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1.发明申请公开(公告)号：US20070036997A1
公开(公告)日：2007-02-15
申请号：US11170836
申请日：2005-06-30
Applicant: Margaret Floyd , Thomas Strangman , Derek Raybould , Paul Mravcak
Inventor： Margaret Floyd , Thomas Strangman , Derek Raybould , Paul Mravcak
CPC classification number: F01D5/288 , C04B35/486 , C04B2235/3251 , C04B2235/762 , C04B2235/765 , C23C28/321 , C23C28/3215 , C23C28/325 , C23C28/345 , C23C28/3455 , F05D2230/313 , F05D2230/90 , F05D2300/2285 , F05D2300/611 , Y02T50/67 , Y02T50/671 , Y02T50/673
Abstract: A turbine engine component includes an electron beam-physical vapor deposition thermal barrier coating covering at least a portion of a substrate. The thermal barrier coating includes an inner layer having a columnar-grained microstructure with inter-columnar gap porosity. The inner layer includes a stabilized ceramic material. The thermal barrier coating also includes a substantially non-porous outer layer, covering the inner layer and including the stabilized ceramic material. The outer layer is deposited with continuous line-of-sight exposure to the vapor source under oxygen deficient conditions. The outer layer may further comprise a dopant oxide that is more readily reducible than the stabilized ceramic material. During deposition, the outer layer may also have an oxygen deficient stoichiometry with respect to the inner layer. Oxygen stoichiometry in the outer layer may be restored by exposure of the coated component to an oxidizing environment.
Abstract translation: 涡轮发动机部件包括覆盖基板的至少一部分的电子束物理气相沉积热障涂层。 隔热涂层包括具有柱状间隙孔隙的柱状微结构的内层。 内层包括稳定的陶瓷材料。 热障涂层还包括基本上无孔的外层，覆盖内层并且包括稳定的陶瓷材料。 在缺氧条件下，外层沉积有连续的视线暴露于蒸汽源。 外层还可以包含比稳定的陶瓷材料更容易还原的掺杂剂氧化物。 在沉积期间，外层也可能具有相对于内层的缺氧化学计量。 可以通过将涂覆的组分暴露于氧化环境来恢复外层中的氧化学计量。
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公开(公告)号：US07785722B2
公开(公告)日：2010-08-31
申请号：US11336438
申请日：2006-01-20
Applicant: Melvin Freling , Kevin W. Schlichting , Michael J. Maloney , David A. Litton , John G. Smeggil , David B. Snow
Inventor： Melvin Freling , Kevin W. Schlichting , Michael J. Maloney , David A. Litton , John G. Smeggil , David B. Snow
IPC: B32B9/00
CPC classification number: C04B35/50 , C04B2235/3224 , C23C26/00 , C23C28/042 , C23C28/048 , C23C28/321 , C23C28/3215 , C23C28/345 , C23C28/3455 , C23C28/36 , C23C28/42 , F01D5/288 , F05D2230/90 , F05D2300/15 , F05D2300/211 , F05D2300/2285 , F05D2300/611 , Y02T50/67
Abstract: A turbine engine component is provided which has a substrate and a thermal barrier coating applied over the substrate. The thermal barrier coating comprises alternating layers of yttria-stabilized zirconia and a molten silicate resistant material. The molten silicate resistant outer layer may be formed from at least one oxide of a material selected from the group consisting of lanthanum, cerium, praseodymium, neodymium, promethium, samarium, europium, gadolinium, terbium, dysprosium, holmium, erbium, thulium, ytterbium, lutetium, scandium, indium, zirconium, hafnium, and titanium or may be formed from a gadolinia-stabilized zirconia. If desired, a metallic bond coat may be present between the substrate and the thermal barrier coating system. A method for forming the thermal barrier coating system of the present invention is described.
