CN1221067A - 用于燃气涡轮发动机密封系统的柱状结构氧化锆研磨涂层 - Google Patents
用于燃气涡轮发动机密封系统的柱状结构氧化锆研磨涂层 Download PDFInfo
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Abstract
一种包括旋转构件的燃气涡轮发动机密封系统,所述旋转构件具有设置成与静止的磨损性密封面呈摩擦关系的研磨端。该研磨端含有具有柱状结构的比所述磨损性密封面更硬的氧化锆研磨层,以便于该研磨端能够切削上述磨损性密封面。
Description
本发明总的说来涉及涂覆于燃气涡轮旋转构件以加强气密封切削(airseal cutting)而降低间隙损失和提高旋构件寿命的研磨涂层(abrasive coating)。
燃气涡轮发动机通常包括各种旋转密封系统以维持对发动机性能至关重要的工作压差。一种通常类型的密封系统包括一个旋转构件,如与静止磨损性密封面成摩擦关系定位的涡轮叶片。该摩擦关系在涡轮叶片和密封面之间产生一个很小的操作间隙以限制穿过涡轮叶片的工作气体的量。如果间隙太大,则穿过涡轮叶片和密封面之间的工作气体量太多,从而降低发动机效率。类似的密封系统典型地用作压气机和涡轮部分的燃气涡轮发动机的内外气密封。
为了维持一个所需的小的工作间隙,旋转构件如涡轮叶片典型地有一个能切削与之配对的密封面的研磨端(abrasive tip)。燃气涡轮发动机组装以后,旋转构件和密封面之间存在一个很小的间隙。在发动机运行的过程中,由于离心力的作用和发动机温度升高,旋转构件伸长且贴着密封面磨擦。旋转构件的研磨端切入磨损性密封面形成紧配合。研磨端和密封面之间的刻意接触,加上燃气涡轮发动机典型的热和压力循环,在密封面和研磨端处均产生一个需要的、高磨损的环境。
为了限制密封面磨蚀和剥落,从而维持旋转构件和密封面之间所需的间隙,密封面典型地由相对较硬的、虽然是磨损性的材料制成。例如,烧结金属纤维毡(felt metal)、覆盖金属结合层的等离子喷涂的陶瓷、含有氮化硼(BN)的等离子喷涂镍合金、或者蜂窝状材料都是常用的密封面材料。
除非旋转构件具有合适的研磨端,否则与之配对的密封面会对旋转构件产生强烈的磨损。这是所不希望的,因为这不仅会降低发动机性能,而且维修或更换旋转构件、尤其是涡轮和压气机叶片是非常昂贵的。因此,用于形成研磨端的材料典型地比与之配对的密封面要硬。例如,在某些应用中,氧化铝(Al2O3),包括氧化锆(Zr2O3)韧化的氧化铝、电镀立方氮化硼(cBN)、碳化钨一钴(WC-Co)、碳化硅(SiC)、氮化硅(Si3N4),包括与金属基质共喷涂的氮化硅磨料、以及用氧化钇稳定的等离子喷涂氧化锆(Y2O3-ZnO2)等材料被用作研磨端材料。最常用的三种研磨端为端罩喷涂研磨端和电镀cBN端。
端罩典型地包括一个填充研磨料和金属基质的高温合金“舟”。研磨料可以是碳化硅、氮化硅、硅铝氧氮化物(SiAlON)以及这些材料的混合物。金属基质可以是包含有活性金属如Y、Hf、Ti、Mo或Mn的Ni、Co或Fe基高温合金(superalloy)。用瞬时液相熔接方法把该“舟”熔接到旋转构件例如涡轮叶片的端上。端罩和瞬时液相熔接技术在共同转让的美国专利3,678,570(授予Paulonis等人)、4,038,041(授予Duval等人)、4,122,992(授予Duval等人)、4,152,488(授予Schilke等人)、4,249,913(授予Johnson等人)、4,735,656(授予Schaefer等人)和4,802,828(授予Rutz等人)中进行了一般描述。尽管端罩已在许多工业应用中得到了利用,但是把它安置到叶端上是有些麻烦的,并且很昂贵。
喷涂研磨端典型地包括氧化铝包覆的碳化硅或金属基质包围的氮化硅研磨料,其中,金属基体被浸蚀以暴露该研磨料。这种研磨端在共同转让的美国专利4,610,698(授予Eaton等人)、4,152,488(授予Schilke等人)、4,249,913(授予Jonnson等人)、4,680,199(授予Vontell等人)、4,468,242(授予Pike等人)、4,741,973(授予Condit等人)和4,744,725(授予Matareset等人)中进行了描述。喷涂研磨端常与等离子喷涂陶瓷或金属涂层密封配合使用。尽管喷涂研磨端已成功地用于多种发动机,但是它们难以制造而且新发动机硬件的每个端中的研磨料分布不同。另外,喷涂耐磨尖的寿命不足以满足未来某些应用的要求。
