CN114616292A - 用于压实涡轮发动机部件的抗腐蚀涂料的方法 - Google Patents
用于压实涡轮发动机部件的抗腐蚀涂料的方法 Download PDFInfo
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Abstract
本发明涉及对机械部件(1)的包括金属颗粒的抗腐蚀涂料进行压实的方法，机械部件例如为涡轮发动机部件，该机械部件(1)沿纵向轴线X延伸并且包括径向外表面，径向外表面涂覆有抗腐蚀涂料的第一层(4，4’)。根据本发明，该方法包括如下的至少一个步骤：在抗腐蚀涂料的所述第一层(4，4’)上产生激光射束(11)，以使金属颗粒接触并且使抗腐蚀涂料导电。
Description
技术领域
本发明涉及机械部件抗腐蚀的表面处理或表面制备的领域。本发明特别旨在一种用于对涂覆部件(特别是涡轮发动机部件)的抗腐蚀涂料进行压实的方法。
背景技术
机械部件(特别是在飞行器涡轮发动机中使用的部件)暴露在温度、腐蚀性物质以及氧化反应等恶劣环境中。部件(例如压缩机和/或涡轮轴)例如由具有减少的钴含量的钢或钢合金制成，以具有高的机械强度。这些钢对腐蚀现象非常敏感，腐蚀现象主要表现为腐蚀坑的发展，腐蚀坑包括局部且深层的侵蚀。在涡轮发动机的运行期间，这些部件还受到强烈的机械应力，这可能导致腐蚀的发展。应力/腐蚀的协同作用导致腐蚀现象显著增加。
一些部件涂覆有耐高温且耐各种腐蚀性物质和氧化性物质(煤油、油等)的涂料，使得部件能够承受部件逐步发展所处的环境，特别地保护部件免受腐蚀。部分由三氧化铬组成的涂料被分类为CMR，CMR是致癌性(Carcinogenic)、致突变性(Mutagenic)、还原性(Reprotoxic)的缩写，受到法规“REACH”(化学品的注册、评估、授权和限制，Registration，Evaluation，Authorization and Restriction of Chemical substances)的打击。
为了避免该规定的限制，开发了包括使涂料阳极化的解决方案。在文献FR-A1-2991216和FR-A1-3040013中描述了该解决方案的示例。特别地，这种解决方案包括向部件的表面喷涂具有矿物质粘合剂的且载有金属颗粒的液体涂料。该涂料通过被操作者或机械臂操控的枪喷涂，然后涂覆有涂料的部件在烘箱中被加热，以使喷涂的涂料聚合。然后，聚合的涂料经历机械作用(例如压实)，以根据所执行的压实的类型使金属颗粒接触而不降低涂料的外观和物理方面。该作用使得能够在涂料的金属颗粒和待处理的金属部分之间实现电连续性。涂料层因此变得致密且导电，以使得涂料层代替被保护的部件的金属成为将优先腐蚀的牺牲层。我们用阳极涂料来表示变得导电的牺牲层。
压实包括在聚合之后用白色刚玉颗粒、玻璃珠或塑料颗粒对涂覆有涂料的部分进行打磨或喷射。然而，用于压实的颗粒可以嵌入在涂料中以及嵌入在涂料的表面上。在运行期间，这些颗粒可能发生释放，这可能会损坏涡轮发动机的在可能具有非常高的硬度的这些颗粒的路径中的其他构件(轴承滚动件)，这些颗粒例如为刚玉(MOHM量表上为9.5)。
为了限制非常硬的颗粒的释放，特别是在非常高的速度下的释放，一些部件没有被压实，这导致涂层的抗腐蚀性能降低。另一个替代方案是用顶部涂层来涂覆压实的抗腐蚀涂料，以在涂料中容纳任何颗粒，这延长了部件的制造时间，更不用说在应用涂料之前、在应用涂料期间以及在应用涂料之后制备部件所需的各种步骤了。此外，涂料的不同层的厚度的控制是精细的，特别是对于具有复杂构造的部件。
发明内容
特别地，本发明的一个目的是提供一种简单且有效的解决方案，该解决方案使得能够提供抗腐蚀涂料的致密化，以增加腐蚀保护，而不使硬颗粒结壳(incrustation)，同时避免抗腐蚀涂料的劣化。
这是按照本发明通过对机械部件的包括金属颗粒的抗腐蚀涂料进行压实的方法来实现的，机械部件例如为涡轮发动机部件，机械部件沿纵向轴线X延伸并且包括径向外表面，该径向外表面涂覆有抗腐蚀涂料的第一层，该方法包括如下的至少一个步骤：在抗腐蚀涂料的第一层上产生激光射束，以使金属颗粒相互接触并且使抗腐蚀涂料导电。
