CN1766150A - Ni基合金制部件的修补方法 - Google Patents
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Abstract
一种Ni基合金制部件的修补方法,是在Ni基合金制母材(11)上形成内涂层(12)和外涂层(13)的Ni基合金制部件中,在所述外涂层(13)上具有损坏时的修补方法,其特征在于,包括除去具有损坏的外涂层(13)的损坏部(13a)和相对于该损坏部(13a)的内涂层(12)的变质部(12a)的工序;在大气中以喷镀粒子速度为300m/s以上、母材温度为300℃以下或者在减压下以喷镀粒子速度低于300m/s、母材温度为低于600℃,在内涂层(12)的开口部上通过喷镀形成另外内涂层(17)的工序;以及在外涂层(13)的剥离部(13a)上形成另外外涂层(18)的工序。
Description
技术领域
本发明涉及一种Ni基合金制部件的修补方法,具体地说是涉及一种燃气轮机、喷气式发动机等的高温部件尤其是用于动叶或静叶的Ni基合金制部件的修补方法。
背景技术
众所周知在动叶或静叶中一般都使用锻造合金。但是,在该类合金中尤其多使用Ni基合金。Ni基合金由于成型性的自由度良好,所以可以容易地进行部件的制造和部分修补。
图4是表示燃气轮机的动叶1的简图,图5是表示图4中部分损坏部的放大剖视图。如图5所示,在母材2上依次形成内涂层3和ZrO2类等的由陶瓷构成的外涂层4。将所述外涂层4的一部分剥离,该剥离部分称为TBC(绝热涂层)剥离部5。另外,在图5中,图号6表示在所述剥离部5的对应位置上形成的内涂层4的表面部的变质部,图号7表示在剥离部5周围的外涂层4上形成的损坏部。
另外,为修补TBC剥离部,例如可以考虑使用低压等离子喷镀法。但是该喷镀法须要清洗(反极性电弧)或800℃以上的预热,从这一点来看若考虑部分修补,就有可能在所述外涂层4中产生损坏而根本不能实施。
所以,以往对TBC剥离部的修补,是通过机械或化学方法全面除去外涂层4和内涂层3后,再重新通过低压等离子喷镀法实施内涂层,进而通过大气压等离子喷镀法等实施外涂层。
但是,在这样以往的修补方法中,即使外涂层4出现部分损坏,也必须对整个动叶进行重新涂层,从而造成成本过高的问题。
发明内容
本发明鉴于这些问题,其目的在于提供一种在除去具有损坏的外涂层的损坏部和相对于该损坏部的内涂层的变质部后,在大气中以喷镀粒子速度300m/s以上、母材温度300℃以下,在内涂层的除去部上通过喷镀形成另外的内涂层,由此能够对涂层进行部分修补并且能够降低成本的Ni基合金制部件的修补方法。
另外,本发明的目的在于提供一种在除去具有损坏的外涂层的损坏部和相对于该损坏部的内涂层的变质部后,在减压下以喷镀粒子速度低于300m/s、母材温度600℃以下,在内涂层的除去部上通过喷镀形成另外的内涂层,进而通过在外涂层的损坏部上形成另外的外涂层,从而能够对涂层进行部分修补并且能够降低成本的Ni基合金制部件的修补方法。
为到达所述目的,本发明的Ni基合金制部件的修补方法,是在Ni基合金制母材上形成内涂层和外涂层的Ni基合金制部件中,在所述外涂层上具有损坏时的修补方法,其特征在于,包括除去具有损坏的外涂层的损坏部和相对于该损坏部的内涂层的变质部的工序;在大气中以喷镀粒子速度300m/s以上、母材温度300℃以下,在内涂层的除去部上通过喷镀形成另外内涂层的工序;以及在外涂层的损坏部位上形成另外外涂层的工序。
本发明的Ni基合金制部件的修补方法,是在Ni基合金制母材上形成内涂层和外涂层的Ni基合金制部件中,在所述外涂层上具有损坏时的修补方法,其特征在于,包括除去具有损坏的外涂层的损坏部和相对于该损坏部的内涂层的变质部的工序;在减压下以喷镀粒子速度低于300m/s、母材温度600℃以下,在内涂层的除去部上进行喷镀的工序;以及在外涂层的损坏部位上形成另外外涂层的工序。
附图说明
图1A~D为分别依次表示本发明实施例1中Ni基合金制部件修补方法的工序说明图。
图2A~D为分别依次表示本发明实施例2中Ni基合金制部件修补方法的工序说明图。
图3A~D为分别依次表示本发明实施例3中Ni基合金制部件修补方法的工序说明图。
图4是表示具有损坏部位的燃气发动机动叶的说明图。
图5是表示以往Ni基合金制部件修补方法的工序说明图。
具体实施方式
以下对本发明进一步详细地说明。
在本发明的第一种修补方法中,之所以把喷镀粒子速度设为300m/s以上,是由于喷镀粒子速度若低于300m/s,在内涂层的除去部位上形成的另外内涂层上容易附有氧化膜。另外,之所以把基材温度设为300℃以下,是由于若超过300℃母材被加热并且受到损坏。
在本发明的第二种修补方法中,之所以把喷镀粒子速度设为低于300m/s,是由于喷镀粒子速度若高于300m/s,在低压下的喷镀中,由于喷镀构架的能量密度变高而导致母材温度显著升高。另外,之所以把基材温度设为600℃以下,是由于若超过600℃就须要急剧的热循环而导致在外涂层上产生损坏。
