CN106660890B - 热和环境阻挡涂层组合物 - Google Patents
热和环境阻挡涂层组合物 Download PDFInfo
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- CN106660890B CN106660890B CN201580035987.3A CN201580035987A CN106660890B CN 106660890 B CN106660890 B CN 106660890B CN 201580035987 A CN201580035987 A CN 201580035987A CN 106660890 B CN106660890 B CN 106660890B
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- C04B41/80—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone of only ceramics
- C04B41/81—Coating or impregnation
- C04B41/85—Coating or impregnation with inorganic materials
- C04B41/87—Ceramics
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- C04B41/009—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone characterised by the material treated
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- C01—INORGANIC CHEMISTRY
- C01B—NON-METALLIC ELEMENTS; COMPOUNDS THEREOF; METALLOIDS OR COMPOUNDS THEREOF NOT COVERED BY SUBCLASS C01C
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- C01G—COMPOUNDS CONTAINING METALS NOT COVERED BY SUBCLASSES C01D OR C01F
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- C01G—COMPOUNDS CONTAINING METALS NOT COVERED BY SUBCLASSES C01D OR C01F
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- C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
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- C04B41/5027—Oxide ceramics in general; Specific oxide ceramics not covered by C04B41/5029 - C04B41/5051
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Abstract
提供涂布基材,其包含:基材;和包含具有式Ln2ABO8的化合物的阻挡涂层,其中Ln包括钪、钇、镧、铈、镨、钕、钷、钐、铕、钆、铽、镝、钬、铒、铥、镱、镥或其混合物;A包括Si、Ti、Ge、Sn、Ce、Hf、Zr或其组合;和B包括Mo、W或其组合。在一个实施方案中,B包括Mo。
Description
优先权信息
本申请要求Kirby等人在2014年6月30日提交的标题为“Thermal andEnvironmental Barrier Coating Compositions and Methods of Deposition (热和环境阻挡涂层组合物以及沉积方法)”的美国临时专利申请序号62/018,983和Kirby等人在2014年10月28日提交的标题为“Thermal And Environmental Barrier CoatingCompositions And Methods Of Deposition (热和环境阻挡涂层组合物以及沉积方法)”的美国临时专利申请序号62/069,346的优先权。两个优先权申请的公开内容通过引用结合在本文中。
发明领域
概括而言,本发明的实施方案涉及用于陶瓷部件和/或金属部件的热和环境阻挡涂层及其制备方法。
发明背景
不断寻求用于燃气涡轮发动机的较高操作温度以便改进其有效性。然而,当操作温度提高时,发动机的部件的高温耐用性必须相应地提高。高温能力的显著进步业已通过铁、镍和钴基超合金的配制获得。然而,在由超合金构建的许多热气路径部件的情况下,热阻挡涂层(TBC)可以用于使部件绝缘且可以在承受负载的合金和涂层表面之间维持明显的温差,因此限制结构部件的热暴露。
虽然业已发现超合金广泛用于在整个燃气涡轮发动机中且尤其是在较高温工段中使用的部件,但是业已提议可替代的较轻重量的基材材料,例如陶瓷基质复合材料(CMC)材料。CMC和整体陶瓷部件可以涂有环境阻挡涂层(EBC)以保护它们免受高温发动机工段的苛刻环境。EBC可以提供致密、气密密封来抵抗热燃烧环境中的腐蚀气体。在干燥的高温环境中,硅基(非氧化物) CMC和整体陶瓷经受氧化以形成保护性氧化硅片状物(scale)。然而,氧化硅与例如见于燃气涡轮发动机中的高温蒸汽快速反应,以形成挥发性硅物类。这种氧化/挥发过程会在发动机部件的寿命期间导致显著的材料损失或衰退。这种衰退还在包含氧化铝的CMC和整体陶瓷部件中出现,原因是氧化铝也与高温蒸汽反应以形成挥发性铝物类。
当前,用于CMC和整体陶瓷部件的大多数EBC由三层涂层体系组成,所述三层涂层体系一般包括粘结涂布层、施加到粘结涂布层的至少一个过渡层和施加到过渡层的任选的外层。任选地,二氧化硅层可以存在于粘结涂布层和相邻的过渡层之间。这些层一起可以为CMC或整体陶瓷部件提供环境保护。
更具体而言,所述粘结涂布层可以包含硅且一般可以具有约0.5密耳(约12.7 μm)-约6密耳(约152 μm)的厚度。对于硅基非氧化物CMC和整体陶瓷,所述粘结涂布层充当氧化阻挡物以防止基材氧化。所述二氧化硅层可以施加到粘结涂布层,或者可以在粘结涂布层上自然或有意形成。所述过渡层通常可以包含莫来石、铝硅酸钡锶(BSAS)及其各种组合,而任选的外层可以包含BSAS。可以存在1-3个过渡层,各个层具有约0.1密耳(约2.5 μm)-约6密耳(约152 μm)的厚度,且任选的外层可以具有约0.1密耳(约2.5 μm)-约40密耳(约1mm)的厚度。
过渡层和外层各自可以具有不同的孔隙率。在约10%或更小的孔隙率下,所述层对燃烧环境中的热气体气密密封。在约10%-约40%孔隙率的情况下,所述层可以呈现机械完整性,但热气体可以渗透通过涂布层损坏下面的EBC。虽然至少一个过渡层或外层为气密的是有必要的,但是可能有利的是具有一些较高孔隙率范围的层以减轻由涂层材料和基材之间的任何热膨胀失配引发的机械应力。
