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    Protective barrier coatings
    3.
    发明申请
    Protective barrier coatings 有权
    防护涂料

    公开(公告)号：US20080193657A1

    公开(公告)日：2008-08-14

    申请号：US11704447

    申请日：2007-02-09

    申请人： Derek Raybould ,  Thomas E. Strangman ,  Christian DelaCruz

    发明人： Derek Raybould ,  Thomas E. Strangman ,  Christian DelaCruz

    IPC分类号： B05D3/02

    CPC分类号： C23C24/08 ,  C23C18/04 ,  C23C18/1216 ,  C23C18/1225 ,  C23C18/1241 ,  C23C18/1254 ,  C23C26/00 ,  C23C28/321 ,  C23C28/325 ,  C23C28/345 ,  C23C28/3455 ,  C23C28/42 ,  F01D5/286 ,  F01D5/288 ,  F05D2230/90 ,  Y02T50/67

    摘要： Exemplary embodiments of the invention provide barrier coated substrates and methods of coating a substrate with a barrier coating derived from sol gels. An example includes a barrier coated aerospace component that is subject to hot salt corrosion during use. The barrier coating is derived from oxidation of a coating composition that includes at least one sol gel. The barrier coating resists hot salt corrosion for an incubation period of such duration that an uncoated superalloy substrate under the same conditions would suffer corrosion to a depth of about 2.0 mils. Methods of applying the barrier coating include the steps of selecting a first liquid sol gel and wetting surfaces of the superalloy substrate with the selected first liquid sol gel. The wetted surfaces of the superalloy substrate are subjected to heat treatment. The heat treatment includes sintering of sol gel to oxide to produce a barrier coating.

    摘要翻译： 本发明的示例性实施方案提供了阻挡涂层的基材和使用衍生自溶胶凝胶的阻挡涂层涂覆基材的方法。 一个例子包括在使用过程中遭受热盐腐蚀的阻隔涂层航空航天部件。 阻挡涂层源自包括至少一种溶胶凝胶的涂料组合物的氧化。 阻隔涂层在相当条件下的未涂覆的超级合金基材将受到约2.0密耳深度的腐蚀的潜伏期下，抵抗热盐腐蚀。 施加阻隔涂层的方法包括以下步骤：用所选择的第一液体溶胶凝胶选择第一液体溶胶凝胶并润湿超合金基底的表面。 对超合金基板的润湿表面进行热处理。 热处理包括将溶胶凝胶烧结成氧化物以产生阻挡涂层。

    NANOLAMINATE THERMAL BARRIER COATINGS
    9.
    发明申请
    NANOLAMINATE THERMAL BARRIER COATINGS 有权
    纳米酸盐热障涂层

    公开(公告)号：US20100068507A1

    公开(公告)日：2010-03-18

    申请号：US11517138

    申请日：2006-09-06

    申请人： Thomas E. Strangman ,  Derek Raybould

    发明人： Thomas E. Strangman ,  Derek Raybould

    IPC分类号： B32B5/00 ,  B05D1/36

    CPC分类号： C23C14/083 ,  C23C14/30 ,  C23C28/321 ,  C23C28/3215 ,  C23C28/325 ,  C23C28/345 ,  C23C28/3455 ,  C23C28/42 ,  C23C30/00 ,  Y02T50/67 ,  Y10T428/12458 ,  Y10T428/12479 ,  Y10T428/12549 ,  Y10T428/12576 ,  Y10T428/12611 ,  Y10T428/12618 ,  Y10T428/26

    摘要： An article having a thermal barrier coating includes a superalloy substrate having a columnar grained ceramic coat formed thereon. The ceramic coat includes a nanolaminate region comprising repeating layers of ceramic material with each layer being less than 500 nm in thickness, with dispersions of metal oxide doping material situated between each of the layers. The ceramic coat further includes a non-doped region having a thickness greater than 500 nm adjacent to the nanolaminate region, the non-doped region including one layer or a plurality of adjacent layers of ceramic material without dispersions of metal oxide doping material situated between each of the layers. In one embodiment, and by way of example only, a bond coat is formed between the substrate and the columnar grained ceramic coat. According to another embodiment, the superalloy substrate forms an adherent alumina scale, and no bond coat is necessary.

    摘要翻译： 具有热障涂层的物品包括在其上形成有柱状粒状陶瓷涂层的超合金基底。 该陶瓷涂层包括一层纳米层状区域，其中每层厚度小于500nm的重复陶瓷材料层，其间位于各层之间的金属氧化物掺杂材料的分散体。 陶瓷涂层还包括与纳米级氨基酸区域相邻的厚度大于500nm的非掺杂区域，非掺杂区域包括一层或多层相邻的陶瓷材料层，而不分散在每层之间的金属氧化物掺杂材料 的层。 在一个实施方案中，仅作为实例，在基材和柱状粒状陶瓷涂层之间形成粘合涂层。 根据另一个实施方案，超合金基底形成粘附氧化铝垢，并且不需要粘合涂层。

    Methods of forming high strength coatings
    10.
    发明授权
    Methods of forming high strength coatings 有权
    形成高强度涂层的方法

    公开(公告)号：US07479299B2

    公开(公告)日：2009-01-20

    申请号：US11044873

    申请日：2005-01-26

    申请人： Derek Raybould ,  Murali N. Madhava

    发明人： Derek Raybould ,  Murali N. Madhava

    IPC分类号： B05D1/02

    CPC分类号： C23C24/04 ,  Y10T428/12181

    摘要： The present invention thus provides an improved method for coating turbine engine components. The method utilizes a cold high velocity gas spray technique to coat turbine blades, compressor blades, impellers, blisks, and other turbine engine components. These methods can be used to coat a variety of surfaces thereon, thus improving the overall durability, reliability and performance of the turbine engine itself. The method includes the deposition of powders of alloys of nickel and aluminum wherein the powders are formed so as to have an amorphous microstructure. Layers of the alloys may be deposited and built up by cold high velocity gas spraying. The coated items displayed improved characteristics such as hardness, strength, and corrosion resistance.

    摘要翻译： 因此，本发明提供了一种用于涂覆涡轮发动机部件的改进方法。 该方法利用冷高速气体喷射技术来涂覆涡轮叶片，压缩机叶片，叶轮，叶片和其它涡轮发动机部件。 这些方法可用于在其上涂覆各种表面，从而提高涡轮发动机本身的整体耐久性，可靠性和性能。 该方法包括沉积镍和铝的合金粉末，其中形成粉末以具有无定形微结构。 可以通过冷高速气体喷涂沉积和堆积合金层。 涂层物品显示出改善的特性，如硬度，强度和耐腐蚀性。