Abstract translation: 提供了一种涡轮发动机部件，其具有施加在基板上的基板和热障涂层。 热障涂层包括交替的氧化钇稳定的氧化锆层和耐熔融硅酸盐材料。 熔融硅酸盐外层可以由选自镧，铈，镨，钕，ium，钐，铕，钆，铽，镝，钬，铒，ium，镱，镱， 镥，钪，铟，锆，铪和钛，或者可由氧化钆稳定的氧化锆形成。 如果需要，可以在基材和热障涂层体系之间存在金属粘结涂层。 对本发明的热障涂敷系统的形成方法进行说明。
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3.发明申请Erosion-protective coatings on polymer-matrix composites and components incorporating such coated composites 失效聚合物基复合材料和包含这种涂层复合材料的组分的防腐蚀涂层公开(公告)号：US20080056905A1
公开(公告)日：2008-03-06
申请号：US11515476
申请日：2006-08-31
Applicant: Ilan Golecki
Inventor： Ilan Golecki
IPC: F03B3/12
CPC classification number: C23C30/00 , C23C28/322 , C23C28/34 , C23C28/42 , F01D5/14 , F01D5/282 , F01D5/286 , F01D5/288 , F01D17/16 , F04D29/023 , F04D29/462 , F04D29/563 , F05D2230/90 , F05D2300/133 , F05D2300/134 , F05D2300/2262 , F05D2300/228 , F05D2300/2284 , F05D2300/2285 , F05D2300/603 , F05D2300/611 , F05D2300/702 , Y02T50/672
Abstract: A stator vane is provided that includes an airfoil and a coating. The airfoil comprises a polymer matrix fiber composite having a melting point, glass transition temperature, or maximum exposure temperature that is less than about 150° C. The coating is formed over the airfoil and comprises a material that is more erosion-resistant than the polymer matrix fiber composite, where the material is the selected from a group of constituents consisting of titanium, chromium, vanadium, and zirconium, and nitrides, carbides, mixed carbonitrides, oxides, oxynitrides, oxycarbides, and oxycarbonitrides thereof. Methods for making the stator vane are provided as well.
Abstract translation: 提供了包括翼型件和涂层的定子叶片。 翼型包括具有熔点，玻璃化转变温度或小于约150℃的最大暴露温度的聚合物基质纤维复合材料。该涂层形成在翼型上方并且包括比聚合物更耐侵蚀的材料 基质纤维复合材料，其中材料选自钛，铬，钒和锆组成的组分，以及氮化物，碳化物，混合碳氮化物，氧化物，氧氮化物，碳氧化物和碳氮氧化物。 还提供了制造定子叶片的方法。
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4.发明授权High temperature erosion resistant coating and material containing compacted hollow geometric shapes 有权耐高温侵蚀涂层和含有压实中空几何形状的材料公开(公告)号：US06641907B1
公开(公告)日：2003-11-04
申请号：US09467237
申请日：1999-12-20
Applicant: Gary Brian Merrill , Jay Alan Morrison
Inventor： Gary Brian Merrill , Jay Alan Morrison
IPC: B32B300
CPC classification number: C04B38/0038 , C04B38/08 , C04B2111/00482 , C04B2111/28 , C23C30/00 , F01D5/282 , F01D5/284 , F01D5/288 , F01D11/125 , F05D2250/241 , F05D2300/2112 , F05D2300/2118 , F05D2300/2261 , F05D2300/2262 , F05D2300/2263 , F05D2300/2283 , F05D2300/2285 , F05D2300/603 , F05D2300/702 , Y02T50/67 , Y02T50/672 , Y10T428/249974 , Y10T428/249977 , Y10T428/249985 , Y10T428/252 , C04B14/30
Abstract: A material system (60) contains close packed hollow shapes (50, 70) having a dense wall structure (52, 66), which are bonded together and which may contain a matrix binder material (56) between the shapes, where the system has a stable porosity, and is abradable and thermally stable at temperatures up to possibly 1700° C., where such systems are useful in turbine apparatus.