遗憾地,业已观察到铝硅酸钙镁(CMAS)的沉积物在位于燃气涡轮发动机的较高温工段内、特别是在燃烧器和涡轮工段中的部件上形成。这些CMAS沉积物对热阻挡涂层寿命表现出有害作用,且已知BSAS和CMAS在高温即高于CMAS的熔点(约1150℃-1650℃)下化学相互作用。还已知通过BSAS和CMAS相互作用形成的反应副产物可能对EBC有害,以及在高温蒸汽的存在下易于挥发。这种挥发可以导致涂层材料和对下面部件的保护的损失。因此,预期存在的CMAS将与EBC相互作用,由此危害部件性能以及部件寿命。因此,需要用于制备抗CMAS且抗衰退的EBC和陶瓷部件的方法。
发明概述
本发明的各方面和优点将部分地在以下描述中说明,或可以从该描述显而易见,或可以通过实施本发明获知。
概括而言,提供了涂布基材,其包含:基材;和包含具有式Ln2ABO8的化合物的阻挡涂层,其中Ln包括钪、钇、镧、铈、镨、钕、钷、钐、铕、钆、铽、镝、钬、铒、铥、镱、镥或其混合物;A包括Si、Ti、Ge、Sn、Ce、Hf、Zr或其组合;和B包括M、W或其组合。在一个实施方案中,B包括Mo。
概括而言,还提供了包含上文所述的涂布基材的燃气涡轮。在一个实施方案中,所述涂布基材限定位于燃气涡轮的热气流动路径内的涡轮部件,使得所述涂层在部件上形成阻挡涂层以在暴露于热气流动路径时保护燃气涡轮内的部件。
参考以下描述和随附权利要求,本发明的这些和其他特征、方面和优点将变得更好理解。结合在本说明书中且构成本说明书的一部分的附图说明了本发明的实施方案,且与本说明书一起用于解释本发明的原理。
附图简述
认为是本发明的主题被特别指出且在说明书的结论部分明确要求保护。然而,结合附图参考以下描述,可以最好理解本发明,其中:
图1为根据文中所公开的一个实施方案的例示性涂布基材的横截面示意图;
图2为根据文中所公开的一个实施方案的另一个例示性涂布基材的横截面示意图;
图3为根据文中所公开的一个实施方案的又一个例示性涂布基材的横截面示意图;
图4为根据文中所公开的一个实施方案的再一个例示性涂布基材的横截面示意图;
图5为根据文中所公开的一个实施方案的再一个例示性涂布基材的横截面示意图;
图6为根据文中所公开的一个实施方案的再一个例示性涂布基材的横截面示意图;和
图7显示与超合金材料(N5)相比各种例示性Ln2ABO8化合物的CTE曲线。
在本说明书和附图中重复使用附图标记旨在表示本发明的相同或类似的特征或要素。
发明详述
现在将详细提及本发明的实施方案,其一个或多个实施例在附图中说明。通过解释本发明提供各个实施例,并非限制本发明。实际上,本领域技术人员将显而易见的是在不偏离本发明的范围或精神的情况下,可以在本发明中进行各种修改和变化。例如,作为一个实施方案的一部分说明或描述的特征可以与另一个实施方案一起使用以产生又一个实施方案。因此,本发明旨在涵盖落入随附权利要求及其等价物范围内的这些修改和变化。
在本公开中,当层描述为在另一个层或基材“上”或“上方”时,应当理解,层可以直接彼此接触或在层之间具有另一个层或结构(feature),除非明确作出相反说明。因此,这些术语仅描述层彼此的相对位置且并不必表示“在顶部”,原因是相对位置的高或低取决于装置相对于观察者的取向。
在本公开中使用化学元素的常见化学缩写(例如元素周期表上通常所见)来对其进行讨论。例如,氢通过其常见化学缩写H表示;氦通过其常见化学缩写He表示;等等。
