Thermodynamic Analysis of a Gas Turbine

Öz

This study involves analyzing of a natural gas turbine system by using the first and second laws of thermodynamics. As a result of the study, the optimal operating conditions of a gas turbine were determined and some information was given on what needs to be done to increase the efficiency. It was determined that an average of 81.1% of the energy produced in the gas turbine was consumed in the compressor while the compressor compression ratio was 10:1; also an average of 78% while the compressor compression ratio was 15:1, an average of 76.2% while the compressor compression ratio was 20:1 and an average of 75.7% while the compressor compression ratio was 25:1 at compressor air inlet temperatures between 270 and 303 K. A 33^oC increase in compressor inlet temperature leads to a 6% reduction in thermal efficiency when the compressor pressure ratio is 10:1, and leads to a 4.8% reduction when the compressor pressure ratio is 25:1. The increase in the compressor inlet air temperature reduces the thermal efficiency at all compressor pressure ratios. However, the effect of reducing the thermal efficiency of the increase in compressor inlet air temperature is reduced as the compressor pressure ratio increases. Also the reversible work and the second law efficiency of the compressor of the gas turbine system were calculated at different compressor pressure ratios for different compressor air inlet temperatures.

Anahtar Kelimeler

• Gas turbine; Compressor; Thermodynamic analysis; Optimal operating conditions

Kaynakça

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