Solve the bellow question: In a marine gas turbine unit, a High-pressure turbine stage drives the compressor, and a low-pressure turbine stage drives the propeller through suitable gearing. The overall pressure ratio is (4/1), and the maximum temperature is (650 C). The isentropic efficiencies of the compressor, HP and LP turbines are (80, 83 and 85%) respectively, and the mechanical efficiency of both shafts is (98%). Calculate the pressure between turbine stages when the air intake condition are (1.01 bar and 25 C). Also, calculate the thermal efficiency and the shaft power when the mass flow is (60 kg/s). Neglect changes in kinetic energy and the pressure losses in the combustion chamber.
Solve the bellow question: In a marine gas turbine unit, a High-pressure turbine stage drives the compressor, and a low-pressure turbine stage drives the propeller through suitable gearing. The overall pressure ratio is (4/1), and the maximum temperature is (650 C). The isentropic efficiencies of the compressor, HP and LP turbines are (80, 83 and 85%) respectively, and the mechanical efficiency of both shafts is (98%). Calculate the pressure between turbine stages when the air intake condition are (1.01 bar and 25 C). Also, calculate the thermal efficiency and the shaft power when the mass flow is (60 kg/s). Neglect changes in kinetic energy and the pressure losses in the combustion chamber.
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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Transcribed Image Text:Solve the bellow question:
In a marine gas turbine unit, a High-pressure turbine
stage drives the compressor, and
a low-pressure turbine stage drives the propeller
through suitable gearing. The overall
pressure ratio is (4/1), and the maximum temperature is
(650 C). The isentropic
efficiencies of the compressor, HP and LP turbines are
(80, 83 and 85%) respectively,
and the mechanical efficiency of both shafts is (98%).
Calculate the pressure between
turbine stages when the air intake condition are (1.01
bar and 25 C). Also, calculate the
thermal efficiency and the shaft power when the mass
flow is (60 kg/s). Neglect changes
in kinetic energy and the pressure losses in the
combustion chamber.
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