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 . <EOS>