得清楚,所述描述只是通过表明本发明的方式给出,决没有限制本发明。
图1是在涡轮机元件的主体和其保护涂层之间具有接合缺陷的涡轮机元件的横截面的部分视图。
图2表示经受了本发明复原方法的图1中所示的涡轮机元件。
图3示例了排除涡轮机元件的基质和保护涂层之间接合缺陷的操作。
具体实施方式
图1是涡轮机元件,例如叶片1的横截面的部分视图。叶片1由基质2和保护涂层3构成,该基质2形成元件的主体。
基质2是金属材料,例如基于镍、钴、铁或钛的金属材料。例如,保护层3由通过等离子体沉积或通过激光沉积所获得的氧化铝、氧化锆、氧化钇或金属碳化物(例如钛或钨的碳化物)的层构成。例如,涂层的厚度是在0.05mm和0.5mm之间。保护涂层3必须粘接基质2。然而,可以出现一个或几个缺陷(涂层没有接合、涂层的剥离),如附图标记4所示。
为了克服这种接合缺陷,本发明建议再熔化缺陷区域中的保护涂层以确保涂层和基质之间的物理连续性。
如图2所示,通过激光束5获得涂层3和下面基质2的局部熔化。例如,通过YAG激光器发射激光束,并且通过光纤传输该激光束一直到区域6,该区域6包括一部分保护涂层3和一部分基质2。该YAG激光器的特征可以如下:
-涡轮机元件上激光束的焦斑的直径:0.2mm和0.8mm之间,
-脉冲频率:从3到10Hz,
-激光束的平均功率:50和100W之间,
-脉冲持续时间:从5ms到15ms。
目的是不管区域的表面积,向待复原的每个区域供应连续的能量密度。
本发明的方法首先包括控制涡轮机元件以精确定点具有接合缺陷的区域,诸如,图1中所示区域4的步骤。在该操作前,元件表面的清洁是必需的,以确保基质/保护涂层接合的冶金学和机械学的质量。所涉及的区域有利地免除任何污染(油脂、油类、渗色产品等)。
在三维中(定位、几何学、维度等)用几何学分析每个缺陷区域的轮廓,以确保激光束的最佳轨道。
一旦完成涡轮机元件的特征描述,就进行元件的开始配合性(the bring intocompliance)。没有金属输入的情况下实施该方法。手动或自动地管理实施它时的速率。激光束焦斑的维度作为工作区域几何学的函数而改变。由激光束供应的平均能量是低的(小于100W),以限制变形,并且在叶片的情况下,以避免叶片上部的毁坏。
图3示例了排除涡轮机叶片10的基质和保护涂层之间接合缺陷的操作。附图标记11表示激光源,例如YAG激光源。通过光纤12传输由激光源11所发射的激光束,一直到激光头部13。激光头部13向待复原的区域引导激光束14。在操作期间,气体保护系统15保护叶片免受腐蚀和氧化。通过吹送惰性(例如,氩)或还原气体可以完成气体保护。
Claims (8)
1.一种复原涡轮机元件(1,10)的方法,该涡轮机元件由基质(2)和粘接基质的保护涂层(3)构成,该基质(2)形成元件的主体,其中该方法包括:
涡轮机元件的控制,以精确定点保护涂层(3)和基质(2)之间具有接合缺陷的区域;
保护涂层和基质之间接合缺陷的排除;
其特征在于:通过向具有接合缺陷的每个区域上引导激光束(5),并且引起保护涂层和下面的基质的局部熔化以在停止激光束后,在所述区域的水平上,在每个区域冷却后,在保护涂层和基质之间能够得到可靠的接合,来排除接合缺陷。
2.根据权利要求1所述的方法,其中在三维中,用几何学分析具有缺陷的、在涡轮机元件控制期间被精确定点的区域,并且记录,以给激光束提供确定的路径,并且以给激光束提供一些特征以使它能够排除每个接合缺陷。
3.根据权利要求2所述的方法,其中尽可能快地确定涡轮机元件上激光束的路径。
4.根据权利要求1至3中任一权利要求所述的方法,其中在惰性或还原环境下进行通过激光束(14)引起的局部熔化。
5.根据权利要求1至4中任一权利要求所述的方法,其中通过光纤(12)向具有接合缺陷的区域上引导激光束(14)。
6.根据权利要求1至5中任一权利要求所述的方法,其中通过YAG激光器(11)发射激光束(14)。
7.根据权利要求1至6中任一权利要求所述的方法,包括接合缺陷排除后涡轮机元件的新控制,以检查是否接合缺陷存在于保护涂层和基质之间。
8.权利要求1至7中任一权利要求所述的方法应用于涡轮机叶片或刀口密封的复原。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0757869A FR2921284B1 (fr) | 2007-09-26 | 2007-09-26 | Procede de recuperation d'elements de turbomachine |
FR0757869 | 2007-09-26 |
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CN101397662A true CN101397662A (zh) | 2009-04-01 |
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EP (1) | EP2042618B1 (zh) |
JP (1) | JP5511167B2 (zh) |
CN (1) | CN101397662A (zh) |
CA (1) | CA2639960C (zh) |
FR (1) | FR2921284B1 (zh) |
RU (1) | RU2481937C2 (zh) |
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CN103079754A (zh) * | 2010-08-31 | 2013-05-01 | 汉莎技术股份公司 | 用于修整用于气体涡轮机的压缩机或涡轮机叶片的方法 |
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GB201500304D0 (en) | 2015-01-09 | 2015-02-25 | Rolls Royce Plc | A method of surface-treating a cast intermetallic component |
RU2603751C1 (ru) * | 2015-06-01 | 2016-11-27 | Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Владимирский государственный университет имени Александра Григорьевича и Николая Григорьевича Столетовых" (ВлГУ) | Способ получения покрытия из микроструктурированного карбида титана на поверхности изделия из титана или титанового сплава с использованием лазерного излучения |
US20170167277A1 (en) * | 2015-12-10 | 2017-06-15 | General Electric Company | Methods for modifying components |
US10410892B2 (en) * | 2016-11-18 | 2019-09-10 | Taiwan Semiconductor Manufacturing Company Ltd. | Method of semiconductor wafer bonding and system thereof |
US10241036B2 (en) * | 2017-05-08 | 2019-03-26 | Siemens Energy, Inc. | Laser thermography |
US11028486B2 (en) * | 2018-12-04 | 2021-06-08 | General Electric Company | Coating systems including infiltration coatings and reactive phase spray formulation coatings |
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2007
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Cited By (2)
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CN103079754A (zh) * | 2010-08-31 | 2013-05-01 | 汉莎技术股份公司 | 用于修整用于气体涡轮机的压缩机或涡轮机叶片的方法 |
CN103079754B (zh) * | 2010-08-31 | 2016-08-03 | 汉莎技术股份公司 | 用于修整用于气体涡轮机的压缩机或涡轮机叶片的方法 |
Also Published As
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JP5511167B2 (ja) | 2014-06-04 |
CA2639960C (en) | 2015-11-24 |
EP2042618A1 (fr) | 2009-04-01 |
FR2921284B1 (fr) | 2009-12-11 |
US20090079110A1 (en) | 2009-03-26 |
CA2639960A1 (en) | 2009-03-26 |
JP2009079590A (ja) | 2009-04-16 |
RU2481937C2 (ru) | 2013-05-20 |
US7722793B2 (en) | 2010-05-25 |
EP2042618B1 (fr) | 2016-07-20 |
RU2008138273A (ru) | 2010-03-27 |
FR2921284A1 (fr) | 2009-03-27 |
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