Abstract translation: 材料系统（60）包含具有致密壁结构（52,66）的紧密堆积的中空形状（50,70），它们结合在一起，并且可以在形状之间包含基体粘合剂材料（56），其中系统具有 稳定的孔隙度，并且在高达可能的1700℃的温度下是可磨损和热稳定的，其中这种系统可用于涡轮机设备中。
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公开(公告)号：US20030129378A1
公开(公告)日：2003-07-10
申请号：US10064791
申请日：2002-08-16
Applicant: General Electric Company
Inventor： Boris A. Movchan , Yuriy E. Rudoy , Leonella M. Nerodenko , Ramgopal Darolia , Irene Spitsberg , Anthony Mark Thompson , Curtis Alan Johnson , David John Wortman
IPC: B32B003/26
CPC classification number: C23C28/3215 , C23C8/02 , C23C14/06 , C23C28/321 , C23C28/345 , C23C28/3455 , F01D5/284 , F01D5/288 , F05D2300/2118 , F05D2300/224 , F05D2300/2285 , Y10T428/249954 , Y10T428/249956 , Y10T428/249957 , Y10T428/249967 , Y10T428/249976 , Y10T428/249986 , Y10T428/24999
Abstract: A thermal barrier coating (TBC 26) and method for forming the TBC (26) on a component (10) characterized by a stabilized microstructure that resists grain growth, sintering and pore coarsening or coalescence during high temperature excursions. The TBC (26) contains elemental carbon and/or a carbon-containing gas that increase the amount of porosity (32) initially within the TBC (26) and form additional fine closed porosity (32) within the TBC (26) during subsequent exposures to high temperatures. A first method involves incorporating elemental carbon precipitates by evaporation into the TBC microstructure. A second method is to directly incorporate an insoluble gas, such as a carbon-containing gas, into an as-deposited TBC (26) and then partially sinter the TBC (26) to entrap the gas and produce fine stable porosity within the TBC (26).
Abstract translation: 一种隔热涂层（TBC26）和在组分（10）上形成TBC（26）的方法，其特征在于稳定的微结构，其在高温偏移期间抵抗晶粒生长，烧结和孔粗化或聚结。 TBC（26）含有元素碳和/或含碳气体，其最初在TBC（26）内增加孔隙率（32），并在随后的曝光期间在TBC（26）内形成额外的细闭孔率（32） 到高温。 第一种方法包括通过蒸发将元素碳沉淀物并入到TBC微结构中。 第二种方法是直接将诸如含碳气体的不溶性气体直接掺入沉积的TBC（26）中，然后部分烧结TBC（26）以截留气体并在TBC内产生精细的稳定孔隙（ 26）。
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Patent Agency Ranking
6.发明申请公开(公告)号：US20090038935A1
公开(公告)日：2009-02-12
申请号：US12102186
申请日：2008-04-14
Applicant: Margaret M. Floyd , Thomas Strangman , Derek Raybould , Paul J. Mravcak
Inventor： Margaret M. Floyd , Thomas Strangman , Derek Raybould , Paul J. Mravcak
IPC: C23C14/34
CPC classification number: F01D5/288 , C04B35/486 , C04B2235/3251 , C04B2235/762 , C04B2235/765 , C23C28/321 , C23C28/3215 , C23C28/325 , C23C28/345 , C23C28/3455 , F05D2230/313 , F05D2230/90 , F05D2300/2285 , F05D2300/611 , Y02T50/67 , Y02T50/671 , Y02T50/673
Abstract: A turbine engine component includes an electron beam-physical vapor deposition thermal barrier coating covering at least a portion of a substrate. The thermal barrier coating includes an inner layer having a columnar-grained microstructure with inter-columnar gap porosity. The inner layer includes a stabilized ceramic material. The thermal barrier coating also includes a substantially non-porous outer layer, covering the inner layer and including the stabilized ceramic material. The outer layer is deposited with continuous line-of-sight exposure to the vapor source under oxygen deficient conditions. The outer layer may further comprise a dopant oxide that is more readily reducible than the stabilized ceramic material. During deposition, the outer layer may also have an oxygen deficient stoichiometry with respect to the inner layer. Oxygen stoichiometry in the outer layer may be restored by exposure of the coated component to an oxidizing environment.
