Gas turbine engine component with an abrasive coating

    公开(公告)号:US10465536B2

    公开(公告)日:2019-11-05

    申请号:US15136308

    申请日:2016-04-22

    Abstract: A gas turbine engine component includes a rotor blade having a squealer tip comprising a projecting lip, the rotor blade further having a raised rim running along both edges of each projecting kip of the squealer tip, and an abrasive coating formed of hard particles embedded in a retaining matrix covering a tip region of the rotor blade within an area bounded by the raised rim. The raised rim has a height of between 50% and 75% of a mean diameter of the hard particles.

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