Patent ID: 7883311
Filing Date: 2011-02-08
Classification: F04D,F16C,Y10T

Abstract:
1. A method of assembling a gas turbine engine including a compressor assembly including a compressor rotor and a compressor stator, said method comprising: coupling a bearing assembly including a radial foil bearing, a pair of foil thrust bearings, and a pair of spring packs within a portion of the compressor assembly to facilitate supporting the compressor rotor; coupling the pair of foil thrust bearings to an axially extending portion of the compressor rotor, said pair of foil thrust bearings configured to engage a respective side of a radially outwardly extending portion of the stator such that the first thrust bearing is coupled upstream from the radially outwardly extending stator portion and the second thrust bearing is coupled downstream from the radially outwardly extending stator portion; coupling the pair of spring packs substantially co-axially to respective ones of the pair of foil thrust bearings, wherein the pair of foil thrust bearings and the pair of spring packs are coupled together with a coupling mechanism, such that the first spring pack is upstream from the first thrust bearing and the second spring pack is downstream from the second thrust bearing to facilitate load transfer between the first and second thrust bearings during operation of the engine; and coupling the radial foil bearing between the compressor stator and a forward end of the compressor rotor and radially outward from the pair of foil thrust bearings.