因此，该解决方案使得能够实现上述目的。特别地，至少一个激光射束的使用避免了当机械部件被驱动旋转时可能释放的介质(塑料、陶瓷、金属等)的使用。这种类型的压实使铝基金属颗粒相互接触以获得导电性，从而获得抗腐蚀性能，且这种类型的压实是通过向表面提供能量来实现的。这种能量提供将使得能够改变颗粒的材料的状态，使得颗粒彼此聚集(agglomérer)。因此，涂料的物理完整性被保留。最后，这种方法可以容易地进行自动化，并且使得能够克服外来颗粒的释放，而不需要施加顶部涂层，从而减少制造时间和成本。
该方法还包括被单独采用或组合采用的以下特征或步骤中的一项或多项：
-该方法包括将机械部件安装在旨在接纳惰性气体的外壳中的步骤，惰性气体例如为氮气或氩气。
-通过将金属颗粒加热到温度阈值来确定金属颗粒的接触，温度阈值小于或等于金属颗粒的材料的熔融温度。
-激光射束的功率介于200W至1000W之间。
-激光射束包括单个射束，该单个射束的发射波长介于1000nm至1500nm之间。
-激光射束沿着螺旋形路径扫描在该部件上的抗腐蚀涂料的第一层。
-该方法包括沿着与纵向轴线X正交的第一方向移动激光射束的步骤，机械部件围绕纵向轴线旋转并且沿纵向轴线平移。
-机械部件是中空的。
-机械部件包括径向内表面，该径向内表面涂覆有抗腐蚀涂料的第二层，激光射束在机械部件内部产生并且在机械部件内部反射以到达抗腐蚀涂料的第二层，激光射束沿着螺旋形路径扫描抗腐蚀涂料的第二层。
-机械部件是涡轮发动机轴。
-该方法包括沿着与纵向轴线正交的第一方向和与纵向轴线平行的第二方向移动激光源的步骤，机械部件围绕纵向轴线旋转。
-激光器是Nd:YAG类型的。
-涂料中的金属颗粒包括铝。
本发明涉及用于制造阳极涂层的方法，该方法包括以下步骤：
-提供具有纵向轴线的机械部件，
-将载有金属颗粒的液体涂料喷涂到机械部件的至少一个表面上，
-使喷涂在部件上的涂料聚合以获得旨在保护部件的抗腐蚀涂料的层，
-压实抗腐蚀涂料以获得阳极涂料，压实包括在所述抗腐蚀涂料的方向上至少一次地投射激光射束，以使金属颗粒接触并且使抗腐蚀涂料导电。
本发明还涉及使用来自至少一个激光源的激光射束，以对涂覆了机械部件(特别是涡轮发动机部件)的抗腐蚀涂料进行压实。
本发明还涉及一种机械部件，特别是涡轮发动机的机械部件，该机械部件至少部分涂覆有根据上述方法压实的抗腐蚀涂料。
最后，本发明涉及用于执行对机械部件进行压实的方法的压实设备，该压实设备包括：
-外壳；
-具有纵向轴线的机械部件，该机械部件包括至少一个径向外表面，该径向外表面涂覆有包括金属颗粒的第一抗腐蚀涂料层，该机械部件被安装在外壳中；以及
-压实装置，该压实装置包括激光源，激光源旨在产生朝向第一涂料层的至少一个激光射束，以使金属颗粒接触并使抗腐蚀涂料导电。
附图说明
通过阅读本发明的以完全说明性的且非限制性的示例给出的实施例的以下详细的说明性描述，并且参照示意性附图，本发明将被更好地理解，并且本发明的其他目的、细节、特征以及优点将变得更加清楚，在附图中：
[图1]图1是机械部件(例如涡轮发动机轴)的示意性轴线截面视图，该机械部件被安装在根据本发明的压实设备的外壳中；
[图2]图2是根据本发明的机械部件的示意性径向横截面视图，该机械部件在其径向内表面和外表面上包括涂料层；
[图3]图3示出了根据本发明的用于制造涂料的层的压实装置的布置，该涂料的层被布置在中空的部件内部，并且是导电的；
[图4]图4示意性地示出了激光在根据本发明的机械部件的径向外表面上的扫描路径；
[图5]图5示意性地示出了根据本发明的具有被激光热影响的区域的抗腐蚀涂料层。
具体实施方式
图1至图3示出了在用于压实抗腐蚀涂料的设备中的机械部件1(特别是飞行器涡轮发动机的机械部件)的轴向截面，该抗腐蚀涂料涂覆了机械部件1的至少一个表面。
“机械部件”是指旨在确保运行中的机械功能的部件，这意味着这些部件具有良好的机械强度和良好的耐腐蚀性和耐磨性。因此，涡轮发动机轴(特别是压缩机轴和/或涡轮轴)是本发明所关注的机械部件的示例。通常，涡轮发动机轴由金属材料或金属合金制成。金属材料或金属合金包括例如钢。
如在图1至图3中可以看到，机械部件1是沿纵向轴线X延伸的涡轮发动机轴。涡轮发动机轴在此是中空的。轴包括沿着垂直于纵向轴线X的径向轴线Z彼此相对的径向外表面2和径向内表面3。
回想起在采用压实方法之前，如在图2中示意性地示出，部件1的径向外表面涂覆有抗腐蚀涂料的第一层4。涂料是无机涂料或包括金属颗粒的任何涂料。特别地，载有金属颗粒的液体涂料被喷涂在部件的表面上。有利地，金属颗粒是铝颗粒。施加到部件的表面的抗腐蚀涂料的示例是以品牌名称为Sermetel 
或Maberbind
而已知的涂料。
