A gas turbine engine assembly comprising: a gas turbine engine comprising a rotor assembly having an axis of rotation, and one or more power shafts configured to rotate about the axis of rotation; a first fan coupled to said one or more power shafts; a second fan coupled to said one or more power shafts coaxially with said first fan and said gas turbine engine, said second fan axially displaced forward of said first fan; a first fan duct comprising a first inlet opening and a first outlet opening, said first fan duct configured to direct a first stream of air to said first fan, said first outlet opening configured to direct the first stream of air axially aftward in a direction of the axis of rotation; a second fan duct comprising a second inlet opening and a second outlet opening, said second fan duct configured to direct a second stream of air to said second fan, said second outlet opening configured to direct the second stream of air axially aftward in a direction of the axis of rotation, wherein the second stream of air being separate from the first stream of air; and an exhaust duct configured to direct a stream of exhaust gases of said gas turbine engine in a direction of the axis of rotation; wherein: said second inlet opening is axisymmetric; said first inlet opening is axially and radially offset and non-concentric with respect to said second inlet opening to accommodate the second stream of air out from the second fan being channeled around first inlet opening; and the second outlet opening is configured to route the second stream of air out from the second fan around the first fan and the first fan duct. a gas turbine engine comprising a rotor assembly having an axis of rotation, and one or more power shafts configured to rotate about the axis of rotation; a first fan coupled to said one or more power shafts; a second fan coupled to said one or more power shafts coaxially with said first fan and said gas turbine engine, said second fan axially displaced forward of said first fan; a first fan duct comprising a first inlet opening and a first outlet opening, said first fan duct configured to direct a first stream of air to said first fan, said first outlet opening configured to direct the first stream of air axially aftward in a direction of the axis of rotation; a second fan duct comprising a second inlet opening and a second outlet opening, said second fan duct configured to direct a second stream of air to said second fan, said second outlet opening configured to direct the second stream of air axially aftward in a direction of the axis of rotation, wherein the second stream of air being separate from the first stream of air; and an exhaust duct configured to direct a stream of exhaust gases of said gas turbine engine in a direction of the axis of rotation; wherein: said second inlet opening is axisymmetric; said first inlet opening is axially and radially offset and non-concentric with respect to said second inlet opening to accommodate the second stream of air out from the second fan being channeled around first inlet opening; and the second outlet opening is configured to route the second stream of air out from the second fan around the first fan and the first fan duct. said second inlet opening is axisymmetric; said first inlet opening is axially and radially offset and non-concentric with respect to said second inlet opening to accommodate the second stream of air out from the second fan being channeled around first inlet opening; and the second outlet opening is configured to route the second stream of air out from the second fan around the first fan and the first fan duct.