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 each 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 kJ/kg.K and c,=0.718 kJ/kg.K to analyze this problem and air can be assumed ideal gas. (Hint: Try to use equation of to relate pressure and temperature in the isentropic processes) and (k =). c, a) Determine the pressure ratio of each of the compressors and total specific work input to the compressors. b) What is the pressure ratio of the high-pressure turbine? (Hint: The work output of the first turbine should be equal to total work input to the compressors.) c) Find the net specific work output of the cycle. d) Determine the thermal efficiency of the cycle.
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 each 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 kJ/kg.K and c,=0.718 kJ/kg.K to analyze this problem and air can be assumed ideal gas. (Hint: Try to use equation of to relate pressure and temperature in the isentropic processes) and (k =). c, a) Determine the pressure ratio of each of the compressors and total specific work input to the compressors. b) What is the pressure ratio of the high-pressure turbine? (Hint: The work output of the first turbine should be equal to total work input to the compressors.) c) Find the net specific work output of the cycle. d) Determine the thermal efficiency of the cycle.
Introduction to Chemical Engineering Thermodynamics
8th Edition
ISBN:9781259696527
Author:J.M. Smith Termodinamica en ingenieria quimica, Hendrick C Van Ness, Michael Abbott, Mark Swihart
Publisher:J.M. Smith Termodinamica en ingenieria quimica, Hendrick C Van Ness, Michael Abbott, Mark Swihart
Chapter1: Introduction
Section: Chapter Questions
Problem 1.1P
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I have asked this question but it was rejected. I am submitting the problems to check my understanding. This problem is from an older exam that I am using as practice and I am not being graded on them.
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Transcribed Image Text: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 each
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 kJ/kg.K and c,=0.718
kJ/kg.K to analyze this problem and air can be assumed ideal gas. (Hint: Try to use equation of
to relate pressure and temperature in the isentropic processes) and (k =).
c,
a) Determine the pressure ratio of each of the compressors and total specific work input to the
compressors.
b) What is the pressure ratio of the high-pressure turbine? (Hint: The work output of the first turbine
should be equal to total work input to the compressors.)
c) Find the net specific work output of the cycle.
d) Determine the thermal efficiency of the cycle.
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