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公开(公告)号：EP1798311B1
公开(公告)日：2017-09-06
申请号：EP06126417.2
申请日：2006-12-18
CPC分类号： C23C4/04 , C23C28/027 , C23C28/028 , F01D5/288 , F01D25/007 , Y02T50/67 , Y10T428/12028 , Y10T428/12611
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2.发明公开Environmental barrier coating for silicon-containing substrates and process therefor 审中-公开对于含有硅衬底和其方法环境屏蔽涂层
公开(公告)号：EP1944280A3
公开(公告)日：2013-01-23
申请号：EP07122658.3
申请日：2007-12-07
CPC分类号： C04B41/85 , C04B35/195 , C04B41/009 , C04B41/5024 , C04B41/52 , C04B41/89 , C04B2235/3213 , C04B2235/3215 , C04B2235/3217 , C04B2235/3481 , C04B2235/79 , C04B2235/80 , C23C4/11 , C23C4/18 , C23C28/04 , C23C30/00 , F01D5/288 , F05D2230/90 , F05D2300/211 , F05D2300/2112 , F23M2900/05004 , F23R3/007 , Y02T50/67 , Y02T50/672 , C04B41/4527 , C04B41/5096 , C04B41/5037 , C04B41/5042 , C04B35/565 , C04B35/584 , C04B35/806 , C04B41/0072 , C04B41/4519 , C04B2111/0025
摘要： A protective coating (20) for use on a silicon-containing substrate (12), and deposition methods therefor, The coating (20) has a strontium-aluminosilicate (SAS) composition that is less susceptible to degradation by volatilization and in corrosive environments as a result of having at least an outer surface region (22) that consists essentially of one or more stoichiometric crystalline phases of SAS and is substantially free of a nonstoichiometric second crystalline phase of SAS that contains a substoichiometric amount of silica. The coating (20) can be produced by carrying out deposition and heat treatment steps that result in the entire coating (20) or just the outer surface region (22) of the coating (20) consisting essentially of the stoichiometric celsian phase.
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3.发明公开Turbine engine blade with multi-layer protective coating for the interior cooling passages 审中-公开Gasturbinenschaufelturbinenschaufel mit mehrschichtigerSchutzumhüllungfürdieInnenkühlungskanäle
公开(公告)号：EP2072759A2
公开(公告)日：2009-06-24
申请号：EP08170925.5
申请日：2008-12-08
发明人： Wortman, David John , Wustman, Roger Dale , Polley, Nicole Marie , Brammer, Kathleen Diana , Hazel, Brian Thomas
CPC分类号： F01D5/187 , F01D5/288 , F05D2230/30 , F05D2230/31 , F05D2230/80 , F05D2230/90 , Y02T50/67 , Y02T50/671 , Y02T50/676
摘要： A gas turbine blade 10 comprises a base metal, a platform 14, an airfoil 12 extending upwardly from the platform, a shank 18 extending downwardly from the platform. The shank has an exterior wall 71 and an internal passage 84, and the airfoil 12 has a cooling flow channel 34 inside the airfoil for flowing a cooling flow therethrough. The blade has a first chromide coating 102 contacting the base metal of at least a portion of an interior surface of the shank 18 and interdiffused therewith, wherein the first chromide coating does not have an aluminide coating deposited over it. The blade has a second chromide coating 144 contacting the base metal of at least a portion of an interior surface of the airfoil 12 and interdiffused therewith. A method 200 for preparing a gas turbine blade comprises the steps of applying chromide coatings 71, 72, 73, 74, sealing the interior passages 80 of the shank and airfoil and applying 82, 84 an aluminide or platinum aluminide coating and an optional ceramic layer 86 on the airfoil.
