A gas turbine engine (10; 100; 200) comprising: a housing ; first and second spools coaxial with one another and arranged within the housing , the first spool arranged within the second spool and extending between forward and aft ends , the aft end extending axially beyond the second spool ; and first and second bearings supporting the aft end of the first spool relative to the housing ; a combustor section and high and low pressure turbine sections 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 , and a second housing portion arranged aft of the low pressure turbine sections ; wherein the first and second bearings 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 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 respectively supporting the first and second bearings , the first and second hub walls 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 providing an integrated, unitary structure. a housing ; first and second spools coaxial with one another and arranged within the housing , the first spool arranged within the second spool and extending between forward and aft ends , the aft end extending axially beyond the second spool ; and first and second bearings supporting the aft end of the first spool relative to the housing ; a combustor section and high and low pressure turbine sections 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 , and a second housing portion arranged aft of the low pressure turbine sections ; wherein the first and second bearings 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 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 respectively supporting the first and second bearings , the first and second hub walls 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 providing an integrated, unitary structure. <EOS>