喷涂涂料之后，使被涂覆的部件1聚合，使得涂料硬化并且形成旨在保护部件的抗腐蚀涂料。
然后将抗腐蚀涂料压实。为此，压实是在压实设备5中执行的。在本发明中，术语“压实”指的是在涂覆有金属颗粒涂料层的部件的表面外部使用能量，以至少部分地改变材料的状态并且使金属颗粒接触。这样，抗腐蚀涂料被致密化，金属颗粒与涂料的接触增加了其耐腐蚀性。涂料具有导电性。因此我们得到阳极涂层。
设备5包括压实装置6，压实装置配备有连接到能量源的头部7，能量源旨在向抗腐蚀涂料的第一层4的表面提供能量。该能量源由设备的电子命令系统8控制。通常，电子命令系统8配备有至少一个微控制器9和存储器10，许多压实参数被存储在该存储器中。
在本示例中，能量源被构造成产生或发射至少一个主激光射束11到对机械涡轮发动机部件进行涂覆的涂料上。激光射束的输出传输波长介于紫外(UV)和红外(IR)之间。激光的功率介于200瓦(W)至1000瓦之间。
压实装置6有利地安装在为此而提供的外壳12中。外壳12例如通过门部而闭合，部件1穿过该门部被引入。激光射束11的产生是在气体保护下进行的，以避免在金属颗粒的加热或温度升高期间涂料的任何氧化，并且保持涂料的抗腐蚀性能。使用的气体是惰性气体，例如氩气或氮气。
有利地，惰性气体流通过与激光射束同轴的至少一个喷嘴13喷射，使得最关键的区域(直接接收激光射束)持续地受到中性气氛的保护。电子命令系统8还连接到惰性气体流喷射喷嘴。可替代地，惰性气体流是通过布置在激光射束附近的喷嘴喷射的，使得气体流保护关键区域以及也保护关键区域周围的环境。
通过将金属颗粒加热到温度阈值来确定金属颗粒的接触，温度阈值小于或等于金属颗粒的材料的熔融温度。在该示例中，铝金属颗粒的熔融温度约为660℃。由于粘合剂的热收缩(硅酸盐网状结构的收缩)和金属颗粒的蠕变，低于金属的熔融温度的温度阈值是可能的。
金属颗粒(和涂料层)的加热由激光射束的聚焦和线能量密度限定。特别地，通过调节光阑的开口来控制射束的聚焦，光阑使得能够管理激光射束的尺寸。如下所述，颗粒的材料的加热导致方向的改变。
激光的线能量密度(LE)是根据涂料的参数(厚度、行为等)及其导电性能来调节的。在本发明中，线能量密度对应于激光功率P(以焦耳(J)/秒(s)表示)与激光的扫描速度V(以毫米(mm)/s表示)之间的比。线能量密度以J/mm表示。实际上，过低的线能量密度可能会产生颗粒之间缺乏连接的类型的缺陷，并且可能降低牺牲层的导电性能的质量。另一方面，过多的能量可能导致铝颗粒熔融过多，并导致不均匀的涂料层(孔隙率、厚度)。
有利地但非限制性地，激光源是掺杂有钕的Nd:YAG(钇铝石榴石，yttriumaluminium garnet)类型。这种类型的激光产生了与用于本申请的能量需求匹配的能量。激光射束的发射波长约为1064纳米(nm)。激光射束的功率介于200瓦(W)至400瓦之间。
参照图4，为了在涂料层4中提供均匀的导电性，沿着螺旋形路径110或螺旋型路径执行激光在抗腐蚀涂料上的扫描。在此，涂料的厚度介于20μm至90μm之间。激光射束被施加到涂料的表面，其中，重叠率Re约为10％，带宽Lb约为1mm。线能量密度取决于源、激光射束的聚焦以及涂料的类型。
在本发明中，术语“螺旋形路径”是指激光射束在抗腐蚀涂料上的路径，该路径对应于激光射束相对于部件，或部件相对于激光射束，沿第一方向的平移移位以及在与第一方向正交的平面中的旋转移位。
在一个实施例中，涡轮发动机轴围绕纵向轴线X旋转并且沿着纵向轴线移动，并且优选地同时围绕纵向轴线X旋转和沿纵向轴线移动。有利地，轴的移位是平移。为此，压实设备5包括安装在框架15上的用于使轴旋转的元件14。安装在框架上的引导轴承16使得轴能够相对于框架旋转。有利地，旋转元件14是电动马达或热马达。该马达连接到电子命令系统8，电子命令系统控制马达在一个方向上或另一个方向上的旋转。类似地，激光的产生头部7沿着平行于径向轴线Z的方向r移动。这也是平移。换言之，激光的产生头部沿方向l和方向t将是静止的。该词用于激光头部的移位。头部7将沿着r方向移动，以调整激光的聚焦，并且适应涡轮发动机轴的几何形状。旋转的轴以预定的螺距前进。螺距可以约为1mm/转。涡轮发动机轴的旋转和平移的结合将使得激光能够沿着螺旋形路径扫描。有利地但非限制性地，电子命令系统连接到压实装置6，以控制头部7的移位。
在另一实施例中，涡轮发动机轴围绕纵向轴线旋转，并且压实装置6的头部7沿着方向r和平行于纵向轴线X的方向移动，以实现激光沿着螺旋形路径的扫描。
