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    Coating and coating method for gas turbine component
    2.
    发明公开
    Coating and coating method for gas turbine component 审中-公开
    Beschichtung und BeschichtungsverfahrenfürGasturbinenkomponente

    公开(公告)号：EP2631325A2

    公开(公告)日：2013-08-28

    申请号：EP13155956.9

    申请日：2013-02-20

    申请人： Howmet Corporation

    发明人： Murphy, Kenneth S. ,  Basta, William C.

    IPC分类号： C23C10/00 ,  C23C10/02 ,  C23C10/18 ,  C23C10/60

    CPC分类号： F01D5/288 ,  C23C10/02 ,  C23C10/58 ,  C25D3/04 ,  C25D5/022 ,  C25D5/12 ,  C25D5/44 ,  C25D5/50 ,  C25D13/02 ,  C25D13/12 ,  C25D13/16 ,  F01D5/3007 ,  F05D2230/31 ,  F05D2300/121 ,  F05D2300/132

    摘要： The present invention provides a protective coating for a gas turbine blade or other component wherein the duplex coating includes an aluminum-bearing coating, such as a diffusion aluminide, formed on a first, relatively higher temperature region of the blade/component and a later-applied chromium-bearing diffusion coating formed on an adjacent relatively lower temperature region of the blade/component subject to hot corrosion in service. The chromium-bearing coating is applied after the aluminum-bearing coating by masking that coating and depositing a metallic chromium coating on the adjacent region followed by diffusing the chromium into the blade/component alloy to form a chromium-enriched diffusion coating thereon.

    摘要翻译： 本发明提供了一种用于燃气轮机叶片或其它部件的保护涂层，其中双相涂层包括形成在叶片/部件的第一较高温度区域上的含铝涂层，例如扩散铝化物， 在施加热腐蚀的叶片/部件的相邻较低温度区域上形成的施加的含铬扩散涂层。 通过掩蔽该涂层并在相邻区域上沉积金属铬涂层，然后将铬扩散到叶片/部件合金中以在其上形成富铬扩散涂层，在含铝涂层之后施加含铬涂层。

    Thermal barrier coating system
    4.
    发明公开
    Thermal barrier coating system 失效
    WärmehemmendesBeschichtungssystem

    公开(公告)号：EP0733723A1

    公开(公告)日：1996-09-25

    申请号：EP96103228.1

    申请日：1996-03-02

    申请人： HOWMET CORPORATION

    发明人： Murphy, Kenneth S.

    IPC分类号： C23C28/00

    CPC分类号： C23C28/02 ,  C23C14/083 ,  C23C16/12 ,  C23C28/042 ,  C23C28/42 ,  Y10S428/938 ,  Y10T428/12549 ,  Y10T428/1259 ,  Y10T428/12618 ,  Y10T428/12931

    摘要： A thermal barrrier protected nickel based or cobalt based superalloy component for use in a gas turbine engine includes a thermal barrier coating system having a multi-layered structure. The first bondcoat layer of the thermal barrier coating system comprises a chemical vapor deposited, platinum modified diffusion aluminide layer on the superalloy component (substrate). The diffusion aluminide layer includes an inner diffusion zone proximate the substrate and an outer layer region comprising a platinum modified (platinum-bearing) intermediate phase of aluminum and at least one of nickel and cobalt depending on the superalloy composition. The intermediate phase is a non-ordered solid solution having a range of compositions and is free of other phase constituents. The intermediate phase has an average aluminum concentration in the range of about 18 to about 28 % by weight, an average platinum concentration in the range of about 8 to about 35% by weight, and an average nickel concentration in the range of about 50 to 60% by weight and is non-stoichiometric relative to intermetallic compounds of aluminum and nickel, aluminum and cobalt, and aluminum and platinum. An adherent alpha alumina layer is thermally grown on the diffusion aluminide layer and receives an outer ceramic thermal barrier layer deposited thereon.

