This invention belongs to the field of
aviation propulsion
system technology and discloses a method for operating a
hybrid lift and thrust
system for a low-altitude vertical
takeoff and landing aircraft. The
system includes a low-pressure compressor, a
starter / generator, a high-pressure compressor, a gas
turbine, an adjustable thrust
nozzle, a PEM fuel
cell, an
electric motor, and a lift
propeller. The low-pressure compressor,
starter / generator, high-pressure compressor, and gas
turbine are coaxial. The
compressed air from the low-pressure compressor is divided into two paths. One path of
compressed air enters the high-pressure compressor for further pressurization and then enters the main
combustion chamber, which is connected to the gas
turbine at the rear end. The other path of
compressed air from the low-pressure compressor enters the
cathode inlet of the PEM fuel
cell and the adjustable thrust
nozzle. The PEM fuel
cell supplies power to the electrical
busbar, and the reaction end of the PEM fuel cell is connected to a mixer. The exhaust port of the gas turbine is connected to the mixer, which mixes the
exhaust gas from the gas turbine and the
exhaust gas from the PEM fuel cell before supplying it to the adjustable thrust
nozzle at the rear end to provide thrust. The
starter / generator is connected to the electrical
busbar, which is connected to the
electric motor, and the
motor shaft drives the lift
propeller. This invention can be used in manned and unmanned aircraft that employ rotor
takeoff and landing and thrust
cruise, reducing the number of shafts used, simplifying the
system structure, reducing the demand for H2, and increasing system
operating time.