在本实施例中，轴的径向内表面3还包括被称为“第二涂料层”4’的包括金属颗粒的抗腐蚀涂料层。该抗腐蚀涂料的第二层4’与第一层4相同。替代地，第一层4和第二层4’是不同的。
为了达到涂料的第二层4、4’(位于轴内部)，偏转构件17安装在涡轮发动机轴内部。偏转构件17枢转地安装在轴内部，偏转构件的枢转由电子命令系统8控制，偏转构件连接到该电子命令系统。有利地，偏转构件17是偏转镜子。这样，射到镜子上的激光射束反射到涂料的第二层上。该第二涂料层4’的扫描以与第一涂料层4相同的方式进行，即按照螺旋形路径。
图5示出了厚度在20μm至90μm的范围内的、具有铝颗粒的抗腐蚀涂料层4或4’。根据激光射束的聚焦，铝颗粒将或多或少地扩散到涂料层的整个厚度。例如，100％的聚焦产生了区域Z1，区域Z1的深度近似等于涂料层的厚度。另一方面，约40％的聚焦产生了区域Z2，区域Z2的深度小于涂料层4、4’的厚度。
我们现在将描述使用以上所描述的设备5压实涡轮发动机部件的方法。该方法包括将机械部件安装在外壳12中的步骤。部件被电子命令系统8旋转。与旋转步骤同时地或在旋转步骤之后，在涂覆部件1的涂料层4上产生激光射束。机械部件1也沿着纵向轴线平移移动，使得激光沿着螺旋形路径扫描涂料层。在该产生步骤期间，能量供应将允许使铝颗粒的温度达到与铝颗粒的熔融温度对应的值或达到低于铝颗粒的熔融温度的值，使得颗粒熔融或者部分熔融并且能够彼此聚集。我们理解，这使得金属颗粒能够改变方向或者移位以进行接触。接触的颗粒实现了电连续性。此外，与激光的产生步骤同时地，惰性气体被喷射到外壳中。
随后，将镜子(偏转构件17)安装在中空的部件内，并且也沿着螺旋形路径用激光射束扫描第二层4’。
Claims (13)
1.对机械部件(1)的包括金属颗粒的抗腐蚀涂料进行压实的方法，所述机械部件例如为涡轮发动机部件，所述机械部件(1)沿纵向轴线X延伸并且包括径向外表面(2)，所述径向外表面涂覆有抗腐蚀涂料的第一层(4，4’)，其特征在于，所述方法包括如下的至少一个步骤：在抗腐蚀涂料的所述第一层(4，4’)上产生激光射束(11)，以使所述金属颗粒接触并且使所述抗腐蚀涂料导电。
2.根据前一项权利要求所述的方法，其特征在于，所述方法包括将所述机械部件(1)安装在旨在接纳惰性气体的外壳(12)中的步骤，所述惰性气体例如为氮气或氩气。
3.根据前述权利要求中任一项所述的方法，其特征在于，通过将所述金属颗粒加热到温度阈值来确定所述金属颗粒的接触，所述温度阈值小于或等于所述金属颗粒的材料的熔融温度。
4.根据前述权利要求中任一项所述的方法，其特征在于，所述激光射束的功率介于200W至1000W之间。
5.根据前述权利要求中任一项所述的方法，其特征在于，所述激光射束包括单个射束，所述单个射束的发射波长介于1000nm至1500nm之间。
6.根据前述权利要求中任一项所述的方法，其特征在于，所述激光射束沿着螺旋形路径扫描在所述机械部件(1)上的抗腐蚀涂料的所述第一层(4，4’)。
7.根据前一项权利要求所述的方法，其特征在于，所述方法包括沿着与所述纵向轴线X正交的第一方向移动所述激光射束(11)的步骤，所述机械部件(1)围绕所述纵向轴线X旋转并且沿着所述纵向轴线X平移。
8.根据前述权利要求中任一项所述的方法，其特征在于，所述机械部件(1)是中空的。
9.根据前一项权利要求所述的方法，其特征在于，所述机械部件(1)包括径向内表面(3)，所述径向内表面涂覆有抗腐蚀涂料的第二层(4’)，所述激光射束(11)在所述机械部件(1)内部产生并且在所述机械部件内部反射以到达所述抗腐蚀涂料的第二层(4’)，所述激光射束(11)沿着螺旋形路径扫描所述抗腐蚀涂料的第二层(4’)。
10.根据前述权利要求中任一项所述的方法，其中，所述机械部件是涡轮发动机轴。
11.根据前述权利要求中任一项所述的方法，其特征在于，激光器是Nd:YAG类型的。
12.根据前述权利要求中任一项所述的方法，其特征在于，所述涂料的金属颗粒包括铝。
13.根据前述权利要求中任一项所述的方法，其中，所述抗腐蚀涂料通过以下方法施加：将载有金属颗粒的液体涂料喷涂到所述机械部件的至少一个表面上，并且使喷涂在所述部件上的涂料聚合，以获得旨在保护所述部件的抗腐蚀涂料的层。
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR1912298 | 2019-10-31 | ||
