Abstract: A combustor liner and a method for combusting fuel in air with lowered production of NOX in a stationary, industrial gas turbine. The liner comprises a fuel injection location within the liner at an upstream end of the liner; combustion air openings in a liner wall sized to admit from about 10% to about 25% of total mass airflow entering the liner; suppression air openings in the liner wall from about 0.3 to about 0.5 equivalent diameters downstream of the combustion air openings, the suppression air openings being sized to admit from about 0.8 to about 4 times the mass airflow entering the liner through the combustion air openings; and wall cooling openings distributed in the liner wall for cooling thereof, the wall cooling openings being sized to admit from about 10% to about 40% of the total mass airflow entering the liner.

Abstract: An ambient pressure gas turbine system is provided for mid-range power plants (for example, 1-4 MW) while achieving low NOx emission levels. The system includes a combustor that burns a hydrocarbon fuel at ambient pressure. A first heat exchanger upstream of the combustor heats the working fluid. A turbine downstream from the combustor expands combustion gases. The combustion gases are directed to the first heat exchanger for heat exchange with the working fluid and then to a compressor operative to compress the combustion gases. A second heat exchanger between the first heat exchanger and the compressor further cools the combustion gases to the compressor inlet temperature.

Abstract: A combustor liner and a method for combusting fuel in air with lowered production of NOX in a stationary, industrial gas turbine. The liner comprises a fuel injection location within the liner at an upstream end of the liner; combustion air openings in a liner wall sized to admit from about 10% to about 25% of total mass airflow entering the liner; suppression air openings in the liner wall from about 0.3 to about 0.5 equivalent diameters downstream of the combustion air openings, the suppression air openings being sized to admit from about 0.8 to about 4 times the mass airflow entering the liner through the combustion air openings; and wall cooling openings distributed in the liner wall for cooling thereof, the wall cooling openings being sized to admit from about 10% to about 40% of the total mass airflow entering the liner.

Abstract: A multi-annular swirl burner includes a plurality of overlapping tubular wall members which form a rich combustion zone and a lean combustion zone with a throat section therebetween. Annular passages are located between adjacent wall members, and vanes located therein input a tangential velocity to entering air. The tangential velocity of the swirling flows increases with increasing radius to produce centrifugal separating force on particulates moving from the rich combustion zone to the throat section. A collection system scavenges particulates from the throat section for disposal.