电镀cBN研磨叶片端典型地包括一些由电镀金属基质包围的cBN磨料。该基质可以是Ni、MCrAlY,其中M代表Fe、Ni、Co或Ni和Co的混合,或其它金属或合金。cBN比金刚石以外的其它任何磨料都硬,因此立方氮化硼端是优良的刀具。电镀cBN端非常适于压气机(因其温度较低,即低于约1500°F[815℃])。但是,由于涡轮部分温度较高,会引起cBN磨料甚至可能是金属基体的氧化,因此这种研磨端在涡轮部分使用时寿命很短。尽管制造电镀cBN端比制造喷涂研磨端便宜,但是实现用于制造cBN的技术难度和成本较高。
因此,工业领域需要一种与现有研磨端相比研磨性更好、寿命更长、制造更便宜的用于燃气涡轮密封系统的研磨端。
本发明涉及一种与现有的那些相比研磨性更好、寿命更长、制造费用更低的用于燃气涡轮密封系统的研磨端。
本发明的一个方面包括一种具有旋转构件的燃气涡轮发动机密封系统,该旋转构件具有与静止磨损性密封面呈摩擦关系的研磨端。该研磨端比磨损性密封面更硬,以便于该研磨端能够切割该磨损性密封面,该研磨端包括直接沉积于旋转构件上的基本无磨料的表面上的氧化锆研磨层。该氧化锆研磨层具有柱状结构,含有氧化锆和约3wt%到约25wt%的稳定剂。稳定剂可以是氧化钇、氧化镁、氧化钙和这些材料的混合物。
本发明的另一个方面是研磨端包括一个沉积于旋转构件的基本无磨料的表面上的金属结合层,一个沉积于该金属结合层上的氧化铝层,以及一个沉积于该氧化铝层且具有柱状结构的氧化锆研磨层。该氧化锆研磨层包括氧化锆和约3wt%到约25wt%的稳定剂,稳定剂可以是氧化钇、氧化镁、氧化钙和它们的混合物。
本发明的再一个方面包括一种具有研磨端的燃气涡轮发动机叶片或刀刃。该研磨端包括一个具有柱状结构的氧化锆研磨层,其中的氧化锆研磨层包括氧化锆和约3wt%到约25wt%的稳定剂,稳定剂可以是氧化钇、氧化镁、氧化钙和它们混合物。
本发明的上述和其它特征和优点由下面的描述和附图变得更加明了。
附图的简要说明如下:
图1是燃气涡轮发动机的剖视图。
图2是本发明的压气机外部和内部气封的截面图。
图3是具有本发明的研磨端的涡轮叶片的透视图。
图4是本发明的研磨端的柱状结构的放大图。
本发明的研磨端可以用于需要维持旋转构件和静止构件之间紧配合的高磨损的燃气涡轮发动机中。例如,本发明特别适合于用作耐磨涡轮或压气机叶片端或者涡轮或压气机刀刃。本发明的研磨叶片端或刀刃可以配合合适的磨损性密封面使用以形成外部或内部气封。
图1显示了一个典型的包括压气机部分4和涡轮部分6的燃气涡轮发动机2。压气机部分4包括一个设置于压气机机壳10内的压气机转子8。作为发动机旋转构件之一的一些压气机叶片12安装在转子8上而一些压气机定子14设置于叶片12之间的。同样,涡轮部分6包括设置于涡轮机壳18内的涡轮转子16。作为发动机内的旋转构件的另一些涡轮叶片20安装在转子16上而一些涡轮导向叶片22设置于这些叶片20之间。
图2显示了压气机部分4的外部气封24和内部气封26。每个外部气封24包括设置于压气机叶片12末端与磨损性外封面30成摩擦关系的研磨端28。对于这种应用,当发动机组装后运行时,两构件之间的间隙允许它们至少在某个时间内直接接触时两构件呈摩擦关系。每个内部气封26包括设置于压气机刀刃34末端的、与设置于压气机定子14上的磨损性内封面36呈磨擦关系的研磨端32。本领域的熟练人员将会理解,除压气机部分4外,类似于上面所描述的那些类似的外部气封和内部气封还可以用在涡轮部分6和发动机其它部分。
图3示出了本发明的一个具有研磨端28的涡轮叶片20,其中的研磨端28包括一个沉积于涡轮叶片20的端40上的金属结合层38,在该结合层38上的氧化铝(Al2O3)层42,以及沉积于该氧化铝层42上的氧化锆(ZrO2)研磨层44。本发明的研磨端可以直接沉积于旋转构件上(如图所示),或者沉积在旋转构件表面的底涂层上或渗入该旋转构件的该表面。例如,本发明的研磨端可以沉积于扩散进旋构件表面的铝化物渗层之上。但是本发明的研磨端应该沉积于基本上无研磨料的表面上以防止使磨料的研磨功能加倍和增加构件的成本。刀刃34上的研磨端32也应该按类似的结构形成。在这两种情况下,应用了本发明研磨端28、32的旋转构件(即涡轮或压气机叶片20、12,压气机刀刃34,或涡轮刀刃[未图示])典型地包括镍基或钴基高温合金或钛合金。
