Effervescent atomizing structure and method of operation for rotating detonation propulsion system

A method of operating a propulsion system at a constant detonation cell size for a propulsion system comprising a rotating detonation combustion (RDC) system with effervescent atomization of a liquid fuel, the method comprising:

• flowing the liquid fuel through a fuel injection port of a nozzle assembly of the RDC system;
• flowing a gaseous fuel through the fuel injection port of the nozzle assembly volumetrically proportional to the liquid fuel;
• producing a gaseous fuel-liquid fuel mixture at the fuel injection port by mixing the flow of the gaseous fuel and the flow of the liquid fuel;
• flowing an oxidizer through a nozzle flowpath of the RDC system;
• producing an oxidizer-gaseous fuel-liquid fuel mixture by mixing the gaseous fuel-liquid fuel mixture and the flow of the oxidizer within the nozzle flowpath;
• igniting the oxidizer-gaseous fuel-liquid fuel mixture within a combustion chamber of the RDC system;
• and
• adjusting a volumetric flow of the gaseous fuel relative to the liquid fuel based at least on a commanded operating condition of the propulsion system.

A method of effervescent atomization of a liquid fuel for a rotating detonation combustor (RDC) system for a propulsion system, the method comprising:

• flowing the liquid fuel through a fuel injection port of a nozzle assembly of the RDC system;
• flowing a gas through the fuel injection port of the nozzle assembly volumetrically proportional to the liquid fuel, wherein the gas is an inert gas;
• producing a gas-liquid fuel mixture at the fuel injection port by mixing the flow of the gas and the flow of the liquid fuel;
• flowing an oxidizer through a nozzle flowpath of the RDC system;
• producing an oxidizer-gas-liquid fuel mixture by mixing the gas-liquid fuel mixture and the flow of the oxidizer within the nozzle flowpath;
• igniting the oxidizer-gas-liquid fuel mixture within a combustion chamber of the RDC system;
• and
• adjusting a volumetric flow of the gas relative to the liquid fuel based at least on a commanded operating condition of the propulsion system.