Hot combustion gases enter the nozzle of a turbojet engine at 230 kPa, 627C, and 60 m/s
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Hot combustion gases enter the nozzle of a turbojet engine at 230 kPa, 627°C, and 60 m/s and exit at 70 kPa and 450°C. Assuming the nozzle to be adiabatic and the surroundings to be at 20°C, determine
(a) The exit velocity
(b) The decrease in the exergy of the gases. Take k = 1.3 and cp = 1.15 kJ/kg·°C for the combustion gases.
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Related Book For
Thermodynamics An Engineering Approach
ISBN: 9781259822674
9th Edition
Authors: Yunus Cengel, Michael Boles, Mehmet Kanoglu
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