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    Thermal barrier coating for industrial gas turbine blade, and Industrial gas turbine using the same
    14.
    发明公开
    Thermal barrier coating for industrial gas turbine blade, and Industrial gas turbine using the same 审中-公开
    Gasturbinenschaufel工业公司和工业公司Gurburbine damit

    公开(公告)号：EP2684976A2

    公开(公告)日：2014-01-15

    申请号：EP13175928.4

    申请日：2013-07-10

    申请人： Hitachi Ltd. ,  National University Corporation Hokkaido University

    发明人： Izumi, Takeshi ,  Arikawa, Hideyuki ,  Kojima, Yoshitaka ,  Mebata, Akira ,  Kasuya, Tadashi ,  Narita, Toshio

    IPC分类号： C23C10/00 ,  C23C28/00

    CPC分类号： F01D5/288 ,  C23C10/00 ,  C23C10/02 ,  C23C10/38 ,  C23C10/60 ,  C23C28/00 ,  C23C28/321 ,  C23C28/3215 ,  C23C28/325 ,  C23C28/3455 ,  C23C28/42 ,  F05D2300/10 ,  Y02T50/672 ,  Y10T428/12618

    摘要： Disclosed is a turbine blade for an industrial gas turbine including a blade substrate; a multilayer alloy coating containing a diffusion barrier layer; a bond coat; and a top coat, the blade substrate being formed of a single crystal alloy which consists essentially of 0.06 to 0.08% of C, 0.016 to 0.035% of B, 0.2 to 0.3% of Hf, 6.9 to 7.3% of Cr, 0.7 to 1.0% of Mo, 7.0 to 9.0% of W, 1.2 to 1.6% of Re, 8.5 to 9.5% of Ta, 0.6 to 1.0% of Nb, 4.9 to 5.2% of Al, 0.8 to 1.2% of Co, and the balance being Ni and incidental impurities by weight, the multilayer alloy coating, the bond coat and the top coat being directly and sequentially laminated on a surface of the blade substrate, in which the diffusion barrier layer is a multilayer and a discontinuous layer. Thus, the thermal barrier coating structure including a diffusion barrier layer can be provided for the single-crystal turbine blade for the industrial gas turbine formed of a single crystal alloy. The thermal barrier coating structure can suppress growth of a secondary reaction zone caused by element diffusion into the substrate, and can provide durability against thermal fatigue due to thermal cycles and durability against mechanical fatigue.

    摘要翻译： 公开了一种用于工业燃气轮机的涡轮叶片，其包括叶片基板; 含有扩散阻挡层的多层合金涂层; 粘合外套; 和顶涂层，所述刀片基材由单晶合金形成，所述单晶合金基本上由C：0.06〜0.08％，B：0.016〜0.035％，Hf：0.2〜0.3％，Cr：6.9〜7.3％，0.7〜1.0 Mo为7.0〜9.0％，Re为1.2〜1.6％，Ta为8.5〜9.5％，Nb为0.6〜1.0％，Al为4.9〜5.2％，Co为0.8〜1.2％，余量为 Ni和重量杂质，多层合金涂层，粘结涂层和顶涂层直接依次层压在其中扩散阻挡层为多层和不连续层的叶片基板的表面上。 因此，对于由单晶合金形成的工业燃气轮机的单晶涡轮叶片，能够提供包括扩散阻挡层的热障涂覆结构。 热障涂层结构可以抑制由元件扩散到基板中引起的二次反应区的生长，并且可以提供耐热循环和对机械疲劳的耐久性的热疲劳的耐久性。

    Gas turbine component having thermal barrier coating and a gas turbine using the component
    16.
    发明公开
    Gas turbine component having thermal barrier coating and a gas turbine using the component 有权
    Gasturbinenkomponente mitWärmegrenzbeschichtungund Gasturbine mit der Komponente

    公开(公告)号：EP2471974A1

    公开(公告)日：2012-07-04

    申请号：EP11195047.3

    申请日：2011-12-21

    申请人： Hitachi Ltd.

    发明人： Arikawa, Hideyuki ,  Mebata, Akira ,  Kojima, Yoshitaka ,  Ichikawa, Kunihiro ,  Haruyama, Hiroshi

    IPC分类号： C23C24/00 ,  C23C28/04 ,  F01D5/28

    CPC分类号： C23C28/04 ,  C23C28/042 ,  C23C28/046 ,  C23C28/048 ,  F01D5/288 ,  Y02T50/67 ,  Y02T50/671 ,  Y02T50/6765

    摘要： The present invention provides gas turbine components having durability and reliability for use in a corrosive environment such as a turbine employing a low grade fuel, and also provides a gas turbine equipped with the components. One of the components is a gas turbine bucket/nozzle comprising a substrate (10) made from an alloy containing Ni, Co, or Fe, a bonding layer (11) made from an alloy and disposed over the substrate (10), and a thermal barrier coating (12, 13, 14) disposed over the bonding layer. The thermal barrier coating includes a thermal barrier layer (12) of porous ceramics, an environmental barrier layer (13) containing silica, and an impregnation layer (14) having a silica-containing material in the pores of the porous ceramics.

    摘要翻译： 本发明提供了具有耐久性和可靠性的燃气轮机部件，其用于诸如使用低等级燃料的涡轮机等腐蚀性环境中，并且还提供了配备有部件的燃气轮机。 其中一个部件是包括由包含Ni，Co或Fe的合金制成的基底（10）的燃气涡轮机桶/喷嘴，由合金制成并设置在基板（10）上的粘合层（11），以及 设置在结合层上的隔热涂层（12,13,14）。 隔热涂层包括多孔陶瓷的隔热层（12），含有二氧化硅的环境阻挡层（13）和在多孔陶瓷的孔中具有二氧化硅的浸渍层（14）。

    Diffusion aluminide coating process
    17.
    发明公开
    Diffusion aluminide coating process 有权
    扩散铝化物涂层工艺

    公开(公告)号：EP1927672A3

    公开(公告)日：2009-04-22

    申请号：EP07022592.5

    申请日：2007-11-21

    申请人： Hitachi, Ltd.