| FR1912298A FR3102687B1 (fr) | 2019-10-31 | 2019-10-31 | Procede de compactage d’une peinture anti-corrosion d’une piece de turbomachine |
| PCT/FR2020/051943 WO2021084202A1 (fr) | 2019-10-31 | 2020-10-27 | Procede de compactage d'une peinture anti-corrosion d'une piece de turbomachine |
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| CN114616292A true CN114616292A (zh) | 2022-06-10 |
| CN114616292B CN114616292B (zh) | 2023-10-20 |
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| Country | Link |
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| US (1) | US20220410208A1 (zh) |
| EP (1) | EP4051826A1 (zh) |
| CN (1) | CN114616292B (zh) |
| FR (1) | FR3102687B1 (zh) |
| WO (1) | WO2021084202A1 (zh) |
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| FR3122342A1 (fr) * | 2021-04-30 | 2022-11-04 | Safran Aircraft Engines | Procede de compactage d’une peinture anti-corrosion d’une piece de turbomachine |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1583835A (en) * | 1977-03-28 | 1981-02-04 | Avco Everett Res Lab Inc | Metal surface modification |
| US4847112A (en) * | 1987-01-30 | 1989-07-11 | Centre De Recherches Metallurgiques-Centrum Voor Research In De Metallurgie | Surface treatment of a rolling mill roll |
| FR3040013A1 (fr) * | 2015-08-13 | 2017-02-17 | Snecma | Procede de compactage d'une peinture anti-corrosion d'une piece de turbomachine |
| FR3060608A1 (fr) * | 2016-12-20 | 2018-06-22 | Safran Helicopter Engines | Procede de fabrication d'une structure abradable pour une turbomachine |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4042349A1 (de) * | 1990-06-08 | 1991-12-19 | Fraunhofer Ges Forschung | Verfahren zur oberflaechenbehandlung von werkstuecken mit laserstrahlung |
| US5066846A (en) * | 1990-06-26 | 1991-11-19 | Westinghouse Electric Corp. | System and method for laser welding the inner surface of heat exchanger tubes |
