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    Diffusion barrier and protective coating for turbine engine component and method for forming
    1.
    发明申请
    Diffusion barrier and protective coating for turbine engine component and method for forming 审中-公开
    用于涡轮发动机部件的扩散阻挡层和保护涂层以及成型方法

    公开(公告)号：US20070020399A1

    公开(公告)日：2007-01-25

    申请号：US11168660

    申请日：2005-06-28

    申请人： Mark Gorman ,  Bangalore Nagaraj ,  Ramgopal Darolia

    发明人： Mark Gorman ,  Bangalore Nagaraj ,  Ramgopal Darolia

    IPC分类号： B05D3/00 ,  B05D3/04 ,  B05D1/36 ,  H05H1/24 ,  B05D1/08 ,  B05D3/02

    CPC分类号： C25D5/48 ,  C23C4/02 ,  C23C4/18 ,  C23C28/322 ,  C23C28/345 ,  C23C28/3455 ,  C23C28/36 ,  C25D5/34 ,  F01D5/288 ,  F05D2230/90 ,  F05D2300/143 ,  F05D2300/21 ,  F05D2300/2112 ,  F05D2300/2118 ,  F05D2300/22 ,  F05D2300/228 ,  F05D2300/2281 ,  F05D2300/611 ,  Y02T50/67 ,  Y02T50/6765

    摘要： A turbine engine component comprising a substrate made of a nickel-base or cobalt-base superalloy, a non-metallic oxide or nitride diffusion barrier layer overlying the substrate, and a protective coating overlying the barrier layer, the protective coating comprising at least one platinum group metal selected from the group consisting of platinum, palladium, rhodium, ruthenium and iridium. The diffusion barrier layer may be a deposited or thermally grown oxide material, especially aluminum oxide. The protective coating may be heat treated to increase homogeneity of the coating and adherence with the substrate. The component typically further comprises a ceramic thermal barrier coating overlying the protective coating. Also disclosed are methods for forming a protective coating system on the turbine engine component by forming the non-metallic oxide or nitride diffusion barrier layer on the substrate and then depositing the platinum group metal on top of the barrier layer.

    摘要翻译： 一种涡轮发动机部件，包括由镍基或钴基超合金制成的基板，覆盖在基板上的非金属氧化物或氮化物扩散阻挡层以及覆盖在阻挡层上的保护涂层，所述保护涂层包含至少一种铂 选自铂，钯，铑，钌和铱的组金属。 扩散阻挡层可以是沉积的或热生长的氧化物材料，特别是氧化铝。 可以对保护涂层进行热处理以增加涂层的均匀性和与基材的粘合性。 该组件通常还包括覆盖保护涂层的陶瓷热障涂层。 还公开了通过在衬底上形成非金属氧化物或氮化物扩散阻挡层然后将铂族金属沉积在阻挡层的顶部上来在涡轮发动机部件上形成保护涂层系统的方法。

    THERMAL BARRIER COATING SYSTEM
    5.
    发明申请
    THERMAL BARRIER COATING SYSTEM 有权
    热障涂层系统

    公开(公告)号：US20050170200A1

    公开(公告)日：2005-08-04

    申请号：US10708020

    申请日：2004-02-03

    申请人： Bangalore Nagaraj ,  Ramgopal Darolia

    发明人： Bangalore Nagaraj ,  Ramgopal Darolia

    IPC分类号： B32B15/04

    CPC分类号： C23C28/36 ,  C23C4/073 ,  C23C4/10 ,  C23C4/134 ,  C23C28/321 ,  C23C28/3215 ,  C23C28/345 ,  C23C28/3455 ,  Y02T50/67 ,  Y10T428/1259 ,  Y10T428/12611 ,  Y10T428/12618

    摘要： A TBC system suitable for protecting the surface of a substrate subjected to a hostile thermal environment. The TBC system comprises a bond coat on the substrate surface, an alumina scale on the bond coat, and a multilayer TBC comprising a thermal-sprayed first ceramic layer on the alumina scale and a thermal-sprayed second ceramic layer overlying the first ceramic layer. The first ceramic layer consists essentially of partially stabilized zirconia so as to comprise the tetragonal and cubic phases of zirconia. The second ceramic layer consists essentially of fully stabilized zirconia so as to consist essentially of the cubic phase of zirconia. The second ceramic layer is also characterized by having vertical microcracks that extend through the thickness thereof. The second ceramic layer is thicker and more erosion resistant than the first ceramic layer.

