Aircraft turbomachine with reducer

A turbomachine with an axis of rotation, comprising:

• a single ducted fan comprising a first shaft carrying blades and driven in rotation by a second shaft via a speed reducer, said second shaft being driven in rotation by a third shaft of a turbine, said first, second and third shafts sharing the axis of rotation, said first shaft being guided in rotation with respect to a fixed structure of the turbomachine via a first bearing and a second bearing located upstream of said speed reducer, wherein the second shaft is guided in rotation with respect to the first shaft via a third rolling bearing located upstream of said speed reducer, said third rolling bearing comprising an outer ring housed in said first shaft, an inner ring attached to said second shaft, and rolling elements disposed between said inner and outer rings.