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 c_p = 1.15 kJ/kg·°C for the combustion gases.

230 kPa Combustion 70 kPa 627°C gases 450°C 60 m/s

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Thermodynamics An Engineering Approach

ISBN: 9781259822674

9th Edition

Authors: Yunus Cengel, Michael Boles, Mehmet Kanoglu

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Question Posted: Nov 05, 2020 08:01 AM

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Hot combustion gases enter the nozzle of a turbojet engine at 230 kPa, 627C, and 60 m/s

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230 kPa Combustion 70 kPa 627°C gases 450°C 60 m/s

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Hot combustion gases are accelerated in an adiabatic nozzle The exit velocity and the decrease in ...View the full answer

Thermodynamics An Engineering Approach

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