Two-shaft turbofan engines are powering a regional jet. Assume perfect gas with specific heat at constant pressure for air, Cp(air) is 1.005 kJ/(kg K), and the specific heat at constant pressure for combustion gas, Cp(comb) is 1.147 kJ/(kg K). You may assume the specific gas constant, R is 287.05 J/(kg K) for air as well as for combustion gas.
(a) The Fuel-to-Air Ratio (FAR) of the engine’s burner is 0.025. If the burnet inlet temperature is at 800 K, find the burner exit temperature. Use the FAR chart.
(b) The high pressure (HP) turbine has 6 (six) stages. The pressure drop ratio of each stage is 0.8 with polytropic efficiency of 90%. Calculate the overall HP turbine temperature drop ratio and the HP turbine exit temperature.