Abstract: A power generation system includes a gas turbine system. The turbine system includes a combustion chamber configured to combust a fuel stream a compressor configured to receive a feed oxidant stream and supply a compressed oxidant to the combustion chamber and an expander configured to receive a discharge from the combustion chamber and generate an exhaust comprising carbon dioxide and electrical energy. The system further includes a retrofittable exhaust gas recirculation system including a splitter configured to split the exhaust into a first split stream and a second split stream, a heat recovery steam generator configured to receive the first split stream and generate a cooled first split stream and a purification system configured to receive the first cooled split stream and the second split stream and generate a recycle stream, wherein the recycle stream is mixed with the fresh oxidant to generate the feed oxidant stream.

Abstract: A flexible fuel fuel-air mixer includes an annular shroud; a center body; an inner swirler disposed around an outer surface of the center body; a low-energy-content fuel plenum having an annul us formed by inner and outer shrouds forming a gap therebetween, a fuel inlet, and a fuel plenum swirler disposed in the gap; an outer swirler having an inner circumferential end portion disposed around the outer shroud of the fuel plenum; and a high-energy-content fuel shroud disposed at the upstream end portion of the annular shroud outwardly from the second swirler in the radial direction and circumferentially around the annular shroud, the fuel shroud being in flow communication with the outer swirler.

Abstract: A combined cycle system includes, a pre-steam-methane-reformer operating at a temperature of less than about 800 degrees Celsius to reform a mixed fuel stream to generate a first reformate stream, a water-gas-shift reactor to convert carbon monoxide in the first reformate stream to carbon dioxide and form a second reformate stream, a carbon dioxide removal unit for removing carbon dioxide from the second reformate stream and form a carbon dioxide stream and a third reformate stream; wherein less than about 50 percent of the carbon contained in the mixed fuel stream is recovered as carbon dioxide by the removal unit, a gas turbine unit for generating power and an exhaust stream, and a steam generator unit configured to receive the exhaust stream, wherein the heat of the exhaust stream is transferred to a water stream to generate the steam for the mixed fuel stream and for a steam turbine.

Abstract: A turbine system comprises a compressor for compressing air to generate a compressed flow, an air separation unit for receiving and separating at least a portion of the compressed flow into oxygen and a low-oxygen stream, a combustor for receiving and combusting at least a portion of the low-oxygen stream, a portion of the compressed flow and a fuel to generate a high temperature exhaust gas, and a turbine for receiving and expanding the high temperature exhaust gas to generate electricity and a reduced temperature low-NOx exhaust gas.

Abstract: A system for reducing NOx emissions, includes a reformer configured to receive a fuel and produce a hydrogen-enriched stream, a combustion system configured to burn the hydrogen enriched-stream and produce electricity and an exhaust stream, and a recuperator configured to recover heat from the exhaust stream, wherein the recovered heat is recycled back to the reformer.

Abstract: Guide vanes include a first flange connected with a casing of a gas turbine engine, a second flange connected with the casing, a first airfoil disposed between the first and second flanges and connected thereto, and a second airfoil disposed between the first and second flanges and connected thereto so as to form a gap extending radially between a first trailing portion of the first airfoil and a second leading portion of the second airfoil, the hollow portion being in flow communication with the gap so as to allow a gaseous fuel to flow from the hollow portion through the gap and into a fluid flowing over the guide vane. Gas turbines that use the guide vanes and methods for injecting a gaseous fuel for combustion in a gas turbine engine are also disclosed.

Abstract: A fuel-air mixer includes an annular shroud, inner and outer counter-rotating swirlers, a hub separating the inner and outer swirlers, a center body extending axially along the annular shroud, a fuel shroud disposed radially outwardly from the outer swirler circumferentially around the annular shroud, and a radial swirler disposed downstream of the inner and outer swirlers, the radial swirler being configured to allow an independent radial rotation of a second gas stream entering the annular shroud from a region outside a wall of the annular shroud separately from a stream flowing through the inner and outer swirlers, the radially rotating second gas stream entering the annular shroud at a region adjacent an outer wall of the annular shroud.

Abstract: A combustor for a gas turbine engine comprises a housing, and a swirler assembly disposed in physical communication with the housing. The swirler assembly comprises a first stage comprising a plurality of first vanes, a second stage comprising a plurality of second vanes, and a third stage comprising a plurality of third vanes. The second stage is disposed downstream of, in fluid communication with, and in physical communication with the first stage. The third stage is disposed downstream of, in fluid communication with, and in physical communication with the second stage.

Abstract: A fuel/oxidant premixing device for a gas turbine includes an annular array of Coanda profiled fuel injected airfoils configured to receive a fluid stream containing the oxidant, wherein each one of the airfoils comprises a leading edge, a trailing edge and a fuel injection opening configured for introducing fuel at about the leading edge to provide a Coanda effect. Also disclosed herein are methods for its operation.

Abstract: A device is provided. The device includes an inlet manifold configured to direct an exhaust gas flow within the device, an air inlet configured to introduce an airflow within the device and at least one surface of the device having a Coanda profile configured to entrain incoming air through the exhaust gas flow to generate a high velocity airflow.

Abstract: A carbon dioxide separation system comprises a first flow path for directing a fluid comprising carbon dioxide therethrough, a second flow path for directing a sweep fluid therethrough, and a separator comprising a material with selective permeability of carbon dioxide for separating the first and the second flow paths and for promoting carbon dioxide transport therebetween. A carbon dioxide separation unit is in fluid communication with the second flow path for separating the transported carbon dioxide from the sweep fluid.

Abstract: A carbon dioxide separation system comprises a heat exchanger having a first flow path for directing a fluid comprising carbon dioxide, for example an exhaust gas, therethrough and a second flow path for directing a heat transfer fluid therethrough, a separator comprising a material with selective permeability of carbon dioxide for separating the first and second flow paths and for promoting thermal transfer and carbon dioxide transport therebetween, and a condenser for condensing the heat transfer fluid to isolate the carbon dioxide.

Abstract: A power generation system and method includes a first gas turbine system comprising a first combustion chamber configured to combust a first fuel stream of primarily hydrogen that is substantially free of carbon-based fuels. The first gas turbine system also includes a first compressor configured to supply a first portion of compressed oxidant to the first combustion chamber and a first turbine configured to receive a first discharge from the first combustion chamber and generate a first exhaust and electrical energy. The power generation system further includes a second gas turbine system comprising a second combustion chamber configured to combust a second fuel stream to generate a second discharge. The first compressor of the first gas turbine system is configured to supply a second portion of compressed oxidant to the second combustion chamber.