A schematic representation of a jet engine is presented in Figure. Flow of air at 50 kPa and -16 °C enters compressor (state 1 in figure) and then it leaves from compressor at 2850 kPa and 560 °C (state 2 in figure). After combustion, air flow enters the turbine at 1250 °C and 2750 kPa (state 3 in figure) and then it leaves from the turbine at 325 kPa and 650 °C (state 4 in figure). Finally, air flow leaves from the nozzle at 50 kPa and 420 °C (state 5 in figure). Assume there is no heat transfer and neglect kinetic energy except out of the nozzle. determine; a-) The compressor specific work (work per unit mass) b-) The turbine specific work (work per unit mass) c-) The velocity of air leaving the nozzle. Compressor Combustors Turbine Air Product gases out a 3 5 Diffuser Nozzle 2. in

A schematic representation of a jet engine is presented in Figure. Flow of air at 50 kPa and -16 °C enters compressor (state 1 in figure) and then it leaves from compressor at 2850 kPa and 560 °C (state 2 in figure). After combustion, air flow enters the turbine at 1250 °C and 2750 kPa (state 3 in figure) and then it leaves from the turbine at 325 kPa and 650 °C (state 4 in figure). Finally, air flow leaves from the nozzle at 50 kPa and 420 °C (state 5 in figure). Assume there is no heat transfer and neglect kinetic energy except out of the nozzle. determine; a-) The compressor specific work (work per unit mass) b-) The turbine specific work (work per unit mass) c-) The velocity of air leaving the nozzle. Compressor Combustors Turbine Air Product gases out a 3 5 Diffuser Nozzle 2. in

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

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Question

Thermodynamics question

A schematic representation of a jet engine is presented in Figure. Flow of air at 50 kPa and
-16 °C enters compressor (state 1 in figure) and then it leaves from compressor at 2850 kPa
and 560 °C (state 2 in figure). After combustion, air flow enters the turbine at 1250 °C and
2750 kPa (state 3 in figure) and then it leaves from the turbine at 325 kPa and 650 °C (state 4
in figure). Finally, air flow leaves from the nozzle at 50 kPa and 420 °C (state 5 in figure).
Assume there is no heat transfer and neglect kinetic energy except out of the nozzle.
determine;
a-) The compressor specific work (work per unit mass)
b-) The turbine specific work (work per unit mass)
c-) The velocity of air leaving the nozzle.
Compressor
Combustors
Turbine
Air
Product
in
gases out
a
2
3
4
Diffuser
Nozzle

Science that deals with the amount of energy transferred from one equilibrium state to another equilibrium state.

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