CN103157907A - 用于激光加工具有陶瓷层的层系统的方法 - Google Patents
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- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
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- B23K2103/16—Composite materials, e.g. fibre reinforced
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- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
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Abstract
用于激光加工具有陶瓷层的层系统的方法,由于陶瓷层(7)在其加工之前有意的增厚部而可能的是,连同杂质(16)一起去除所述增厚部。
Description
技术领域
本发明涉及具有陶瓷层的层系统的激光加工。
背景技术
如涡轮机叶片的高温构件具有用于隔热的外部的陶瓷层。所述陶瓷隔热层施加在金属增附层或者金属基底上。此外,在这种高温部件中引入贯通孔,所述贯通孔穿过陶瓷层并且进入或者穿过金属基底。在此,必须注意的是,不污染陶瓷层的外表面。这通常通过遮盖实现。
发明内容
因此,本发明的目的是解决该问题。所述目的通过一种用于激光加工层系统的方法来实现,其中所述层系统具有至少一个金属基底和外部的陶瓷层,其中在对所述构件执行完整的激光加工,尤其制造多个贯通孔,更尤其是制造具有附加的扩散部的贯通孔之后,在后处理步骤中降低所述层的层厚度。
在本文中列出其他有利的措施,所述措施能够任意地彼此组合,以便实现其他的优点。
附图说明
其示出:
图1示出根据本发明的方法的过程,
图2示出涡轮机叶片,
图3示出超合金列表。
具体实施方式
附图和描述仅代表本发明的实施例。
图1示出所加工的构件1、120、130、155作为层系统。尤其根据图3所示,构件1具有金属基底4,所述金属基底尤其在涡轮机叶片120、130中是镍基和/或钴基的。在基底4上直接地存在陶瓷层7或者金属增附层(未示出),必要时具有直接在陶瓷层之下、即在基底上或者在金属增附层(MCrAlX)上的氧化铝层。陶瓷层7优选是二氧化锆层或者黄绿石层(Pyrochlorschicht)或者两者的组合。能够考虑其他的陶瓷材料。
孔,优选是贯通孔19应当穿过始于陶瓷层7的外表面13的层系统产生,如虚线所示;至少去除金属材料。加工通过能量束来进行,其中所述能量束优选能够是电子束或者激光器10的激光束11。在加工金属材料(增附层和/或基底4)时,金属飞溅物会沉积在外表面13上。这当然是不期望的,因为所述金属飞溅物在稍后的使用中能够氧化并且能够损害陶瓷层7。
根据现有技术,在此在表面13上施加粉末层或者大面积地施加特殊的机械覆盖部。
根据本发明,外部的层7具有厚度d,但是所述厚度大于制成的构件1、120、130、155的层7’期望的最终尺寸d’。不使用掩模并且容许堆积部16,其中所述堆积部通过降低层厚度d而被一起去除。
要剥离的区域d-d’优选为30μm至80μm。
为了改变具有层厚度d的层7的层厚度,能够应用激光工艺或者磨光工艺,使得因此最终产物的层7’的表面13’没有任何的金属飞溅物16。
在如涡轮机叶片120、130的具体的构件中可能的是,仅叶身具有借助激光器10制造的冷却空气孔19。因此,能够在叶身的区域中仅局部地提高陶瓷层7的层厚度并且在叶身形状上已经具有最终尺寸。
更厚的层7能够极其简单地通过如HVOF(高速氧燃料喷涂)或者等离子喷涂方法的已知的覆层方法来制造,因为这本来就通过逐层的涂覆来进行并且能够通过其他的涂覆层(30μm-80μm)来简单地形成增加的层厚度。
图2在立体图中示出流体机械的沿着纵轴线121延伸的转子叶片120或导向叶片130。
所述流体机械可以是飞机的或用于发电的发电厂的燃气轮机,也可以是蒸汽轮机或压缩机。
叶片120、130沿着纵轴线121相继具有:固定区域400、邻接于固定区域的叶片平台403以及叶身406和叶片梢部415。
作为导向叶片130,叶片130可以在其叶片梢部415处具有另一平台(未示出)。
在固定区域400中形成有用于将转子叶片120、130固定在轴或盘上的叶片根部183(未示出)。叶片根部183例如构成为锤头形。作为枞树形根部或燕尾形根部的其他构形是可行的。叶片120、130对于流过叶身406的介质具有迎流棱边409和出流棱边412。
在传统叶片120、130中,在叶片120、130的所有区域400、403、406中使用例如实心的金属材料、尤其是超合金。例如由EP 1204776B1、EP 1306454、EP 1319729A1、WO 99/67435或WO 00/44949已知这样的超合金。在这种情况下,叶片120、130可以通过铸造法,也可以借助定向凝固、通过锻造法、通过铣削法或其组合来制造。
将带有一个或多个单晶结构的工件用作机器的在运行中承受高的机械的、热的和/或化学的负荷的构件。这种单晶工件的制造例如通过由熔融物的定向凝固来进行。在此,这涉及一种浇注法,其中液态金属合金凝固为单晶结构、即单晶工件,或者定向凝固。在这种情况下,枝状晶体沿热流定向,并且形成柱状晶体的晶粒结构(柱状地,这就是说在工件的整个长度上分布的晶粒,并且在此根据一般的语言习惯称为定向凝固),或者形成单晶结构,这就是说整个工件由唯一的晶体构成。在这些方法中,必须避免过渡成球形(多晶的)凝固,因为通过非定向的生长不可避免地构成横向和纵向晶界,所述横向和纵向晶界使定向凝固的或单晶的构件的良好特性不起作用。如果一般性地提到定向凝固组织,则是指不具有晶界或最多具有小角度晶界的单晶和确实具有沿纵向方向分布的晶界但不具有横向晶界的柱状晶体结构。第二种所提到的晶体结构也称为定向凝固组织(directionally solidified structures)。由US-PS 6,024,792和EP 0892090A1已知这样的方法。
