INTEGRATED AIRCRAFT PROPULSION SYSTEM
An integrated propulsion system comprising at least two gas turbine engines, at least one fan, and a transmission assembly coupling the at least two gas turbine engines to the at least one fan wherein the at least two gas turbine engines are disposed within a main body of an airframe comprising the main body and a pair of wings, and wherein the number of gas turbine engines is greater than the number of fans.
1 . An integrated propulsion system comprising:
at least two gas turbine engines;
at least one fan; and
a transmission assembly coupling said at least two gas turbine engines to said at least one fan;
wherein said at least two gas turbine engines are disposed within a main body of an airframe comprising said main body and a pair of wings, and wherein the number of gas turbine engines is greater than the number of fans.
2 . The system of claim 1 , each of said gas turbine engines having an exclusive engine air flow duct comprising an engine inlet and an engine exhaust.
3 . The system of claim 2 , said fan having an exclusive fan air flow duct comprising a fan inlet and a fan exhaust.
4 . The system of claim 3 , wherein said fan exhaust comprises a fan exhaust duct and a thrust vectoring mechanism.
5 . The system of claim 4 , wherein each of said engine inlet and said fan inlet comprise an inlet duct extending radially outward from said main body of the airframe.
6 . The system of claim 5 , wherein said at least one fan is mounted within the main body of the airframe.
7 . The system of claim 1 , wherein said transmission assembly comprises a clutch mechanism.
8 . The system of claim 7 , wherein output power of said at least two gas turbine engines is distributed to said at least one fan when said clutch mechanism is engaged.
9 . The system of claim 1 , said fan having a fan exhaust duct and each of said gas turbine engines having an engine inlet duct connected to said fan exhaust duct.
10 . An integrated propulsion system consisting of:
a first gas turbine engine and a second gas turbine engine;
a fan; and
wherein a transmission assembly couples said first gas turbine engine and said second gas turbine engine to said fan.
11 . The system of claim 10 wherein said first gas turbine engine, said second gas turbine engine, and said fan each have an exclusive air flow duct.
12 . The system of claim 11 wherein the air flow duct of said fan comprises an inlet duct, exhaust duct, and thrust vectoring mechanism.
13 . The system of claim 10 wherein each of said first gas turbine engine, said second gas turbine engine, and said fan have an axis of rotation which is parallel to a central axis of a main body of an airframe.
14 . The system of claim 10 wherein said first gas turbine engine and said second gas turbine engine an axis of rotation which is disposed at an angle to a central axis of a main body of an airframe.
15 . The system of claim 10 wherein said fan has an axis of rotation normal to a central axis of a main body of an airframe.
16 . The system of claim 10 wherein said transmission assembly comprises a gearbox.
17 . The system of claim 10 wherein said transmission assembly comprises a clutch.
18 . A method of reducing drag in a turbofan aircraft comprising:
reducing the required cross-sectional area of an aircraft body and reducing the total weight of the aircraft propulsion system by:
disposing a first gas turbine engine on a first side of said aircraft body and a second gas turbine engine on a second side of said aircraft body;
disposing a fan unit on said aircraft body, said fan unit coupled to said first gas turbine engine and said second gas turbine engine by a transmission assembly comprising a clutch and more than one rotating linkages;
venting each of said first gas turbine engine and said second gas turbine engine via a respective exclusive engine duct comprising an engine inlet duct and an engine exhaust duct; and
venting said fan unit via an exclusive fan duct comprising a fan inlet duct and a fan exhaust duct.
19 . The method of claim 18 wherein said fan exhaust duct includes a thrust vectoring mechanism.
20 . The method of claim 19 wherein each of said first gas turbine engine, said second gas turbine engine, and said fan unit have an axis of rotation which is parallel to a central axis of a main body of an airframe.