In a turbojet, air is compressed in an axial compressor at inlet conditions of 1 bar and 10°C 3.5 bar. The final temperature is 1.25 times that for isentropic compression. The temperature of gases at inlet to turbine is 480°C. The exhaust gases from turbine are expanded in a velocity of approach is negligible and expansion may be taken to be isentropic in both turbine and nozzle. Value of gas constant R'and index r are same for air and flue gases. Determine, (a) Power required to drive the compressor per kg or air/sec (b) Air-fuel ratio if the calorific value of fuel is 42,000 kJ/kg (c) Thrust developed /kg of air fsec.

In a turbojet, air is compressed in an axial compressor at inlet conditions of 1 bar and 10°C 3.5 bar. The final temperature is 1.25 times that for isentropic compression. The temperature of gases at inlet to turbine is 480°C. The exhaust gases from turbine are expanded in a velocity of approach is negligible and expansion may be taken to be isentropic in both turbine and nozzle. Value of gas constant R'and index r are same for air and flue gases. Determine, (a) Power required to drive the compressor per kg or air/sec (b) Air-fuel ratio if the calorific value of fuel is 42,000 kJ/kg (c) Thrust developed /kg of air fsec.

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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