Hot combustion gases enter the nozzle of a turbojet engine at 260 kPa, 747 deg C, and 80 m s and exit at 70 kPa and 500 deg C Assuming the nozzle to be adiabatic and the surroundings to be at 20 deg C, determine (a) The exit velocity and (b) The decrease in the energy of the gases Take k 1 3 and cp 1 15 kJ kg cent deg C for the combustion gases 260 kPa 747C 80 m s Combustion gases 70kPa 500 C

Question: Hot combustion gases enter the nozzle of a turbojet engine at 260 kPa, 747°C, and 80 m/s and exit at 70 kPa and 500°C. Assuming

Hot combustion gases enter the nozzle of a turbojet engine at 260 kPa, 747°C, and 80 m/s and exit at 70 kPa and 500°C. Assuming the nozzle to be adiabatic and the surroundings to be at 20°C, determine
(a) The exit velocity and
(b) The decrease in the energy of the gases. Take k = 1.3 and cp = 1.15 kJ/kg €¢ °C for the combustion gases.

Hot combustion gases enter the nozzle

260 kPa 747C--+ 80 m/s Combustion gases 70kPa 500 C

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