A gas turbine engine comprising: a compressor section for receiving air and delivering it to a combustor; a turbine section (28, 96) downstream of said combustor, an upstream location leading from the compressor section in a downstream direction toward the turbine section (28, 96), the turbine section (28, 96) including at least one rotating blade row for rotation about a rotational axis, and a blade outer air seal positioned radially outward of blades in the rotating blade row relative to the rotational axis, 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 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 is less than 90° on a side of the brush seal (124; 128) opposite the leading edge and trailing edge attachment features (104, 108). a compressor section for receiving air and delivering it to a combustor; a turbine section (28, 96) downstream of said combustor, an upstream location leading from the compressor section in a downstream direction toward the turbine section (28, 96), the turbine section (28, 96) including at least one rotating blade row for rotation about a rotational axis, and a blade outer air seal positioned radially outward of blades in the rotating blade row relative to the rotational axis, 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 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 is less than 90° on a side of the brush seal (124; 128) opposite the leading edge and trailing edge attachment features (104, 108).