Patent ID: 9506402
Filing Date: 2016-11-29
CPC Classification: F01D,F02C,F05D

Claim Text:
1. A gas turbine engine assembly comprising: a core section including a compressor, a combustor and a turbine supported along an axis; a low spool supported for rotation about the axis, the low spool including a low turbine section; an intermediate spool including an intermediate turbine section axially forward of the low turbine section, the intermediate turbine section including all stages rotatable with the intermediate spool, the intermediate spool supported for rotation coaxially with the low spool by an aft intermediate spool bearing supported on the low spool, wherein the aft intermediate spool bearing is axially rearward of turbine blades attached to the low spool for rotation with the low spool; a high spool supported for rotation coaxially with the low spool and the intermediate spool; and a high spool bearing compartment supporting an aft high spool bearing, wherein the high spool bearing compartment and the aft high spool bearing are disposed within a radial space between the combustor and the axis.