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公开(公告)号：US20050136249A1
公开(公告)日：2005-06-23
申请号：US11006763
申请日：2004-12-08
IPC分类号： F01D5/28 , B05D1/08 , B32B15/04 , C23C4/02 , C23C4/08 , C23C4/10 , C23C28/00 , F02C7/00 , H05H1/26
CPC分类号： C23C28/3215 , C23C4/02 , C23C28/3455 , Y02T50/67 , Y10T428/12611 , Y10T428/12861 , Y10T428/12944 , Y10T428/24997 , Y10T428/26 , Y10T428/263
摘要： A thermal barrier coating comprises a bond coating 12 made of high temperature corrosion resistance superior to a substrate 11 and a thermal barrier coating 13 made of ZrO2 series ceramics formed on the bond coating. The thermal barrier coating has cracks extending in the direction of the thickness of the barrier coat. Substantially all of the tips of the cracks have a distance between the tips and the boundary at the substrate side.
摘要翻译： 热障涂层包括由耐热性高于基材11的粘结涂层12和形成在粘结涂层上的ZrO 2系陶瓷制成的热障涂层13。 隔热涂层具有在阻挡涂层的厚度方向上延伸的裂纹。 基本上所有的裂纹的尖端在顶端和衬底侧的边界之间具有一定距离。
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公开(公告)号：US08460799B2
公开(公告)日：2013-06-11
申请号：US12822208
申请日：2010-06-24
CPC分类号： F01D5/284 , C23C24/00 , C23C24/08 , C23C28/321 , C23C28/3215 , C23C28/345 , C23C28/3455 , F05D2230/90 , F05D2260/95 , F05D2300/134 , F05D2300/21 , Y02T50/67 , Y02T50/671 , Y10T428/12479 , Y10T428/12597 , Y10T428/12611
摘要： A high-temperature resistant component for, e.g., a gas turbine hot part, includes an alloy substrate containing Ni, Co, or Fe as the principal component, and a thermal barrier coating formed over the surface of the substrate via a bond coat. The thermal barrier coating includes a porous thermal-barrier layer made of ceramic and an environmental barrier layer with corrosion resistance. An impregnated layer is provided between the environmental barrier layer and the thermal barrier layer. In the impregnated layer, the thermal barrier layer is impregnated with a part of the environmental barrier layer. The thermal barrier layer is made of a porous zirconia layer, and the environmental barrier layer includes silica as the principal component. The porous zirconia layer has pores impregnated with the part of the environmental barrier layer. As a result, the high-temperature resistant component has excellent corrosion resistance and excellent heat resistance.
摘要翻译： 用于例如燃气轮机热部件的耐高温部件包括以Ni，Co或Fe为主要成分的合金基材，以及通过粘结涂层形成在基材的表面上的热障涂层。 热障涂层包括由陶瓷制成的多孔热障层和具有耐腐蚀性的环境阻挡层。 浸渍层设置在环境阻挡层和热障层之间。 在浸渍层中，热障层浸渍有环境阻挡层的一部分。 隔热层由多孔氧化锆层构成，环境阻挡层包含二氧化硅作为主要成分。 多孔氧化锆层具有浸渍有环境阻挡层的一部分的孔。 结果，耐高温组分具有优异的耐腐蚀性和优异的耐热性。
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公开(公告)号：US08485788B2
公开(公告)日：2013-07-16
申请号：US11917547
申请日：2006-06-09
CPC分类号： C23C4/08 , C22C38/44 , C22C38/46 , C22C38/48 , C22C38/52 , C23C4/06 , C23C4/129 , C23C4/18 , C23C30/00 , F01D5/02 , F05D2220/31 , F05D2230/311 , F05D2230/90 , F05D2300/132 , Y10T428/12965 , Y10T428/12979
摘要： A steam turbine rotor shaft and method of manufacturing the same are provided wherein the sliding characteristics of a journal are improved, and the journal is free from welding cracks and does not need a post heat treatment. The low alloy steel coating layer having better sliding characteristics than 9 to 13% Cr heat resisting steel and an area rate of defects including pores and oxides in a range of 3 to 15% is formed by a high velocity flame spray coating method on a sliding surface of the journal.
