Abstract: A gas turbine engine rotor assembly is provided for rotatably mounting a rotor mounted power takeoff gear of an inlet gear box and a forward end of a high pressure rotor within an engine frame. The gear and rotor are mounted to forward and aft portions respectively of a gear shaft which is at least partially supported by a radial roller bearing having an outer race supportably mounted to the fan frame of the engine frame and an inner race directly mounted to the gear shaft between the gear and rotor.

Abstract: A bearing assembly includes a split inner race disposed on a distal end of an output shaft disposed coaxially about an input shaft. A plurality of bearing elements are disposed around the inner race, with a stationary outer race surrounding the elements. The inner race includes a plural number A.sub.1 of radially extending splitline channels in flow communication with a circumferential splitline manifold between the inner race and the output shaft distal end. A first half of the inner race includes a plural number B.sub.1 of radially extending first channels disposed in flow communication with a circumferential first manifold defined between the inner race first half and the output shaft distal end for channeling oil to the cage. The output shaft distal end includes a number A.sub.2 of axial splitline feed groves joined in flow communication with a respective number of radial splitline feed holes therein for channeling oil to the splitline maniflod, and a number B.sub.