摘要翻译： 燃气轮机叶片10包括贱金属，平台14，从平台向上延伸的翼型件12，从平台向下延伸的柄18。 柄部具有外壁71和内部通道84，翼型件12在翼型件内部具有用于使冷却流动流过其中的冷却流道34。 刀片具有与刀柄18的内表面的至少一部分的基底金属接触并与其相互扩散的第一铬化物涂层102，其中第一铬酸盐涂层不具有沉积在其上的铝化物涂层。 叶片具有与翼型件12的内表面的至少一部分的基底金属接触并与其相互扩散的第二铬化物涂层144。 一种用于制备燃气轮机叶片的方法200包括以下步骤：施加铬酸盐涂层71,72,73,74，密封柄和翼型件的内部通道80，并施加82,84铝化物或铂铝化物涂层和任选的陶瓷层 86在翼型上。
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4.发明公开
公开(公告)号：EP1734025A3
公开(公告)日：2009-06-03
申请号：EP06251991.3
申请日：2006-04-10
CPC分类号： C23C28/04 , C04B41/009 , C04B41/52 , C04B41/89 , F01D5/284 , F01D5/288 , Y10T428/12576 , C04B41/4527 , C04B41/5096 , C04B41/5037 , C04B41/5024 , C04B41/5031 , C04B41/5044 , C04B41/5042 , C04B41/4529 , C04B41/522 , C04B35/565 , C04B35/584 , C04B35/806
摘要： A coating system (14) for Si-containing materials, particularly Si-based composites used to produce articles (10) exposed to high temperatures. The coating system (14) is a compositionally-graded thermal/environmental barrier coating (T/EBC) system (14) that includes an intermediate layer (24) containing yttria-stabilized hafnia (YSHf) and mullite, alumina and/or an aluminosilicate, which is used in combination with an inner layer (22) between a Si-containing substrate (12) and the intermediate layer (24) and a thermal-insulating top coat (18) overlying the intermediate layer (24). The intermediate layer (24) provides environmental protection to the silicon-containing substrate (12), and has a coefficient of thermal expansion between that of the top coat (18) and that of the inner layer (22) so as to serve as a transition layer therebetween. The intermediate layer (24) is particular well suited for use in combination with an inner layer (22) of an alkaline earth metal aluminosilicate (such as BSAS) and a top coat (18) formed of YSZ or YSHf.
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公开(公告)号：EP1683774A3
公开(公告)日：2009-04-15
申请号：EP05257002.5
申请日：2005-11-14
发明人： Spitsberg, Irene , Govern, Christine , Nagaraj, Bangalore Aswatha , Hazel, Brian Thomas , Mitchell, David Joseph
CPC分类号： F01D5/288 , C04B41/009 , C04B41/52 , C04B41/89 , C23C28/042 , C23C28/048 , Y10T428/12576 , Y10T428/12667 , Y10T428/12729 , C04B41/4527 , C04B41/5024 , C04B41/5037 , C04B41/5042 , C04B2111/00405 , C04B41/5044 , C04B41/4529 , C04B41/522 , C04B35/565 , C04B35/584 , C04B35/806
摘要： An article (10) comprises a substrate (12) formed of a silicon-comprising material, such as an article (10) exposed to the hostile thermal environment of a gas turbine engine. The article (10) further comprises an environmental barrier layer (16), e.g., an alkaline earth metal aluminosilicate, and a top coat (18) comprising hafnia stabilized with from 0.5 mole % to 10 mole % of an oxide of a metal selected from the group consisting of magnesium, calcium, scandium, yttrium, and lanthanide metals, and mixtures thereof. The article (10) optionally comprises a transition layer (20) between the environmental barrier layer (16) and the top coat (18). A method for preparing a thermal/environmental barrier coating (14) on a substrate (12) formed of a silicon-comprising material is also disclosed.
摘要翻译： 制品（10）包括由含硅材料（例如暴露于燃气涡轮发动机的不利热环境的制品（10））形成的基底（12）。 制品（10）还包含环境阻挡层（16），例如碱土金属硅铝酸盐和顶层（18），所述顶层（18）包含用0.5摩尔％至10摩尔％的选自 由镁，钙，钪，钇和镧系金属组成的组，以及它们的混合物。 制品（10）可选地包括在环境阻挡层（16）和顶部涂层（18）之间的过渡层（20）。 还公开了在由含硅材料形成的基板（12）上制备热/环境屏障涂层（14）的方法。
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6.发明公开
公开(公告)号：EP1666437A3
公开(公告)日：2007-06-27
申请号：EP05256089.3
申请日：2005-09-29
发明人： Boutwell, Brett Allen Rohrer , Govern, Christine , Hazel, Brian Thomas , Spitsberg, Irene , Nagaraj, Bangalore A.
CPC分类号： C04B41/009 , C04B41/52 , C04B41/89 , C23C28/042 , F01D5/288 , F05D2230/90 , F05D2300/2118 , F05D2300/50211 , F05D2300/611 , C04B41/4527 , C04B41/5096 , C04B41/5024 , C04B41/5037 , C04B41/5042 , C04B41/5031 , C04B41/522 , C04B41/4529 , C04B35/565 , C04B35/584 , C04B35/806 , C04B35/597
摘要： In accordance with an embodiment of the invention, a thermal barrier coating (TBC) for inclusion in a thermal barrier coating/environmental barrier coating system (TBC/EBC system) for use on a silicon containing material substrate is provided. The TBC comprises a compound having a primary constituent portion and a stabilizer portion stabilizing said primary constituent. The primary constituent portion of the TBC comprises hafnia present in an amount of at least about 5 mol% of the primary constituent. The stabilizer portion of said thermal barrier coating comprises at least one metal oxide comprised of cations with a +2 or +3 valence present in the amount of about 10 to about 40 mol% of the thermal barrier coating (14).
