Patent ID: 6619030
Filing Date: 2003-09-16
Classification: F01D,F02C,F02K,F05D,Y02T

Abstract:
An aircraft gas turbine engine assembly comprising:a high pressure rotor including a high pressure turbine, a low pressure turbine having counter rotating low pressure inner and outer rotors located aft of said high pressure rotor, an inter-turbine frame axially located between said high and low pressure turbines, said low pressure inner and outer rotors including low pressure inner and outer shafts which are at least in part rotatably disposed co-axially with and radially inwardly of said high pressure rotor, said inter-turbine frame comprising; a first structural ring, a second structural ring disposed co-axially with and radially spaced inwardly of said first structural ring about a centerline, a plurality of circumferentially spaced apart struts extending radially between said first and second structural rings, forward and aft sump members having forward and aft central bores, said forward and aft sump members fixedly joined to axially spaced apart forward and aft portions of said inter-turbine frame by forward and aft bearing support structures respectively, said low pressure inner and outer rotors rotatably supported by an aftwardmost low pressure rotor support bearing mounted in said aft central bore of said aft sump member, said high pressure rotor is aftwardly radially rotatably supported by a fifth bearing mounted in said forward bearing support structure, and a frame connecting means for connecting said engine to an aircraft located on said first structural ring.