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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：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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3.发明申请公开(公告)号：US20060251916A1
公开(公告)日：2006-11-09
申请号：US11233379
申请日：2005-09-23
申请人： Hideyuki Arikawa , Akira Mebata , Yoshitaka Kojima , Kunihiro Ichikawa , Takayuki Yoshioka , Mitsutoshi Okada , Tohru Hisamatsu
发明人： Hideyuki Arikawa , Akira Mebata , Yoshitaka Kojima , Kunihiro Ichikawa , Takayuki Yoshioka , Mitsutoshi Okada , Tohru Hisamatsu
CPC分类号： C23C28/321 , C23C28/3215 , C23C28/345 , C23C28/3455 , F01D5/288 , F05D2230/90 , F05D2300/611 , Y02T50/67 , Y02T50/671 , Y10T428/12611 , Y10T428/12618 , Y10T428/12847 , Y10T428/12931 , Y10T428/12937 , Y10T428/12944
摘要： There is provided a high temperature component with a thermal barrier coating, which can be used as a high temperature component for a gas turbine, an aircraft gas turbine engine, or the like. A top coat is formed of a ceramic on a bond coat, the bond coat being formed on a heat resistant alloy substrate composed mainly of at least one element of nickel and cobalt, wherein the bond coat contains at least one of nickel and cobalt, chromium and aluminum, and further contains at least one selected from a group consisting of tantalum, cesium, tungsten, silicon, platinum, manganese and boron in a range of 0 to 20 wt %. The high temperature component according to the present invention has very high durability of a thermal-insulating ceramic layer, and is less susceptible to spalling damage.
摘要翻译： 提供了具有热障涂层的高温部件，其可以用作燃气轮机，飞机燃气轮机等的高温部件。 顶涂层由粘结涂层上的陶瓷形成，粘合涂层形成在主要由至少一种镍和钴元素组成的耐热合金基底上，其中粘合涂层含有镍和钴中的至少一种，铬， 铝，还含有选自钽，铯，钨，硅，铂，锰和硼中的至少一种为0〜20重量％。 根据本发明的高温部件具有非常高的绝热陶瓷层的耐久性，并且不易受剥落损伤。
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4.发明授权公开(公告)号：US07901790B2
公开(公告)日：2011-03-08
申请号：US11233379
申请日：2005-09-23
申请人： Hideyuki Arikawa , Akira Mebata , Yoshitaka Kojima , Kunihiro Ichikawa , Takayuki Yoshioka , Mitsutoshi Okada , Tohru Hisamatsu
发明人： Hideyuki Arikawa , Akira Mebata , Yoshitaka Kojima , Kunihiro Ichikawa , Takayuki Yoshioka , Mitsutoshi Okada , Tohru Hisamatsu
IPC分类号： B32B15/00
CPC分类号： C23C28/321 , C23C28/3215 , C23C28/345 , C23C28/3455 , F01D5/288 , F05D2230/90 , F05D2300/611 , Y02T50/67 , Y02T50/671 , Y10T428/12611 , Y10T428/12618 , Y10T428/12847 , Y10T428/12931 , Y10T428/12937 , Y10T428/12944
摘要： There is provided a high temperature component with a thermal barrier coating, which can be used as a high temperature component for a gas turbine, an aircraft gas turbine engine, or the like. A top coat is formed of a ceramic on a bond coat, the bond coat being formed on a heat resistant alloy substrate composed mainly of at least one element of nickel and cobalt, wherein the bond coat contains at least one of nickel and cobalt, chromium and aluminum, and further contains at least one selected from a group consisting of tantalum, cesium, tungsten, silicon, platinum, manganese and boron in a range of 0 to 20 wt %. The high temperature component according to the present invention has very high durability of a thermal-insulating ceramic layer, and is less susceptible to spalling damage.
摘要翻译： 提供了具有热障涂层的高温部件，其可以用作燃气轮机，飞机燃气轮机等的高温部件。 顶涂层由粘结涂层上的陶瓷形成，粘合涂层形成在主要由至少一种镍和钴元素组成的耐热合金基底上，其中粘合涂层含有镍和钴中的至少一种，铬， 铝，还含有选自钽，铯，钨，硅，铂，锰和硼中的至少一种为0〜20重量％。 根据本发明的高温部件具有非常高的绝热陶瓷层的耐久性，并且不易受剥落损伤。
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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：US20120107103A1
公开(公告)日：2012-05-03
申请号：US13242951
申请日：2011-09-23
申请人： Yoshitaka Kojima , Hideyuki Arikawa , Akira Mebata , Tadashi Kasuya , Hiroyuki Doi , Kunihiro Ichikawa , Takao Endo , Kazuto Mikazuki , Hidetoshi Kuroki
发明人： Yoshitaka Kojima , Hideyuki Arikawa , Akira Mebata , Tadashi Kasuya , Hiroyuki Doi , Kunihiro Ichikawa , Takao Endo , Kazuto Mikazuki , Hidetoshi Kuroki
CPC分类号： F01D11/122 , F05D2230/311 , F05D2240/11 , F05D2300/514 , F05D2300/522 , Y10T29/49323
摘要： A gas turbine shroud includes a ceramic abradable coating superior in abradable property and durability. The gas turbine ceramic abradable coating of the present invention is configured by an abradable metal layer and a porous ceramic abradable layer (hardness RC15Y: 80±3), the porous ceramic abradable layer is provided with slit grooves by machining work, and a slit groove width is 0.5 to 5 mm. Thereby, the abradable property, and durability against a thermal cycle and high-temperature oxidation are improved.
