Chapter 11: Problem 5
What is the difference between an open and a closed feedwater heater?
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Chapter 11: Problem 5
What is the difference between an open and a closed feedwater heater?
These are the key concepts you need to understand to accurately answer the question.
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The power plant shown in Fig. 11.40 combines a gas-turbine cycle and a steam- turbine cycle. The following data are known for the gas-turbine cycle. Air enters the compressor at \(100 \mathrm{kPa}\) \(25^{\circ} \mathrm{C},\) the compressor pressure ratio is \(14,\) and the isentropic compressor efficiency is \(87 \%\); the heater input rate is \(60 \mathrm{MW}\); the turbine inlet temperature is \(1250^{\circ} \mathrm{C}\), the exhaust pressure is \(100 \mathrm{kPa},\) and the isentropic turbine efficiency is \(87 \%\); the cycle exhaust temperature from the heat exchanger is \(200^{\circ} \mathrm{C}\). The following data are known for the steam-turbine cycle. The pump inlet state is saturated liquid at \(10 \mathrm{kPa}\), the pump exit pressure is \(12.5 \mathrm{MPa}\), and the isentropic pump efficiency is \(85 \%\); turbine inlet temperature is \(500^{\circ} \mathrm{C}\), and the isentropic turbine efficiency is \(87 \% .\) Determine a. The mass flow rate of air in the gas-turbine cycle. b. The mass flow rate of water in the steam cycle c. The overall thermal efficiency of the combined cycle.
Consider an air-standard jet engine cycle operating in a \(280-\mathrm{K}, 100\) -kPa environment. The compressor requires a shaft power input of \(4000 \mathrm{kW}\) Air enters the turbine state 3 at \(1600 \mathrm{K}\) and 2 \(\mathrm{MPa}\), at the rate of \(9 \mathrm{kg} / \mathrm{s}\), and the isentropic efficiency of the turbine is \(85 \%\). Determine the pressure and temperature entering the nozzle.
A gasoline engine has a volumetric compression ratio of 10 and before compression has air at \(290 \mathrm{K}, 85 \mathrm{kPa},\) in the cylinder. The combustion peak pressure is 6000 kPa. Assume cold air properties. What is the highest temperature in the cycle? Find the temperature at the beginning of the exhaust (heat rejection) and the overall cycle efficiency.
Consider a gas-turbine cycle with two stages of compression and two stages of expansion. The pressure ratio across each compressor stage and each turbine stage is 8 to \(1 .\) The pressure at the entrance to the first compressor is \(100 \mathrm{kPa}\), the temperature entering each compressor is \(20^{\circ} \mathrm{C}\) and the temperature entering each turbine is \(1100^{\circ} \mathrm{C} .\) A regenerator is also incorporated into the cycle and it has an efficiency of \(70 \%\). Determine the compressor work, the turbine work, and the thermal efficiency of the cycle.
Consider an ideal Stirling-cycle engine in which the state at the beginning of the isothermal compression process is \(100 \mathrm{kPa}, 25^{\circ} \mathrm{C}\), the compression ratio is \(6,\) and the maximum temperature in the cycle is \(1100^{\circ} \mathrm{C}\). Calculate the maximum cycle pressure and the thermal efficiency of the cycle with and without regenerators.
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