Chapter 9: Problem 66
How does the ideal Ericsson cycle differ from the Carnot cycle?
Chapter 9: Problem 66
How does the ideal Ericsson cycle differ from the Carnot cycle?
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Get started for freeWhen we double the compression ratio of an ideal Otto cycle, what happens to the maximum gas temperature and pressure when the state of the air at the beginning of the compression and the amount of heat addition remain the same? Use constant specific heats at room temperature.
A simple ideal Brayton cycle is modified to incorporate multistage compression with intercooling, multistage expansion with reheating, and regeneration without changing the pressure limits of the cycle. As a result of these modifications, (a) Does the net work output increase, decrease, or remain the same? (b) Does the back work ratio increase, decrease, or remain the same? \((c) \quad\) Does the thermal efficiency increase, decrease, or remain the same? (d) Does the heat rejected increase, decrease, or remain the same?
Compare the thermal efficiency of a two-stage gas turbine with regeneration, reheating and intercooling to that of a three-stage gas turbine with the same equipment when \((a)\) all components operate ideally, \((b)\) air enters the first compressor at \(100 \mathrm{kPa}\) and \(20^{\circ} \mathrm{C},(c)\) the total pressure ratio across all stages of compression is \(16,\) and \((d)\) the maximum cycle temperature is \(800^{\circ} \mathrm{C}\)
A turbojet is flying with a velocity of \(900 \mathrm{ft} / \mathrm{s}\) at an altitude of \(20,000 \mathrm{ft}\), where the ambient conditions are 7 psia and \(10^{\circ} \mathrm{F}\). The pressure ratio across the compressor is \(13,\) and the temperature at the turbine inlet is 2400 R. Assuming ideal operation for all components and constant specific heats for air at room temperature, determine ( \(a\) ) the pressure at the turbine exit, \((b)\) the velocity of the exhaust gases, and \((c)\) the propulsive efficiency.
Consider a regenerative gas-turbine power plant with two stages of compression and two stages of expansion. The overall pressure ratio of the cycle is \(9 .\) The air enters each stage of the compressor at \(300 \mathrm{K}\) and each stage of the turbine at \(1200 \mathrm{K}\). Accounting for the variation of specific heats with temperature, determine the minimum mass flow rate of air needed to develop a net power output of \(110 \mathrm{MW}\)
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