Aircraft engine with inter-turbine engine frame

A gas turbine engine assembly comprising:

• an inter-turbine frame axially located between first and second turbines of first and second rotors respectively,
• said first turbine located forward of said second turbine,
• said second rotor includes a second shaft which is at least in part rotatably disposed co-axially with and radially inwardly of said first 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 axis,
• 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 forward and aft portions of said turbine frame respectively,
• said second rotor supported by a respective aftwardmost second turbine frame bearing mounted in said aft central bore of said aft sump member,
• said first rotor partly supported by a respective first turbine frame bearing mounted in said forward central bore of said forward sump member, and
• a frame connecting means for connecting said engine to an aircraft located on said first structural ring.

An aircraft gas turbine engine assembly comprising:

• an inter-turbine frame axially located between high and low pressure turbines of 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,
• 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 axis,
• 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 forward and aft portions of said turbine frame respectively,
• said low pressure rotor supported by a respective aftwardmost second turbine frame bearing mounted in said aft central bore of said aft sump member,
• said high pressure rotor partly supported by a respective first turbine frame bearing mounted in said forward central bore of said forward sump member, and
• a frame connecting means for connecting said engine to an aircraft local d on said first structural ring.

An aircraft gas turbine engine assembly comprising:

• co-axial first and second rotors rotatably supported by only two axially spaced apart frames,
• said frames being axially spaced apart forward and aft frames rotatably supporting said first and second 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,
• a first shaft of said second rotor disposed radially inwardly of said first rotor,
• said aft frame located between turbines of said first and second rotors, and
• forward and aft frame connecting means for connecting said engine to an aircraft disposed on said forward and aft frames.

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,
• forward and aft sump members having forward and aft central bores,
• said forward and aft sump members fixedly joined to forward and aft portions of said turbine frame respectively,
• said low pressure rotor supported by a respective aftwardmost second turbine frame bearing mounted in said aft central bore of said aft sump member,
• said high pressure rotor partly supported by a respective first turbine frame bearing mounted in said forward central bore of said forward sump member, and
• a frame connecting means for connecting said engine to an aircraft located on said first structural ring.