A diesel engine operating on the air- standard diesel cycle has six cylinders of 100 mm bore and 120 mm stroke. The engine speed is 1800 r.p.m. At the beginning of compression the pressure and temperature of air are 103 bar and 35 °C, respectively. If the clearance volume is 1/8th of the stroke volume, calculate (i) the pressure and temperature at the salient points of the cycle; (ii) the compression ratio; (iii) the efficiency of the cycle; (iv) the power output if the air is heated to 1500 °C Assume Cp and C, of air to be 1.004 and 0-717 kJ/kgK, respectively.

Elements Of Electromagnetics
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(b) A diesel engine operating on the air-
standard diesel cycle has six cylinders
of 100 mm bore and 120 mm stroke.
The engine speed is 1800 r.p.m. At the
beginning of compression the pressure
and temperature of air are 1-03 bar and
35 °C, respectively. If the clearance
volume is 1/8th of the stroke volume,
calculate-
(i) the pressure and temperature at
the salient points of the cycle;
(i) the compression ratio;
(iii) the efficiency of the cycle;
(iv) the power output if the air is heated
to 1500 °C
Assume C, and C, of air to be 1-004
and 0:717 kJ/kgK, respectively.
Transcribed Image Text:(b) A diesel engine operating on the air- standard diesel cycle has six cylinders of 100 mm bore and 120 mm stroke. The engine speed is 1800 r.p.m. At the beginning of compression the pressure and temperature of air are 1-03 bar and 35 °C, respectively. If the clearance volume is 1/8th of the stroke volume, calculate- (i) the pressure and temperature at the salient points of the cycle; (i) the compression ratio; (iii) the efficiency of the cycle; (iv) the power output if the air is heated to 1500 °C Assume C, and C, of air to be 1-004 and 0:717 kJ/kgK, respectively.
A consuming air at
A jet propelled plane
the rate of 18-2 kg/s is to fly at a Mach
number 0-6 at an altitude of 4500 m
= 0-55 bar and T. = 255 K). The
diffuser which has a pressure coefficient
of 0-9, decreases the flow to a negligible
velocity. The compressor pressure ratio
is 5 and maximum temperature in the
%3D
combustion chamber is 1273 K. After
expanding in the turbine, the gases
continue to expand in the nozzle to a
pressure of 0-69 bar. The isentropic
efficiencies of compressor, turbine and
are 0-81, 0-85 and 0:915
respectively. The heating value of the
kJ/kg. Assuming
Cpg = 1-147
1-33,
nozzle
fuel is
45870
C, = 1-005 kJ/kgK,
kJ/kgK., Yair =
1.4,
Ygas
calculate the–
(9 power input to the compressor;
(i) power output of the turbine;
(üi) fuel-air ratio;
fiv} thrust provided by the engine;
(v) thrust power developed.
Transcribed Image Text:A consuming air at A jet propelled plane the rate of 18-2 kg/s is to fly at a Mach number 0-6 at an altitude of 4500 m = 0-55 bar and T. = 255 K). The diffuser which has a pressure coefficient of 0-9, decreases the flow to a negligible velocity. The compressor pressure ratio is 5 and maximum temperature in the %3D combustion chamber is 1273 K. After expanding in the turbine, the gases continue to expand in the nozzle to a pressure of 0-69 bar. The isentropic efficiencies of compressor, turbine and are 0-81, 0-85 and 0:915 respectively. The heating value of the kJ/kg. Assuming Cpg = 1-147 1-33, nozzle fuel is 45870 C, = 1-005 kJ/kgK, kJ/kgK., Yair = 1.4, Ygas calculate the– (9 power input to the compressor; (i) power output of the turbine; (üi) fuel-air ratio; fiv} thrust provided by the engine; (v) thrust power developed.
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