| US7411150B2 (en) * | 2002-06-12 | 2008-08-12 | Alstom Technology Ltd. | Method of producing a composite component |
| SE0203224D0 (sv) * | 2002-10-31 | 2002-10-31 | Cerbio Tech Ab | Method of making structured ceramic coatings and coated devices prepared with the method |
| US20100136296A1 (en) * | 2006-11-30 | 2010-06-03 | United Technologies Corporation | Densification of coating using laser peening |
| FR2991216B1 (fr) | 2012-05-29 | 2014-07-04 | Snecma | Procede de compactage de peintures anodiques avec collision des jets de sablage |
-
2019
- 2019-10-31 FR FR1912298A patent/FR3102687B1/fr active Active
-
2020
- 2020-10-27 US US17/771,738 patent/US20220410208A1/en active Pending
- 2020-10-27 EP EP20807835.2A patent/EP4051826A1/fr active Pending
- 2020-10-27 CN CN202080075349.5A patent/CN114616292B/zh active Active
- 2020-10-27 WO PCT/FR2020/051943 patent/WO2021084202A1/fr unknown
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1583835A (en) * | 1977-03-28 | 1981-02-04 | Avco Everett Res Lab Inc | Metal surface modification |
| US4847112A (en) * | 1987-01-30 | 1989-07-11 | Centre De Recherches Metallurgiques-Centrum Voor Research In De Metallurgie | Surface treatment of a rolling mill roll |
| FR3040013A1 (fr) * | 2015-08-13 | 2017-02-17 | Snecma | Procede de compactage d'une peinture anti-corrosion d'une piece de turbomachine |
| FR3060608A1 (fr) * | 2016-12-20 | 2018-06-22 | Safran Helicopter Engines | Procede de fabrication d'une structure abradable pour une turbomachine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114616292B (zh) | 2023-10-20 |
| FR3102687B1 (fr) | 2021-10-15 |
| FR3102687A1 (fr) | 2021-05-07 |
| WO2021084202A1 (fr) | 2021-05-06 |
| EP4051826A1 (fr) | 2022-09-07 |
| US20220410208A1 (en) | 2022-12-29 |
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