概括而言,提供了具有包含式Ln2ABO8的化合物的涂层的基材,其中Ln包括稀土元素或稀土元素的混合物;A包括Si、Ti、Ge、Sn、Ce(例如,Ce4+)、Hf、Zr或其组合;和B包括Mo、W或其组合。在一个实施方案中,所述化合物在涂层内具有锆石晶体结构。例如,所述涂层可以具有单相结构(例如,锆石晶体结构或白钨矿晶体结构),第二晶体相小于约10体积%。
“Ln”指钪(Sc)、钇(Y)、镧(La)、铈(Ce)、镨(Pr)、钕(Nd)、钷(Pm)、钐(Sm)、铕(Eu)、钆(Gd)、铽(Tb)、镝(Dy)、钬(Ho)、铒(Er)、铥(Tm)、镱(Yb)、镥(Lu)或其混合物的稀土元素。在具体的实施方案中,Ln选自钕、钆、铒、钇及其混合物。
在一个实施方案中,B包括Mo。在某些实施方案中,B包括Mo和W的组合。例如,所述化合物可以具有式Ln2AMoxW1-xO8,其中0 ≤ x ≤约0.5 (例如,约0.1 ≤ x ≤ 约0.5)。
虽然式Ln2ABO8的化合物在高温蒸汽(例如在燃气涡轮的热气路径中所见)中表现出高稳定性,但是化合物中最不稳定的元素在B位点(即,Mo和/或W)上。然而,即使一些Mo或W挥发,结果会是在表面上的Ln2AO5化合物,该化合物也对高温蒸汽衰退具有很强的抵抗力。因此,在一个实施方案中,可以选择在Ln位点的材料使得在涂层表面上形成氧磷灰石(oxyapetite)相和Ln2AO5相的混合物。这种反应使材料密封,以免熔融铝硅酸盐深入渗透到EBC体系中。而且,在Ln2ABO8熔融铝硅酸盐反应层中存在Ln2AO5组分改进了粘合,原因是Ln2AO5具有低于氧磷灰石的热膨胀;导致净热膨胀接近于基材的热膨胀。此外,由熔融铝硅酸盐和包括Ln2ABO8的层之间的反应产生的Ln2AO5和氧磷灰石相两者对高温蒸汽衰退具有抵抗力。
虽然A可以为Si、Ti、Ge、Sn、Ce、Hf、Zr中的任一种或其组合,在一个具体的实施方案中,A包括单独的Si或与Ti、Sn、Ce、Ge、Hf和/或Zr的组合。例如,所述化合物可以具有式:Ln2SiyA1-yMoxW1-xO8,其中0 ≤ x ≤ 约0.5;0 < y ≤ 约0.5;且A为Ti、Ge、Sn、Ce、Hf、Zr或其组合。在某些实施方案中,A可以为单独的Hf和/或Zr,或与Ti、Sn、Ce、Ge和/或Si的组合,原因是Hf和/或Zr的存在对升高化合物的熔点具有显著的作用。
概括而言,在涂层中使用的化合物中的组分的选择可以选择以确保单相晶体结构(例如,锆石结构)和紧密匹配基材的热膨胀系数(“CTE”)。CTE匹配(或接近匹配)可以使得在基材表面上形成和操作致密无裂纹涂布层以确保高温水蒸气不渗透到下面的基材。例如,如果基材为包括碳化硅的CMC,那么包括具有式Y2SiMoO8的化合物的涂层会是特别合适的,原因是SiC和Y2SiMoO8的CTE接近。因此,所述化合物的一个优选实施方案可以具有式:Ln2SiyA1-yMoxW1-xO8,其中0 ≤ x ≤ 约0.5;0 < y ≤ 约0.5;且A为Ti、Ge、Sn、Ce、Hf、Zr或其组合,尤其当所述化合物具有锆石晶体结构时。
Ln2ABO8的许多其他化合物具有白钨矿结构,白钨矿结构可以具有几乎等价于SiCCMC的热膨胀或高于SiC CMC的热膨胀。然而,如果高于SiC,则由这些材料形成的白钨矿构成的垂直开裂层仍可以提供对高温蒸汽的一些抵抗力,特别是如果在下面存在无裂纹的另外的层来充当气密层。另外,式Ln2ABO8的化合物(具有锆石或白钨矿结构)提供免受熔融铝硅酸盐(特别是包含灰尘或砂的那些)的保护。也就是,所述涂层对熔融铝硅酸盐本身具有抵抗力,使得所述涂布层尽管与熔融铝硅酸盐反应仍保持气密。
