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

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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
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)
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-powered aircraft is flying at 220 m/s and 8000-m altitude, where the ambient temperature and pressure are 236K and 35kPa, respectively.The pressure ratio of the compressor is 6 and the turbine inlet temperaturer is 970k. Estimate the thrust developed by the engine when the air flow rate is 55kg/s. employ an air standard-cycle analysis using the constant-pressurree specific heat c_p and specific heat ratio γ for air and neglecting the fuel properties.
Air enters the compressor of an ideal air-standard Brayton cycle at 100 kPa, 27°C, with a volumetric flow rate of 5 m/s. The compressor pressure ratio is 10:1. The turbine inlet temperature is 1127°C. Both turbine and compressor operate with 80% efficiency. Using appropriate assumptions, evaluate; (i) (ii) (iii) the thermal efficiency of the cycle; the back work ratio; and the net power developed (kW).
28. In a marine gas turbine unit a high-pressure stage turbine drives the compressor, and a low-pressure stage turbine drives the propeller through suitable gearing. The overall pressure ratio is 4: 1, and the maximum temperature is 650°C. The isentropic efficiencies of the compressor, H.P. turbine, and L.P. turbine are 0.8, 0.83, and 0.85 respectively, and the mechanical efficiency of both shafts is 98%. Calculate the pressure between turbine stages when the air intake conditions are 1.01 bar and 25°C. Calculate also the thermal efficiency and the shaft power when the mass flow is 60 kg/s. Neglect kinetic energy changes, and pressure [Ans. 1.57 bar; 14.9% ; 4560 kW) loss in combustion.
Air enters the compressor of an ideal cold air-standard Brayton cycle at 100 kPa, 300 K, with a mass flow rate of 6 kg/s. The compressor pressure ratio is 10, and the turbine inlet temperature is 1400 K. For k = 1.4 and Cp = 1.005 kJ/kg, calculate:(a) the percent thermal efficiency of the cycle.(b) the back work ratio.(c) the net power developed, in kW.
Air enters the compressor of an ideal cold air-standard Brayton cycle at 100 kPa, 300 K, with a mass flow rate of 6 kg/s. The compressor pressure ratio is 13, and the turbine inlet temperature is 1200 K.For k = 1.4 and Cp = 1.005 kJ/kg, calculate:(a) the percent thermal efficiency of the cycle.(b) the back work ratio.(c) the net power developed, in kW.
SIMPLE NON-IDEAL BRAYTON CYCLE GAS TURBINE: Use Cold-Air Standard Analysis Show complete solution and explain briefly.
SIMPLE NON-IDEAL BRAYTON CYCLE GAS TURBINE: Use Cold-Air Standard Analysis Show complete solution and explain briefly.

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