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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.

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
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
Section: Chapter Questions
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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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