Patent attributes
A method for assembling a gas turbine engine including providing a core gas turbine engine at least partially defined by a frame. The gas turbine engine has a drive shaft that is rotatable about a longitudinal axis of the core gas turbine engine. A counter-rotating fan assembly is coupled to the low-pressure turbine. The counter-rotating fan includes a first fan assembly that rotates in a first direction and a second fan assembly that rotates in an opposite second direction. A booster compressor is coupled to the second fan assembly. A first bearing assembly is mounted between the drive shaft and the frame and operatively coupled to the first fan assembly to transmit thrust force from the first fan assembly to the frame. A second bearing assembly is mounted with respect to the second fan assembly and operatively coupled to the second fan assembly to transfer thrust force from at least one of the second fan assembly and the booster compressor to the second bearing assembly.