尽管图3示出了本发明的具有金属结合层38的研磨端28,然而,该结合层是可选择性的,如果在无结合层38的情况下氧化锆研磨层44能很好地粘附于旋转构件,那么就可以省去金属结合层38。如果不使用结合层,那么就希望旋转构件由能够形成粘附性氧化铝层(可与氧化铝层42相比的)的合金制成。标定组成为5.0Cr-10Co-1.0Mo-5.9W-3.0Re-8.4Ta-5.65Al-0.25Hf-0.013Y余量Ni的合金就是这样一种合金。在众多应用中,优选一种结合层38以提供研磨端28、32和旋转构件之间的良好的粘附性以及提供一个良好的表面用于形成氧化铝层42和用于涂覆氧化锆研磨层44。选择合适的结合层38可以限制或防止发动机运行过程中氧化锆研磨层44从结合层38剥落以及整个研磨端28、32的剥落。发动机运行过程中氧化锆研磨层44或整个研磨端28、32的剥落将会因加大旋转构件和磨损性密封面之间的运行间隙而降低旋转构件寿命并损失发动机性能。
本发明的金属结合层38可以是本领域已知的能够在燃气涡轮发动机旋转构件和氧化锆研磨层44之间形成持久结合力的任何金属材料。这种材料典型地含有大量的Al以形成能与氧化锆研磨层44良好结合的粘附性氧化铝层。例如,该金属结合层38可以包括铝化物渗层(包括含有一种或多种贵重金属的铝化物)、Ni和Al的合金、或MCrAlY合金,其中M代表Fe、Ni、Co或Ni和Co的混合。在这种应用中,术语MCrAlY合金还包括那些含有本领域已知的如Si、Hf、Ta、Re的添加元素或贵金属元素。该MCrAlY还可含有一层扩散型铝化物、特别是含有一种或多种贵金属的铝化物。优选的金属结合层38含有标定组成为Ni-22Co-17Cr-12.5Al-0.25Hf-0.4Si-0.6Y的MCrAlY。该组成在共同转让的美国专利4,585,481和Re32,121(均授予Gupta等人)中有描述,这里将它们引入本文作为参考。
金属结合层38可以用本领域已知的任何方法沉积这种材料。例如,用低压等离子喷涂(LPPS)、空气等离子喷涂(APA)、电子束物理气相沉积(EB-PVD)、电镀、阴极弧、或其它任何方法沉积结合层38。涂覆于旋转构件的金属结合层38应具有足够的厚度以提供旋转构件和氧化锆研磨层44之间的强的结合力,并且防止产生于氧化锆研磨层44内的裂纹扩展进旋转构件。对于多数应用,该金属结合层38的厚度为约1mil(25μm)至约10mil(250μm)。优选地,该结合层38厚度为约1mil(25μm)至约3mil(75μm)。沉积金属结合层38之后,应该对该结合层38进行喷砂处理以封闭在沉积过程中可能扩大的孔隙或通道,或者进行其他机械或抛光处理,从而制备接受氧化锆研磨层44的结合层38。
氧化铝层42,有时指热生长氧化物,可以用任意能形成均匀粘附层的方法形成于金属结合层38或旋转构件上。对于金属结合层38来说,氧化铝层42是可选择性的。但是研磨端28优选地包括氧化铝层42。例如,层42可以在涂覆氧化锆研磨层44之前通过高温氧化处理金属结合层38中的或旋转构件中的铝而形成。作为一种可替代方式,可以用化学气相沉积或本领域其它合适方法沉积得到氧化铝层42。如果存在氧化铝层42的话,其厚度取决于其密度和均匀性而确定。优选地,氧化铝层42的厚度为约0.004mil(0.1μm)至约0.4mil(10μm)。
氧化锆研磨层44可以包括氧化锆和一种稳定剂的混合物,稳定剂例如为氧化钇(Y2O3)、氧化镁(MgO)、氧化钙(CaO)、或者它们的混合物。氧化钇为优选的稳定剂。氧化锆研磨层44应该含有足够的稳定剂以防止在一个特定燃气涡轮发动机整个工作温度范围不希望产生的氧化锆相变(即:从优选的四方或立方结构转变为不希望的单斜晶体结构)。优选地,氧化锆研磨层44包含氧化锆和约3wt%至约25wt%的氧化钇的混合物。最优选地,氧化锆研磨层44将包含约6wt%至约8wt%氧化钇或约11wt%至约13wt%氧化钇,具体含量视工作温度而定。
