A gas turbine engine comprising: a combustor ; high and low pressure turbines downstream from the combustor ; first and second spools coaxial with one another about an engine central longitudinal axis (A), 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 supporting the low pressure turbine , wherein the high pressure turbine is mounted on the second spool , and the low pressure turbine is mounted on the first spool; a housing portion arranged downstream from the low pressure turbine ; and first and second bearings mounted to the aft end of the first spool and supported by the housing portion , wherein the housing portion is a turbine exhaust case and includes a bearing hub removably secured to an annular flange , the first and second bearings are mounted to the bearing hub , the first and second bearings are arranged in a bearing compartment aft of the second spool , the low pressure turbine includes multiple turbine rotors , the first bearing is arranged axially forward of an aft side of a last rotor stage of the low pressure turbine , the bearing hub includes first and second hub walls respectively supporting the first and second bearings , the first and second hub walls are inclined radially to the first and second bearings from an annular apex at which the first and second hub walls are joined near the annular flange , and a portion of the first hub wall is arranged radially beneath the low pressure turbine , characterised in that : the first hub wall is oriented at a first angle of between 30° and 60° relative to a line parallel to the longitudinal axis (A); the second hub wall is oriented at a second angle of between 30° and 60° relative to a line parallel to the longitudinal axis (A); and the first and second hub walls are canted toward one another in opposing directions and provide an integrated, unitary structure. a combustor ; high and low pressure turbines downstream from the combustor ; first and second spools coaxial with one another about an engine central longitudinal axis (A), 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 supporting the low pressure turbine , wherein the high pressure turbine is mounted on the second spool , and the low pressure turbine is mounted on the first spool; a housing portion arranged downstream from the low pressure turbine ; and first and second bearings mounted to the aft end of the first spool and supported by the housing portion , wherein the housing portion is a turbine exhaust case and includes a bearing hub removably secured to an annular flange , the first and second bearings are mounted to the bearing hub , the first and second bearings are arranged in a bearing compartment aft of the second spool , the low pressure turbine includes multiple turbine rotors , the first bearing is arranged axially forward of an aft side of a last rotor stage of the low pressure turbine , the bearing hub includes first and second hub walls respectively supporting the first and second bearings , the first and second hub walls are inclined radially to the first and second bearings from an annular apex at which the first and second hub walls are joined near the annular flange , and a portion of the first hub wall is arranged radially beneath the low pressure turbine , the first hub wall is oriented at a first angle of between 30° and 60° relative to a line parallel to the longitudinal axis (A); the second hub wall is oriented at a second angle of between 30° and 60° relative to a line parallel to the longitudinal axis (A); and the first and second hub walls are canted toward one another in opposing directions and provide an integrated, unitary structure. <EOS>