    摘要翻译： 一种用于燃气涡轮发动机的热障碍保护的基于镍或钴的超级合金部件包括具有多层结构的热障涂层系统。 热障涂层系统的第一粘结涂层包括在超合金部件（基底）上的化学气相沉积的铂改性扩散铝化物层。 扩散铝化物层包括靠近衬底的内部扩散区域和包含铝的铂改性（含铂载体）中间相的外层区域和根据超级合金组合物的镍和钴中的至少一种。 中间相是具有一定范围的组成并且不含其它相成分的无序固溶体。 中间相的平均铝浓度在约18至约28重量％的范围内，平均铂浓度在约8至约35重量％的范围内，平均镍浓度在约50至 60重量％，相对于铝和镍，铝和钴以及铝和铂的金属间化合物而言是非化学计量的。 粘附的α氧化铝层在扩散铝化物层上热生长并接收沉积在其上的外陶瓷热障层。

    Coating and coating method for gas turbine component
    5.
    发明公开
    Coating and coating method for gas turbine component 审中-公开
    燃气轮机部件的涂装和涂装方法

    公开(公告)号：EP2631325A3

    公开(公告)日：2017-08-09

    申请号：EP13155956.9

    申请日：2013-02-20

    申请人： Howmet Corporation

    发明人： Murphy, Kenneth S. ,  Basta, William C.

    IPC分类号： C23C10/02 ,  C23C10/58 ,  C25D5/02 ,  C25D5/12 ,  C25D13/02 ,  C25D13/12 ,  C25D13/16 ,  F01D5/28

    CPC分类号： F01D5/288 ,  C23C10/02 ,  C23C10/58 ,  C25D3/04 ,  C25D5/022 ,  C25D5/12 ,  C25D5/44 ,  C25D5/50 ,  C25D13/02 ,  C25D13/12 ,  C25D13/16 ,  F01D5/3007 ,  F05D2230/31 ,  F05D2300/121 ,  F05D2300/132

    摘要： The present invention provides a protective coating for a gas turbine blade or other component wherein the duplex coating includes an aluminum-bearing coating, such as a diffusion aluminide, formed on a first, relatively higher temperature region of the blade/component and a later-applied chromium-bearing diffusion coating formed on an adjacent relatively lower temperature region of the blade/component subject to hot corrosion in service. The chromium-bearing coating is applied after the aluminum-bearing coating by masking that coating and depositing a metallic chromium coating on the adjacent region followed by diffusing the chromium into the blade/component alloy to form a chromium-enriched diffusion coating thereon.

    摘要翻译： 本发明提供了一种用于燃气轮机叶片或其他部件的保护涂层，其中双层涂层包括形成在叶片/部件的第一相对较高温度区域上的含铝涂层，例如扩散铝化物， 在工作中经受热腐蚀的叶片/部件的相邻较低温度区域上形成的涂覆的含铬扩散涂层。 通过掩蔽该涂层并在相邻区域上沉积金属铬涂层，随后将铬扩散到刀片/部件合金中以在其上形成富铬扩散涂层，在含铝涂层之后施加含铬涂层。

    A maskant for use in aluminizing a turbine component
    7.
    发明公开
    A maskant for use in aluminizing a turbine component 审中-公开
    面包师urbㄧe e e e e e e e e e e e e e e e

    公开(公告)号：EP2778251A1

    公开(公告)日：2014-09-17

    申请号：EP14158581.0

    申请日：2014-03-10

    申请人： Howmet Corporation

    发明人： Murphy, Kenneth S. ,  Basta, William C. ,  Russo, Vincent J.

    IPC分类号： C23C10/04 ,  F01D5/28 ,  C23C10/08 ,  C23C10/38 ,  C23C10/32

    CPC分类号： C23C10/04 ,  C23C10/08 ,  C23C10/32 ,  C23C10/38 ,  F01D5/288 ,  F01D5/3092 ,  F05D2230/31

    摘要： A mask is used in aluminizing of superalloy turbine component, such as a turbine blade, where a region exposed to relatively high operating temperature is aluminized to form a diffusion aluminide coating and another region exposed to relatively lower operating temperatures is masked to prevent aluminizing of the masked region while concurrently being enriched in Cr and/or retaining a pre-existing Cr-content from the superalloy chemistry itself or from a previous chromizing operation.

    摘要翻译： 超级合金涡轮机部件如涡轮叶片的镀铝中使用掩模，其中暴露于较高工作温度的区域被镀铝以形成扩散铝化物涂层，并且掩盖暴露于较低工作温度的另一区域以防止 同时富集Cr和/或从超级合金化学本身或之前的铬化操作中保留预先存在的Cr含量。