Chapter 9: Problem 76
For fixed maximum and minimum temperatures, what is the effect of the pressure ratio on \((a)\) the thermal efficiency and ( \(b\) ) the net work output of a simple ideal Brayton cycle?
Chapter 9: Problem 76
For fixed maximum and minimum temperatures, what is the effect of the pressure ratio on \((a)\) the thermal efficiency and ( \(b\) ) the net work output of a simple ideal Brayton cycle?
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Get started for freeAn ideal gas turbine cycle with many stages of compression and expansion and a regenerator of 100 percent effectiveness has an overall pressure ratio of \(10 .\) Air enters every stage of compressor at \(290 \mathrm{K}\), and every stage of turbine at \(1200 \mathrm{K}\). The thermal efficiency of this gas-turbine cycle is \((a) 36\) percent (b) 40 percent \((c) 52\) percent \((d) 64\) percent \((e) 76\) percent
A gas-turbine plant operates on the regenerative Brayton cycle with two stages of reheating and two-stages of intercooling between the pressure limits of 100 and 1200 kPa. The working fluid is air. The air enters the first and the second stages of the compressor at \(300 \mathrm{K}\) and \(350 \mathrm{K},\) respectively, and the first and the second stages of the turbine at \(1400 \mathrm{K}\) and \(1300 \mathrm{K},\) respectively. Assuming both the compressor and the turbine have an isentropic efficiency of 80 percent and the regenerator has an effectiveness of 75 percent and using variable specific heats, determine ( \(a\) ) the back work ratio and the net work output, \((b)\) the thermal efficiency, and \((c)\) the secondlaw efficiency of the cycle. Also determine ( \(d\) ) the exergies at the exits of the combustion chamber (state 6 ) and the regenerator (state 10 ) (See Fig. \(9-43\) in the text).
Air enters a turbojet engine at \(320 \mathrm{m} / \mathrm{s}\) at a rate of \(30 \mathrm{kg} / \mathrm{s},\) and exits at \(650 \mathrm{m} / \mathrm{s}\) relative to the aircraft. The thrust developed by the engine is \((a) 5 \mathrm{kN}\) \((b) 10 \mathrm{kN}\) \((c) 15 \mathrm{kN}\) \((d) 20 \mathrm{kN}\) \((e) 26 \mathrm{kN}\)
An air-standard Diesel cycle has a compression ratio of \(18.2 .\) Air is at \(120^{\circ} \mathrm{F}\) and 14.7 psia at the beginning of the compression process and at \(3200 \mathrm{R}\) at the end of the heataddition process. Accounting for the variation of specific heats with temperature, determine \((a)\) the cutoff ratio, \((b)\) the heat rejection per unit mass, and ( \(c\) ) the thermal efficiency.
Consider an ideal gas-turbine cycle with two stages of compression and two stages of expansion. The pressure ratio across each stage of the compressor and turbine is 3 The air enters each stage of the compressor at \(300 \mathrm{K}\) and each stage of the turbine at \(1200 \mathrm{K}\). Determine the back work ratio and the thermal efficiency of the cycle, assuming \((a)\) no regenerator is used and \((b)\) a regenerator with 75 percent effectiveness is used. Use variable specific heats.
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