The flame temperature of combustion in a turboshaft engine, as in other types of aircraft engines, refers to the temperature reached during the combustion of fuel in the engine’s combustion chamber. The flame temperature is a crucial parameter influencing the engine’s efficiency, performance, and emissions.
The adiabatic flame temperature Tadiabatic is an estimate of the maximum temperature reached during combustion when no heat is lost to the surroundings. The formula for adiabatic flame temperature is:
Where:
- Tadiabatic: Adiabatic flame temperature (in Kelvin).
- : Inlet air temperature (in Kelvin).
- : Fuel temperature (in Kelvin).
- : Specific heat at constant pressure (in J/(kg·K)).
- : Ratio of specific heats ().
- : Specific gas constant (in J/(kg·K)).