摘要翻译： 燃气轮机罩包括耐磨性和耐久性优异的陶瓷耐磨涂层。 本发明的燃气轮机陶瓷耐磨涂层由耐磨金属层和多孔陶瓷耐磨层（硬度RC15Y：80±3）构成，多孔陶瓷耐磨层通过加工加工而形成狭缝槽，狭缝槽 宽度为0.5〜5mm。 由此，能够提高耐磨损性，耐热循环性和耐高温氧化性。
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公开(公告)号：US20110182720A1
公开(公告)日：2011-07-28
申请号：US13012017
申请日：2011-01-24
申请人： Yoshitaka KOJIMA , Hideyuki Arikawa , Akira Mebata , Tadashi Kasuya , Hiroyuki Doi , Kunihiro Ichikawa
发明人： Yoshitaka KOJIMA , Hideyuki Arikawa , Akira Mebata , Tadashi Kasuya , Hiroyuki Doi , Kunihiro Ichikawa
CPC分类号： C23C28/00 , F01D11/122 , F05D2230/90 , F05D2240/11 , F05D2250/181 , F05D2300/21
摘要： There is provided a gas turbine shroud including a ceramic abradable coating used as a gap adjusting component that can reduce a fluid leakage from a gap and increase turbine efficiency. A gas turbine ceramic abradable coating includes a bond layer, a thermal barrier ceramic layer, and a porous ceramic abradable layer (hardness may be RC15Y: 80±3). A slit groove is provided in the porous ceramic abradable layer by machining. A width of a rectangular section of the ceramic abradable layer divided by the slit groove may be set to a range of 2 to 7 mm.
摘要翻译： 提供了一种燃气轮机罩，其包括用作间隙调节部件的陶瓷耐磨涂层，其可以减少从间隙泄漏的液体并提高涡轮机效率。 燃气轮机陶瓷耐磨涂层包括粘合层，热障陶瓷层和多孔陶瓷耐磨层（硬度可以是RC15Y：80±3）。 通过机械加工在多孔陶瓷耐磨层中设置狭缝槽。 由狭缝槽划分的陶瓷耐磨层的矩形截面的宽度可以设定在2〜7mm的范围内。
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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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公开(公告)号：US08801373B2
公开(公告)日：2014-08-12
申请号：US12825525
申请日：2010-06-29
申请人： Yoshitaka Kojima , Hideyuki Arikawa , Akira Mebata , Hiroyuki Doi , Hajime Toriya , Kenjiro Narita
发明人： Yoshitaka Kojima , Hideyuki Arikawa , Akira Mebata , Hiroyuki Doi , Hajime Toriya , Kenjiro Narita
CPC分类号： F01D11/02 , C22C19/00 , C22C19/058 , C22C19/07 , C23C4/073 , C23C28/02 , C23C30/00 , F01D11/001 , F01D11/122 , F05D2220/31 , F05D2300/509 , Y10T428/249961 , Y10T428/249974 , Y10T428/249981 , Y10T428/249989
摘要： A metal sealing material used in a sealing device which can reduce a gap between a stator and a rotor of a turbine. The metal sealing material used in a sealing device for a stator and a rotor of a turbine includes a surface layer and a lower layer composed of a porous metal layer, wherein the porosity of the surface layer is smaller than the porosity of the lower layer; the porosity of the surface layer is 60 to 65% and the porosity of the lower layer is 67 to 75% or less; and the porous metal layer has a thickness of 0.3 to 3.0 mm and may include, as a main component, an MCrAlY alloy where M is either one of Ni and Co or both thereof, and h-BN as a solid lubricant.
摘要翻译： 用于密封装置中的金属密封材料，其可以减小定子和涡轮机的转子之间的间隙。 用于定子的密封装置和涡轮机的转子的金属密封材料包括表面层和由多孔金属层构成的下层，其中表面层的孔隙率小于下层的孔隙率; 表面层的孔隙率为60〜65％，下层的孔隙率为67〜75％以下。 多孔金属层的厚度为0.3〜3.0mm，作为主要成分，可以举出M是Ni和Co中的任一种或两者的MCrAlY合金以及作为固体润滑剂的h-BN。
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