Please explain 7 onlyUsing Chatgpt is prohibited Otherwise I will report 6. Air enters the compressor of a cold-air-standard Brayton cycle at 200 kPa and 300 K, with avolumetric flow rate of 5 m³/s. The compressor pressure ratio is 15. The turbine inlettemperature is 1600 K. There is no pressure drop between the turbine and compressor on eitherside. Determine (a) the work required by the compressor, (b) the work generated by the turbine,(c) the net power output of this cycle, (d) and the thermal efficiency of the cycle.7. Solve problem 6 assuming that the isentropic efficiencies of the compressor and turbine are 85%and 90% respectively.

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Answered: 6. Air enters the compressor of a…

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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For an air-standard Brayton cycle the air flow rate entering the compressor is 10 m3/s at 300 K and 100 kPa. The pressure ratio is 12, and the cycle maximum temperature is 1100 K. Determine (a) the net power developed; (b) the cycle thermal efficiency.
In a gas turbine cycle. the pressure ratio is 6 and maximum cycle temperature is 650°C. The efficiencies of turbine and compressor are 0.85 and 0.82. Air enters the compressor at 15°C and flow rate of air is 12 kg/sec. For compression process. C = 1.005 kJ/kg-K. y 1.32. For combustion process, C= 1.11 kJ/kg-K. Determine, (a) Power developed (b) Thermal efficiency (c) Work ratio.
Air enters the compressor of an ideal air-standard Brayton cycle at 88 kPa, 280 K, with a volumetric flow rate of 1225 m3/s. The compressor pressure ratio is 12. The turbine inlet temperature is 1225 K. Take Specific heat at constant pressure and constant volume for air as 1.006 kJ/kg K and 0.717 kJ/kg K respectively. Calculate the thermal efficiency of the plant to one decimal place and include the correct unit (percentage). Use cold air standard assumption
Air enters the compressor of an ideal air-standard Brayton cycle at P1-98 kPa and T1-320 K, with a volumetric flow rate of 15 m3/s. The compressor pressure ratio is 8. The turbine inlet temperature is 1480 K. Determine: P2 Pi 8 2 Compressor P₁=98 kPa T₁=320 K Heat exchanger Heat exchanger Cour T3 = 1480 K Turbine a. The mass flow rate b. The backwards ratio c. The rate of Heat addition to the system d. Thermal efficiency cycle T T3=1480 K P= 784 kPa P=98 kPa T₁= 320 K S
Air enters the compressor of an ideal air-standard Brayton cycle at 106 kPa, 281 K, with a volumetric flow rate of 1577 m3/s. The compressor pressure ratio is 13. The turbine inlet temperature is 1577 K. Take Specific heat at constant pressure and constant volume for air as 1.006 kJ/kg K and 0.717 kJ/kg K respectively. Calculate the work ratio of the plant to one decimal place and include the correct unit (percentage). Us cold air standard assumption.
Consider an air standard Brayton cycle. Air enters the compressor at 100 kPa, 300 K. At the cycle, pressure ratio is 9 and rejected heat (qout) is 450 kJ/kg. Determine the work output (wnet) in kJ/kg applying the cold-air-standard assumptions. (for air c,-0.718 kJ/kg.K, Cp 1.005 kJ/kg.K, k-1.4)
The adiabatic efficiencies of the compressor and turbine used in an air-standard Brayton cycle are 85% and 90%, respectively. If the cycle operates between 14.7 and 55 psia and if the maximum and minimum temperatures are 1500 F and 80 F, respectively, compute the thermal efficiency of the cycle. Assume constant specific heats.
2. Consider an ideal Brayton cycle that has a pressure ratio of 12, a compressor inlet temperature of 300 K, and a turbine inlet temperature of 1000K. Determine the required mass flow rate of air, in kg/s, for a net power output of 70 MW. (Assume cold-air-standard assumptions)
a turbojet aircraft is travelling at a speed of 925 kilometres per hour in atmospheric conditions of 0.45 bars and -26 degree centigrade. the compression ratio used is 8 and the air mass flow rate is 45 kg/sec and the allowable maximum cycle temperature is 827 degree centigrade. the entry duct, compressor, gas turbine and jet pipe stagnation isentropic efficiency are 0.9, 0.85, 0.89 and 0.9. the mechanical efficiency of the drive is 0.98 and the combustion efficiency is 0.99. assuming a convergent propeller nozzle a loss of stagnation pressure in the combustion chamber is 0.2 bars and fuel of cv 43.3 mj/kg is used. calculate:- i) required nozzle area ii) net thrust developed iii) specific fuel consumption for gases in turbine and nozzle take υ = 1.333, cp = 1.15 kj/kg-k and for combustion process take equivalent cp = 1.15 kj/kg-k.
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