Metal-air battery combustion engine hybrid system

An engine for a hybrid propulsion system, comprising:

• a metal-air battery pack;
• a generator;
• a combustion chamber;
• a propulsion power bus;
• a turbine;
• a compressor operatively coupled to the turbine and that supplies compressed air to the metal-air battery pack;
• and
• a heat exchanger,
• wherein the heat exchanger utilizes exhaust heat from the engine to heat air provided to the metal-air battery pack,
• wherein the metal-air battery pack incorporates management and safety features to manage a temperature, a voltage, a current, and a pressure of the metal-air battery pack, balance battery cells, manage thermal conditions, and communicate with other aircraft components,
• wherein the generator converts mechanical energy from the turbine into electrical energy to power an aircraft's electrical systems, and
• wherein the propulsion power bus is configured to distribute energy from the metal-air battery pack and the combustion chamber, regulate power of the engine, manage an electric load of the engine, monitor electrical system faults or abnormalities, manage heat generated within the engine, and distribute a power supply to propulsion-related components.

An engine for a hybrid propulsion system, comprising:

• a metal-air battery pack comprising battery cells, wherein an anode of the battery cells includes Li, an electrolyte of the battery cells includes one of organic electrolytes, ionic liquids, alkaline electrolytes, or ceramic electrolytes, a cathode of the battery cells includes oxygen, and a cathode support of the battery cells is porous carbon, the metal-air battery pack further comprising an internal layer formed of a material capable of withstanding temperatures greater than 250° C. and having a plurality of openings ranging from 200 micrometers to 1 millimeter in size and an outer protective shell surrounding the internal layer;
• a generator;
• a combustion chamber;
• a propulsion power bus;
• a turbine;
• a compressor;
• and
• a heat exchanger,
• wherein the heat exchanger utilizes exhaust heat from the engine to heat air provided to the metal-air battery pack,
• wherein the generator converts mechanical energy from the turbine into electrical energy for powering an aircraft's electrical systems, and
• wherein the propulsion power bus is configured to distribute energy from the metal-air battery pack and the combustion chamber to propulsion-related components.