Hybrid-electric aircraft propulsion system and method

A propulsion system for an aircraft, the system comprising:

• an electric generator configured to produce electrical power;
• a compressor configured to selectively produce a flow of compressor air at an air pressure greater than an ambient air pressure;
• an internal combustion (IC) engine configured to selectively intake the flow of compressor air during operation and produce an exhaust gas flow during operation, the IC engine in communication with a mechanical power management device (MPMD);
• a turbine in communication with and configured to power the compressor and the electric generator, wherein the turbine is powered by the exhaust gas flow, the turbine configured to drive a shaft in communication with the electric generator and the compressor;
• the compressor disposed between the turbine and the electric generator, and the MPMD disposed between the electric generator and the compressor;
• an electric power storage unit in communication with the electric generator;
• an electric motor in communication with the MPMD, the electric motor powered by the electrical power produced by the electric generator;
• and
• an electric power management control (EPMC) configured to receive the electrical power from the electric generator and selectively distribute the electrical power to at least one of the electric power storage unit or the electric motor;
• wherein the IC engine and the electric motor are both configured to selectively provide motive force to the MPMD.

An aircraft, comprising:

• a fuselage;
• at least one nacelle;
• a propulsor;
• at least one propulsion system for driving the propulsor, the propulsion system having:
• an electric generator configured to produce electrical power;
• a compressor configured to selectively produce a flow of compressor air at an air pressure greater than an ambient air pressure;
• an internal combustion (IC) engine configured to selectively intake the flow of compressor air during operation and produce an exhaust gas flow during operation, the IC engine in communication with a mechanical power management device (MPMD);
• a turbine in communication with and configured to power the compressor and the electric generator, wherein the turbine is powered by the exhaust gas flow;
• the compressor disposed between the turbine and the electric generator;
• an electric power storage unit in communication with the electric generator;
• an electric motor in communication with the MPMD, the electric motor powered by the electrical power produced by the electric generator;
• and
• an electric power management control (EPMC) configured to receive the electrical power from the electric generator and selectively distribute the electrical power to at least one of the electric power storage unit or the electric motor;
• wherein the IC engine and the electric motor are both configured to selectively provide motive force to the MPMD and the MPMD provides motive force to the propulsor.