如图4所示,氧化锆研磨层44应该具有一系列均匀分布于整个研磨层上的柱状段,从而使垂直于涂覆了研磨层的表面的研磨层的横截面呈现典型的物理气相沉积层的柱状微观结构。该柱状结构应该具有穿过氧化锆研磨层44整个厚度的长度。这种研磨层在共同转让的美国专利4,321,310(授予Ulion等人)、4,321,311(授予Strang-man)、4,401,697(授予Strangman等人)、4,405,659(授予Strangman)、4,405,660(授予Ulion等人)、4,414,249(授予Ulion等人)以及5,262,245(授予Ulion等人)中有描述,这里将其引入作为参考。在某些应用中,需要在叶片20的翼面46和平台48上涂覆与研磨端38成份基本相同的涂层作为热障层。
氧化锆研磨层44可以用现有的EB-PVD或任何其它物理蒸汽沉积方法沉积成柱状涂层结构。优选地,本发明的研磨层44用EB-PVD沉积,因为有现成的EB-PVD设备和熟练的技术人员。如上所述,研磨层44可以涂覆于金属结合层38或直接涂覆于旋转构件上,在上述两种情况下,优选地,都配合氧化铝层42使用。在上述两种情况下,研磨层44应该涂覆至足够的厚度以提供与所涂覆表面的较强的结合力。在多数情况下,研磨层44可以约为5mil(125μm)至约50mil(1250μm)厚,优选为约5mil(125μm)至25mil(265μm)厚。当涂覆于涡轮或压气机叶片时,需要较厚的研磨层44以允许它们被安装在其中的压气机和涡轮转子的装配研磨(assembly grinding)。装配研磨去除叶片端上的部分研磨层44以补偿沉积过程过程中的容许误差所产生的涂层厚度的微小变化。从相对较厚的研磨层44着手,允许装配研磨以得到一个较圆的转子,同时保持足够的最终研磨层44的厚度以切削密封面。
本发明的磨损性密封面30、36可以包括已知的与燃气涡轮发动机环境良好适应并且能被研磨层44切割的任何材料。对于高压涡轮而言,优选的磨损性密封材料包括一种金属结合层(标定为5.0Cr-10Co-1.0Mo-5.9W-3.0Re-8.4Ta-5.65Al-0.25Hf-0.013Y-余量Ni)和一种多孔陶瓷层(标定为由约7wt%氧化钇稳定的氧化锆)。结合层可以用等离子喷涂或高速氧一燃料沉积方法涂覆。陶瓷层可以用等离子喷涂由约88wt%至约99wt%的陶瓷粉末和约1wt%至12wt%芳族聚酯树脂的混合物而沉积。然后把聚酯树脂从陶瓷层中烧掉产生多孔结构。对于高压压气机应用来说,优选的磨损性密封材料包括一种镍基高温合金结合层和一种由镍基高温合金(标定为9Cr-9W-6.8Al-3.25Ta-0.02C-余量Ni和少量增加抗氧化性的元素)和表层的氮化硼组合而成的复合层。结合层可以由等离子喷涂通过快速固化率的方法(rapid solidification rate method)形成的粉末来形成的。表层可以由等离子喷涂结合层粉末和氮化硼粉末的混合物来形成。另一个可能的磨损性密封材料包括一种分级等离子喷涂陶瓷材料,它包括一种金属结合层(标定为Ni-6Al-18.5Cr)、一种分级的金属/陶瓷层(标定为Co-23Cr-13Al-0.65Y/氧化铝)、一种分级致密陶瓷层(标定为氧化铝/由约20wt%氧化钇稳定的氧化锆)、以及一种多孔陶瓷层(标定为由约7wt%氧化钇稳定的氧化锆)的连续层。另一种可能的密封表面材料包括烧结金属纤维毡和一种蜂窝材料。合适的密封材料在美国专利4,481,237(授予Bosshart等人)、4,503,130(授予Bosshart等人)、4,585,481(授予Gupta等人)、4,588,607(授予Matarese等人)、4,936,745(授予Vine等人)、5,536,022(授予Sileo等人)和Re32,121(授予Gupta等人)中有描述,将这些专利引入本文作为参考。
下面是一个说明本发明的实施例,但是它并不限制本发明的范围。
实施例
