Blade outer air seal (boas) assembly for a gas turbine engine

A blade outer air seal (BOAS) segment comprising:

• a segment body extending between and to an outer radial surface and an inner radial surface relative to a BOAS axis, the segment body including an outer passage wall, an inner passage wall, a first lateral side wall, and a second lateral side wall forming an internal cooling passage between the outer radial surface and the inner radial surface, the segment body forming a flow augmentation feature assembly at the inner passage wall within the internal cooling passage, the flow augmentation feature assembly including a plurality of trip strips arranged in a tread pattern along the inner passage wall, the plurality of trip strips arranged in the tread pattern including a plurality of chevron trip strips, a plurality of first lateral trip strips, and a plurality of second lateral trip strips,
• the plurality of chevron trip strips disposed between the plurality of first lateral trip strips and the plurality of second lateral trip strips in a widthwise direction extending between the first lateral side wall and the second lateral side wall, each of the plurality of chevron trip strips including transverse trip strip segments,
• the plurality of first lateral trip strips disposed along the first lateral side wall, each of the first lateral trip strips extending from the first lateral side wall toward a respective one of the plurality of chevron trip strips, and
• the plurality of second lateral trip strips disposed along the second lateral side wall, each of the second lateral trip strips extending from the second lateral side wall toward a respective one of the plurality of chevron trip strips.