Chapter 9: Problem 10
Define the following terms related to reciprocating engines: stroke, bore, top dead center, and clearance volume.
Chapter 9: Problem 10
Define the following terms related to reciprocating engines: stroke, bore, top dead center, and clearance volume.
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Get started for freeA turbojet aircraft is flying with a velocity of \(280 \mathrm{m} / \mathrm{s}\) at an altitude of \(9150 \mathrm{m},\) where the ambient conditions are \(32 \mathrm{kPa}\) and \(-32^{\circ} \mathrm{C} .\) The pressure ratio across the compressor is \(12,\) and the temperature at the turbine inlet is 1100 K. Air enters the compressor at a rate of \(50 \mathrm{kg} / \mathrm{s}\), and the jet fuel has a heating value of \(42,700 \mathrm{kJ} / \mathrm{kg}\). Assuming ideal operation for all components and constant specific heats for air at room temperature, determine ( \(a\) ) the velocity of the exhaust gases, \((b)\) the propulsive power developed, and \((c)\) the rate of fuel consumption.
A gas turbine operates with a regenerator and two stages of reheating and intercooling. This system is designed so that when air enters the compressor at \(100 \mathrm{kPa}\) and \(15^{\circ} \mathrm{C}\) the pressure ratio for each stage of compression is \(3 ;\) the air temperature when entering a turbine is \(500^{\circ} \mathrm{C} ;\) and the regenerator operates perfectly. At full load, this engine produces \(800 \mathrm{kW} .\) For this engine to service a partial load, the heat addition in both combustion chambers is reduced. Develop an optimal schedule of heat addition to the combustion chambers for partial loads ranging from 400 to \(800 \mathrm{kW}\)
Helium is used as the working fluid in a Brayton cycle with regeneration. The pressure ratio of the cycle is 8 the compressor inlet temperature is \(300 \mathrm{K},\) and the turbine inlet temperature is \(1800 \mathrm{K}\). The effectiveness of the regenerator is 75 percent. Determine the thermal efficiency and the required mass flow rate of helium for a net power output of \(60 \mathrm{MW},\) assuming both the compressor and the turbine have an isentropic efficiency of \((a) 100\) percent and \((b) 80\) percent.
A Brayton cycle with regeneration using air as the working fluid has a pressure ratio of \(7 .\) The minimum and maximum temperatures in the cycle are 310 and 1150 K. Assuming an isentropic efficiency of 75 percent for the compressor and 82 percent for the turbine and an effectiveness of 65 percent for the regenerator, determine \((a)\) the air temperature at the turbine exit, \((b)\) the net work output, and \((c)\) the thermal efficiency.
An ideal Ericsson engine using helium as the working fluid operates between temperature limits of 550 and \(3000 \mathrm{R}\) and pressure limits of 25 and 200 psia. Assuming a mass flow rate of \(14 \mathrm{lbm} / \mathrm{s}\), determine (a) the thermal efficiency of the cycle, \((b)\) the heat transfer rate in the regenerator, and \((c)\) the power delivered.
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