PROTECTIVE COATING SYSTEMS FOR GAS TURBINE ENGINE APPLICATIONS AND METHODS FOR FABRICATING THE SAME

    公开(公告)号:US20230033942A1

    公开(公告)日:2023-02-02

    申请号:US17443693

    申请日:2021-07-27

    Abstract: A method of applying a protective coating to a substrate includes the steps of: providing a turbine engine component substrate formed of a ceramic matrix composite material, forming an environmental barrier coating layer including a rare earth disilicate material directly on the substrate, treating an outer surface of the environmental barrier coating layer to form a thermal barrier coating layer including a porous rare earth monociliate material directly on the environmental barrier coating layer. The step of treating the outer surface is performed using a thermal process consisting of the application of heat or a chemical-thermal process consisting of the application of heat and a chemical. The method further includes infiltrating at least a portion of the pores with a metal solution or suspension.

    NON-CONTACT RADIATIVE HEATING FOR SINTERING HIGH TEMPERATURE COATINGS

    公开(公告)号:US20220348511A1

    公开(公告)日:2022-11-03

    申请号:US17302011

    申请日:2021-04-21

    Abstract: A method for forming a high temperature coating includes forming a pre-sintered ceramic coating on a ceramic composite substrate. The pre-sintered ceramic coating comprises a plurality of ceramic particles. The method further includes sintering at least a portion of the pre-sintered ceramic coating by heating the portion of the pre-sintered ceramic coating to a sintering temperature of the pre-sintered ceramic coating using one or more non-contact radiative heating elements. The sintering temperature is greater than about 1000 degrees Celsius (° C.).

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