叶片120、130同样可以具有抗腐蚀或抗氧化的覆层,例如(McrAlX;M是铁(Fe)、钴(Co)、镍(Ni)中的至少一种元素,X是活性元素并代表钇(Y)和/或硅和/或至少一种稀土元素,或铪(Hf))。由EP 0486489B1、EP 0786017B1、EP 0412397B1或EP 1306454A1已知这样的合金。密度优选地是理论密度的95%。在(作为中间层或最外层的)MCrAlX层上形成保护性氧化铝层(TGO=thermal grown oxide layer(热生长氧化层))。
优选地,层成分具有Co-30Ni-28Cr-8Al-0.6Y-0.7Si或Co-28Ni-24Cr-10Al-0.6Y。除这些钴基保护覆层外,也优选地使用镍基保护层,例如Ni-10Cr-12Al-0.6Y-3Re或Ni-12Co-21Cr-11Al-0.4Y-2Re或Ni-25Co-17Cr-10Al-0.4Y-1.5Re。
在MCrAlX上还可以有隔热层,隔热层优选是最外层并例如由ZrO2、Y2O3-ZrO2组成,即,隔热层通过氧化钇和/或氧化钙和/或氧化镁非稳定、部分稳定或完全稳定。隔热层覆盖整个MCrAlX层。通过例如电子束气相淀积(EB-PVD)的适当的覆层方法在隔热层中产生柱状晶粒。其他覆层方法也是可以考虑的,例如气相等离子喷涂(APS)、LPPS(低压等离子喷涂)、VPS(真空等离子喷涂)或CVD(化学气相沉积)。隔热层可以具有多孔的、有微观裂缝或宏观裂缝的晶粒,用于更好地耐热冲击。因此,隔热层优选地比MCrAlX层更为多孔。
再加工(Refurbishment)意味着在使用构件120、130之后,必要时必须将保护层去除(例如通过喷砂)。接着,去除腐蚀层和/或氧化层及腐蚀产物和/或氧化产物。必要时,还修复在构件120、130中的裂缝。然后,进行构件120、130的再覆层以及构件120、130的重新使用。
叶片120、130可以构造成空心的或实心的。如果要冷却叶片120、130,则叶片为空心的并且必要时还具有薄膜冷却孔418(由虚线表示)。
Claims (5)
1.用于激光加工层系统(1、120、130、155)的方法,其中所述层系统(1,120,130,155)具有至少一个金属基底(4)和外部的陶瓷层(7),其中,在对所述构件(1,120,130,155)执行完整的激光加工,尤其制造多个贯通孔,更尤其是制造具有附加的扩散部的贯通孔之后,在后处理步骤中降低所述层(7)的层厚度(d)。
2.根据权利要求1所述的方法,其中应用激光方法来减小所述层(7)的所述层厚度(d)。
3.根据权利要求1或者2中的一项或者两项所述的方法,其中使用磨光方法来减小所述层(7)的所述层厚度(d)。
4.根据权利要求1、2或3中的一项或多项所述的方法,其中将所述层(7)的所述层厚度(d)降低30μm至80μm。
5.根据权利要求1至4中的一项或多项所述的方法,其中对于所述层系统(1,120,130,155)的所述激光加工而言,对所述陶瓷层(7)不使用掩模。
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EP11193801.5A EP2604377B1 (de) | 2011-12-15 | 2011-12-15 | Verfahren zur Laserbearbeitung eines Schichtsystems mit keramischer Schicht |
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CN104827194A (zh) * | 2015-05-13 | 2015-08-12 | 西安交通大学 | 用水—二氧化硅作为涡轮叶片激光加工中的后壁防护方法 |
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CN110860785A (zh) * | 2019-11-21 | 2020-03-06 | 中国航空制造技术研究院 | 一种用于超快激光去除加工的边缘防护方法 |
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- 2011-12-15 EP EP11193801.5A patent/EP2604377B1/de not_active Not-in-force
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2012
- 2012-12-10 US US13/709,100 patent/US20130153555A1/en not_active Abandoned
- 2012-12-17 CN CN2012105483004A patent/CN103157907A/zh active Pending
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CN104827194A (zh) * | 2015-05-13 | 2015-08-12 | 西安交通大学 | 用水—二氧化硅作为涡轮叶片激光加工中的后壁防护方法 |
Also Published As
Publication number | Publication date |
---|---|
EP2604377B1 (de) | 2015-07-15 |
EP2604377A1 (de) | 2013-06-19 |
US20130153555A1 (en) | 2013-06-20 |
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