Patent ID: 7195447
Filing Date: 2007-03-27
Classification: F01D,F02C,F05D

Abstract:
1. A method for assembling a gas turbine engine, said method comprising: providing a low-pressure turbine inner rotor that includes a first plurality of turbine blade rows configured to rotate in a first direction; providing a low-pressure turbine outer rotor that includes a second plurality of turbine blade rows configured to rotate in a second direction that is opposite the first direction; coupling a turbine mid-frame assembly including a plurality of spokes within the engine such that the spokes are spaced axially forward of the inner rotor; coupling a plurality of yokes to a hub assembly such that the plurality yokes are coupled to the plurality of spokes using at least one expandable pin; coupling a bearing between the turbine mid-frame assembly and the inner rotor such that the inner rotor is rotatably coupled to the turbine mid-frame; and adjusting the plurality of spokes to align the bearing in a radial direction.