1 A jet propelled plane consuming air at a rate of 18.2 kg/sec is to fly at Mach. No. 0.6 at an altitude of 4500 meter. (P 0.55 bar, T 255° K). The diffuser which has a pressure coefficient 0.9, decreases the flow to a negligible velocity. The compressor pressure ratio is 5 and inaximum temperature in the combustion ehamber is 1273 K. After expansing in the turbine, the gases continue to expand in the nozzle to a pressure of 0.69 bar. The isentropic efficiency of compressor is 0.81 and of turbine 0.95 and of nozzle 0.915. The heating value of the fuel if 45870 kJ/kg. Assuming C, = 1.005 kJ/kg=K, C, = 1.147 kJ/kg-K, Y,ir = 1.4, Yu. 1.33. Calculate %3D %3D %3D

Elements Of Electromagnetics
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Q.21 A jet propelled plane consuming air at a rate of 18.2 kg/sec is to fly at Mach. No. 0.6
at an altitude of 4500 meter. (P 0.55 bar, T 255° K). The diffuser which has a
pressure coefficient 0.9, decreases the flow to a negligible velocity. The compressor
pressure ratio is 5 and inaximum temperature in the combustion ehamber is
1273 K. After expansing in the turbine, the gases continue to expand in the nozzle to
a pressure of 0.69 bar. The isentropic efficiency of compressor is 0.81 and of turbine
0.95 and of nozzle 0.915. The heating value of the fuel if 45870 kJ/kg. Assuming
%3D
C, = 1.005 kJ/kg=K, C, = 1.147 kJ/kg-K, Y, = 1.4, y.. = 1.33. Calculate
%3D
gas
) Power input to the compresSor.
(11) Power output of turbine.
(iii) The fuel-air ratio.
(iv) The thrust provided by the engine.
(v) The thrust power developed.
Transcribed Image Text:Q.21 A jet propelled plane consuming air at a rate of 18.2 kg/sec is to fly at Mach. No. 0.6 at an altitude of 4500 meter. (P 0.55 bar, T 255° K). The diffuser which has a pressure coefficient 0.9, decreases the flow to a negligible velocity. The compressor pressure ratio is 5 and inaximum temperature in the combustion ehamber is 1273 K. After expansing in the turbine, the gases continue to expand in the nozzle to a pressure of 0.69 bar. The isentropic efficiency of compressor is 0.81 and of turbine 0.95 and of nozzle 0.915. The heating value of the fuel if 45870 kJ/kg. Assuming %3D C, = 1.005 kJ/kg=K, C, = 1.147 kJ/kg-K, Y, = 1.4, y.. = 1.33. Calculate %3D gas ) Power input to the compresSor. (11) Power output of turbine. (iii) The fuel-air ratio. (iv) The thrust provided by the engine. (v) The thrust power developed.
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