Ceramic matrix composite blade outer air seal feather seal configuration and method

A feather seal arrangement for a ceramic matrix composite (CMC) blade outer air seal (BOAS) of a turbine engine, comprising:

• a CMC BOAS segment including:
• a shoe having a flowpath side configured for exposure to a hot gas path of the turbine engine, an opposing non-flowpath side, and first and second matefaces extending axially between the flowpath side and the non-flowpath side from an upstream leading edge to a downstream trailing edge;
• one or more support flanges extending substantially transverse from the non-flowpath side;
• and
• a substantially flat first feather seal surface disposed on the non-flowpath side adjacent and substantially transverse to the first mateface;
• a first feather seal disposed atop the non-flowpath side on the first feather seal surface and extending to an adjacent feather seal surface of an adjacent CMC BOAS segment;
• and
• a first full hoop retainer configured for retaining an upstream end of the first feather seal and/or a second full hoop retainer configured for retaining a downstream end of the first feather seal,
• wherein the first and/or second full hoop retainer comprises an axial recess configured to axially hold the upstream and/or downstream end of the first feather seal, respectively.