Air passes from a fan exit into a turbofan engine core at the rate of 62 kg/s. The air then passes through a gas generator compressor, combustion chamber and turbine and then through a low pressure turbine which drives the fan on a separate shaft. This figure shows the arrangement and station numbers. the fibe Exit pressure 160.054 kPa Exit temperature 332.22K Power required 11.540 MW Pressure ratio 19.5 Isentropic efficiency 88.0% Pressure loss 4% of c-c inlet P Exit gas temperature 1620K Combustion efficiency 98.8% Fuel calorific value 43300 kJ/kg Isentropic efficiency 87.0% Mechanical efficiency 90.5 The engine component details are listed below: Fan Gas generator compressor Combustion chamber (c-c) Gas generator turbine LP turbine (driving fan) Isentropic efficiency 83.0%

Air passes from a fan exit into a turbofan engine core at the rate of 62 kg/s. The air then passes through a gas generator compressor, combustion chamber and turbine and then through a low pressure turbine which drives the fan on a separate shaft. This figure shows the arrangement and station numbers. the fibe Exit pressure 160.054 kPa Exit temperature 332.22K Power required 11.540 MW Pressure ratio 19.5 Isentropic efficiency 88.0% Pressure loss 4% of c-c inlet P Exit gas temperature 1620K Combustion efficiency 98.8% Fuel calorific value 43300 kJ/kg Isentropic efficiency 87.0% Mechanical efficiency 90.5 The engine component details are listed below: Fan Gas generator compressor Combustion chamber (c-c) Gas generator turbine LP turbine (driving fan) Isentropic efficiency 83.0%

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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Question

Air passes from a fan exit into a turbofan engine core at the rate of 62 kg/s. The air then passes
through a gas generator compressor, combustion chamber and turbine and then through a low pressure
turbine which drives the fan on a separate shaft. This figure shows the arrangement and station
numbers.
M
The engine component details are listed below:
Fan
Exit pressure 160.054 kPa
Exit temperature 332.22K
Power required 11.540 MW
Gas generator compressor
Pressure ratio 19.5
Isentropic efficiency 88.0%
Pressure loss 4% of c-c inlet P
Combustion chamber (c-c)
Exit gas temperature 1620K
Combustion efficiency 98.8%
Fuel calorific value 43300 kJ/kg
Isentropic efficiency 87.0%
Gas generator turbine
Mechanical efficiency 90.5
LP turbine (driving fan)
Isentropic efficiency 83.0%

Pressure ratio 19.5
Isentropic efficiency 88.0%
Pressure loss 4% of c-c inlet P
Isentropic efficiency 87.0%
Gas generator compressor
Combustion chamber (c-c)
Exit gas temperature 1620K
Combustion efficiency 98.8%
Fuel calorific value 43300 kJ/kg
Gas generator turbine
Mechanical efficiency 90.5
LP turbine (driving fan)
Isentropic efficiency 83.0%
Mechanical efficiency 99.0%
Core Flow Propelling nozzle
Isentropic efficiency 96.0%
The following assumptions may be made:
For air: y = 1.4, Cp = 1.005 kJ/kg.K
For combustion products: y = 1.333, Cp = 1.148 kJ/kg.K
The mass flow of fuel added in the combustion chamber may be ignored when calculating
turbine performance.
No external extraction of bleed air or shaft power.
Calculate the shaft power that must be extracted from the combustion gases by the
gas generator turbine.
Give your answer in megawatts (MW).

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