THERMODYNAMIC STUDY OF ADVANCED GAS TURBINE COOLING SYSTEM

Abstract

A gas turbine's power output is directly proportional to and limited by the mass flow rate of compressed air available to it from the air compressor that supplies highpressure air to the gas turbine system's combustion chamber. An air compressor has a set capacity for handling a volumetric flow rate of air. Even though a compressor's volumetric capacity is constant, with changes in ambient air temperature, the mass flow rate of air it supplies to the gas turbine changes. With rising ambient temperature, this mass flow rate of air decreases as the density of air decreases as the temperature of the air increases. Therefore, when there is a rise in ambient temperature, the power output of a combustion turbine decreases below its rated capacity, so this paper deals with various inlet air cooling systems integrated into gas turbines. The purpose of this analysis is to combine two separate cooling systems (evaporative cooling system and mechanical cooling system). Modeling of thermodynamics is carried out and presented along with results that demonstrate the effect of the integrated cooling system on different gas turbine output parameters and their main environmental benefits and disadvantages. The incorporation of the inlet air cooling system reduces the air compression work required and increases the gas turbine's net working performance and thus increases the gas turbine's overall efficiency. The simulation is also carried out using various parameters to change.