Patent ID: 8622693

Claim:
A blade outer air seal assembly of a gas turbine engine having a main axis of rotation defining axial, radial and circumferential directions, the blade outer air seal assembly comprising: an array of circumferentially adjacent blade outer air seal segments forming a static turbine shroud surrounding a turbine rotor; and an array of blade outer air seal support segments forming a support ring around the turbine shroud, each of the support segments supporting at least one of the blade outer air seal segments and defining a recess on respective opposed circumferential sides of each of the support segments, the support ring defining a cooling air distribution system for directing cooling air to pass through the respective support segments and to be discharged onto the blade outer air seal segments, the cooling air distribution system including a plurality of inlet cavities extending axially and inwardly from a forward end of the support ring to communicate with an inner cooling air passage of the respective support segments, each of the inlet cavities being formed with two of said recesses defined in respective adjacent two of said blade outer air seal support segments.