Patent ID: 9022725
Filing Date: 2015-05-05
Classification: F01D,F02C,F02K,Y02T

Abstract:
1. A gas turbine engine comprising: a shaft defining an axis of rotation; a turbine section comprising: an outer rotor directly driving the shaft, the outer rotor including an outer set of blades; and an inner rotor having an inner set of blades interspersed with the outer set of blades, the inner rotor configured to rotate in an opposite direction about the axis of rotation from the outer rotor; a first bearing supporting a fore end of the inner rotor; a second bearing supporting an aft end of the inner rotor, wherein the first and second bearings are mounted on the shaft; and a gear system coupling the inner rotor to the shaft and configured to rotate the inner set of blades at a faster speed than the outer set of blades.