Blade outer air seal

A turbine engine blade outer air seal segment comprising:

• a body having:
• a base portion having:
• a transversely concave 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, a plurality of outlet holes extending through the base portion to the ID face,
• 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
• the at least one protruding portion comprises:
• an essentially full height axial rib of the body;
• a partial height circumferential rib of the body, the axial rib and circumferential rib cooperating to divide the compartment into four quadrants;
• and
• four circumferentially elongate blisters on the cover plate, each along a respective one of the four quadrants.

A turbine engine blade outer air seal segment comprising:

• a body having:
• a base portion having:
• a transversely concave 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, a plurality of outlet holes extending through the base portion to the ID face,
• 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
• the at least one protruding portion comprises:
• a partial height axial rib of the body
• an essentially full height circumferential rib of the body, the axial rib and circumferential rib cooperating to divide the compartment into four quadrants;
• four circumferentially elongate blisters on the cover plate, each along a respective one of the four quadrants;
• and
• four axially elongate blisters on the cover plate, each along a respective one of the four quadrants.

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 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, a plurality of outlet holes extending through the base portion to the ID face, wherein:
• at least one of the base portion and cover plate comprises means for providing an operational axial/circumferential pressure gradient within the cavity to compensate for an operational core flow pressure drop along the ID face,
• the method comprising;
• determining an indication of an operational core flow pressure drop along the ID face;
• selecting a characteristic 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.

A method for manufacturing a turbine engine blade outer air seal segment including reengineering a configuration of a turbine engine blade outer air seal segment from a baseline configuration to a reengineered configuration, the baseline configuration comprising:

• a body having:
• a base portion having:
• a transversely concave 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 impingement cavity and having a plurality of feed holes, a plurality of outlet holes extending through the base portion to the ID face, the method comprising:
• determining an indication of an operational core flow pressure drop along the ID face;
• selecting a characteristic of the protruding portion to provide a fore-aft pressure drop with the cavity;
• adding a protrusion into the cavity from at least one of the cover plate and base portion in the reengineering;
• manufacturing the at least one of the cover plate and base portion with the protrusion;
• and
• securing the at least one of the cover plate and base portion to the other of the cover plate and base portion, wherein:
• the baseline configuration has a mean location of the feed holes;
• and the reengineered configuration has a mean location of the feed holes forward of the baseline configuration mean location.