在本发明的第一、第二种方法中,作为形成于内涂层的损坏部上的另外内涂层,相对于以往的材料Co基类(Co-32%Ni-21%Cr-8%Al-0.5%Y),例如可以举出Ni基类。另外,作为形成于外涂层的除去部上的另外外涂层,相对于以往的材料ZrO2·8Y2O3,例如可以举出ZrO2·DY2O3、ZrO2-Yb2O3。
在第一、第二发明中,作为在内涂层的除去部中形成另外内涂层的方法,例如可以考虑通过喷镀枪进行喷镀。另外,作为在外涂层的损坏部中形成另外外涂层的方法,也可以通过喷镀枪直接进行喷镀,或者也可以使用电子束蒸镀法(EB·PVD法)。若根据EB·PVD法可以进一步提高外涂层的耐久性。
根据本发明,在除去具有损坏的外涂层的损坏部和相对于该损坏部的内涂层的变质部后,在大气中以喷镀粒子速度300m/s以上、母材温度300℃以下,在内涂层的除去部上通过喷镀形成另外内涂层,并且进一步通过在外涂层的损坏部中形成另外的外涂层,就能够对涂层进行部分修补并且还可以降低成本。
另外,根据本发明,在除去具有损坏的外涂层的损坏部和相对于该损坏部的内涂层的变质部后,在减压下以喷镀粒子速度低于300m/s、母材温度600℃以下,在内涂层的除去部上通过喷镀形成另外的内涂层,进而通过在外涂层的损坏部上形成另外的外涂层,从而能够对涂层进行部分修补并且能够降低成本。
以下,对本发明各实施例中Ni基合金制部件的修补方法进行说明。另外,在以下实施例中所述的各部件的材料、数值等只表示其中一个例子,并不限定本发明的权利要求。
实施例1
参照图1A~D。
如图1A所示,在母材11上形成表面具有变质部12a的Co类材料例如由Co-32%Ni-21%Cr-8%Al-0.5%Y构成的下涂层12。另外,如图1A所示,在所述内涂层12上形成在剥离部(除去部)13a及该剥离部13a的周围具有损坏部13b的外涂层13。所述外涂层13是由ZrO2·8Y2O3构成。由该种状态,首先将位于剥离部13a的下部的所述内涂层12及外涂层13的损坏部13b掺和研磨并且选择性地除去,然后在内涂层12和外涂层13上形成开口部(除去部)14(参照图1B)。另外,在图1B中,图号12’表示内涂层12的除去部分,图号13’表示外涂层13的除去部分。
然后,将相对于所述开口部14的部分开口的屏蔽材15配置于外涂层13的正上方,同时将喷镀枪16配置于所述开口部14的正上方。接着在大气中以喷镀粒子速度500m/s、母材温度150℃,在所述开口部14上进行喷镀,并且在内涂层12的除去部分12’上形成Co基类合金层例如CoNiCrAlY层17,从而对内涂层12修补完毕(参照图1C)。进而利用所述喷镀枪16,在所述开口部14上进行喷镀并且在外涂层13的除去部分13’上形成由ZrO2-Yb2O3构成的外涂层18,从而对外涂层13修补完毕(参照图1D)。
在所述实施例1中,选择性地除去位于外涂层13的剥离部13a的下部的内涂层12和损坏层13b并且在内涂层12和外涂层13上形成开口部14后,从正上方用喷镀枪16,在大气中以喷镀粒子速度500m/s、母材温度150℃以下在开口部14上进行喷镀,然后依次对内涂层12的除去部分12’、外涂层13的除去部分13’进行修补。所以,如以往所示,由于不须要对整个动叶重新涂层,所以可以降低成本。
另外,在实施例1中,由于在从开口部14露出的内涂层12的除去部分中形成Ni基类合金层17,所以与以往的内涂层12相比可以提高耐久性。进而由于在外涂层13的剥离部13a上形成由ZrO2-Yb2O3构成的外涂层18,所以与以往的外涂层13相比可以提高耐久性。
实施例2
参照图2A~D。但是与图1A~D相同的部件附有同样的图号,所以省略其说明。
如图2A所示,在母材11上形成具有变质部12a的内涂层12。这里内涂层12是由Ni类材料例如NiCoCrAlY构成。另外,如图2A所示在内涂层12上形成在剥离部(除去部)13a和该剥离部13a的周围具有损坏部13b的外涂层13。所述外涂层13由ZrO2·8Y2O3构成。由该种状态,首先将位于剥离部13a的下部的所述内涂层12及外涂层13的损坏部13b掺和研磨并且选择性地除去,然后在内涂层12和外涂层13上形成开口部(除去部)14(参照图2B)。
然后,将相对于所述开口部14的部分开口的屏蔽材15配置于外涂层13的正上方,同时将喷镀枪16配置于所述开口部14的正上方。接着在减压下以喷镀粒子速度200m/s、母材温度150℃在所述开口部14上进行喷镀,并且在内涂层12的除去部分12’上形成Ni基类合金层例如NiCoCrAlY层21,从而对内涂层12修补完毕(参照图2C)。进而利用所述喷镀枪16,在所述开口部14上进行喷镀并且在外涂层13的除去部分13’上形成由ZrO2-Yb2O3构成的外涂层22,从而对外涂层13修补完毕(参照图2D)。
