Full Flow Staged Combustion (FFSC) engines are a type of rocket engine that uses a staged combustion cycle where both the fuel and oxidizer are fully burned before entering the combustion chamber. These engines are known for their high efficiency and performance.
In a Full Flow Staged Combustion engine, the mass flow rate of exhaust gases is influenced by the efficiency of the combustion process in both the fuel and oxidizer stages. The exhaust velocity is determined by the combustion characteristics, and the pressure of the exhaust gases is influenced by the combustion and expansion processes.
The thrust equation for a turbojet engine using control volume analysis is expressed as:
where,
- is the thrust force,
- ṁe is the mass flow rate of exhaust gases in kilograms per second (kg/s).
- is the Exhaust velocity at the nozzle exit in meters per second (m/s).
- ṁ0 is the mass flow rate of inlet gases in kilograms per second (kg/s).
- is the Exhaust velocity at the nozzle Inlet in meters per second (m/s).
- is the Pressure at the nozzle exit in pascals (Pa).
- is the Pressure at the nozzle inlet in pascals (Pa).
- is the Area of the nozzle exit in square meters (m²).