4. An ideal turbojet engine operates on the Brayton cycle. At the inlet of the compressor (at station 2) the stagnation pressure is 100 kPa and the temperature is 250 K. The compressor pressure ratio (P03/P02) is 20. The fuel-air ratio (f) is 0.023 and the heating value of the fuel (QR) is 45,000 kJ/kg fuel. The exhaust nozzle expands the air to a static pressure at the exhaust (P) of 100 kPa. ( 30 pts) (1) Determine the stagnation temperature at compressor exit, T03. (2) Determine the maximum temperature in this engine. (3) Determine the work extracted by the turbine, per unit mass of air. (4) Determine the stagnation pressure and temperature at turbine exit P05 and T05 (5) Determine the stagnation pressure and temperature at nozzle exit P07 and T07.