Patent ID: 8813503
Filing Date: 2014-08-26
Classification: F02C,F05D,Y02E

Abstract:
1. A gas turbine system, comprising: a gas turbine comprising an inlet configured to receive inlet air and being configured to combust a fuel to generate power, wherein the gas turbine comprises: a chilling assembly configured to reduce the temperature of the inlet air to produce chilled air at or upstream of the inlet; a low pressure compressor configured to compress the chilled air to produce a first compressed air supply; an intercooler configured to cool the first compressed air supply to produce a cooled air supply; a high pressure compressor configured to compress the cooled air supply to produce a second compressed air supply, wherein the intercooler is disposed in-line between the low pressure compressor and the high pressure compressor; and a combustor configured to combust the fuel in the presence of the second compressed air supply to generate the power; and a control system programmed to determine a first expected condensation level at the intercooler and to control operation of the chilling assembly to produce the chilled air at a temperature corresponding to a second expected condensation level reduced from the first expected condensation level.