Patent ID: 9021779
Filing Date: 2015-05-05
Classification: F02C,F05D,F23J

Abstract:
1. A gas turbine engine system, comprising: a gas turbine engine comprising a compressor, a fuel system, a combustor, and a turbine; a nitrogen oxides reduction system in communication with a flow of combustion gases downstream from the gas turbine engine; and a nitrogen oxides controller operable to control a ratio of nitrogen dioxide to nitrogen monoxide in the flow of combustion gases entering the nitrogen oxides reduction system; wherein the nitrogen oxides controller is operable to determine a desired ratio of nitrogen dioxide to nitrogen monoxide in the flow of combustion gases entering the nitrogen oxides reduction system; wherein the nitrogen oxides controller is in communication with an inlet air conditioner positioned upstream of the compressor, a plurality of inlet guide vanes of the compressor, and/or the fuel system; and wherein the nitrogen oxides controller is operable to change a temperature of the flow of combustion gases entering the nitrogen oxides reduction system until the desired ratio is met by causing the inlet air conditioner to change a temperature of an incoming flow of air, causing the inlet guide vanes to change a flow rate of the incoming flow of air, and/or causing the fuel system to change a flow rate of a flow of fuel to the combustor.