CN101429893B - 气冷燃气轮机部件及其制造和修理方法 - Google Patents
气冷燃气轮机部件及其制造和修理方法 Download PDFInfo
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Abstract
一种适用于燃气涡轮发动机的部件。所述部件包括限定所述部件表面的基底,并具有第一表面和第二表面。至少一个孔口从所述第一表面至所述第二表面延伸通过所述基底,并具有第一开口区域。部件具有在邻近所述至少一个孔口的所述第一表面和所述第二表面的至少一个上的第一涂层。部件还具有覆盖邻近所述至少一个孔口的所述第一涂层的第二涂层,使得所述第一涂层的至少一部分在邻近所述至少一个孔口处被暴露。所述第一涂层限定小于所述第一开口区域的第二开口区域。另一方面,一种制造适用于燃气涡轮发动机的部件的方法,包括如下步骤:由具有第一表面和第二表面的基底形成所述部件,从所述第一表面到所述第二表面穿过所述基底形成具有第一开口区域的至少一个孔口,涂覆第一涂层至邻近所述至少一个孔口的所述第一表面和所述第二表面的至少一个上,所述孔口至少部分地保持不受第一涂层的阻碍,涂覆第二涂层至邻近所述至少一个孔口的所述第一涂层上,所述孔口至少部分地保持不受所述第二涂层的阻碍,以及从所述孔口去除第二涂层,留下大部分或整个所述第一涂层以限定小于所述第一开口区域的第二开口区域。在另一方面,一种修理适用于燃气涡轮发动机的部件的方法,包括如下步骤,从所述部件去除涂层,修理在部件的基底中的任何缺陷,并如上所述涂覆涂层。
Description
相关申请的交叉引用
本申请要求2007年10月18日提交的美国临时申请NO.60/981066的优先权。
技术领域
本发明总体涉及一种燃气涡轮发动机,尤其涉及一种用在燃气轮机中的气冷部件,以及制造和修理这种部件的方法。
背景技术
燃气涡轮发动机包括压缩机,其用来压缩与燃料混合并导入燃烧器的空气,其中,混合物在燃烧室内部点燃以产生热的燃烧气体。至少一些已知的燃烧器包括拱形组件、整流罩和衬套以引导燃烧气体至涡轮,该涡轮从燃烧气体中吸取能量以向压缩机提供动力,同时产生有用功以推进飞行中的飞行器或向负载(例如发电机)提供动力。衬套由整流罩连接至拱形组件,并且从整流罩向下游延伸以限定燃烧室。
燃气涡轮发动机内的运行环境在热和化学方面是不利的。通过对铁、镍和钴基超级合金的配制实现了高温合金的重要进展,但是如果由这些合金形成的部件位于燃气涡轮发动机的某个部位(例如涡轮、燃烧器或增压器)时,那么这些部件通常不能承受长期的暴露。通常的解决方式是利用环保涂层系统来保护这些部件的表面,例如铝化物涂层或隔热涂层(TBC)系统。隔热涂层系统通常包括耐环境粘合层和沉积在所述粘合层上的隔热涂层。粘合层通常由抗氧化合金形成,例如,MCrAlY,这里M是铁、钴和/或镍,或者由扩散铝化物或铂铝化物形成,该扩散铝化物或铂铝化物形成抗氧化的金属间化合物。
虽然隔热涂层系统对下面的部件基底提供有效的热防护,但是部件(例如燃烧器衬套)的内部冷却通常是必要的,并且可能结合或代替隔热涂层来使用。燃气涡轮发动机的燃烧器衬套常常要求复杂的冷却策略,其中冷却空气围绕燃烧器流动并随后通过在燃烧器衬套上周密设置的冷却孔排入燃烧器。燃烧器的性能直接关系到通过有限的冷却空气量对燃烧器表面均匀冷却的能力。因此,冷却孔及其开口的形成和设置过程通常是关键的,因为每个开口的尺寸和形状决定了离开开口的空气流量及经过表面的空气流的分布,并且影响燃烧器内部总体的流动分布。其它因素例如衬套的局部表面温度也受开口尺寸变化的影响。
