(2). A gas turbine unit has a pressure ratio of 6:1 and a maximum cycletemperature of 600°C. The isentropic efficiencies of the compressor andturbine are 82% and 85% respectively. The turbine and compressor areconnected by a rigid shaft. Calculate:(a). the power output of a generator driven by the turbine when the airenters the compressor at 15°C at a rate of 15kg/s. The generatorefficiency is 95%(b). the cycle thermal efficiency.

The gas power plant operates on the Bryton cycle concept, in which the gas enters the compressor,…

Answered: A gas turbine unit has a pressure ratio…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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A refrigeration reciprocating compressor has a displacement volume of 0.06 m3 with a volumetric efficiency of 84.6%. It operates at 600 rpm (revolutions per minute) and receives R134a at 101.325 kPa and -20 °C. The compression process is isentropic with a discharge pressure of 600kPa. The compression and expansion processes in the cycle follow the relationship pv^n =constant, where n=1.13.a) Plot the cycle on a P-V diagram and indicate the area which represents the power input for one cycle. b) Calculate the mass flow rate of the refrigerant c) Calculate the power required for the compression process when the properties of R134a are obtained from the table attached. d) Find the power required for the compression process if the vapour is considered as ideal gas, and compare it with the value in c). e) If the above compression process is achieved by two-stage compression process (in series) with an intercooler, plot the cycle on the P-V diagram, indicate the area which represents the…
A turbo-generator has a combined steam rate of 5.35 kg/kW-hr at its rated output of 20 MW. The steam is supplied at 17 bar, 300oC and exhaust at 0.1 bar. Calculate (a) the combined heat rate, (b) the combined thermal efficiency, (c) the engine efficiency, and (d) the combined work.used the readings in steam table at KJ/kg, and draw the T-S diagram
An ideal Brayton cycle has a pressure ratio of 7:1. The temperature of the air is 24 0C at the inlet to the compressor and 1,120 0C at the inlet to the turbine. Take Specific heat at constant pressure and constant volume for air as 1.006 kJ/kg K and 0.717 kJ/kg K respectively. Calculate the work ratio of the plant to three decimal places.
Q5/ For a steam power plant, the turbine operates isentropically and adiabatically with inlet steam at 6800 kPa and 550 °C and the exhaust steam enters the condenser at 50 °C. Saturated liquid water leaves the condenser, and is pumped to the boiler. Neglecting pump work and kinetic and potential energy changes, determine the thermal efficiency of the cycle?
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 the maximum cycle temperature is 800°C.
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An ideal gas turbine cycle consisting of 2 stages of compression and 2 stages of expansion has an overall pressure ratio of 9. Air enters the compressors at the temperature of 320 K while, being intercooled between the stages. Air enters the first compressor at 100 kPa and the pressure ratio of cach of the compressors are selected in a way that minimizes the total power input for the compressors. The high-pressure turbine (First one) drives the compressors and the low-pressure one produces power output. The compressors and both the high-pressure and low-pressure turbines can be assumed ideal. To increase the efficiency of the cycle a regenerator with effectiveness of 85% is used to recover some heat from the exhaust of the second turbine. In this cycle, air with the temperature of 1400 K enters the first turbine. After expansion in the first turbine, air is reheated to the same temperature at the inlet of the first turbine (1400 K). You can consider constant specific heats of c,=1.005…
Explain why the second law efficiencies for the two turbines are not the same

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