PROCESS FOR PRODUCING REFRACTORY CERAMICS FOR GAS TURBINE PLANTS
    3.
    发明申请
    PROCESS FOR PRODUCING REFRACTORY CERAMICS FOR GAS TURBINE PLANTS 审中-公开
    生产用于气体涡轮机植物的耐火陶瓷的工艺

    公开(公告)号:US20140165573A1

    公开(公告)日:2014-06-19

    申请号:US14240179

    申请日:2012-08-14

    申请人: Claus Krusch

    发明人: Claus Krusch

    摘要: A process for producing refractory ceramics (K) for use as heat shield in the hot gas path of gas turbine plants: introducing a casting composition into a component casing mold for the refractory ceramic (K), closing the casting mold so that the casting composition is under a defined static pressure after closure; orienting vibration of the casting mold in the direction (V) of a normal (N) to a surface of the refractory ceramic (K) to be produced, and subsequently removing the casting from the mold and firing the cast component.

    摘要翻译: 一种用于在燃气轮机设备的热气路径中用作隔热层的耐火陶瓷(K)的方法:将铸造组合物引入用于耐火陶瓷(K)的部件壳体模具中,关闭铸模,使得铸造组合物 关闭后处于定义的静压下; 将铸模的正常(N)方向(V)定向到待制造的耐火陶瓷(K)的表面,然后从模具中取出铸件并点火铸造组件。

    PROCESS FOR BRAZING WIDE GAPS
    5.
    发明申请
    PROCESS FOR BRAZING WIDE GAPS 有权
    制作宽幅裁片的方法

    公开(公告)号:US20110174867A1

    公开(公告)日:2011-07-21

    申请号:US12743440

    申请日:2008-11-11

    IPC分类号: B23K31/02

    摘要: A method for repairing wider gaps in a substrate of a component by brazing at a brazing temperature is provided. Filler material and solder are prevented from separating in that, in a two-stage process, first the filler material and then the solder are applied to the wider gap. The powder does not melt at the brazing temperature and the filler metal does melt at the brazing temperature.

    摘要翻译: 提供了通过在钎焊温度下钎焊来修复部件的基板中较宽间隙的方法。 防止填料和焊料分离,因为在两阶段工艺中,首先将填充材料,然后将焊料施加到更宽的间隙。 该粉末在钎焊温度下不熔化,并且填料金属在钎焊温度下熔化。

    Coating process and corrosion protection coating for turbine components
    10.
    发明申请
    Coating process and corrosion protection coating for turbine components 审中-公开
    涡轮机部件的涂层工艺和防腐涂层

    公开(公告)号:US20110117377A1

    公开(公告)日:2011-05-19

    申请号:US13003055

    申请日:2009-06-23

    IPC分类号: C23C16/34 H05H1/24 B32B15/04

    摘要: A process for coating a surface of a potentially fuel-conducting component of a turbine, in particular a gas turbine, in which the surface is firstly coated with a titanium nitride layer and subsequently with an a-aluminium oxide layer by means of chemical vapour deposition, is disclosed. In addition, a turbine component for example a component of a gas turbine, which includes a base material and a potentially fuel-conducting surface is described. The surface has an intermediate layer including titanium nitride and a covering layer including a-aluminium oxide.

    摘要翻译: 一种用于涂覆涡轮机,特别是燃气轮机的潜在燃料导电部件的表面的方法,其中表面首先用氮化钛层涂覆,随后通过化学气相沉积 ,被披露。 此外,描述了涡轮机部件,例如燃气轮机的部件,其包括基础材料和潜在的燃料导电表面。 表面具有包括氮化钛的中间层和包含α-氧化铝的覆盖层。