通过常规的沉积技术把本发明的柱状结构氧化锆研磨端涂覆到0.25英寸(0.63cm)×0.15英寸(0.38cm)的长方形磨擦试验台(rubrig)试样上。该研磨端包括一个低压等离子喷涂的金属结合层,其厚度约为3mil(75μm),标定为包括Ni-22Co-17Cr-12.5Al-0.25Hf-0.4Si-0.6Y。沉积之后,于1975°F(1079℃)下对金属结合层进行扩散热处理和重力辅助喷砂的喷砂处理。用现有的方法在结合层表面生长一个约0.04mil(1μm)厚的TGO层。最后用常规的电子束物理蒸汽沉积工艺涂覆约5mil(125μm)厚的柱状结构陶瓷,它包含由7wt%氧化钇稳定的氧化锆。该涂覆试样放置于一个摩擦试验台上,并且对向密封材料,该密封材料包括Ni-6Al-18.5Cr金属结合层、Co-23Cr-13Al-0.65Y和氧化铝分级层、氧化铝和约20wt%氧化钇稳定的氧化锆的致密分级层,以及由约7wt%氧化钇稳定的氧化锆多孔层的连续层。磨擦试验从在室温下的密封面开始,使研磨端速度为1000ft/s(305m/s),研磨端和密封面之间的相对速度为1Omil/s(254μm/s)。磨擦试验一直进行直到研磨端达到20mil(508μm)的深度。一旦达到所需深度,停止磨擦试验,取下试样进行分析,确定研磨端和密封面的磨损量。表1给出了试验数据。
表1试样 1 2密封面磨擦-°F(℃) 2200(1204) 1925(1052)叶片磨擦温度-°F(℃) 2800(1538) 2105(1152)平均叶片磨损-mil(μm) 7.0(177.8) 10.0(254.0)平均密封面磨损-mil(μm) 12.0(304.8) 9.0(228.6)总相互作用-mil(μm) 19.0(482.6) 19.0(482.6)线磨损(W/I) 0.368 0.526体磨损(VW/R) 0.075 0.071
线磨损(W/Il)是从旋转构件去除的研磨端线量与从旋转构件和静止构件去除的材料线量之和的比值。W/I的值越低,切削密封材料的研磨端越好。尽管W/I比是分析叶片端磨损的简单有效的方法,但是该值与磨擦试验台试样和密封面的形状有关。另一种测度磨损的方法,体磨损比(VWR),与试样和密封面的形状无关。VWR是在磨擦试验中研磨端体积损失与每单位体积密封涂层去除量的比值。同样,该比值越低表明研磨端越能有效地切削密封材料。
表2给出了一些试验结果的比较,所有密封面材料与实施例1相同,研磨端分别为:现有技术的氧化锆韧化氧化铝端,共喷涂叶片端,喷涂研磨端和电镀cBN端。表2端结构造 平均VWR由氧化锆韧化的氧化铝(现有技术) 1.4共喷涂(现有技术) 1.18喷涂研磨端(现有技术) 0.63电镀cBN(现有技术) <0.01柱状氧化锆(本发明) 0.07
尽管摩擦试验表明本发明的柱状氧化锆研磨端不如电镀cBN端好,但是它确实比现有技术的其它端好得多。另外,柱状氧化锆研磨端与cBN尖相比有几个优点。例如,它没有氧化倾向问题。再者,当柱状氧化锆研磨端与叶片翼面和平台上的EB-PVD热障层一起使用时可以简化制造工艺。相对于其它结构的研磨端来说,这种结构可以在同一时间制得并且在端区内把这种涂层和端结合在一起。
本发明不局限于说明书中所显示和所描述说明的具体实施方案。在不背离权利要求的精神和不超出其范围的情况下可以以其进行各种各样的变更或修正。
Claims (20)
1、一种燃气涡轮发动机密封系统,包括一个旋转构件,其具有与静止的、磨损性密封面设置成呈摩擦关系的研磨端,其中,所述研磨端含有比磨损性密封面更硬的材料,以便于该研磨端能切割磨损性密封面,其特征在于:
上述研磨端包括一个沉积于上述旋转构件上的基本无磨料的表面上的金属结合层,一个设置于该金属结合层的氧化铝层,以及一个沉积于该氧化铝层上的且具有柱状结构的氧化锆研磨层,其中,所述的氧化锆研磨层含有氧化锆和约3wt%到约25w%的选自氧化钇、氧化镁、氧化钙以及它们的混合物的稳定剂。
2、根据权利要求1所述的密封系统,其中,所述金属结合层含有扩散型铝化物、一种Ni和Al的合金、或MCrAlY合金,其中,M代表Ni、Co、Fe或Ni和Co的混合。
3、根据权利要求1所述的密封系统,其中,所述旋转构件是涡轮叶片。
4、根据权利要求3所述的密封系统,其中,所述的涡轮叶片具有翼面部分和平台部分,并且该翼面部分或平台部分或二者都至少部分涂覆有成分与上述研磨端基本相同的柱状热屏障层。
5、根据权利要求1所述的密封系统,其中,所述旋转构件是设置于涡轮转子上的涡轮转子刀刃,而磨损性密封面设置于涡轮导向叶片上形成内部气封。
