A gas turbine engine comprising: a compressor section for receiving air and delivering it to a combustor ; a turbine section downstream of said combustor , an upstream location leading from the compressor section in a downstream direction toward the turbine section , the turbine section including at least one rotating blade row for rotation about a rotational axis (X), and a blade outer air seal positioned radially outward of blades in the rotating blade row relative to the rotational axis (X), the blade outer air seal having a radially inward facing web , spaced from a radially outer tip of the blades, and a radially outer face relative to said radially inward facing web , wherein said blade outer air seal has a leading edge attachment feature adjacent an upstream leading edge of the blade outer air seal and a trailing edge attachment feature adjacent a downstream trailing edge of the blade outer air seal ; and at least one brush seal (124; 128) having bristles extending radially inward from a mount location to contact a sealing surface (116; 114) on the radially outer face , wherein a chamber is defined between said leading edge attachment feature and said trailing edge attachment feature , and adapted to be connected to a source of pressurized cooling air, with an angle (A) defined between said bristles and said sealing surface (116; 114) having a radially inward extending component, and with an axial component in a direction toward said leading edge attachment feature and said trailing edge attachment feature , and the angle (A) is less than 90° on a side of the brush seal (124; 128) opposite the leading edge and trailing edge attachment features . a compressor section for receiving air and delivering it to a combustor ; a turbine section downstream of said combustor , an upstream location leading from the compressor section in a downstream direction toward the turbine section , the turbine section including at least one rotating blade row for rotation about a rotational axis (X), and a blade outer air seal positioned radially outward of blades in the rotating blade row relative to the rotational axis (X), the blade outer air seal having a radially inward facing web , spaced from a radially outer tip of the blades, and a radially outer face relative to said radially inward facing web , wherein said blade outer air seal has a leading edge attachment feature adjacent an upstream leading edge of the blade outer air seal and a trailing edge attachment feature adjacent a downstream trailing edge of the blade outer air seal ; and at least one brush seal (124; 128) having bristles extending radially inward from a mount location to contact a sealing surface (116; 114) on the radially outer face , wherein a chamber is defined between said leading edge attachment feature and said trailing edge attachment feature , and adapted to be connected to a source of pressurized cooling air, with an angle (A) defined between said bristles and said sealing surface (116; 114) having a radially inward extending component, and with an axial component in a direction toward said leading edge attachment feature and said trailing edge attachment feature , and the angle (A) is less than 90° on a side of the brush seal (124; 128) opposite the leading edge and trailing edge attachment features . <EOS>