Aircraft engine with inter-turbine engine frame supported counter rotating low pressure turbine rotors

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.