n a marine gas turbine unit, a high-pressure stage turbine drives the compressor and a low-pressure stage turbine drives the propeller through suitable gearing. The overall pressure ratio is 4/1 and the maximum temperature is 650 oC. the isentropic efficiencies of the compressor, H. P. turbine, L. P. turbine are 0.8, 0.83 and 0.85 respectively and the mechanical efficiency of both shafts is 98 %. Sketch the process on the T-s diagram Calculate the pressure between turbine stages when the air intake conditions are 1.01 bar and 25 oC. Calculate also the thermal efficiency and the shaft power when the mass flow is 60 kg/s. NB: Neglect kinetic energy changes and the pressure loss in combustion.
n a marine gas turbine unit, a high-pressure stage turbine drives the compressor and a low-pressure stage turbine drives the propeller through suitable gearing. The overall pressure ratio is 4/1 and the maximum temperature is 650 oC. the isentropic efficiencies of the compressor, H. P. turbine, L. P. turbine are 0.8, 0.83 and 0.85 respectively and the mechanical efficiency of both shafts is 98 %. Sketch the process on the T-s diagram Calculate the pressure between turbine stages when the air intake conditions are 1.01 bar and 25 oC. Calculate also the thermal efficiency and the shaft power when the mass flow is 60 kg/s. NB: Neglect kinetic energy changes and the pressure loss in combustion.
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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In a marine gas turbine unit, a high-pressure stage turbine drives the compressor and a low-pressure stage turbine drives the propeller through suitable gearing. The overall pressure ratio is 4/1 and the maximum temperature is 650 oC. the isentropic efficiencies of the compressor, H. P. turbine, L. P. turbine are 0.8, 0.83 and 0.85 respectively and the
Calculate the pressure between turbine stages when the air intake conditions are 1.01 bar and 25 oC.
Calculate also the thermal efficiency and the shaft power when the mass flow is 60 kg/s.
NB: Neglect kinetic energy changes and the pressure loss in combustion.
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