不期望受任何具体理论束缚,认为Ln2ABO8化合物的CTE可以通过改变由式中的“A”表示的元素的大小来控制。也就是,通过在Ln2ABO8化合物中有意使用Si、Ti、Ge、Sn、Ce、Hf、Zr或其组合,可以控制所得的涂层的CTE。更具体而言,认为提高式中的由“A”表示的位置的元素的离子大小可以导致涂层中提高的CTE。该特征在下文实施例章节中更详细讨论。
可以作为基材上的孤立涂布层(存在或不存在粘结层)、在基材上的EBC体系的任何层内和/或作为EBC体系上的可磨损层包括这种涂层。
来看图1,例如,显示例示性的涂布基材10,其包括基材12、在基材12的表面13上的粘结涂布层14,和在粘结涂布层14上的阻挡涂层16。共同地,粘结涂布层14和阻挡涂层16形成涂布基材10的EBC体系18。在该实施方案中,阻挡涂层16包括如上文更详细讨论的具有式Ln2ABO8的任何化合物。
I. CMC基材
在一个实施方案中,所述基材包括陶瓷基质复合材料(CMC)材料。如文中使用的“CMC”指含硅或氧化物-氧化物基质和增强材料。文中使用的可接受的CMC的一些实例可以包括但不限于具有基质和增强纤维的材料,所述基质和增强纤维包含非氧化物硅基材料,例如碳化硅、氮化硅、碳氧化硅、氧氮化硅及其混合物。实例包括但不限于具有碳化硅基质和碳化硅纤维、氮化硅基质和碳化硅纤维;和碳化硅/氮化硅基质混合物和碳化硅纤维的CMC。此外,CMC可以具有由氧化物陶瓷构成的基质和增强纤维。这些氧化物-氧化物复合材料如下描述。
具体而言,所述氧化物-氧化物CMC可以由包含氧化物基材料的基质和增强纤维构成,所述氧化物基材料例如为氧化铝(Al2O3)、二氧化硅(SiO2)、铝硅酸盐,及其混合物。铝硅酸盐可以包括晶体材料例如莫来石(3Al2O3 2SiO2),以及玻璃质铝硅酸盐。
如文中使用的“整体陶瓷”指包含仅有的碳化硅、仅有的氮化硅、仅有的氧化铝、仅有的二氧化硅或仅有的莫来石的材料。在文中,CMC和整体陶瓷统称为“陶瓷”。
所述涂层可以在这种CMC上用作环境阻挡涂层(“EBC”)。例如,所述EBC在文中可以适合在高温环境中可见的陶瓷基材部件上使用,例如存在于燃气涡轮发动机中的那些,例如,燃烧器部件、涡轮叶片、护罩、喷嘴、防热罩和导叶。
如图1中所示,包括Ln2ABO8化合物的阻挡涂层16可以用作在粘结涂布层14(例如具有氧化硅热生长氧化物(TGO)的硅金属或硅金属层)上的单个EBC层(即,不存在任何其他ECB层)。可以实现该单个EBC层,原因是Ln2ABO8化合物由于阻挡涂层16的CTE与基材12接近匹配在高温应用期间保持致密和无裂纹的能力。阻挡涂层16还具有抗CMAS性和抗衰退性,原因是如果B位点挥发,其容易形成表面Ln2AO5。
在另一个实施方案中,可以在Ln2ABO8的顶部作为外层24有意地沉积Ln2AO5,而不是让Ln2AO5原位形成。
或者,可以作为CMC基材上的任何EBC体系内的层包括阻挡涂层16。图2和3中显示的实施方案描述例示性EBC体系18,其包括其中的阻挡涂层16。例如,任选的二氧化硅层15可以存在于粘结涂布层14上和位于粘结涂布层14和阻挡涂层16之间。二氧化硅层15可以施加到粘结涂布层14,或者,可以自然或有意地在粘结涂布层14上形成。
气密层20(即,层(a layer that))可以任选地存在于EBC体系18中,例如图2和3的例示性涂布基材10中所示。如果存在,气密层20可以包括稀土二硅酸盐、莫来石、铝硅酸钡锶(BSAS)和/或其组合。这种气密层20防止高温水蒸气渗透,但可能受限于没有CMAS缓和能力。