6、根据权利要求1所述的密封系统,其中,所述旋转构件是压气机叶片。
7、根据权利要求1所述的密封系统,其中,所述旋转构件是设置于压气机转子上的压气机转子刀刃,而磨损性密封面设置于压气机转子上形成的内部气封。
8、一种燃气涡轮发动机密封系统,该系统包括一个具有设置成与静止的磨损性密封面呈摩擦关系的研磨端的旋转构件,其中,所述研磨端含有比该磨损性密封面更硬的材料,以便于该研磨端切削磨损性密封面,其特征在于:
该研磨端包括具有柱状结构的氧化锆研磨层,其中,该氧化锆研磨层包括氧化锆和约3wt%到约25wt%的选自氧化钇、氧化镁、氧化钙以及它们的混合物的稳定剂,并且该研磨端设置在旋转部件上的基本上无研磨料的表面上。
9、根据权利要求8所述的密封系统,其中,所述研磨端进一步包括设置于氧化锆研磨层和旋转构件之间的氧化铝层。
10、根据权利要求8所述的密封系统,其中,所述旋转构件是涡轮叶片。
11、根据权利要求10所述的密封系统,其中,所述涡轮叶片具有翼面部分和平台部分,并且翼面部分或平台部分或二者都至少部分地涂覆有与上述研磨端成分相同的柱状结构的热障层。
12、根据权利要求8所述的密封系统,其中,所述旋转构件是设置于涡轮转子上的涡轮转子刀刃,而磨损性密封面设置于涡轮导向叶片上形成内部气封。
13、根据权利要求8所述的密封系统,其中,所述旋转构件是压气机叶片。
14、根据权利要求8所述的密封系统,其中所述的构件是设置于压气机转子的压气机转子刀刃,而磨损性密封面设置于压气机转子上形成内部气封。
15、一种包括研磨端的燃气涡轮发动机叶片,其中,所述研磨端包括具有柱状结构的氧化锆研磨层,其中,该氧化锆研磨层包括氧化锆和约3wt%到约25wt%的选自氧化钇、氧化镁、氧化钙和它们的混合物的稳定剂。
16、根据权利要求15所述的叶片,其中,所述研磨端还包括设置于氧化锆研磨层和旋转构件之间的金属结合层,该结合层含有扩散型铝化物、一种Ni和Al形成的合金或MCrAlY合金,其中,M代表Ni、Co、Fe或Ni和Co的混合。
17、根据权利要求15所述的叶片,其中,所述研磨端还包括设置于氧化锆研磨层和旋转构件之间的氧化铝层。
18、一种包括研磨端的燃气涡轮发动机刀刃,其中,所述研磨端包括具有柱状结构的氧化锆研磨层,其中,该氧化锆研磨层包括氧化锆和约6wt%到约20wt%的选自氧化钇、氧化镁、氧化钙和它们的混合物的稳定剂。
19、根据权利要求18所述的刀刃,其中,所述研磨端还包括设置于氧化锆研磨层和旋转构件之间的金属结合层,该结合层含有扩散型铝化物、一种Ni和Al形成的合金或MCrAlY合金,其中,M代表Ni、Co、Fe或Ni和Co的混合。
20、根据权利要求18所述的刀刃,其中,所述研磨端还包括设置于氧化锆研磨层和旋转构件之间的氧化铝层。
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US (1) | US6190124B1 (zh) |
EP (1) | EP0919699B2 (zh) |
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CA (1) | CA2252658C (zh) |
DE (1) | DE69826096T3 (zh) |
RU (1) | RU2229031C2 (zh) |
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- 1998-11-03 TW TW087118265A patent/TW411304B/zh not_active IP Right Cessation
- 1998-11-03 CA CA002252658A patent/CA2252658C/en not_active Expired - Fee Related
- 1998-11-24 RU RU98121425/06A patent/RU2229031C2/ru not_active IP Right Cessation
- 1998-11-24 UA UA98116228A patent/UA61908C2/uk unknown
