A gas-turbine power plant operates on a modified Brayton cycle with anoverall pressure ratio of 8. Air enters the compressor at 0°C and 100 kPa. The maximumcycle temperature is 1500 K. The compressor and the turbines are isentropic. The high-pressure turbine develops just enough power to run the compressor. Assume constantproperties for air at 300 K with C₁ = 0.718 kJ/kg K, Cp= 1.005 kJ/kg K, R = 0.287kJ/kg K, k=1.4.(a)Sketch the (T-s) diagram for the cycle.(b) Determine the temperature and pressure at state 4, the exit of the high-pressure turbine.(c) If the net power output is 200 MW, determine the mass flow rate of the air into thecompressor, in kg/s.

Answered: A gas-turbine power plant operates on a…

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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Required information A gas-turbine power plant operates on a modified Brayton cycle shown in the figure with an overall pressure ratio of 8. Air enters the compressor at 0°C and 108 kPa. The maximum cycle temperature is 1500 K. The compressor and the turbines are isentropic. The high-pressure turbine develops just enough power to run the compressor. Assume constant properties for air at 300 K with cy=0.718 kJ/kg-K, cp=1005 kJ/kg-K. R=0.287 kJ/kg-K, and k=1.4. Combustion chamber Compressor to High-pressure Determine the temperature and pressure at state 4, the exit of the high-pressure turbine. The temperature at state 4 is The pressure at state 4 is [ K. Low-pressure kPa.
A gas-turbine power plant operates on a modified Brayton cycle shown in the figure with an overall pressure ratio of 8. Air enters the compressor at 0°C and 100 kPa. The maximum cycle temperature is 1500 K. The compres¬sor and the turbines are isentropic. The high-pressure turbine develops just enough power to run the compressor. Assume constant properties for air at 300 K as cv = 0.718 kJ/kg·K, cp = 1.005 kJ/kg·K, R = 0.287 kJ/kg·K, k = 1.4. (a) Sketch the T-s diagram for the cycle. Label the data states. (b) Determine the temperature and pressure at state 4, the exit of the high-pressure turbine. (c) If the net power output is 200 MW, determine the mass flow rate of the air into the compressor in kg/s.
The ideal air-standard Brayton cycle operates with air entering the compressor at 95 kPa, 22°C. The pressure ratio rp is 6:1 and the air leaves the heat addition process at 1100 K. Determine the compressor work and the turbine work per unit mass flow, the cycle efficiency, the back work ratio, and compare the compressor exit temperature to the turbine exit temperature. Assume constant properties.
A Brayton cycle with a pressure ratio of 15 operates with air entering the compressor at 70 kPa and 0°C, and the turbine at 600°C. Calculate the net specific work produced by this cycle treating the air as an ideal gas with variable specific heats.
A gas turbine power plant operates on a simple thermodynamic cycle. The ambient conditionsare 100 kPa and 24 °C. The air at this condition enters the engine at 150 m/s whose diameteris 0.5 m. The pressure ratio across the compressor is 19, and the temperature at the turbineinlet is 1400 K. Assuming ideal operation for all components and specific heats for air andproducts separately. In addition, neglect the mass of fuel burned. Do the followings:a. Choose the suitable thermodynamic cycleb. Draw pv and Ts diagram and label itc. Calculate the power required by the compressord. Determine the pressure and the temperature at the turbine exit,e. Compute the power produced by the turbinef. Available specific workg. The thermal efficiency
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 oC. the isentropic efficiencies of the compressor, H. P. turbine, L. P. turbine are 0.8, 0.83 and 0.85 respectively and the mechanical efficiency of both shafts is 98 %. Sketch the process on the T-s diagram Calculate the pressure between turbine stages when the air intake conditions are 1.01 bar and 25 oC. Calculate also the thermal efficiency and the shaft power when the mass flow is 60 kg/s. NB: Neglect kinetic energy changes and the pressure loss in combustion.
Air enters the compressor of an ideal air-standard Brayton cycle at 100 kPa, 300K and is compressed to 1000 kPa. The temperature at the inlet to the first turbine is 1400 K. The expansion takes place isentropically in two stages with reheat to 1400 K between the two stages at a constant pressure of 300kPa. A regenerator having an effectiveness of 100% is also incorporated in the cycle. Determine the thermal efficiency of the cycle.
A gas turbine power plant operates on a simple thermodynamic cycle. The ambient conditionsare 100 kPa and 24 °C. The air at this condition enters the engine at 150 m/s whose diameteris 0.5 m. The pressure ratio across the compressor is 11, and the temperature at the turbineinlet is 1400 K. Assuming ideal operation for all components and specific heats for air andproducts separately. In addition, neglect the mass of fuel burned. Do the followings:a. Compute the power produced by the turbineb Available specific workc. The thermal efficiency.
A gas turbine power plant operates on a simple thermodynamic cycle. The ambient conditionsare 100 kPa and 24 °C. The air at this condition enters the engine at 150 m/s whose diameteris 0.5 m. The pressure ratio across the compressor is 11, and the temperature at the turbineinlet is 1400 K. Assuming ideal operation for all components and specific heats for air andproducts separately. In addition, neglect the mass of fuel burned. Do the followings:a. Choose the suitable thermodynamic cycleb. Draw pv and Ts diagram and label itc. Calculate the power required by the compressord. Determine the pressure and the temperature at the turbine exit,e. Compute the power produced by the turbinef. Available specific workg. The thermal efficiency. Explain with clear writing and units and diagram Also if you use tables and equation mention it with explanation
A gas turbine power plant operates on a simple thermodynamic cycle. The ambient conditionsare 100 kPa and 24 °C. The air at this condition enters the engine at 150 m/s whose diameteris 0.5 m. The pressure ratio across the compressor is 18 k and the temperature at the turbineinlet is 1400 K. Assuming ideal operation for all components and specific heats for air andproducts separately. In addition, neglect the mass of fuel burned. Do the followings:a. Choose the suitable thermodynamic cycleb.Draw pv and Ts diagram and label itCalculate the power required by the compressordDetermine the pressure and the temperature at the turbine exit,Compute the power produced by the turbinef.Available specific workg.The thermal efficiency
Determine the thermal efficiency.The adiabatic compression is reversible for An Otto-cycle and the expansion processes are reversible. engine takes air at 25 deg C, with initial pressure 1.1 b with a specific volume of 0..78 m3/kg. The compression ratio is 15 and the peak cycle temperature is equal to 1560 Deg C.
The compression ratio of an air-standard Otto cycle is 9.5. Assume the start of isentropic (reversible adiabatic) compression is state point 1. Prior to the isentropic compression process, the air is at 100 kPa, 35°C, and 600 cm3. The temperature at the end of the isentropic (reversible) expansion process is 800 K. Take the average values of the specific heat capacities, cP = 1.005 kJ/(kg·K) and cv = 0.718 kJ/(kg·K). (a) Draw the Otto cycle on both the P-v and T-s diagrams. Determine the: (b) highest temperature (in K) and pressure (in kPa) in the cycle, (c) amount of total heat transferred in, in kJ, (d) thermal efficiency, and (e) mean effective pressure in kPa.

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