对于没有隔热涂层的燃烧器衬套,冷却孔通常通过例如电火花加工(EDM)和激光加工等常规钻孔技术来形成。然而,EDM不能用于在具有陶瓷TBC的燃烧器衬套上来形成冷却孔,因为陶瓷是不导电的,而激光加工很容易通过使在基底和所述陶瓷之间的界面裂开而使脆性的陶瓷TBC剥落。因此,要求在涂覆TBC系统之前通过EDM和/或激光加工形成冷却孔,这就限制了可涂覆的TBC的厚度或迫使采用后处理来从冷却孔去除陶瓷以便恢复理想的开口大小与形状。常规的处理包括保护冷却孔不受TBC沉积的影响或从所述孔完全去除涂覆的TBC以得到理想的孔的几何尺寸。这就使得底层金属表面在孔位置处暴露于不利的环境条件。
对于空气冷却部件(例如燃烧器衬套)的现有维修方法包括焊接热疲劳裂缝。对面板上的开口(例如冷却孔或稀释孔)的定位,以及隔热涂层的使用都对焊接和修补的使用增加了额外的复杂性。在许多情况下,防护涂层必须从整个面板和/或整个衬套上去除以获得通向下层金属本体的通路,然后再涂覆防护涂层。然而,传统的再涂覆过程包括保护冷却孔不受TBC沉积的影响或者从所述孔上完全除去涂覆的TBC以得到理想的孔的几何尺寸。这就在孔位置处使得底层金属表面暴露于不利的环境条件。在一些情况下,对这种面板的修理是一种不可行的选择,而替代地更换整个燃烧器衬套。
因为常规设计可能依赖下层金属基底以在孔表面未涂覆TBC系统的情况下定义最终的孔几何尺寸,所以对金属基底上的孔的破坏或修理过程可能影响该修理部分的性能。因此,需要一种以如下方式制造气冷部件(例如燃烧器衬套)的方法,即该方式在经济和操作上是可行的,对冷却孔附近的基底提供增强的保护,产生制造和修理都令人满意的冷却孔几何尺寸。
发明内容
一方面,本文所述的是适用于燃气涡轮发动机的部件。所述部件包括限定所述部件表面的基底,并具有第一表面和第二表面。至少一个孔口从所述第一表面至所述第二表面延伸通过所述基底,并具有第一开口区域。所述部件具有在邻近所述至少一个孔口的所述第一表面和所述第二表面的至少一个上的第一涂层。所述部件也具有覆盖在邻近所述至少一个孔口的所述第一涂层上的第二涂层,使得所述第一涂层的至少一部分在邻近所述至少一个孔口处被暴露。所述第一涂层限定了小于所述第一开口区域的第二开口区域。
另一个方面,本文所述的是制造适用于燃气涡轮发动机的部件的方法,其步骤包括,由具有第一表面和第二表面的基底形成所述部件,从第一表面至第二表面穿过所述基底形成具有第一开口区域的至少一个孔口,涂覆第一涂层到邻近所述至少一个孔口的第一表面和第二表面中至少一个上,所述孔口至少部分地保持不受第一涂层的阻碍,涂覆第二涂层至邻近所述至少一个孔口的第一涂层,所述孔口至少部分地保持不受第二涂层的阻碍,以及,从所述孔口去除第二涂层,留下大部分或整个第一个涂层来限定小于第一开口区域的第二开口区域。
还有一方面,本文所述的是修理适用于燃气涡轮发动机的部件的方法,所述部件具有包括第一表面和第二表面的基底和从所述第一表面至所述第二表面延伸通过所述基底的至少一个孔口,所述孔口具有第一开口区域,所述方法包括如下步骤:从所述部件去除涂层,修理在所述部件基底上的任何缺陷,涂覆第一涂层至邻近所述至少一个孔口的所述第一表面和所述第二表面的至少一个上,所述孔口至少部分地保持不受第一涂层的阻碍,涂覆第二涂层至邻近所述至少一个孔口的所述第一涂层上,所述孔口保持至少部分地不受所述第二涂层的阻碍,以及,从所述孔口去除所述第二涂层,留下大部分或整个所述第一涂层以限定小于所述第一开口区域的第二开口区域。
附图说明
以下附图举例说明了本发明的一些实施例,其中,
图1是示例性的燃气涡轮发动机的示意图;
图2是示例性的燃烧器组件的示意性的剖视图,该燃烧器组件可用于图1所示的燃气涡轮发动机;
图3是示例性的燃烧器衬套的一部分的放大透视图,该燃烧器衬套可用于图2所示的燃烧器组件;
图4是在涂覆涂层之前图3所示的燃烧器衬套的局部放大剖视图;和
图5是涂覆涂层之后的图4所示的燃烧器衬套的局部放大剖视图;和
图6是去除一些涂层材料后的图5所示的所述燃烧器衬套的局部放大剖视图;和
图7是示出与示例性的制造方法有关的步骤的流程图;和
图8是示出与示例性的修理方法有关的步骤的流程图。
具体实施方式
