Patent ID: 8123466

Claim:
A method for manufacturing a turbine engine blade outer air seal segment, the method including a reengineering from a baseline configuration and the segment comprising: a body having: a base portion having: a transversely concave ID face; a plurality of outlet holes extending through the base portion to the ID face; a forward end; an aft end; and first and second circumferential edges; and at least one mounting hook; and at least one cover plate secured to the body to define at least one cavity and having a plurality of feed holes through the cover plate, wherein: at least one of the base portion and cover plate comprises at least one protruding portion protruding into the cavity to form at least partial restrictions separating circumferentially and fore-aft offset compartment portions; and at least some of the feed holes are upstream of a given one of the at least one protruding portion and at least some of the feed holes are downstream of said given one of the at least one protruding portion, the method comprising; determining an indication of an operational core flow pressure drop along the ID face; selecting a characteristics of the protruding portion to provide a fore-aft pressure drop within the cavity, wherein a distribution of the feed holes in the plate is shifted forward relative to the baseline configuration; manufacturing the protruding portion with said characteristic via stamping; manufacturing the body via casting; and securing the cover plate to the body.