另外或可替代地,任选的过渡层22可以存在于EBC体系18中,如图2和3中所示。所述过渡层可以包含稀土元素(Ln)、稀土氧化物、氧化锆、氧化铪、用碱土或稀土元素部分或完全稳定的氧化铪、用碱土或稀土元素部分或完全稳定的氧化锆、稀土铪酸盐、稀土锆酸盐、稀土单硅酸盐、氧化铝、堇青石和/或其组合。这种过渡层22防止EBC体系叠层中的相邻层之间的反应,可能受限于不能防止高温水蒸气渗透,且可以或可以不具有CMAS缓和能力。
在这种实施方案中,如果包括式Ln2ABO8化合物(锆石或白钨矿)的阻挡涂层16沉积在另一个EBC层例如气密层20(例如,包括Yb2Si2O7的气密层20)、过渡层22 (例如HfO2)或其组合的顶部,其还可以提供优异的抗CMAS性。
在图2的例示性涂布基材10中,类似于图1中所示的实施方案,阻挡涂层16限定EBC体系的外表面17。在这种实施方案中,暴露的阻挡涂层16可以另外用作EBC体系18和CMC基材12上的可磨损层。
然而,在图3中所示的实施方案中,任选的外涂布层24和任选的可磨损层26可以存在于阻挡涂层16上。这种外涂布层24可以为Ln2AO5,且可磨损层26可以为BSAS或稀土二硅酸盐(例如二硅酸镱或Yb2Si2O7),其中可磨损层为最外层。
例如,图4中所示的具体实施方案具有EBC体系18,其包括基材12 (例如,SiC CMC基材)上的粘结涂布层14 (例如,硅的粘结涂布层)、阻挡涂层16 (例如,如上文所讨论的Ln2SiyA1-yMoxW1-xO8)和外涂布层24 (例如,如上文所讨论的Ln2SiO5,例如Y2SiO5)。其他层可以包括在该例示性EBC体系中,如文中所讨论。
如所述,所述涂布基材可以用作燃气涡轮的涡轮部件。具体而言,所述涡轮部件可以为位于燃气涡轮的热气流动路径内的CMC部件,使得该涂层在部件上形成环境阻挡涂层以在暴露于热气流动路径时保护燃气涡轮内的部件。
II. 金属基材
在其他实施方案中,所述基材包括超合金材料,例如镍基超合金、钴基超合金、钛基超合金或铁基超合金。包括如上文所讨论的Ln2ABO8化合物的涂层可以用作这种超合金上的热阻挡涂层(“TBC”)。例如,文中的TBC可以适合在高温环境中可见的超合金基材部件上使用,例如存在于燃气涡轮发动机中的那些,例如,燃烧器部件、涡轮叶片、护罩、喷嘴、防热罩和导叶。
再来看图1,包括Ln2ABO8的化合物的阻挡涂层16可以用作超合金材料上的单个TBC层(即,不存在任何其他TBC层)。阻挡涂层16还具有抗CMAS性和抗衰退性,原因是,如果B位点挥发,则其容易形成表面Ln2AO5。或者,粘结涂布层14可以存在于金属基材和阻挡涂层16之间。所述粘结涂层可以包括形成氧化铝热生长氧化物(TGO)的材料,例如铂和其他贵金属铝化物(例如,包括钌、铑、钯、银、锇、铱、铂、金的铝化物或其混合物)、铝化镍和MCrAlY(其中M为镍、钴、铁或其组合),或可以包括形成氧化硅TGO的材料例如金属硅化物(例如硅化钼、硅化铁等)。
或者,可以包括阻挡涂层16作为合金基材上的任何TBC体系内的层。来看图2和3中所示的实施方案,任选的氧化物层15 (例如,氧化硅、氧化铝和/或氧化锌,任选地具有作为稳定剂存在的过渡金属,例如氧化钇)可以存在于粘结涂布层14上且位于粘结涂布层14和阻挡涂层16之间。氧化物层15可以施加到粘结涂布层14,或者,可以自然或有意地在粘结涂布层14上形成。
另外或可替代地,任选的TBC层22和/或任选的TBC层24可以存在于TBC体系18中,如图2和3中所示。任选的TBC层可以包含稀土元素(Ln)、稀土氧化物、稀土镓酸盐、稀土硅酸盐、稀土铁氧化物、用碱土或稀土元素部分或完全稳定的氧化铪、用碱土或稀土元素部分或完全稳定的氧化锆、稀土铪酸盐、稀土锆酸盐、稀土单硅酸盐和/或其组合。相对于层16,这种任选的TBC层可以位于下面(任选的TBC层22)、位于外部位置(任选的TBC层24)或以组合定位。