本发明一般适用于气冷部件,并且尤其适用于通过隔热涂层系统进行保护以免受有害的热化学环境影响的部件。这种部件的明显的例子包括燃气涡轮发动机的高压和低压涡轮喷嘴和叶片,罩,燃烧器衬套和增压器部件。本发明的优点特别适用于那些在有害热环境中操作时使用内部冷却和隔热涂层来使部件的工作温度保持在可接受水平的燃气涡轮发动机部件。
图1是示例性的燃气涡轮发动机10的示意图。发动机10包括低压压缩机12,高压压缩机14,燃烧器组件16。发动机10也包括高压涡轮18,和轴向串联布置的低压涡轮20。压缩机12和涡轮20由第一轴21连接,压缩机14和涡轮18由第二轴22连接。在示例性的实施例中,燃气涡轮发动机10是可从CFMInternational,Inc.,Cincinnati,Ohio(俄亥俄州、辛辛那提市CFM国际公司)购买的CFM-56发动机。在另一个实施例中,燃气涡轮发动机10是可从GE’s Aviationbusiness,Cincinnati,Ohio(俄亥俄州、辛辛那提市通用电气的航空公司)购买的CF-34发动机。
在运行中,气流经过低压压缩机12,压缩空气从低压压缩机12供给到高压压缩机14。高压缩空气被送到燃烧器16。来自燃烧器16的气流驱动涡轮18和20并通过喷嘴(未标记)排出燃气涡轮发动机10。
图2是可用于燃气涡轮发动机10(图1所示)的示例性的燃烧器16的示意剖视图。燃烧器16包括布置在燃烧器外壳56和燃烧器内壳58之间的外部衬套52和内部衬套54。外部和内部衬套52与54是彼此径向间隔的,使得燃烧室60限定在它们之间。外部衬套52和外壳56之间形成外部通道62,内部衬套54和内壳58之间形成内部通道64。整流罩组件66分别地连接在外部和内部衬套52和54的上游端。形成在整流罩组件66中的环形开口68能够使得压缩空气沿总体上由箭头A指示方向通过扩散开口进入燃烧器16。压缩空气流过环形开口68以支持燃烧并促进衬套52和54的冷却。
环状拱形板70在外部和内部衬套52和54之间延伸并在接近所述衬套的上游端处连接到所述衬套52和54。多个周向间隔的旋流组件72连接至拱形板70。每个旋流组件72接收来自开口68的压缩空气和来自相应燃料喷射器74的燃料。燃料和空气通过旋流装置72旋流并混合在一起,并且所得到的燃料/空气混合物被排放到燃烧室60中。燃烧器16包括纵轴线75,其从燃烧器16的前端76延伸至后端78。在示例性的实施例中,燃烧器16是单一环形燃烧器。或者,燃烧器16可以是任何其他的燃烧器,包括但并不限于双环形燃烧器。
在示例性的实施例中,每个外部和内部衬套52和54包括多个重叠面板80。更具体地,在所述示例性的实施例中,外部衬套52包括五个面板80且内部衬套54包括四个面板80。在一个替代实施例中,外部和内部衬套52和54两者都可以各自包括任意数量的面板80。面板80在燃烧器16内部限定燃烧室60。特别地,在所述示例性的实施例中,位于上游的一对第一面板82限定了主燃区84,位于第一面板82下游的一对第二面板86限定了中间燃烧区88,位于第二面板86下游(在图3中的方向B)的一对第三面板90和位于第三面板90下游的一对第四面板92限定了下游稀燃烧区94。
燃烧器衬套可包括稀释孔,其用来为所述燃烧器提供进入燃烧环境中的空气,从而改变温度分布或燃烧特性。稀释空气主要地经过多个周向间隔的稀释孔96被引入燃烧室60,这些稀释孔贯穿外部和内部衬套52和54其中之一或全部。在示例性的实施例中,每个稀释孔96基本上是圆的。稀释孔可根据需要被修改(大小、形状和/或布置)以便达到具体部件和具体产品应用所要求的耐用性和性能指标。
图3示出了可用于燃烧器16的示例性的燃烧器衬套52。衬套52也包括多个形成在第三面板90以促进衬套52冷却的冷却孔160。尽管,仅仅图示了第三面板90上的一组冷却孔160,但可以理解的是,成组的冷却孔160是环绕第三面板90周向间隔的。可以理解的是,每组冷却孔160位于相应的热点以便于将冷却流体引导到对应的热点上。第三面板90包括任何数量的有助于冷却衬套52的冷却孔160。
