Aircraft hybrid motive power source system and method for controlling same

An aircraft hybrid motive power source system comprising:

• a gas turbine engine mounted on an aircraft and including a low pressure shaft and a high pressure shaft as rotary shafts;
• a first motor generator drivingly connected to the high pressure shaft;
• a second motor generator drivingly connected to the low pressure shaft;
• a fuel cell to which a fuel gas and an oxidant gas are supplied;
• a heat exchanger configured to heat a discharged object of the fuel cell by heat exchange between an exhaust gas from the gas turbine engine and the discharged object of the fuel cell;
• a turbocharger configured to compress and supply the oxidant gas to the fuel cell by being supplied with the discharged object of the fuel cell heated by the heat exchanger;
• and
• a controller configured to supply an electric power of the fuel cell obtained by a supply of the fuel gas to one of the first motor generator and the second motor generator, based on at least one of information indicating an operating status of the gas turbine engine and an electric power demand of the aircraft.

A method for controlling an aircraft hybrid motive power source system comprises:

• generating a fuel gas for a fuel cell from a raw material by heating using an exhaust gas from a gas turbine engine which is mounted on an aircraft and includes a low pressure shaft and a high pressure shaft as rotary shafts;
• supplying the fuel gas to the fuel cell;
• and
• supplying an electric power of the fuel cell obtained by a supply of the fuel gas to one of a first motor generator drivingly connected to the high pressure shaft and a second motor generator drivingly connected to the low pressure shaft, based on at least one of information indicating an operating status of the gas turbine engine and an electric power demand of the aircraft.

A method for controlling an aircraft hybrid motive power source system comprising:

• pressurizing a discharged object of a fuel cell by heating using heat exchange between the discharged object of the fuel cell and an exhaust gas from a gas turbine engine which is mounted on an aircraft and includes a low pressure shaft and a high pressure shaft as rotary shafts;
• supplying the pressurized discharged object of the fuel cell to a turbine of a turbocharger;
• supplying a fuel gas discharged from a compressor of the turbocharger to the fuel cell;
• and
• supplying an electric power of the fuel cell obtained by a supply of the fuel gas to one of a first motor generator drivingly connected to the high pressure shaft and a second motor generator drivingly connected to the low pressure shaft, based on at least one of information indicating an operating status of the gas turbine engine and an electric power demand of the aircraft.