    发明人： Arikawa, Hideyuki ,  Mebata, Akira ,  Kojima, Yoshitaka

    IPC分类号： C23C10/02 ,  C23C10/04 ,  C23C24/04 ,  C23C28/02

    CPC分类号： C23C10/02 ,  C23C10/04 ,  C23C24/04 ,  C23C28/021 ,  C23C28/022 ,  C23C28/023 ,  C23C28/028

    摘要： A method of applying a diffusion aluminide coating partially to a selective region more simply and conveniently, the method including (a) a step of forming a metal aluminum film onto a selective region of the heat-resistant alloy substrate to be treated; and (b) a step of applying a heat treatment to the heat-resistant alloy substrate on the selective region of which the metal aluminum film is formed and diffusing and penetrating aluminum in the metal aluminum film into the heat-resistant alloy substrate.

    摘要翻译： 本发明的方法包括：（a）在待处理的耐热合金基底的选择区域上形成金属铝膜的步骤; （b）对形成有金属铝膜的选择区域上的耐热合金基板实施热处理，并将金属铝膜中的铝扩散渗透到耐热合金基板中的工序。

    High temperature components with thermal barrier coatings for gas turbine
    19.
    发明公开
    High temperature components with thermal barrier coatings for gas turbine 有权
    Hochtemperaturbauteile mitWärmedämmschichtenfürGasturbine

    公开(公告)号：EP2725120A1

    公开(公告)日：2014-04-30

    申请号：EP13189647.4

    申请日：2013-10-22

    申请人： Hitachi Ltd.

    发明人： Arikawa, Hideyuki ,  Kojima, Yoshitaka ,  Kasuya, Tadashi ,  Mebata, Akira ,  Ichikawa, Kunihiro ,  Endo, Hiroyuki ,  Endo, Takao

    IPC分类号： C23C24/08 ,  C23C28/00 ,  F01D5/28 ,  F01D5/18 ,  C23C4/08

    CPC分类号： F01D5/288 ,  C23C4/073 ,  C23C4/08 ,  C23C24/04 ,  C23C28/3215 ,  C23C28/3455 ,  F01D5/183 ,  F01D5/186

    摘要： The most principal feature of the present invention is as follows: Namely, in the gas-turbine-use high-temperature component including the thermal barrier coating and a cooling structure, micro passages are provided inside an alloy bond-coat layer (2) and a thermal-barrier ceramic top-coat layer (3) of the thermal barrier coating, the micro passages being in communication from the substrate side to the surface side. Moreover, a partial amount of coolant of a coolant (8) for cooling the high-temperature component is caused to flow out to the outside of the high-temperature component via these micro passages. The employment of the structure like this makes it possible to expect the implementation of a high-temperature component's heat-resistant-temperature enhancement effect based on the transpiration cooling effect.

    摘要翻译： 本发明的主要特征如下：即，在具有隔热涂层和冷却结构的燃气轮机用高温部件中，在合金接合涂层（2）的内部设置微通道， 所述热障涂层的热障陶瓷顶涂层（3），所述微通道从所述基板侧至所述表面侧连通。 此外，使用于冷却高温部件的冷却剂（8）的一部分冷却剂通过这些微通道流出到高温部件的外部。 使用这样的结构使得可以期望基于蒸腾冷却效果实现高温部件的耐热温度增强效果。

    High-temperature resistant gas turbine component
    20.
    发明公开
    High-temperature resistant gas turbine component 审中-公开
    HochtemperaturbeständigeGasturbinenkomponente

    公开(公告)号：EP2270313A2

    公开(公告)日：2011-01-05

    申请号：EP10167624.5

    申请日：2010-06-29

    申请人： Hitachi, Ltd.

    发明人： Arikawa, Hideyuki ,  Mebata, Akira ,  Kojima, Yoshitaka ,  Ichikawa, Kunihiro ,  Haruyama, Hiroshi

    IPC分类号： F01D5/28

    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 (10) containing Ni, Co, or Fe as the principal component, and a thermal barrier coating formed over the surface of the substrate (10) via a bond coat. The thermal barrier coating includes a porous thermal-barrier layer (12) made of ceramic and an environmental barrier layer (13) with corrosion resistance. An impregnated layer (14) is provided between the environmental barrier layer (13) and the thermal barrier layer (12). In the impregnated layer (14), the thermal barrier layer (12) is impregnated with a part of the environmental barrier layer (13). The thermal barrier layer (12) is made of a porous zirconia layer, and the environmental barrier layer (13) includes silica as the principal component. The porous zirconia layer has pores (16) impregnated with the part of the environmental barrier layer (13). 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为主成分的合金基板（10），以及通过粘合涂层形成在基板（10）的表面上的隔热涂层。 隔热涂层包括由陶瓷制成的多孔热障层（12）和具有耐腐蚀性的环境阻挡层（13）。 浸渍层（14）设置在环境阻挡层（13）和热障层（12）之间。 在浸渍层（14）中，热阻层（12）浸渍有环境阻挡层（13）的一部分。 隔热层（12）由多孔氧化锆层构成，环境阻挡层（13）以二氧化硅为主要成分。 多孔氧化锆层具有浸渍有环境阻挡层（13）的一部分的孔（16）。 结果，耐高温部件具有优异的耐腐蚀性和优异的耐热性。