在燃气涡轮发动机10运行期间,衬套52的内表面33变热并需要冷却。因此,在所述示例性的实施例中,冷却特征,例如冷却孔160位于衬套52中以便于引导冷却流体到衬套52的热点上。更具体地是,冷却孔160引导冷却流体从外部通道62和/或内部通道64流到燃烧室60,因此向内表面33的提供冷却流体层。应当理解的是,其它的实施例可使用任何冷却孔160的结构,该结构使得冷却孔160的能够起到本文所述的功能。类似地,孔160可以在衬套54上以冷却衬套54的外表面。
在运行期间,当雾化燃料注入燃烧室60并点燃时,在燃烧室60内部产生热量。虽然空气经过冷却特征160进入燃烧室60,并沿着燃烧器衬套表面33形成薄的空气保护边界,但燃烧器衬套表面对高温的暴露变化可导致进入面板80中的热应力。由于持续暴露在热应力下,经过一段时间,面板80可能会损坏。
图4是燃烧器衬套52部分的局部放大的剖视图,以举例说明所述冷却孔160和衬套表面33之间的关系,以及孔160的轴线220。
现在参照图5和6,隔热材料层210被涂覆到图4所示的燃烧器衬套52的燃烧器衬套表面33。隔热材料还将燃烧器衬套表面33与高温燃烧气体隔离。层210包括内层212,例如粘合涂覆层,和外层214,例如隔热层。
下面将关于气冷部件(例如燃烧器衬套52)来描述所述示例性的方法,气冷部件的金属基底33是通过隔热涂层系统来保护的,该隔热涂层系统包括形成在基底(内表面33)上的粘合层212以及通过粘合层212粘接到所述表面33的陶瓷层214。粘合层212和陶瓷层214可以分别是单独的材料层,或由合适材料形成的两个或更多层(即,多层)构成。对于燃气涡轮发动机的高温部件的情况,所述表面33可为铁、镍或钴基超级合金。所述粘合层212优选地为抗氧化组分,例如扩散铝化物或MCrAlY,在暴露于升高的温度时,所述组分在表面形成氧化铝(Al2O3)层或氧化铝垢(未示出)。所述氧化铝垢防止下面的超级合金表面33氧化并提供陶瓷层214可更加牢固粘附的表面。
所述陶瓷层214可由空气等离子体喷涂(APS)、低压等离子体喷雾(LPPS)、或物理汽相淀积(PVD)技术来沉积,例如电子束物理汽相淀积(EBPVD),电子束物理汽相淀积产生抗变形的柱状晶粒结构。用于陶瓷层214的示例性材料是由氧化钇部分稳定的氧化锆(氧化钇稳定氧化锆,或YSZ),但是也可以使用由氧化钇完全稳定的氧化锆,还可以采用由其它的氧化物稳定的氧化锆,例如氧化镁(MgO),氧化钙(CaO),二氧化铈(CeO2)或氧化钪(Sc2O3)。
本发明的方法需要产生冷却孔160(在图4-6示出),所述冷却孔可经开口162穿过陶瓷层214、粘合层212和表面33,从而得到适于冷却孔160和开口162的结构,该结构提供所述部件(例如衬套52)外表面上适当计量的冷却空气分布。如图5所示,冷却孔开口162在被初始涂覆时相对于所述表面以大角度(角β)形成小的开口(具有轴线230)。如图6所示,在去除与所述孔对准的陶瓷层214的那部分以后,开口162相对表面33成相对小的角度,从而在运行期间流过所述开口162的冷却空气可下降成为附在部件表面上的有效薄膜。
图7和8示出了本文详细描述的示例性方法的流程图。虽然两个方法都具有一些共同的步骤,但是方法200尤其适于制造新的气冷部件,而方法300尤其适于在气冷部件的使用寿命期间修理和修复所述气冷部件。