在该实施方案中,如果沉积在任选的TBC层22 (例如,用稀土元素部分或完全稳定的氧化锆)的顶部,包括式Ln2ABO8的化合物(锆石或白钨矿)的阻挡涂层16还可以提供优异的抗CMAS性。在这种情况下,任选的TBC层22还可以防止阻挡涂层16和合金基材12、粘结涂层14或粘结涂层TGO 15之间的反应。
在图2的例示性涂布基材10中,类似于图1中所示的实施方案,阻挡涂层16限定TBC体系的外表面17。在这种实施方案中,暴露的阻挡涂层16可以另外用作TBC体系18和合金基材12上的可磨损层。
例如,图5中所示的具体实施方案具有TBC体系18,其包括基材12 (例如,超合金基材)上的粘结涂布层14 (例如,Pt铝化物的粘结涂布层)、粘结涂布层14上的氧化物层15(例如,包含氧化钇稳定的ZrO2)和阻挡涂层16 (例如,如上文所讨论的Ln2ABO8)。其他层可以包括在如文中所讨论的例示性TBC体系中。
然而,在图3中所示的实施方案中,任选的TBC层24和任选的可磨损层26可以存在于阻挡涂层16上。任选的可磨损层26可以包含Ln2ABO8、上文所述的任选的TBC层24材料中的任一种,或其组合。
如所述,所述涂布基材可以用作燃气涡轮的涡轮部件。具体而言,所述涡轮部件可以为位于燃气涡轮的热气流动路径内的超合金部件,使得涂层在部件上形成热阻挡涂层以在暴露于热气流动路径时保护燃气涡轮内的部件。
III. 可磨损层
上文讨论的式Ln2ABO8化合物还可以用作可磨损涂层形成基材上的任何类型的TBC或EBC体系的外部暴露表面。所述可磨损涂层可以由单层或多层形成。例如,可磨损层26的实施方案可以包括连续致密层(例如,孔隙率小于约15%)、连续多孔层(例如,孔隙率大于约15%)和/或致密(例如,孔隙率小于约15%)可磨损脊型图案。
来看图6,显示具有在基材12上的EBC或TBC体系18和在EBC或TBC体系18上的可磨损涂层26的例示性实施方案。在文中,可磨损涂层26限定外表面,该外表面构造成在与另一个部件接触时磨损,有效保护下面的EBC或TBC体系18。使用上文讨论的式Ln2ABO8化合物可以进一步增加对EBC或TBC体系18的阻挡性质以及根据具体的EBC或TBC体系18和/或基材12定制CTE。
例如,如果基材12为SiC CMC,那么EBC体系18可以包括粘结涂布层(例如,硅的粘结涂布层)、气密层(例如,包括稀土二硅酸盐)、过渡层(例如,如上文所讨论的Ln2SiO5,例如Y2SiO5),和包含式Ln2ABO8化合物的可磨损层26。EBC层(例如,包含BSAS)和/或另外的气密层(例如,包含稀土二硅酸盐)还可以存在于EBC体系18上,例如在粘结涂布层和气密层之间。
实施例
尽管不期望受任何具体理论束缚,但还是认为,增加由式中的“A”表示的位置的元素的离子大小可以导致涂层的CTE提高。图7显示与以下材料相比较各种例示性Ln2ABO8化合物的CTE:超合金材料(从General Electric Company以商品名称N5市售);CMC材料(SiC-SiC CMC);已知的稀土单硅酸盐EBC材料;和另一种已知的稀土单硅酸盐EBC材料;和已知的TBC层(8YSZ)。如所示,由式中的“A”表示的位置使用较大的元素通常导致在Ln2ABO8化合物中的提高的CTE。同样地,与Mo相比,在“B”位置上使用较大的W导致Ln2ABO8化合物的CTE提高。对于Ln位点,则反过来是正确的,其中较小的Ln元素导致Ln2ABO8化合物的CTE提高。通过调节Ln、A和B元素,材料的CTE可以向SiC CMC(具有较低CTE)或镍基超合金(具有较高CTE)的涂层的CTE的方向定制。