根据实施例2,选择性地除去位于外涂层13的剥离部13a的下部的内涂层12和损坏层13b并且在内涂层12和外涂层13上形成开口部14后,从正上方用喷镀枪16,在减压下以喷镀粒子速度500m/s、母材温度150℃以下在开口部14上进行喷镀,然后依次对内涂层12的除去部分12’、外涂层13的除去部分13’进行修补。所以,如以往所示,由于不须要对整个动叶重新涂层,所以可以降低成本。
另外,在实施例2中,由于在从开口部14露出的内涂层12的除去部分中形成Ni基类合金层21,所以与以往的内涂层12相比可以提高耐久性。进而由于在外涂层13的剥离部13a上形成由ZrO2-Yb2O3构成的外涂层22,所以与以往的外涂层13相比可以提高耐久性。
实施例3
参照图3A~D。但是与图1A~D相同的部件附有同样的图号,所以省略其说明。
与实施例1相同,如图3A所示,在母材11上形成具有变质部12a的内涂层12,在所述内涂层12上形成在剥离部(除去部)13a和该剥离部13a的周围具有损坏部13b的外涂层13。所述外涂层13由ZrO2·8Y2O3构成。由该种状态,与实施例1相同,将对应于剥离部13a的所述内涂层12及内涂层12的损坏部13b掺和研磨并且选择性地除去,然后在内涂层12和外涂层13上形成开口部(除去部)14(参照图3B)。
然后,将相对于所述开口部14的部分开口的屏蔽材15配置于外涂层13的正上方,同时将喷镀枪16配置于所述开口部14的正上方。接着在大气中以喷镀粒子速度500m/s、母材温度150℃在所述开口部14上进行喷镀,并且在内涂层12的除去部分12’上形成Co基类合金层即CoNiCrAlY层17,从而对内涂层12修补完毕(参照图3C)。进而将所述屏蔽材15及喷镀枪16除去后,在外涂层13的除去部分13’上通过EB-PVD法形成由ZrO2-Yb2O3构成的外涂层23,从而修补完毕(参照图3D)。
根据实施例3,与实施例1相同,由于不须要如以往所示对整个动叶重新涂层,所以可以降低成本,同时除可以提高内涂层12和外涂层23的耐久性外,由于通过EB-PVD法形成外涂层23,所以也可以进一步提高外涂层23的耐久性。
Claims (4)
1、一种Ni合金制部件的修补方法,是在Ni基合金制母材上形成内涂层和外涂层的Ni基合金制部件中,在所述外涂层上具有损坏时的修补方法,其特征在于,包括除去具有损坏的外涂层的损坏部和相对于该损坏部的内涂层的变质部的工序;在减压下以喷镀粒子速度低于300m/s、母材温度600℃以下,在内涂层的除去部上进行喷镀形成与所述内涂层材料不同的另外内涂层的工序;以及在外涂层的除去部上形成与所述外涂层材料不同的另外外涂层的工序。
2、根据权利要求1所述的Ni基合金制部件的修补方法,其特征在于,作为另外的内涂层是使用由耐氧化优良的材料构成的层。
3、根据权利要求1所述的Ni基合金制部件的修补方法,其特征在于,作为另外的外涂层是使用由耐氧化优良的材料构成的层。
4、根据权利要求1所述的Ni基合金制部件的修补方法,其特征在于,在内涂层的除去部上进行喷镀后,通过电子束物理蒸镀法在外涂层的除去部位上形成另外外涂层。
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EP1591561A1 (de) * | 2004-04-28 | 2005-11-02 | ALSTOM (Switzerland) Ltd | Verfahren zum Aufbringen einer schützenden Beschichtung auf ein thermisch beanspruchtes Bauteil |
EP1798302A4 (en) * | 2004-08-23 | 2009-12-02 | Toshiba Kk | METHOD AND DEVICE FOR REPAIRING A ROTOR |
JP4680067B2 (ja) * | 2006-01-05 | 2011-05-11 | 株式会社日立製作所 | タービン翼の補修方法及びタービン翼 |
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JP5574683B2 (ja) * | 2009-11-30 | 2014-08-20 | 三菱重工業株式会社 | 補修方法およびそれにより補修されたガスタービンの耐熱部材 |
DE102011086803A1 (de) | 2011-11-22 | 2013-05-23 | Ford Global Technologies, Llc | Reparaturverfahren einer Zylinderlauffläche mittels Plasmaspritzverfahren |
DE102013200912B4 (de) | 2012-02-02 | 2018-05-30 | Ford Global Technologies, Llc | Kurbelgehäuse |
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