Patent ID: 6883303
Filing Date: 2005-04-26
Classification: F01D,Y02T

Abstract:
1. An aircraft gas turbine engine assembly comprising: axially spaced apart fan and inter-turbine frames rotatably supporting co-axial high and low pressure rotors, each of said frames comprising a first structural ring and a second structural ring, said second structural ring disposed co-axially with and radially spaced inwardly of said first structural ring about a centerline axis, and a plurality of circumferentially spaced apart struts extending radially between said first and second structural rings, said inter-turbine frame axially located between high and low pressure turbines of said high and low pressure rotors respectively, said high pressure turbine located forward of said low pressure turbine, said low pressure rotor includes a low pressure shaft which is at least in part rotatably disposed co-axially with and radially inwardly of said high pressure rotor, aft sump member having an aft central bore fixedly joined to said inter-turbine frame, said low pressure rotor supported by an aftwardmost bearing mounted in said aft central bore of said aft sump member, said high pressure rotor partly supported by a differential bearing mounted in an annular recess that is located radially inwardly of said aftwardmost bearing, and a frame connecting means for connecting said engine to an aircraft located on said first structural ring.