摘要翻译： 提供了一种汽轮机转子轴及其制造方法，其中轴颈的滑动特性得到改善，轴颈没有焊接裂纹，不需要后热处理。 通过高速火焰喷涂法在滑动中形成具有比9〜13％Cr耐热钢更好的滑动特性的低合金钢涂层和包含孔和氧化物在3〜15％范围内的缺陷面积率 日记表面。
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公开(公告)号：US20100330391A1
公开(公告)日：2010-12-30
申请号：US12822208
申请日：2010-06-24
IPC分类号： B32B5/18
CPC分类号： F01D5/284 , C23C24/00 , C23C24/08 , C23C28/321 , C23C28/3215 , C23C28/345 , C23C28/3455 , F05D2230/90 , F05D2260/95 , F05D2300/134 , F05D2300/21 , Y02T50/67 , Y02T50/671 , Y10T428/12479 , Y10T428/12597 , Y10T428/12611
摘要： A high-temperature resistant component for a gas turbine hot part and so on is provided, which has durability and reliability enough to withstand a corrosive environment with use of the low-grade oil. The high-temperature resistant component includes an alloy substrate containing Ni, Co, or Fe as the principal component, and a thermal barrier coating formed over the surface of the substrate via a bond coat. The thermal barrier coating includes a porous thermal-barrier layer made of ceramic and an environmental barrier layer with corrosion resistance. An impregnated layer is provided between the environmental barrier layer and the thermal barrier layer. In the impregnated layer, the thermal barrier layer is impregnated with a part of the environmental barrier layer. The thermal barrier layer is made of a porous zirconia layer, and the environmental barrier layer includes silica as the principal component. The porous zirconia layer has pores impregnated with the part of the environmental barrier layer. As a result, the high-temperature resistant component has excellent corrosion resistance and excellent heat resistance.
摘要翻译： 提供了一种用于燃气轮机热部件等的耐高温部件，其耐久性和可靠性足以承受使用低等级油的腐蚀性环境。 耐高温部件包括以Ni，Co或Fe为主要成分的合金基材，以及通过粘合涂层在基材的表面上形成的热障涂层。 热障涂层包括由陶瓷制成的多孔热障层和具有耐腐蚀性的环境阻挡层。 浸渍层设置在环境阻挡层和热障层之间。 在浸渍层中，热障层浸渍有环境阻挡层的一部分。 隔热层由多孔氧化锆层构成，环境阻挡层包含二氧化硅作为主要成分。 多孔氧化锆层具有浸渍有环境阻挡层的一部分的孔。 结果，耐高温组分具有优异的耐腐蚀性和优异的耐热性。
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公开(公告)号：US20120084981A1
公开(公告)日：2012-04-12
申请号：US13253164
申请日：2011-10-05
IPC分类号： B23P15/02
CPC分类号： F01D5/288 , C23C4/02 , C23C4/134 , C23C4/18 , C23C28/3215 , C23C28/3455 , F01D5/186 , F05D2230/12 , F05D2230/80 , F05D2230/90 , Y02T50/67 , Y02T50/676 , Y02T50/6765 , Y10T29/49341
摘要： In a method of working a film cooling hole which communicates with an internal cooling passage of a turbine blade from an outer surface, in the turbine blade which has a heat shield coating and the internal cooling passage, there is employed a method of working a cooling hole of a turbine including a step of executing a bond coat on a blade base material a step of piercing a cooling hole in accordance with an electric discharge machining, a step of executing a top coat, and a step of removing the top coat in accordance with a mechanical method with respect to a band-like region including a row of cooling holes, by using an abrasive blasting, a water jet method or the like. Accordingly, an occlusion of the cooling hole, and a damage of the TBC due to the piercing are hardly generated.
