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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Transcribed Image Text: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.
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