Patent ID: 7703290
Filing Date: 2010-04-27
Classification: F01D,F05D,Y02T

Abstract:
1. A gas turbine engine comprising a rotary axial-flow air compressor mounted on an axial shaft for generating a bleed of air under pressure, and a turbine, said axial shaft having a forward end in advance of the air compressor and a rearward end, said forward end being defined by a forward facing surface located in a void in advance of the air compressor to form an air thrust bearing, said turbine being located between the compressor and the rearward end of the axial shaft, a pressurized air cushion maintained by said bleed of air from the compressor to the thrust bearing, said pressurized air cushion opposing only the forward thrust of the compressor transmitted by the axial shaft, said axial shaft having a degree of forward end float to allow said forward facing surface to move axially within said void to thereby compensates for relative changes between the air pressure in the air cushion and the forward thrust transmitted by the shaft.