Wear resistant turbine blade tip
    11.
    发明授权

    公开(公告)号:US10662788B2

    公开(公告)日:2020-05-26

    申请号:US15920878

    申请日:2018-03-14

    Abstract: A gas turbine engine includes: a turbine section including a casing extending circumferentially about a plurality of turbine blades and having at least one seal member coated with an abradable coating. At least one turbine blade has sides and a tip and at least one seal member is located adjacent to the tip of the at least one turbine blade. The tip of the at least one turbine blade has a wear resistant layer and an abrasive coating disposed on the wear resistant layer. The wear resistant layer has a thickness less than or equal to 10 mils (254 micrometers) and includes metal boride compounds.

    WEAR RESISTANT COATING, METHOD OF MANUFACTURE THEREOF AND ARTICLES COMPRISING THE SAME

    公开(公告)号:US20190136701A1

    公开(公告)日:2019-05-09

    申请号:US15804430

    申请日:2017-11-06

    Abstract: Disclosed herein is an article comprising a substrate; an abrasive coating disposed on the substrate; where the abrasive coating comprises a matrix having abrasive grit particles dispersed therein; and a layer of material disposed on the abrasive coating; where the layer of material is a titanium nitride (TiN), boron nitride (BN), titanium-aluminum-nitrides [(TiAl)N], titanium-aluminum-silicon-nitrides [(TiAlSi)N], chromium nitrides (CrN), aluminum oxide (Al2O3), titanium oxide (TiO2), silicon carbo-nitride (SiCN), titanium carbo-nitride (TiCN), or a combination thereof.

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