A gas turbine engine (10; 100; 200) comprising: a housing; first and second spools (12, 14) coaxial with one another and arranged within the housing, the first spool arranged within the second spool and extending between forward and aft ends (12a, 12b), the aft end extending axially beyond the second spool; and first and second bearings (38, 40) supporting the aft end of the first spool relative to the housing; a combustor section and high and low pressure turbine sections (28, 24) downstream from the combustor section, the high pressure turbine section mounted on the second spool, and the low pressure turbine section mounted on the first spool, wherein the housing includes a first housing portion arranged axially between high and low pressure turbine sections (28, 24), and a second housing portion arranged aft of the low pressure turbine sections; wherein the first and second bearings (38, 40) are supported by the second housing portion; characterised in that the second housing portion includes a hub removably secured to an annular flange, the first and second bearings (38, 40) mounted to the hub, the low pressure turbine section includes a turbine rotor, and the first bearing is arranged axially forward of an aft side of a last rotor stage of the low pressure turbine section, wherein the turbine rotor is inclined radially outward and aftward, and the hub includes first and second hub walls (68, 70) respectively supporting the first and second bearings (38, 40), the first and second hub walls (68, 70) inclined radially outward and toward one another to provide an annular apex, a portion of the first hub wall arranged radially beneath the low pressure turbine section, and the first and second hub walls (68, 70) providing an integrated, unitary structure. a housing; first and second spools (12, 14) coaxial with one another and arranged within the housing, the first spool arranged within the second spool and extending between forward and aft ends (12a, 12b), the aft end extending axially beyond the second spool; and first and second bearings (38, 40) supporting the aft end of the first spool relative to the housing; a combustor section and high and low pressure turbine sections (28, 24) downstream from the combustor section, the high pressure turbine section mounted on the second spool, and the low pressure turbine section mounted on the first spool, wherein the housing includes a first housing portion arranged axially between high and low pressure turbine sections (28, 24), and a second housing portion arranged aft of the low pressure turbine sections; wherein the first and second bearings (38, 40) are supported by the second housing portion; characterised in that the second housing portion includes a hub removably secured to an annular flange, the first and second bearings (38, 40) mounted to the hub, the low pressure turbine section includes a turbine rotor, and the first bearing is arranged axially forward of an aft side of a last rotor stage of the low pressure turbine section, wherein the turbine rotor is inclined radially outward and aftward, and the hub includes first and second hub walls (68, 70) respectively supporting the first and second bearings (38, 40), the first and second hub walls (68, 70) inclined radially outward and toward one another to provide an annular apex, a portion of the first hub wall arranged radially beneath the low pressure turbine section, and the first and second hub walls (68, 70) providing an integrated, unitary structure.