Patent ID: 6226975
Filing Date: 2001-05-08
Classification: F01D,F02C,F16J

Abstract:
A stationary gas turbine engine for a power plant having a floating brush seal and comprising:(a) a multistage axial compressor, the compressor having a rotor, the rotor having a cylindrical land region downstream of at least a major portion of the compressor, the land region having an outside diameter;(b) a turbine shaft-coupled to the rotor;(c) a stationary inner barrel member having an end and a cavity positioned in the end of the inner barrel member, the cavity having an inner surface, the inner barrel being downstream of at least a major portion 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;(d) a floating brush seal for controlling air passage into the chamber from the compressor, the floating brush seal comprising:(i) a ring-shaped holder positioned in the cavity;(ii) a multiplicity of bristle members extending radially inwardly from the holder toward the land region of the rotor, outer extremities of the bristle members being rigidly retained relative to the holder;(iii) a retainer connected to the end of the inner barrel to form an enclosure to contain the holder; and,(iv) a plurality of springs mounted between the outside circumference of the holder and the inner surface of the cavity to urge the bristle members into contact with the land region of the rotor.