摘要翻译： 在从外表面与涡轮叶片的内部冷却通道连通的薄膜冷却孔的工作方法中，在具有隔热涂层和内部冷却通路的涡轮叶片中，采用了一种冷却 包括在叶片基材上执行粘合涂层的步骤，根据放电加工刺穿冷却孔的步骤，执行顶涂层的步骤，以及根据所述顶涂层的去除步骤 通过使用喷砂法，水喷射法等，相对于包括一排冷却孔的带状区域的机械方法。 因此，几乎不产生冷却孔的堵塞和由于穿孔引起的TBC的损坏。
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公开(公告)号：US07449251B2
公开(公告)日：2008-11-11
申请号：US11006763
申请日：2004-12-08
CPC分类号： C23C28/3215 , C23C4/02 , C23C28/3455 , Y02T50/67 , Y10T428/12611 , Y10T428/12861 , Y10T428/12944 , Y10T428/24997 , Y10T428/26 , Y10T428/263
摘要： A thermal barrier coating comprises a bond coating 12 made of high temperature corrosion resistance superior to a substrate 11 and a thermal barrier coating 13 made of ZrO2 series ceramics formed on the bond coating. The thermal barrier coating has cracks extending in the direction of the thickness of the barrier coat. Substantially all of the tips of the cracks have a distance between the tips and the boundary at the substrate side.
摘要翻译： 热障涂层包括由耐热性高于基材11的粘结涂层12和形成在粘结涂层上的ZrO 2系陶瓷制成的热障涂层13。 隔热涂层具有在阻挡涂层的厚度方向上延伸的裂纹。 基本上所有的裂纹的尖端在顶端和衬底侧的边界之间具有一定距离。
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17.发明授权
公开(公告)号：US5545484A
公开(公告)日：1996-08-13
申请号：US351705
申请日：1994-12-08
申请人： Shizuka Yamaguchi , Yoshitaka Kojima , Sai Ogawa , Hideyuki Arikawa , Mitsuo Haginoya , Yukihiko Wada , Kyozo Iwao
发明人： Shizuka Yamaguchi , Yoshitaka Kojima , Sai Ogawa , Hideyuki Arikawa , Mitsuo Haginoya , Yukihiko Wada , Kyozo Iwao
CPC分类号： C04B41/009 , C04B41/52 , C04B41/89 , C23C14/08 , C23C14/22 , Y02T50/67 , Y10T428/30
摘要： A heat and oxidation resistive high strength material utilized in structural body parts subject to bleaching in high temperature/oxidative atmosphere, the body structure of a space vehicle, a combustor, the combustor for a gas turbine, a turbine blade, and a turbine nozzle, is presented. A method for producing this heat and oxidation resistive high strength material is also explained.
摘要翻译： 用于在高温/氧化气氛中漂白的结构体部件，空间车辆的主体结构，燃烧器，燃气轮机的燃烧器，涡轮机叶片和涡轮喷嘴的热和氧化电阻高强度材料， 被呈现。 还说明了生产该耐高温和抗氧化的高强度材料的方法。
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公开(公告)号：US6042951A
公开(公告)日：2000-03-28
申请号：US17320
申请日：1998-02-02
申请人： Yoshitaka Kojima , Hideyuki Arikawa , Mitsuo Haginoya , Katsuo Wada , Ryuta Watanabe , Yoshiaki Matsushita , Shin Yoshino
发明人： Yoshitaka Kojima , Hideyuki Arikawa , Mitsuo Haginoya , Katsuo Wada , Ryuta Watanabe , Yoshiaki Matsushita , Shin Yoshino
CPC分类号： C23C28/3215 , C23C28/345 , C23C28/3455 , C23C4/02 , Y02T50/67 , Y10T428/12535 , Y10T428/12611 , Y10T428/12618
摘要： A ceramic-coated blade of a gas turbine and a method of producing the same, in which the thickening of an Al.sub.2 O.sub.3 layer at the interface between a ceramic layer and a primary layer is sufficiently prevented for a long period of time, thereby positively suppressing the separation of the ceramic layer. Using powder of MCrAlY alloy (Co-32% Ni-21% Cr-8% Al-0.5% Y), a primary layer (alloy coating layer) is formed on a surface of a substrate made of a heat-resistant Ni base alloy (Rene'-80). Further, a heat-resistant ceramic layer, comprising a mixture of ion-conductive ZrO.sub.2 -8 wt. % Y.sub.2 O.sub.3 ceramic and insulative ceramic (e.g. Al.sub.2 O.sub.3), is formed on the alloy coating layer. This mixture has a columnar structure in which columnar crystals are grown by a gas phase in a direction of a thickness of the coating, or a porous structure in which flattened particles brought about from molten particles caused to fly at high velocity are laminated.
