Patent ID: 7186073
Filing Date: 2007-03-06
Classification: F01D,F02C,F02K,F05D,Y10T

Abstract:
1. A method for assembling a gas turbine engine, said method comprising: providing a low-pressure turbine inner rotor that includes at least a first pair of adjacent rows of inner rotor turbine blades that are configured to rotate in a first direction; providing a low-pressure turbine outer rotor that includes a forward end, an aft end, and at least one row of outer rotor turbine blades that is rotatably coupled between the first pair of inner rotor turbine blades, wherein the at least one row of outer rotor turbine blades is configured to rotate in a second direction that is opposite the first direction; coupling a support assembly between the first pair of inner rotor turbine blades such that the support assembly supports the outer rotor forward end; coupling a support ring to a first row of the at least one row of outer rotor turbine blades; and rotatably coupling at least one bearing to the support assembly such that the at least one bearing rotatably supports the support ring.