Aircraft including parallel hybrid gas turbine electric propulsion system

An aircraft comprising:

• at least one gas turbine engine including a core and a supplementary power motor;
• a power distribution system electrically connected to the supplementary power motor, and including an energy storage component configured to provide power to, and receive power from, the supplementary power motor;
• and
• the at least one gas turbine engine is undersized relative to a required thrust during at least one mode of operations.

A method of operating a gas turbine engine comprising:

• providing power to a taxiing system using an electric motor during a taxi mode of operation;
• providing thrust from fan rotation during at least one of a take-off and climb mode of operations, wherein the fan is rotated by a turbine and the electric motor simultaneously;
• and
• providing thrust from fan rotation during a cruise mode of operation, wherein the fan is rotated exclusively by the turbine.