Chapter 9: Problem 23
What four processes make up the ideal Otto cycle?
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Key Concepts
These are the key concepts you need to understand to accurately answer the question.
Chapter 9: Problem 23
What four processes make up the ideal Otto cycle?
These are the key concepts you need to understand to accurately answer the question.
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Get started for freeA four-stroke turbocharged \(V-16\) diesel engine built by GE Transportation Systems to power fast trains produces 4400 hp at 1500 rpm. Determine the amount of work produced per cylinder per ( \(a\) ) mechanical cycle and ( \(b\) ) thermodynamic cycle.
Air is used as the working fluid in a simple ideal Brayton cycle that has a pressure ratio of \(12,\) a compressor inlet temperature of \(300 \mathrm{K},\) and a turbine inlet temperatureof \(1000 \mathrm{K} .\) Determine the required mass flow rate of air for a net power output of \(70 \mathrm{MW}\), assuming both the compressor and the turbine have an isentropic efficiency of \((a) 100\) percent and \((b) 85\) percent. Assume constant specific heats at room temperature.
An 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
Consider the ideal regenerative Brayton cycle. Determine the pressure ratio that maximizes the thermal efficiency of the cycle and compare this value with the pressure ratio that maximizes the cycle net work. For the same maximumto- minimum temperature ratios, explain why the pressure ratio for maximum efficiency is less than the pressure ratio for maximum work.
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 \((a) 5 \mathrm{kN}\) \((b) 10 \mathrm{kN}\) \((c) 15 \mathrm{kN}\) \((d) 20 \mathrm{kN}\) \((e) 26 \mathrm{kN}\)
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