Patent ID: 7059827
Filing Date: 2006-06-13
Classification: F01D,F05D,F16J

Abstract:
1. A stationary gas turbine engine for a power plant, comprising: (a) a multistage axial compressor, the compressor having a rotor, the rotor having a cylindrical land region downstream of a last-stage of the compressor, the land region having an outside diameter D; (b) a turbine shaft-coupled to the rotor of the compressor; (c) a combustor fluid coupled between the compressor and the turbine; (d) a stationary inner barrel member downstream of the compressor, air flowing from the compressor to the combustor passing outside of the inner barrel member, a chamber within the inner barrel member forming a passage for cooling air from the compressor, the cooling air flowing from the chamber and being mixed with combustion gases upstream of the turbine; (e) a brush seal for restricting air passage into the chamber from the compressor, the brush seal comprising: