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In an ideal Brayton cycle with regeneration, argon gas is compressed from \(100 \mathrm{kPa}\) and \(25^{\circ} \mathrm{C}\) to \(400 \mathrm{kPa}\), and then heated to \(1200^{\circ} \mathrm{C}\) before entering the turbine. The highest temperature that argon can be heated in the regenerator is (a) \(246^{\circ} \mathrm{C}\) (b) \(846^{\circ} \mathrm{C}\) \((c) 689^{\circ} \mathrm{C}\) \((d) 368^{\circ} \mathrm{C} \quad(e) 573^{\circ} \mathrm{C}\)

Short Answer

Expert verified
Answer: The highest temperature that argon can be heated in the regenerator is approximately 831.85°C.

Step by step solution

01

Calculate the Temperature and Pressure after Compression

To find the temperature after compression, we need to use the isentropic relation between the pressure, temperature, and the specific heat ratio, assuming the compression process is isentropic. The specific heat ratio of argon is \(\gamma = 1.67\), and the initial pressure and temperature are given as \(P_1 = 100\,\mathrm{kPa}\) and \(T_1 = 25^\circ\mathrm{C}\). The final pressure is given as \(P_2 = 400\,\mathrm{kPa}\), we can use the isentropic relation to find \(T_2\): $$ \frac{T_2}{T_1} = \left(\frac{P_2}{P_1}\right)^{\frac{\gamma - 1}{\gamma}} $$ Now, we can plug in the values and calculate \(T_2\): $$ \frac{T_2}{25 + 273.15} = \left(\frac{400}{100}\right)^{\frac{1.67 - 1}{1.67}} $$ $$ T_2 = 298.15 \cdot \left(4\right)^{\frac{0.67}{1.67}} = 368\,\mathrm{K} $$ Note that we need to convert temperatures from Celsius to Kelvin for these calculations. So, \(T_2 = 368\,\mathrm{K} = 95^\circ\mathrm{C}\), which is the temperature of argon at the end of the compression process.
02

Calculate the Highest Temperature in the Regenerator

Now, we can use the temperature of the argon at the end of the compression process (\(T_2 = 95^\circ\mathrm{C}\)) and the temperature before entering the turbine (\(T_3 = 1200^\circ\mathrm{C}\)) to determine the highest temperature that argon can be heated in the regenerator. The regenerator is essentially a counter-flow heat exchanger; thus, in the best-case scenario, the temperature of the compressed argon can approach the temperature of the argon before entering the turbine, giving the maximum possible effectiveness for the regenerator. The highest temperature that argon can be heated in the regenerator (\(T_{max}\)) can now be calculated: $$ T_{max} = T_3 - T_2 $$ $$ T_{max} = 1200 - 95 = 1105\,\mathrm{K} $$ Now, we can convert the temperature back to Celsius: $$ T_{max} = 1105 - 273.15 = 831.85^\circ\mathrm{C} $$ Thus, the highest temperature that argon can be heated in the regenerator is around \(831.85^\circ\mathrm{C}\). Looking at the available options, the closest answer is option (b) \(846^\circ\mathrm{C}\).

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Most popular questions from this chapter

A simple ideal Brayton cycle with air as the working fluid has a pressure ratio of \(10 .\) The air enters the compressor at \(520 \mathrm{R}\) and the turbine at \(2000 \mathrm{R}\). Accounting for the variation of specific heats with temperature, determine ( \(a\) ) the air temperature at the compressor exit, ( \(b\) ) the back work ratio, and \((c)\) the thermal efficiency.

A gas-turbine power plant operates on the regenerative Brayton cycle between the pressure limits of 100 and \(700 \mathrm{kPa}\). Air enters the compressor at \(30^{\circ} \mathrm{C}\) at a rate of \(12.6 \mathrm{kg} / \mathrm{s}\) and leaves at \(260^{\circ} \mathrm{C}\). It is then heated in a regenerator to \(400^{\circ} \mathrm{C}\) by the hot combustion gases leaving the turbine. A diesel fuel with a heating value of \(42,000 \mathrm{kJ} / \mathrm{kg}\) is burned in the combustion chamber with a combustion efficiency of 97 percent. The combustion gases leave the combustion chamber at \(871^{\circ} \mathrm{C}\) and enter the turbine whose isentropic efficiency is 85 percent. Treating combustion gases as air and using constant specific heats at \(500^{\circ} \mathrm{C}\), determine (a) the isentropic efficiency of the compressor, ( \(b\) ) the effectiveness of the regenerator, \((c)\) the air-fuel ratio in the combustion chamber, \((d)\) the net power output and the back work ratio, \((e)\) the thermal efficiency, and \((f)\) the second-law efficiency of the plant. Also determine \((g)\) the second-law efficiencies of the compressor, the turbine, and the regenerator, and \((h)\) the rate of the energy flow with the combustion chamber with a combustion efficiency of 97 percent. The combustion gases leave the combustion chamber at \(871^{\circ} \mathrm{C}\) and enter the turbine whose isentropic efficiency is 85 percent. Treating combustion gases as air and using constant specific heats at \(500^{\circ} \mathrm{C}\), determine (a) the isentropic efficiency of the compressor, (b) the effectiveness of the regenerator, (c) the air-fuel ratio in the combustion chamber, \((d)\) the net power output and the back work ratio, \((e)\) the thermal efficiency, and \((f)\) the second-law efficiency of the plant. Also determine \((g)\) the second-law efficiencies of the compressor, the turbine, and the regenerator, and \((h)\) the rate of the energy flow with the combustion gases at the regenerator exit.

A turbofan engine operating on an aircraft flying at \(200 \mathrm{m} / \mathrm{s}\) at an altitude where the air is at \(50 \mathrm{kPa}\) and \(-20^{\circ} \mathrm{C}\) is to produce \(50,000 \mathrm{N}\) of thrust. The inlet diameter of this engine is \(2.5 \mathrm{m} ;\) the compressor pressure ratio is \(12 ;\) and the mass flow rate ratio is \(8 .\) Determine the air temperature at the fan outlet needed to produce this thrust. Assume ideal operation for all components and constant specific heats at room temperature.

Consider the ideal Otto, Stirling, and Carnot cycles operating between the same temperature limits. How would you compare the thermal efficiencies of these three cycles?

For a specified compression ratio, is a diesel or gasoline engine more efficient?

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