Abstract translation: 涡轮发动机部件包括覆盖基板的至少一部分的电子束物理气相沉积热障涂层。 隔热涂层包括具有柱状间隙孔隙的柱状微结构的内层。 内层包括稳定的陶瓷材料。 热障涂层还包括基本上无孔的外层，覆盖内层并且包括稳定的陶瓷材料。 在缺氧条件下，外层沉积有连续的视线暴露于蒸汽源。 外层还可以包含比稳定的陶瓷材料更容易还原的掺杂剂氧化物。 在沉积期间，外层也可能具有相对于内层的缺氧化学计量。 可以通过将涂覆的组分暴露于氧化环境来恢复外层中的氧化学计量。
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7.发明授权公开(公告)号：US07416788B2
公开(公告)日：2008-08-26
申请号：US11170836
申请日：2005-06-30
Applicant: Margaret M. Floyd , Thomas E. Strangman , Derek Raybould , Paul J. Mravcak
Inventor： Margaret M. Floyd , Thomas E. Strangman , Derek Raybould , Paul J. Mravcak
IPC: B32B9/00
CPC classification number: F01D5/288 , C04B35/486 , C04B2235/3251 , C04B2235/762 , C04B2235/765 , C23C28/321 , C23C28/3215 , C23C28/325 , C23C28/345 , C23C28/3455 , F05D2230/313 , F05D2230/90 , F05D2300/2285 , F05D2300/611 , Y02T50/67 , Y02T50/671 , Y02T50/673
Abstract: A turbine engine component includes an electron beam-physical vapor deposition thermal barrier coating covering at least a portion of a substrate. The thermal barrier coating includes an inner layer having a columnar-grained microstructure with inter-columnar gap porosity. The inner layer includes a stabilized ceramic material. The thermal barrier coating also includes a substantially non-porous outer layer, covering the inner layer and including the stabilized ceramic material. The outer layer is deposited with continuous line-of-sight exposure to the vapor source under oxygen deficient conditions. The outer layer may further comprise a dopant oxide that is more readily reducible than the stabilized ceramic material. During deposition, the outer layer may also have an oxygen deficient stoichiometry with respect to the inner layer. Oxygen stoichiometry in the outer layer may be restored by exposure of the coated component to an oxidizing environment.
Abstract translation: 涡轮发动机部件包括覆盖基板的至少一部分的电子束物理气相沉积热障涂层。 隔热涂层包括具有柱状间隙孔隙的柱状微结构的内层。 内层包括稳定的陶瓷材料。 热障涂层还包括基本上无孔的外层，覆盖内层并且包括稳定的陶瓷材料。 在缺氧条件下，外层沉积有连续的视线暴露于蒸汽源。 外层还可以包含比稳定的陶瓷材料更容易还原的掺杂剂氧化物。 在沉积期间，外层也可能具有相对于内层的缺氧化学计量。 可以通过将涂覆的组分暴露于氧化环境来恢复外层中的氧化学计量。
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公开(公告)号：US20070172703A1
公开(公告)日：2007-07-26
申请号：US11336438
申请日：2006-01-20
Applicant: Melvin Freling , Kevin W. Schlichting , Michael J. Maloney , David A. Litton , John G. Smeggil , David B. Snow
Inventor： Melvin Freling , Kevin W. Schlichting , Michael J. Maloney , David A. Litton , John G. Smeggil , David B. Snow
CPC classification number: C04B35/50 , C04B2235/3224 , C23C26/00 , C23C28/042 , C23C28/048 , C23C28/321 , C23C28/3215 , C23C28/345 , C23C28/3455 , C23C28/36 , C23C28/42 , F01D5/288 , F05D2230/90 , F05D2300/15 , F05D2300/211 , F05D2300/2285 , F05D2300/611 , Y02T50/67
Abstract: A turbine engine component is provided which has a substrate and a thermal barrier coating applied over the substrate. The thermal barrier coating comprises alternating layers of yttria-stabilized zirconia and a molten silicate resistant material. The molten silicate resistant outer layer may be formed from at least one oxide of a material selected from the group consisting of lanthanum, cerium, praseodymium, neodymium, promethium, samarium, europium, gadolinium, terbium, dysprosium, holmium, erbium, thulium, ytterbium, lutetium, scandium, indium, zirconium, hafnium, and titanium or may be formed from a gadolinia-stabilized zirconia. If desired, a metallic bond coat may be present between the substrate and the thermal barrier coating system. A method for forming the thermal barrier coating system of the present invention is described.