    摘要翻译： 适用于保护受到恶劣热环境的基板表面的TBC系统。 所述TBC系统包括在所述基材表面上的粘合涂层，所述粘结涂层上的氧化铝垢，以及在所述氧化铝垢上包含热喷涂的第一陶瓷层的多层TBC和覆盖所述第一陶瓷层的热喷涂的第二陶瓷层。 第一陶瓷层基本上由部分稳定的氧化锆组成，以便包含氧化锆的四方晶相和立方相。 第二陶瓷层基本上由完全稳定的氧化锆组成，以便基本上由立方相的氧化锆组成。 第二陶瓷层的特征在于具有延伸穿过其厚度的垂直微裂纹。 第二陶瓷层比第一陶瓷层更厚并且更耐腐蚀。

    Aluminide coating of turbine engine component
    7.
    发明申请
    Aluminide coating of turbine engine component 失效
    涡轮发动机部件的铝酸盐涂层

    公开(公告)号：US20050008780A1

    公开(公告)日：2005-01-13

    申请号：US10615094

    申请日：2003-07-08

    申请人： John Ackerman ,  Michael Weimer ,  Joseph Heaney ,  William Walston ,  Bangalore Nagaraj

    发明人： John Ackerman ,  Michael Weimer ,  Joseph Heaney ,  William Walston ,  Bangalore Nagaraj

    IPC分类号： C23C10/08 ,  C23C16/04 ,  C23C16/20 ,  C23C16/56 ,  C23C16/00

    CPC分类号： C23C16/56 ,  C23C10/08 ,  C23C16/045 ,  C23C16/20 ,  Y02T50/67

    摘要： A method for forming an aluminide coating on a turbine engine component having an external surface and an internal cavity defined by an internal surface that is connected to the external surface by at least one hole. The method is conducted in a vapor coating container having a hollow interior coating chamber, and includes the steps of loading the coating chamber with the component to be coated; flowing a tri-alkyl aluminum coating gas into the loaded coating chamber at a specified temperature, pressure, and time to deposit an aluminum coating on the external and internal surfaces of the component; and heating the component in a nonoxidizing atmosphere at a specified temperature and time to form an aluminide coating on the external and internal surfaces. The coated component is typically then maintained at an elevated temperature in the presence of oxygen to form an oxide coating on the external and internal surfaces of the component. In one embodiment, the turbine engine component is a turbine engine blade having an external surface and an internal cooling cavity having an internal surface that is connected to the external surface by cooling holes.

    摘要翻译： 一种用于在涡轮发动机部件上形成铝化物涂层的方法，所述方法具有外表面和由内表面限定的内腔，所述内表面通过至少一个孔连接到所述外表面。 该方法在具有中空的内部涂覆室的蒸气涂覆容器中进行，并且包括以下步骤：将涂覆室与待涂覆的部件装载; 在特定温度，压力和时间下将三烷基铝涂层气体流入装载的涂覆室中，以将铝涂层沉积在部件的外表面和内表面上; 并在特定温度和时间下在非氧化气氛中加热组分，以在外表面和内表面上形成铝化物涂层。 然后将涂覆的组分在氧的存在下保持在升高的温度，以在组件的外表面和内表面上形成氧化物涂层。 在一个实施例中，涡轮发动机部件是具有外表面和内部冷却腔的涡轮发动机叶片，其具有通过冷却孔连接到外表面的内表面。

    Layered paint coating for turbine blade environmental protection
    8.
    发明申请
    Layered paint coating for turbine blade environmental protection 有权

    公开(公告)号：US20070104969A1

    公开(公告)日：2007-05-10

    申请号：US11266857

    申请日：2005-11-04

    申请人： Bangalore Nagaraj ,  Brian Hazel

    发明人： Bangalore Nagaraj ,  Brian Hazel

    IPC分类号： B05D1/32 ,  B05D1/12 ,  B05D3/02

    CPC分类号： C23C24/08 ,  C23C26/00 ,  C23C30/00 ,  F01D5/288 ,  F05D2300/50212 ,  Y02T50/67 ,  Y02T50/671

    摘要： The present invention is a gas turbine engine turbine blade comprising an airfoil section having at least an exterior surface, a platform section having an exterior surface, an under platform section having an exterior surface, and a dovetail section having an exterior surface. The blade further comprises a corrosion resistant coating on a surface of a turbine blade section selected from the group consisting of the exterior surface of the under platform section, the exterior surface of the dovetail section, and combinations thereof, the corrosion resistant coating comprising a particulate corrosion resistant component comprising from about 5 weight percent to about 100 weight percent corrosion resistant non-alumina particulates having a CTE greater than that of alumina particulates and balance alumina particulates, and a binder component. The present invention also includes methods for making such a gas turbine engine blade.