Flame Temperature of Combustion in an Turboprop Engine Calculator

The flame temperature of combustion in a turbofan engine, like 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 critical parameter influencing the engine’s efficiency, performance, and emissions.

The adiabatic flame temperature T_adiabatic 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:

• T_adiabatic: Adiabatic flame temperature (in Kelvin).
• T_inlet​: Inlet air temperature (in Kelvin).
• T_fuel​: Fuel temperature (in Kelvin).
• C_p​: Specific heat at constant pressure (in J/(kg·K)).
• $\gamma$: Ratio of specific heats (C_p​/C_v​).
• $R$: Specific gas constant (in J/(kg·K)).