Hot combustion gases enter the nozzle of a turbojet engine at 250 kPa, 650°C, and 70 m/s and exit at 80 kPa and 420°C. The mass flow rate is 1.2 kg/s. Assume the heat losses to the surroundings is 90kW and the surroundings is at 27°C. Determine (a) the exit velocity and (b) the decrease in the exergy of the gases. Take k = 1.3 and c, = 1.15 kJkg-°C for the combustion gases. Qtoss = 90kW 250 kPa Combustion gases 80 kPa 650°C 420°C 70 m/s m = 1.2 kg/s m = 1.2 kg/s

Elements Of Electromagnetics
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Author:Sadiku, Matthew N. O.
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Hot combustion gases enter the nozzle of a turbojet engine at 250 kPa, 650°C, and 70 m/s and exit at
80 kPa and 420°C. The mass flow rate is 1.2 kg/s. Assume the heat losses to the surroundings is 90kW
and the surroundings is at 27°C. Determine (a) the exit velocity and (b) the decrease in the exergy of
the gases. Take k = 1.3 and c, = 1.15 kJkg-°C for the combustion gases.
Qtoss = 90kW
250 kPa
Combustion
gases
80 kPa
650°C
420°C
70 m/s
m = 1.2 kg/s
m = 1.2 kg/s
Transcribed Image Text:Hot combustion gases enter the nozzle of a turbojet engine at 250 kPa, 650°C, and 70 m/s and exit at 80 kPa and 420°C. The mass flow rate is 1.2 kg/s. Assume the heat losses to the surroundings is 90kW and the surroundings is at 27°C. Determine (a) the exit velocity and (b) the decrease in the exergy of the gases. Take k = 1.3 and c, = 1.15 kJkg-°C for the combustion gases. Qtoss = 90kW 250 kPa Combustion gases 80 kPa 650°C 420°C 70 m/s m = 1.2 kg/s m = 1.2 kg/s
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