虽然业已描述本发明的一个或多个具体的实施方案,显而易见的是本领域技术人员可以采用其他形式。应当理解结合文中所述的涂层组合物使用“包含”具体公开和包括其中所述涂层组合物“基本上由所指定的组分组成”(即,包含所指定的组分且没有显著不利影响所公开的基本特征和新特征的其他组分)的实施方案,和其中所述涂层组合物“由所指定的组分组成”(即,只包含除了天然且不可避免地存在于各种所指定的组分中的污染物以外的所指定的组分)的实施方案。
本书面描述使用实施例来(包括最佳方式)公开本发明,且还使得本领域任何技术人员能够实施本发明,包括制备和使用任何设备或系统且进行任何结合的方法。本发明的可授予专利的范围通过权利要求限定,且可以包括本领域技术人员想到的其他实施例。如果这种其他实施例包括不与权利要求的书面语言不同的结构元素,或如果这种其他实施例包括与权利要求的书面语言无实质差别的等价结构元素,则它们旨在权利要求的范围内。
Claims (15)
1.用于燃气涡轮发动机的涂布基材(10),其包含:
基材(12),所述基材(12)包含陶瓷基质复合材料;和
包含具有下式的化合物的阻挡涂层(16):
Ln2ABO8
其中
Ln包括钪、钇、镧、铈、镨、钕、钷、钐、铕、钆、铽、镝、钬、铒、铥、镱、镥或其混合物;
A包括Si、Ti、Ge、Sn、Ce、Hf、Zr或其组合;和
B包括Mo、W或其组合。
2.权利要求1的涂布基材(10),其中Ln选自钪(Sc)、钇(Y)、镧(La)、铈(Ce)、镨(Pr)、钕(Nd)、钷(Pm)、钐(Sm)、铕(Eu)、钆(Gd)、铽(Tb)、镝(Dy)、钬(Ho)、铒(Er)、铥(Tm)、镱(Yb)、镥(Lu)及其混合物。
3.权利要求1的涂布基材(10),其中Ln包括钇。
4.权利要求1的涂布基材(10),其中B包括Mo。
5.权利要求4的涂布基材(10),其中所述化合物具有式:
Ln2AMoxW1-xO8,
其中
0.1 ≤ x ≤ 0.5。
6.权利要求1的涂布基材(10),其中B包括W、或Mo和W的组合。
7.权利要求6的涂布基材(10),其中所述化合物具有式:
Ln2AMoxW1-xO8
其中
0 ≤ x ≤ 0.5。
8.权利要求7的涂布基材(10),其中A包括Si。
9.权利要求8的涂布基材(10),其中所述化合物具有式:
Ln2SiyA1-yMoxW1-xO8
其中
0 ≤ x ≤ 0.5;
0 < y ≤ 0.5;和
A为Ti、Ge、Sn、Ce、Hf、Zr或其组合。
10.权利要求1的涂布基材(10),其中所述化合物具有式:Y2SiMoO8。
11.权利要求1的涂布基材(10),其中A包括Hf和/或Zr。
12.权利要求1的涂布基材(10),其中所述化合物包含锆石晶体结构或白钨矿结构。
13.权利要求1的涂布基材(10),其中所述涂布基材(10)还包含位于所述基材(12)和所述阻挡涂层(16)之间的粘结涂布层(14)。
14.权利要求13的涂布基材(10),其中所述粘结涂布层(14)包含硅、碳化硅、氮化硅、硅化钼、硅化铼或其组合。
15.权利要求1的涂布基材(10),其中所述涂布基材(10)还包含阻挡涂层(16)上的外涂布层(24),且其中所述外涂布层(24)包含Ln2SiO5,其中Ln为钪(Sc)、钇(Y)、镧(La)、铈(Ce)、镨(Pr)、钕(Nd)、钷(Pm)、钐(Sm)、铕(Eu)、钆(Gd)、铽(Tb)、镝(Dy)、钬(Ho)、铒(Er)、铥(Tm)、镱(Yb)、镥(Lu)或其混合物。
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