Abstract translation: 提供了一种涡轮发动机部件，其具有施加在基板上的基板和热障涂层。 热障涂层包括交替的氧化钇稳定的氧化锆层和耐熔融硅酸盐材料。 熔融硅酸盐外层可以由选自镧，铈，镨，钕，ium，钐，铕，钆，铽，镝，钬，铒，ium，镱，镱， 镥，钪，铟，锆，铪和钛，或者可由氧化钆稳定的氧化锆形成。 如果需要，可以在基材和热障涂层体系之间存在金属粘结涂层。 对本发明的热障涂敷系统的形成方法进行说明。
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公开(公告)号：US20050260425A1
公开(公告)日：2005-11-24
申请号：US10531945
申请日：2003-10-08
Applicant: Mark Shipton , Sophoclis Patsias
Inventor： Mark Shipton , Sophoclis Patsias
CPC classification number: F01D5/26 , C01B13/14 , C01F7/162 , C01P2002/32 , C23C4/00 , C23C4/10 , C23C4/11 , F01D5/284 , F05C2203/0839 , F05D2230/312 , F05D2230/90 , F05D2300/21 , F05D2300/2281 , F05D2300/2283 , F05D2300/2284 , F05D2300/2285 , Y10T428/29
Abstract: A method of forming a vibration damping coating on a metallic substrate, eg a titanium alloy aerospace component, comprises applying to the metallic substrate a coating comprising a spinel having regions of relative oxide or nitride imbalance.
Abstract translation: 在金属基底（例如钛合金航空航天部件）上形成减振涂层的方法包括向金属基底施加包含具有相对氧化物或氮化物不平衡区域的尖晶石的涂层。
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10.发明申请High temperature erosion resistant coating and material containing compacted hollow geometric shapes 有权耐高温侵蚀涂层和含有压实中空几何形状的材料公开(公告)号：US20040219010A1
公开(公告)日：2004-11-04
申请号：US10648922
申请日：2003-08-27
Inventor： Gary Brian Merrill , Jay Alan Morrison
IPC: F01D005/20
CPC classification number: C04B38/0038 , C04B38/08 , C04B2111/00482 , C04B2111/28 , C23C30/00 , F01D5/282 , F01D5/284 , F01D5/288 , F01D11/125 , F05D2250/241 , F05D2300/2112 , F05D2300/2118 , F05D2300/2261 , F05D2300/2262 , F05D2300/2263 , F05D2300/2283 , F05D2300/2285 , F05D2300/603 , F05D2300/702 , Y02T50/67 , Y02T50/672 , Y10T428/249974 , Y10T428/249977 , Y10T428/249985 , Y10T428/252 , C04B14/30
Abstract: A material system (60) contains close packed hollow shapes (50, 70) having a dense wall structure (52, 66), which are bonded together and which may contain a matrix binder material (56) between the shapes, where the system has a stable porosity, and is abradable and thermally stable at temperatures up to possibly 1700null C., where such systems are useful in turbine apparatus.
Abstract translation: 材料系统（60）包含具有致密壁结构（52,66）的紧密堆积的中空形状（50,70），它们结合在一起，并且可以在形状之间包含基体粘合剂材料（56），其中系统具有 稳定的孔隙度，并且在高达可能的1700℃的温度下是可磨损和热稳定的，其中这种系统可用于涡轮机设备中。
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