- 1998-11-24 DE DE69826096T patent/DE69826096T3/de not_active Expired - Lifetime
- 1998-11-24 EP EP98309624A patent/EP0919699B2/en not_active Expired - Lifetime
- 1998-11-25 KR KR1019980050730A patent/KR100597498B1/ko not_active IP Right Cessation
- 1998-11-26 JP JP33516798A patent/JP4322980B2/ja not_active Expired - Lifetime
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Cited By (12)
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CN1298965C (zh) * | 2001-11-09 | 2007-02-07 | 三菱重工业株式会社 | 涡轮机及其制造方法 |
CN101039754B (zh) * | 2004-08-09 | 2010-11-03 | 通用汽车有限责任公司 | 研磨方法和产品 |
CN102971446A (zh) * | 2010-07-06 | 2013-03-13 | 斯奈克玛 | 用于涡轮叶片的、具有带间隔开的柱体的柱状结构的热障 |
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CN104053857A (zh) * | 2012-01-17 | 2014-09-17 | 斯奈克玛 | 涡轮机转子叶片 |
CN104053857B (zh) * | 2012-01-17 | 2016-02-10 | 斯奈克玛 | 涡轮机转子叶片 |
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CN105452530A (zh) * | 2013-08-08 | 2016-03-30 | 索拉透平公司 | 高孔隙度可磨耗涂层 |
CN105452530B (zh) * | 2013-08-08 | 2018-09-11 | 索拉透平公司 | 高孔隙度可磨耗涂层 |
CN115418599A (zh) * | 2022-08-24 | 2022-12-02 | 昆山西诺巴精密模具有限公司 | 一种发动机叶轮的热障涂层及表面处理方法 |
Also Published As
Publication number | Publication date |
---|---|
EP0919699B2 (en) | 2011-07-13 |
DE69826096D1 (de) | 2004-10-14 |
EP0919699A2 (en) | 1999-06-02 |
KR19990045567A (ko) | 1999-06-25 |
CA2252658A1 (en) | 1999-05-26 |
JP4322980B2 (ja) | 2009-09-02 |
US6190124B1 (en) | 2001-02-20 |
DE69826096T2 (de) | 2005-09-29 |
EP0919699A3 (en) | 2000-11-08 |
DE69826096T3 (de) | 2012-01-12 |
SG71165A1 (en) | 2000-03-21 |
RU2229031C2 (ru) | 2004-05-20 |
KR100597498B1 (ko) | 2006-08-30 |
JPH11229810A (ja) | 1999-08-24 |
TW411304B (en) | 2000-11-11 |
CA2252658C (en) | 2002-08-13 |
EP0919699B1 (en) | 2004-09-08 |
UA61908C2 (en) | 2003-12-15 |
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