The invention belongs to the technical field of
aviation second power systems, and provides a dual-fuel aircraft combined power
system which comprises an
air compressor, a heat regenerator, a main
combustion chamber, a gas
turbine, a PEM fuel
cell and a starting / power generator, the starting / power generator, the
air compressor and the gas
turbine are of a coaxial structure, air compressed by the
air compressor is divided into two paths, and the two paths are communicated with each other. One path of
compressed air enters the main
combustion chamber through the cold end of the heat regenerator, and the rear end of the main
combustion chamber is connected with a gas
turbine; the other path of
compressed air enters the PEM fuel
cell, the PEM fuel
cell supplies power to the
electric bus bar, and the reaction rear end of the PEM fuel cell is connected with the gas turbine; the gas turbine is jointly driven by the main
combustion chamber and the PEM fuel cell, and an exhaust channel of the gas turbine passes through the hot end of the heat regenerator. The fuel cell power generation unit composed of the H2
fuel tank, the PEM fuel cell and the secondary
combustion chamber is used for receiving high-temperature compressed gas from the
gas compressor, the high-temperature and high-pressure gas of the
gas compressor can conduct hot air purging on
cold start of the fuel cell, low-temperature start of the PEM fuel cell is helped, and the fuel cell power generation efficiency is improved. And meanwhile, high-temperature and high-pressure air at the outlet of the compressor is humidified and cooled through cooling of
liquid water, and the requirement for
system accessories is simplified.