초록 ▼

A gas turbine engine has a core engine incorporating a core engine turbine. A fan rotor is driven by a fan rotor turbine. The fan rotor turbine is in the path of gases downstream from the core engine turbine. A bypass door is moveable from a closed position at which the gases from the core engine tu

A gas turbine engine has a core engine incorporating a core engine turbine. A fan rotor is driven by a fan rotor turbine. The fan rotor turbine is in the path of gases downstream from the core engine turbine. A bypass door is moveable from a closed position at which the gases from the core engine turbine pass over the fan rotor turbine, and moveable to a bypass position at which the gases are directed away from the fan rotor turbine. An aircraft is also disclosed.

대표청구항 ▼

1. An aircraft comprising: an aircraft body mounting a gas turbine engine, the gas turbine engine including a core engine incorporating a single core engine turbine, a pair of fan rotors each being driven by a fan rotor turbine, and said fan rotor turbines being in the path of gases downstream from

1. An aircraft comprising: an aircraft body mounting a gas turbine engine, the gas turbine engine including a core engine incorporating a single core engine turbine, a pair of fan rotors each being driven by a fan rotor turbine, and said fan rotor turbines being in the path of gases downstream from said single core engine turbine, and a bypass door, said bypass door being moveable from a closed position at which the gases from the core engine turbine pass over said fan rotor turbine, and moveable to a bypass position at which said gases are directed away from said fan rotor turbine;wherein said bypass door is driven to said open position when an aircraft receiving said gas turbine engine is at an airport gate;said core engine turbine drives a generator to generate electricity;said core engine also includes a compressor and a combustor;said aircraft body including a tail, and said gas turbine engine mounted on said tail; andthe generation of electricity at an airport gate allows the replacement of an auxiliary power unit. 2. The aircraft as set forth in claim 1, wherein said fan rotor turbine is positioned at a radially outer location on said fan rotor. 3. The aircraft as set forth in claim 2, wherein a manifold receives the gases downstream of said core engine turbine and delivers the gases across both of said fan rotor turbines. 4. The aircraft as set forth in claim 1, wherein a rotational axis of each said fan rotor, and said core engine turbine all being offset relative to each other. 5. The aircraft as set forth in claim 1, wherein an actuator drives the bypass door to an open position.