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    Application of dense vertically cracked and porous thermal barrier coating to a gas turbine component
    1.
    发明授权
    Application of dense vertically cracked and porous thermal barrier coating to a gas turbine component 有权
    致密的垂直裂纹和多孔隔热涂层应用于燃气轮机部件

    公开(公告)号：US08511993B2

    公开(公告)日：2013-08-20

    申请号：US12541266

    申请日：2009-08-14

    申请人： Dana Kemppainen ,  RuthAnn Rawlings ,  Jonah Klemm-Toole ,  Robert Moore

    发明人： Dana Kemppainen ,  RuthAnn Rawlings ,  Jonah Klemm-Toole ,  Robert Moore

    IPC分类号： F01D5/28

    CPC分类号： F01D5/288 ,  C23C4/01 ,  C23C4/02 ,  C23C4/11 ,  C23C4/129 ,  C23C4/134 ,  C23C28/3215 ,  C23C28/3455 ,  F05D2230/80 ,  F05D2230/90

    摘要： A configuration for coating a turbine component such as a blade or vane with various forms of thermal barrier coating to provide enhanced temperature capability and increased strain tolerance is disclosed. A gas path surface of the platform, airfoil and airfoil fillet region are first coated with a bond coating. A dense vertically cracked (DVC) thermal barrier coating is then applied to at least the gas path surface of the platform and can be applied to the fillet region. A porous thermal barrier coating is then applied to at least the airfoil. The porous thermal barrier coating can also be applied over the DVC thermal barrier coating if desired.

    摘要翻译： 公开了用于涂覆具有各种形式的隔热涂层的涡轮机部件（例如叶片或叶片）以提供增强的温度能力和增加的应变公差的构造。 平台，翼型件和翼型件区域的气体路径表面首先涂覆有粘结涂层。 然后将密集的垂直裂纹（DVC）热障涂层施加到平台的至少气体路径表面，并且可以应用于圆角区域。 然后将多孔热障涂层施加至至少翼型件。 如果需要，多孔隔热涂层也可以涂覆在DVC隔热涂层上。