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7.发明公开Coated silicon comprising material for protection against environmental corrosion 有权涂覆的硅包含用于防止环境腐蚀的材料
公开(公告)号：EP1754802A2
公开(公告)日：2007-02-21
申请号：EP06253141.3
申请日：2006-06-16
发明人： Hazel, Brian Thomas
CPC分类号： C04B41/87 , C04B41/009 , C04B41/5045 , C04B41/52 , C04B41/89 , C23C28/042 , C23C28/322 , C23C28/345 , C23C28/3455 , C04B41/4527 , C04B41/5096 , C04B41/5037 , C04B41/5024 , C04B35/565 , C04B35/584 , C04B35/806
摘要： In accordance with an embodiment of the invention, an article is disclosed which comprises a gas turbine engine component substrate comprising a silicon material; and an environmental barrier coating overlying the substrate, wherein the environmental barrier coating comprises cerium oxide, and the cerium oxide reduces formation of silicate glass on the substrate upon exposure to corrodant sulfates.
摘要翻译： 根据本发明的实施例，公开了一种制品，其包括：包含硅材料的燃气涡轮发动机部件基板; 以及覆盖所述基底的环境屏障涂层，其中所述环境屏障涂层包含氧化铈，并且所述氧化铈减少暴露于腐蚀性硫酸盐时在所述基底上形成的硅酸盐玻璃。
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8.发明公开Turbine component other than airfoil having ceramic corrosion resistant coating and methods for making same 审中-公开Turbinnenkomponente除了Turbinnenschaufel与它们的制备耐腐蚀的陶瓷层和进程
公开(公告)号：EP1710398A1
公开(公告)日：2006-10-11
申请号：EP06251560.6
申请日：2006-03-23
CPC分类号： C23C18/1283 , C23C18/1208 , C23C18/1225 , C23C18/1241 , C23C18/1254 , C23C26/00 , C23C28/042 , C23C28/322 , C23C28/345 , C23C28/3455 , C23C30/00 , F01D5/28 , F01D5/286 , F01D5/288 , F01D25/007 , F05D2230/314 , F05D2230/90 , F05D2260/95 , F05D2300/21 , F05D2300/2118 , F05D2300/611 , Y02T50/67
摘要： An article comprising a turbine component other than an airfoil having a metal substrate (60) and a ceramic corrosion resistant coating (64) overlaying the metal substrate (60). This coating (64) has a thickness up to 127 microns and comprises a ceramic metal oxide selected from the group consisting of zirconia, hafnia and mixtures thereof. This coating (64) can be formed by a method comprising the following steps: (a) providing a turbine component other than an airfoil comprising the metal substrate (60); (b) providing a gel-forming solution comprising a ceramic metal oxide precursor; (c) heating the gel-forming solution to a first preselected temperature for a first preselected time to form a gel; (d) depositing the gel on the metal substrate (60); and (e) firing the gel at a second preselected temperature above the first preselected temperature to form the ceramic corrosion resistant coating (64) comprising the ceramic metal oxide. This coating (64) can also be formed by alternative methods wherein a ceramic composition comprising the ceramic metal oxide is deposited by physical vapor deposition on the metal substrate (60) to provide a strain-tolerant columnar structure, or is thermal sprayed on the metal substrate (60).
