Patent ID: 8596962

Claim:
A blade outer air seal segment for a turbine in a gas turbine engine, the blade outer air seal segment comprising: a leading edge side and a trailing edge side with two mate face sides in-between; an impingement cavity on a backside surface of the blade outer air seal segment; a first cooling air supply hole located on each of the four corners of the impingement cavity; each of the first cooling air supply holes being connected to at least two cooling holes that open onto two sides of the blade outer air seal to discharge cooling air; a plurality of thin metering slots opening into the impingement cavity and adjacent to each of the two mate face sides; each of the thin metering slots being connected to a plurality of cooling holes that open onto the adjacent mate face side of the blade outer air seal segment; a row of second cooling air supply holes opening into the impingement cavity adjacent to the leading edge side of the cavity; and, each of the second cooling air holes is connected to a cooling hole that extends across the blade outer air seal main body and opens onto the trailing edge side of the blade outer air seal to discharge cooling air.