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
![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.](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2F689f95fd-5a58-4a43-b410-4b8387818801%2F1f9c475e-7f3d-41f1-a030-4f5401f99678%2Fvitiqne_processed.jpeg&w=3840&q=75)
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.
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