摘要翻译： 一种制品，包括比具有金属基底（60）和陶瓷的耐腐蚀涂层（64）的翼型件的其它涡轮机部件覆盖所述金属基体（60）。 该涂层（64）的厚度达到127微米，并且包括选自氧化锆，氧化铪及它们的混合物中选出的陶瓷金属氧化物。 该涂层（64）可以通过包括以下步骤的方法形成：（a）提供比翼型包括金属基材（60）以外的涡轮机部件; （B）提供一种形成凝胶的溶液包含陶瓷的金属氧化物前体; （C）加热该形成凝胶的溶液，以第一预选温度下的第一预选的时间以形成凝胶; （d）沉积在金属基板上的凝胶（60）; 和（e）在高于第一预选温度的第二预选温度下烧制所述凝胶以形成陶瓷的耐腐蚀涂层（64）包括陶瓷金属氧化物。 该涂层（64）因此，可以通过可选的方法来形成worin的陶瓷组合物，其包括陶瓷金属氧化物是通过在金属基材的物理气相沉积（60）沉积，以提供应变耐受性柱状结构，或在金属热喷涂 基板（60）。
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公开(公告)号：EP1683774A2
公开(公告)日：2006-07-26
申请号：EP05257002.5
申请日：2005-11-14
发明人： Spitsberg, Irene , Govern, Christine , Nagaraj, Bangalore Aswatha , Hazel, Brian Thomas , Mitchell, David Joseph
CPC分类号： F01D5/288 , C04B41/009 , C04B41/52 , C04B41/89 , C23C28/042 , C23C28/048 , Y10T428/12576 , Y10T428/12667 , Y10T428/12729 , C04B41/4527 , C04B41/5024 , C04B41/5037 , C04B41/5042 , C04B2111/00405 , C04B41/5044 , C04B41/4529 , C04B41/522 , C04B35/565 , C04B35/584 , C04B35/806
摘要： An article (10) comprises a substrate (12) formed of a silicon-comprising material, such as an article (10) exposed to the hostile thermal environment of a gas turbine engine. The article (10) further comprises an environmental barrier layer (16), e.g., an alkaline earth metal aluminosilicate, and a top coat (18) comprising hafnia stabilized with from 0.5 mole % to 10 mole % of an oxide of a metal selected from the group consisting of magnesium, calcium, scandium, yttrium, and lanthanide metals, and mixtures thereof. The article (10) optionally comprises a transition layer (20) between the environmental barrier layer (16) and the top coat (18). A method for preparing a thermal/environmental barrier coating (14) on a substrate (12) formed of a silicon-comprising material is also disclosed.
摘要翻译： 制品（10）包括由诸如暴露于燃气涡轮发动机的恶劣热环境的物品（10）的含硅材料形成的基底（12）。 所述制品（10）还包括环境阻挡层（16），例如碱土金属铝硅酸盐，以及顶涂层（18），其包含用0.5mol％至10mol％的选自以下的金属的氧化物稳定的铪 由镁，钙，钪，钇和镧系金属组成的组及其混合物。 制品（10）任选地包括在环境阻挡层（16）和顶涂层（18）之间的过渡层（20）。 还公开了一种在由含硅材料形成的基底（12）上制备热/环境屏障涂层（14）的方法。
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10.发明公开Corrosion resistant coating composition, coated turbine component and method for coating same 审中-公开一个耐腐蚀层，涂覆的涡轮部件和方法，用于其的涂料组合物。
公开(公告)号：EP1672174A1
公开(公告)日：2006-06-21
申请号：EP05257289.8
申请日：2005-11-28
CPC分类号： C23C30/00 , C23C22/74 , C23C24/08 , C23C26/00 , F01D5/288 , F01D25/007 , F05D2230/90 , F05D2300/611 , Y10T428/12028 , Y10T428/12611 , Y10T428/1275
摘要： A composition comprising a particulate corrosion resistant component, and a glass-forming binder component. The particulate corrosion resistant component comprises from 0 to about 95% alumina particulates, and from 5 to 100% corrosion resistant non-alumina particulates having a CTE greater than that of the alumina particulates. Also disclosed is an article (30) comprising a turbine component (30) comprising a metal substrate (60) and a corrosion resistant coating (64) having thickness up to 254 microns overlaying the metal substrate (60). At least the layer of this coating (64) adjacent to the metal substrate (60) comprises a glass-forming binder component and the particulate corrosion resistant component adhered to the glass-forming binder component. Further disclosed is a method comprising the following steps: (a) providing a turbine component (30) comprising the metal substrate (60); (b) depositing on the metal substrate (60) a corrosion resistant coating composition; and (c) curing the deposited corrosion resistant coating composition to form at least one layer of a corrosion resistant coating (64) having a thickness up to 254 microns.
摘要翻译： 一种组合物，其包含颗粒的耐腐蚀部件，和玻璃形成粘合剂成分。 所述颗粒的耐腐蚀部件包含0至约95％的氧化铝颗粒，和5至100％的耐腐蚀非氧化铝微粒具有CTE比氧化铝颗粒的更大。 所以圆盘游离缺失是包含含有金属基体（60）和耐腐蚀涂层（64）的涡轮机部件（30）具有厚度达254微米覆盖在金属基底（60）的制品（30）。 至少该涂层（64）相邻的金属基体（60）的层包括形成玻璃的粘合剂组分和粘附到玻璃形成粘合剂组分颗粒的耐腐蚀元件。 进一步游离缺失光盘是包括以下步骤的方法：（a）提供包含金属基板的涡轮部件（30）（60）; （B）沉积在金属基板（60）一种耐腐蚀涂料组合物上; 和（c）固化沉积的抗蚀涂料组合物，以形成具有厚度可达254微米的耐腐蚀涂层（64）中的至少一个层。
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