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How does the thermal efficiency of an ideal cycle, in general, compare to that of a Carnot cycle operating between the same temperature limits?

Short Answer

Expert verified
Answer: The thermal efficiency of an ideal cycle is generally less than or equal to the thermal efficiency of a Carnot cycle when given the same temperature limits. The Carnot cycle is the most efficient reversible cycle and is used as a benchmark to compare other cycles.

Step by step solution

01

Define the thermal efficiency formula

The thermal efficiency of any cycle is given by the formula: Efficiency (η) = (Work output) / (Heat input)
02

Define the efficiency of an ideal cycle

The efficiency of an ideal cycle depends on the specific processes within the cycle. There are different ideal cycles, such as the Otto cycle, Diesel cycle, and Brayton cycle, each with its thermal efficiency formula. In general, the thermal efficiency for an ideal cycle can be written as: η_ideal = f(T1, T2) Where T1 and T2 are the temperature limits of the cycle, and f(T1, T2) is a function that varies between different ideal cycles.
03

Define the efficiency of a Carnot cycle

The efficiency of a Carnot cycle operating between two temperature limits T1 (hot/reservoir source) and T2 (cold/reservoir sink) is given by: η_carnot = 1 - T2/T1
04

Compare the thermal efficiency of an ideal cycle and a Carnot cycle

As mentioned earlier, the Carnot cycle is the most efficient reversible cycle, which means its efficiency is always higher than or equal to any other cycle, including ideal cycles, operating between the same temperature limits. So, the general comparison between the thermal efficiency of an ideal cycle and a Carnot cycle is: η_ideal ≤ η_carnot This means that the thermal efficiency of an ideal cycle is less than or equal to the thermal efficiency of a Carnot cycle.

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Most popular questions from this chapter

Consider a simple Brayton cycle using air as the working fluid; has a pressure ratio of \(12 ;\) has a maximum cycle temperature of \(600^{\circ} \mathrm{C} ;\) and operates the compressor inlet at \(100 \mathrm{kPa}\) and \(15^{\circ} \mathrm{C} .\) Which will have the greatest impact on the back-work ratio: a compressor isentropic efficiency of 80 percent or a turbine isentropic efficiency of 80 percent? Use constant specific heats at room temperature.

A gas turbine for an automobile is designed with a regenerator. Air enters the compressor of this engine at \(100 \mathrm{kPa}\) and \(30^{\circ} \mathrm{C}\). The compressor pressure ratio is \(10 ;\) the maximum cycle temperature is \(800^{\circ} \mathrm{C} ;\) and the cold air stream leaves the regenerator \(10^{\circ} \mathrm{C}\) cooler than the hot air stream at the inlet of the regenerator. Assuming both the compressor and the turbine to be isentropic, determine the rates of heat addition and rejection for this cycle when it produces 115 kW. Use constant specific heats at room temperature.

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).

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 gas turbine that has a pressure ratio of 6 and operates on the Brayton cycle with regeneration between the temperature limits of 20 and \(900^{\circ} \mathrm{C}\). If the specific heat ratio of the working fluid is \(1.3,\) the highest thermal efficiency this gas turbine can have is \((a) 38\) percent (b) 46 percent \((c) 62\) percent \((d) 58\) percent \((e) 97\) percent

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