如图4所示,该示例性的方法的第一步是形成穿过衬套52的孔160。随后的第二步如图5所示,在表面33涂覆粘合层212和陶瓷层214。由于在所述孔160的边缘处的涂层积聚,所得到的孔开口162的截面直径比衬套52所要求的冷却孔160的截面直径小,但是不会被完全堵塞,使得孔的位置及其截面的至少一部分仍然基本不受阻碍。例如,对于具有大约0.035英寸(大约0.9mm)到大约0.040英寸(大约1.0毫米)的直径的冷却孔160,在涂覆后,开口162优选具有大约0.020英寸(大约0.5mm)的直径或该直径大约为适用于冷却孔160的直径的一半,使得仍然可以看见并可通过涂层接近“目击孔”。适于形成孔160的技术包括EDM,但是可以预见所述孔160可以由例如铸造、激光、或伴随磨料水射流的钻孔这些其它方法来形成。作为钻孔操作的结果,孔160具有基本上均匀的圆截面,并相对于表面33形成非垂直角度(角α)。
一旦形成孔160,并且涂覆了粘合层212和陶瓷层214,所述部件(衬套52)就要通过细致的受控操作来处理,所述操作利用对准(例如从衬套52的无涂层侧)孔160的加压流体来产生如图5所示的冷却孔160和开口162。可使用包含介质(例如玻璃珠或磨料)不同的流体(例如空气或水)以在覆盖孔160的涂层材料上提供研磨作用。
已经发现本文所述的操作可提供足够的能量以通过去除陶瓷TBC层而不去除粘合层或在下面的母体材料(例如金属基底),从而将开口162扩大至理想的尺寸和理想的角度。因此,虽然该操作去除了陶瓷层214,但是大部分或整个下面的粘合层212仍保持在靠近冷却孔160的开口的表面上,这样,在制造和使用期间,粘合层就为冷却孔附近的衬套边缘提供防护。因为该操作利用的是机械能而不是热能,因此该操作不会损害或剥落围绕孔160并形成所得到的孔开口162的边缘的粘合层212或陶瓷层214。
所述方法能够通过陶瓷隔热涂层(TBC)和其下的基底适当地调整冷却孔和开口的大小和形状。研磨流体流也用于在无需去除或破坏围绕冷却孔和开口的陶瓷的情况下修整所述孔和开口,包括所述孔和开口的理想大小与形状。
如果现场返回的发动机(例如发动机10)显示所述燃烧器衬套52包括至少一块损坏的面板80,那么,可使用各种修理方法将燃烧器衬套52恢复到可使用的状态。这些修理方法可包括替换整个衬套、整个面板和/或衬套和面板的部分或节段,以及例如通过将衬套和面板紧密焊接的方式来修补裂缝。
在修理操作期间,从所述部件(例如燃烧器衬套)正常地去除全部杂质、异物和涂层以允许对部件详细地检查。然后,利用合适且有效的的方法(例如焊接、钎焊、或对部件的个别部分的替换)来修补基底中的任何缺陷,例如裂缝。孔(例如冷却孔)在必要时可被可重新钻孔和/或修理,从而使所述孔恢复至适当的大小、形状和样式。
一旦适当地修补了部件的表面,就可利用上述示例性的方法将保护隔热涂层涂覆到部件表面。因为完成的开口尺寸是由本文所述的可去除和可更换的涂层系统来细致地控制和限定的,因此能够执行并重复修理过程而保持完成的冷却孔尺寸在技术规格要求范围时。
因为所述部件(例如损坏的衬套)是使用本文所述的方法、利用易于获得的涂层技术来修理的,所以与去除和更换整个燃烧器衬套或大块面板或整个面板相比,使用有利于节约成本的修理工艺可以使燃烧器恢复使用。
尽管本文所述的装置和方法是结合燃气涡轮发动机的燃烧器衬套中的冷却孔来描述的,但可以理解的是,所述装置和方法并不局限于燃气涡轮发动机、燃烧器衬套或冷却孔。而且,对燃气涡轮发动机和燃烧器衬套部件的说明也不局限于本文所述的具体实施例,相反,燃气涡轮发动机和燃烧器衬套的部件可与本文所述的其它部件独立地和分离地使用。
尽管依据不同的具体实施例描述了本发明,但本领域技术人员可知,可以在权利要求的精神和范围内改进本发明。
Claims (19)
1.一种适用于燃气涡轮发动机的部件,所述部件包括:
限定所述部件的表面的基底,所述基底具有第一表面和第二表面;
从所述第一表面至所述第二表面延伸通过所述基底的至少一个孔口,所述孔口具有第一开口区域(160);
第一涂层,所述第一涂层在邻近所述至少一个孔口的所述第一表面和所述第二表面的至少一个上;和
第二涂层,所述第二涂层覆盖在邻近所述至少一个孔口的所述第一涂层上,这样,所述第一涂层的至少一部分在邻近所述至少一个孔口处被暴露;
