A gas turbine power plant with the following specifications: two axial compressor stages, the pressure ratio is 6/1 for each compressor. The inlet and exit angles of both moving and fixed blades are 40° and 20° respectively, the work done factor is 0.82, six stages for each compressor. intercooling between stages. A high pressure turbine is used to drive the compressors, and a low pressure turbine drives the generator. The temperature of the gases at entry to the high pressure turbine is 600°C and the gases are reheated to 700°C after expansion in the first turbine. The exhaust gases leaving the low pressure turbine are passed through a heat exchanger to heat the air leaving the high pressure stage compressor. The air inlet temperature to the unit is 20°C. The isentropic efficiency of each turbine stage is 0.95; the heat exchanger thermal ratio is 0.7. A mechanical loss is 5% for both the generator-turbine shaft and the compressor- turbine shaft. Assume any missed values to Calculate the isentropic efficiency of each compressor, thermal efficiency and work ratio of the plant, For air take cp is 1.005kJ/kg.K and y=1.4, and for the gases in the combustion chamber and in the turbines and heat exchanger take cp is 1.1 kJ/kg.K, y=1.333.
A gas turbine power plant with the following specifications: two axial compressor stages, the pressure ratio is 6/1 for each compressor. The inlet and exit angles of both moving and fixed blades are 40° and 20° respectively, the work done factor is 0.82, six stages for each compressor. intercooling between stages. A high pressure turbine is used to drive the compressors, and a low pressure turbine drives the generator. The temperature of the gases at entry to the high pressure turbine is 600°C and the gases are reheated to 700°C after expansion in the first turbine. The exhaust gases leaving the low pressure turbine are passed through a heat exchanger to heat the air leaving the high pressure stage compressor. The air inlet temperature to the unit is 20°C. The isentropic efficiency of each turbine stage is 0.95; the heat exchanger thermal ratio is 0.7. A mechanical loss is 5% for both the generator-turbine shaft and the compressor- turbine shaft. Assume any missed values to Calculate the isentropic efficiency of each compressor, thermal efficiency and work ratio of the plant, For air take cp is 1.005kJ/kg.K and y=1.4, and for the gases in the combustion chamber and in the turbines and heat exchanger take cp is 1.1 kJ/kg.K, y=1.333.
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
Related questions
Question
Transcribed Image Text:A gas turbine power plant with the following specifications:
two axial compressor stages, the pressure ratio is 6/1 for each compressor. The inlet and
exit angles of both moving and fixed blades are 40° and 20° respectively, the work done
factor is 0.82, six stages for each compressor.
intercooling between stages.
A high pressure turbine is used to drive the compressors, and a low pressure turbine
drives the generator.
The temperature of the gases at entry to the high pressure turbine is 600°C and the gases
are reheated to 700°C after expansion in the first turbine.
The exhaust gases leaving the low pressure turbine are passed through a
heat exchanger to heat the air leaving the high pressure stage compressor.
The air inlet temperature to the unit is 20°C. The isentropic efficiency of each turbine
stage is 0.95; the heat exchanger thermal ratio is 0.7. A mechanical loss is 5% for both
the generator- turbine shaft and the compressor- turbine shaft.
Assume any missed values to Calculate the isentropic efficiency of each compressor,
thermal efficiency and work ratio of the plant, For air take cp is 1.005kJ/kg.K and y-1.4,
and for the gases in the combustion chamber and in the turbines and heat exchanger take
Cp is 1.1 kJ/kg.K, y=1.333.
Expert Solution
This question has been solved!
Explore an expertly crafted, step-by-step solution for a thorough understanding of key concepts.
Step by step
Solved in 3 steps with 19 images
Recommended textbooks for you
Introduction to Chemical Engineering Thermodynami…
Chemical Engineering
ISBN:
9781259696527
Author:
J.M. Smith Termodinamica en ingenieria quimica, Hendrick C Van Ness, Michael Abbott, Mark Swihart
Publisher:
McGraw-Hill Education
Elementary Principles of Chemical Processes, Bind…
Chemical Engineering
ISBN:
9781118431221
Author:
Richard M. Felder, Ronald W. Rousseau, Lisa G. Bullard
Publisher:
WILEY
Elements of Chemical Reaction Engineering (5th Ed…
Chemical Engineering
ISBN:
9780133887518
Author:
H. Scott Fogler
Publisher:
Prentice Hall
Introduction to Chemical Engineering Thermodynami…
Chemical Engineering
ISBN:
9781259696527
Author:
J.M. Smith Termodinamica en ingenieria quimica, Hendrick C Van Ness, Michael Abbott, Mark Swihart
Publisher:
McGraw-Hill Education
Elementary Principles of Chemical Processes, Bind…
Chemical Engineering
ISBN:
9781118431221
Author:
Richard M. Felder, Ronald W. Rousseau, Lisa G. Bullard
Publisher:
WILEY
Elements of Chemical Reaction Engineering (5th Ed…
Chemical Engineering
ISBN:
9780133887518
Author:
H. Scott Fogler
Publisher:
Prentice Hall
Industrial Plastics: Theory and Applications
Chemical Engineering
ISBN:
9781285061238
Author:
Lokensgard, Erik
Publisher:
Delmar Cengage Learning
Unit Operations of Chemical Engineering
Chemical Engineering
ISBN:
9780072848236
Author:
Warren McCabe, Julian C. Smith, Peter Harriott
Publisher:
McGraw-Hill Companies, The