摘要翻译： 燃气轮机的陶瓷涂覆刀片及其制造方法，其中在陶瓷层和主层之间的界面处的Al 2 O 3层的增厚被充分地长时间地防止，从而积极地抑制 分离陶瓷层。 使用MCrAlY合金（Co-32％Ni-21％Cr-8％Al-0.5％Y）的粉末，在由耐热Ni基合金制成的基板的表面上形成一层（合金涂层） （Rene'-80）。 此外，一种耐热陶瓷层，其包含离子传导性ZrO 2 -8重量％ ％Y 2 O 3陶瓷和绝缘陶瓷（例如Al 2 O 3）形成在合金涂层上。 该混合物具有柱状结构，其中柱状结晶通过气相在涂层的厚度方向上生长，或多层结构，其中由熔融颗粒引起的高速飞行的扁平颗粒被层压。
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公开(公告)号：US06521293B1
公开(公告)日：2003-02-18
申请号：US09511187
申请日：2000-02-23
申请人： Yoshitaka Kojima , Hideyuki Arikawa , Mitsuo Haginoya , Katsuo Wada , Ryuta Watanabe , Yoshiaki Matsushita , Shin Yoshino
发明人： Yoshitaka Kojima , Hideyuki Arikawa , Mitsuo Haginoya , Katsuo Wada , Ryuta Watanabe , Yoshiaki Matsushita , Shin Yoshino
IPC分类号： C23C1630
CPC分类号： C23C28/3215 , C23C4/02 , C23C28/345 , C23C28/3455 , Y02T50/67 , Y10T428/12535 , Y10T428/12611 , Y10T428/12618
摘要： A ceramic-coated blade of a gas turbine and a method of producing the same, in which the thickening of an Al2O3 layer at the interface between a ceramic layer and a primary layer is sufficiently prevented for a long period of time, thereby positively suppressing the separation of the ceramic layer. Using powder of MCrAlY alloy (Co—32%Ni—21%Cr—8%Al—0.5%Y), a primary layer (alloy coating layer) is formed on a surface of a substrate made of a heat-resistant Ni base alloy (Rene'-80). Further, a heat-resistant ceramic layer, comprising a mixture of ion-conductive ZrO2—8wt. %Y2O3 ceramic and insulative ceramic (e.g. Al2O3), is formed on the alloy coating layer. This mixture has a columnar structure in which columnar crystals are grown by a gas phase in a direction of a thickness of the coating, or a porous structure in which flattened particles brought about from molten particles caused to fly at high velocity are laminated.
摘要翻译： 燃气轮机的陶瓷涂覆刀片及其制造方法，其中在陶瓷层和主层之间的界面处的Al 2 O 3层的增厚被充分地长时间地防止，从而积极地抑制 分离陶瓷层。 使用MCrAlY合金（Co-32％Ni-21％Cr-8％Al-0.5％Y）的粉末，在由耐热Ni基合金制成的基板的表面上形成一层（合金涂层） （Rene'-80）。 此外，还包括耐热陶瓷层，其包含离子传导性ZrO 2 -8wt。 ％Y 2 O 3陶瓷和绝缘陶瓷（例如Al 2 O 3）形成在合金涂层上。 该混合物具有柱状结构，其中柱状结晶通过气相在涂层的厚度方向上生长，或多层结构，其中由熔融颗粒引起的高速飞行的扁平颗粒被层压。
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