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公开(公告)号：US11286789B2
公开(公告)日：2022-03-29
申请号：US16920014
申请日：2020-07-02
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Jaime G Ghigliotty , David J Candelori , San Quach
Abstract: An airfoil for a gas turbine engine is disclosed. In various embodiments, the airfoil includes a cooling passage; an outer wall separating a core flow path from the cooling passage; a diffuser in fluid communication with the cooling passage and opening into the core flow path, the diffuser being characterized by a linear ridge on a downstream end of the diffuser; and a thermal barrier coating covering the outer wall and the linear ridge.
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