A four-cylinder, four-stroke, 2.2-L gasoline engine operates on the Otto cycle with a compression ratio of. The air is at 100 kPa and60°C at the beginning of the compression process, and the maximum pressure in the cycle is 8 MPa. The compression and expansionprocesses may be modeled as polytropic with a polytropic constant of 1.3. Using constant specific heats at 82K, determine (a) thetemperature at the end of the expansion process, (b) the net work output and the thermal efficiency, (c) the mean effective pressure, (d)the engine speed for a net power output of 70 kW, and (e) the specific fuel consumption, in g/kWh, defined as the ratio of the mass of thefuel consumed to the net work produced. The air-fuel ratio, defined as the amount of air divided by the amount of fuel intake, is 16.

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Answered: A four-cylinder, four-stroke, 2.2-L…

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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A four-cylinder, four-stroke, 2.2-L gasoline engine operates on the Otto cycle with a compression ratio of 12. The air is at 100 kPa and 60°C at the beginning of the compression process, and the maximum pressure in the cycle is 8 MPa. The compression and expansion processes may be modeled as polytropic with a polytropic constant of 1.3. Take Cy = 0.716 kJ/kg K, C, = 1.0 kJ/kg K. Determine the: 1. temperature at the end of the compression process. 2. Pressure at end of the compression process 3. net work output. 4. thermal efficiency. 5. mean effective pressure.
Air enters the compressor of a gas turbine at 100 kPa and 25°C. Determine the back work rate and thermal efficiency of the Brayton cycle for a pressure ratio of 5 and a maximum temperature of 850°C.
A four-cylinder, four-stroke, 1.6-L gasoline engine operates on the Otto cycle with a compression ratio of 11. The air is at 100 kPa and 37°C at the beginning of the compression process, and the maximum pressure in the cycle is 8 MPa. The compression and expansion processes may be modeled as polytropic with a polytropic constant of 1.3. Using constant specific heats at 850 K, determine the temperature at the end of the expansion process.
In an air standard gas turbine cycle, air at 14.5 psia and 70 F is first compressed to 80 psia in a compressor of 82 percent efficiency. The hot air leaving the combustion chamber at 1250 F is expanded back to 14.5 psia in a turbine of 85 percent efficiency. If a regenerator is inserted into the cycle to heat the air leaving the compressor to 650 F, determine the thermal efficiency of the cycle and the effectiveness of the regenerator.
The initial pressure and temperature of air in an Otto cycle engine during compression are 90 kPa and 12oC. Determine the maximum pressure occurring in the cycle if the initial and final temperature during heat addition process are 350 oC and 1250 oC, and the compression ratio is 6.
In an Otto cycle engine, air at 1 bar and 50°C is compressed until the pressure reaches 650 KPa. Heat is added during the constant volume process at a rate of 500 kJ/kg. Determine the compression ratio of the engine, the temperature at the end of compression and at the end of heat addition. Also determine the maximum possible compression ratio for this cycle. Take cp = 1.0 kJ/kg-K, cv = 0.706kJ/kg-K.
An ideal diesel engine has a compression ratio of 20 and uses air as the working fluid. The state of air at the beginning of the compression process is 95 kPa and 20°C. If the maximum temperature in the cycle is not to exceed 2200 K, determine the net work of the system as a function of compression ratio, r.
A four-cylinder, four-stroke, 1.6-L gasoline engine operates on the Otto cycle with a compression ratio of 11. The air is at 100 kPa and 37°C at the beginning of the compression process, and the maximum pressure in the cycle is 8 MPa. The compression and expansion processes may be modeled as polytropic with a polytropic constant of 1.3. Using constant specific heats at 850 K, determine the mean effective pressure.\
1.A piston-cylinder device contains air at 427 degrees and 134kPa. A pressure increase of 1.378kPa was recorded after the air was compressed isentropically with minimum work input of 1.422KJ. Assuming air has constant specific heats evaluated at given temperature. Determine the mass of air in the device. 2. Air is used as the working fluid in a simple ideal brayton cycle that has a pressure ratio of 12, a compressor inlet temperature of 300k, and a turbine inlet temperature of 1000k. Determine the required mass flow rate in (kg/s) of air for a net power output of 70MW, assuming both the compressor and the turbine have an isentropic efficiency of 100%. Assume constant specific heats at room temperature
The temperature of air at the beginning of compression in an Otto cycle is 310 K and maximum temperature in the cycle is 2200 K. If the pressure at the end of adiabatic compression is 15 times that at the start, determine the compression ratio, thermal efficiency, and work done. Take k for air = 1.4.
A spark-ignition engine has a compression ratio of 10, an isentropic compression efficiency of 85 percent, and an isentropic expansion efficiency of 90 percent. At the beginning of the compression, the air in the cylinder is at 13 psia and 60°F. The maximum gas temperature is found to be 2300°F by measurement. Determine the heat supplied per unit mass, the thermal efficiency, and the mean effective pressure of this engine when modeled with the Otto cycle. Use constant specific heats at room temperature. The properties of air at room temperature are R = 0.3704 psia·ft3/lbm·R, cp = 0.240 Btu/lbm·R, cv = 0.171 Btu/lbm·R, and k = 1.4. Question: The heat supplied per unit mass is ___________.Btu/lbm. The thermal efficiency is_________________%. The mean effective pressure is________________.psia.
Consider a two stage compression and two stage expansion in an ideal gas-turbine cycle. The air enters each stage of the compressor at 350 K and each stage of the turbine at 1240 K. The pressure ratio across each stage of the compressor and turbine is 3.5. Assuming an efficiency of 82 percent for each compressor stage and an efficiency of 88 percent for each turbine stage. Determine the thermal efficiency of the cycle, assuming (a) no regenerator is used and (b) a regenerator with 85 percent effectiveness is used.

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