其中,所述第一涂层限定第二开口区域(162),所述第二开口区域具有小于所述第一开口区域的完成的开口尺寸,以便提供在所述部件的外表面上适当计量的冷却空气分布;
其中,所述第一涂层覆盖形成在所述至少一个孔口与所述第一表面和所述第二表面中的至少一个交汇处的边缘。
2.如权利要求1所述的部件,其中,所述孔口限定了轴线,该轴线与由所述第一涂层涂覆的所述基底的表面形成非90度的第一角度。
3.如权利要求2所述的部件,其中,所述第二开口区域相对于所述基底的表面形成第二角度,该第二角度不同于所述第一角度。
4.如权利要求1所述的部件,其中,所述部件包括多个孔口。
5.如权利要求1所述的部件,其中,所述第一涂层和所述第二涂层形成隔热系统。
6.如权利要求5所述的部件,其中,所述第一涂层是粘合涂层材料。
7.如权利要求5所述的部件,其中,所述第二涂层是陶瓷层材料。
8.如权利要求1所述的部件,其中,所述基底是金属材料。
9.如权利要求1所述的部件,其中,所述部件是燃烧器衬套。
10.一种制造适用于燃气涡轮发动机的部件的方法,所述方法包括如下步骤:
由具有第一表面和第二表面的基底形成所述部件;
从所述第一表面到所述第二表面穿过所述基底形成至少一个孔口,所述孔口具有第一开口区域(160);
涂覆第一涂层到邻近所述至少一个孔口的所述第一表面和所述第二表面的至少一个上,所述孔口至少部分地保持不受所述第一涂层的阻碍;
涂覆第二涂层到邻近所述至少一个孔口的所述第一涂层上,所述孔口至少部分地保持不受所述第二涂层的阻碍;和
从所述孔口去除所述第二涂层,留下大部分或整个所述第一涂层以限定第二开口区域(162),所述第二开口区域具有小于所述第一开口区域的完成的开口尺寸,以便提供在所述部件的外表面上适当计量的冷却空气分布;
其中,所述第一涂层覆盖形成在所述至少一个孔口与所述第一表面和所述第二表面中的至少一个交汇处的边缘。
11.如权利要求10所述的方法,其中,所述第一涂层和所述第二涂层中的至少一个以某一角度涂覆到所述第一表面和所述第二表面中的至少一个。
12.如权利要求10所述的方法,其中,所述去除步骤是由研磨介质流来完成。
13.如权利要求12所述的方法,其中,所述研磨介质流包括悬浮于空气流中的玻璃珠。
14.如权利要求12所述的方法,其中,所述研磨介质流从所述基底的非涂覆侧引导穿过所述至少一个孔口。
15.一种修理适用于燃气涡轮发动机的部件的方法,所述部件具有包括第一表面和第二表面的基底和从所述第一表面到所述第二表面延伸通过所述基底的至少一个孔口,所述孔口具有第一开口区域(160),所述方法包括如下步骤:
从所述部件去除涂层;
修理在所述部件的基底中的任何缺陷;
涂覆第一涂层到邻近所述至少一个孔口的所述第一表面和所述第二表面的至少一个上,所述孔口至少部分地保持不受所述第一涂层的阻碍;
涂覆第二涂层到邻近所述至少一个孔口的所述第一涂层上,所述孔口至少部分地保持不受所述第二涂层的阻碍;和
从所述孔口去除所述第二涂层,留下大部分或整个所述第一涂层以限定第二开口区域(162),所述第二开口区域具有小于所述第一开口区域的完成的开口尺寸,以便提供在所述部件的外表面上适当计量的冷却空气分布;
其中,所述第一涂层覆盖形成在所述至少一个孔口与所述第一表面和所述第二表面中的至少一个交汇处的边缘。
16.如权利要求15所述的方法,其中,所述第一涂层和所述第二涂层中的至少一个以某一角度涂覆到所述第一表面和所述第二表面中的至少一个。
17.如权利要求15所述的方法,其中,所述去除步骤是由研磨介质流来完成。
18.如权利要求17所述的方法,其中,所述研磨介质流包括悬浮于空气流中的玻璃珠。
19.如权利要求17所述的方法,其中,所述研磨介质流从所述基底的非涂覆侧引导穿过所述至少一个孔口。
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