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: An inlet particle separator system is provided. The system includes an axial flow separator for separating air from an engine inlet into a first flow of substantially contaminated air and a second flow of substantially clean air. The system also includes a scavenge subsystem in flow communication with the axial flow separator for receiving the first flow of substantially contaminated air. Finally, the system includes a fluidic device disposed in flow communication with the first flow of substantially contaminated air for inducting air through the scavenge subsystem and the engine inlet.

Abstract: The low emission combustor includes a combustor housing defining a combustion chamber having a plurality of combustion zones. A liner sleeve is disposed in the combustion housing with a gap formed between the liner sleeve and the combustor housing. A secondary nozzle is disposed along a centerline of the combustion chamber and configured to inject a first fluid comprising air, at least one diluent, fuel, or combinations thereof to a downstream side of a first combustion zone among the plurality of combustion zones. A plurality of primary fuel nozzles is disposed proximate to an upstream side of the combustion chamber and located around the secondary nozzle and configured to inject a second fluid comprising air and fuel to an upstream side of the first combustion zone. The combustor also includes a plurality of tertiary coanda nozzles. Each tertiary coanda nozzle is coupled to a respective dilution hole.

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: In one aspect, the present invention provides a subsurface heating device comprising: (a) a combustion conduit casing defining a combustion conduit; (b) at least two combustors disposed within the combustion conduit casing; (c) at least one fuel supply conduit; d) at least one oxygen supply conduit configured to supply oxygen to at least one combustor; and (e) a combustion product gas outlet. The at least two combustors are characterized by an inter-combustor distance of at least one thousand feet and a combustion power of at least 3.41 million BTU per hour. The at least one fuel supply conduit is configured to supply a combustible fuel to at least one combustor. Also provided in another aspect of the present invention, is a method for heating a subsurface zone.

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 flame stabilizer is in fluid communication with a combustor of a gas turbine engine. The flame stabilizer has a body with an aerodynamic shape that creates a flow recirculation zone by injection of fluid through a plurality of holes in the body of the flame stabilizer. The aerodynamic shape of the body reduces pressure loss in the combustor, particularly when no fuel is being provided to the combustor. In addition, the magnitude of the flow recirculation zone can be modulated by selectively adjusting the flow rate of fluid through the holes, or by selectively adjusting the size of the holes.

Abstract: A thrust generator includes an air inlet configured to introduce air within the thrust generator and a plenum having a plurality of fluid injection devices. The plenum is configured to receive an exhaust gas from a gas generator and direct the exhaust gas via the plurality of fluid injection devices radially into the thrust generator and along a Coanda profile surface configured to facilitate attachment of the exhaust gas to the profile surface to form a boundary layer and to entrain incoming air from the air inlet to generate thrust. The thrust generator has a non-circular shape.

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 method of improving emission performance of a gas turbine is provided. The method includes recirculating a portion of an exhaust gas stream to a compressor of the gas turbine via an exhaust gas recirculating system, to reduce concentration of oxygen in a high pressure feed oxidant stream into a combustor of the gas turbine. The method further includes adding diluent to at least one of a fuel stream directed to the combustor or a low pressure feed oxidant stream directed to the compressor, to reduce concentration of oxides of nitrogen (NOx) and increase concentration of carbon dioxide in a resultant exhaust gas stream.

Abstract: A low emission combustor includes a combustor housing defining a combustion chamber. A secondary nozzle is disposed along a centerline of the combustion chamber and configured to inject air or a first mixture of air and fuel on a downstream side of the combustion chamber. The secondary nozzle includes an air inlet configured to introduce a first fluid including air, a diluent, or combinations thereof into the secondary nozzle. At least one fuel plenum is configured to introduce a second fluid including a fuel, another diluent, or combinations thereof into the secondary nozzle and over a predetermined profile proximate to the fuel plenum. The predetermined profile is configured to facilitate attachment of the second fluid to the profile to form a fluid boundary layer and to entrain incoming first fluid through the fluid boundary layer to promote mixing of the first fluid and the second fluid and fuel to produce the first fluid.

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: A combustor-heat exchanger system comprising a plurality of cans. Each can includes an inner cylinder and an outer cylinder forming an annular space in between, wherein the inner cylinder is configured to receive and combust a fuel and compressed oxidant to generate heat and a hot gas. The outer cylinder is configured to receive a portion of a gas lean in carbon dioxide from a turbine system and utilize the heat from the inner cylinder to generate a heated gas. The combustor-heat exchanger further includes an inlet volute along the surface of the inner cylinder configured to receive the portion of the gas lean in carbon dioxide and distribute the gas lean in carbon dioxide into an axial flow through the annular space of each can.

Abstract: A device is provided. The device is configured to introduce a pressurized flow along a Coanda profile and to entrain additional fluid flow to create a high velocity fluid flow; wherein the high velocity fluid flow is directed to an end use system through a flow path in flow communication with the device.

Abstract: A device is provided. The device is configured to introduce a pressurized flow along a Coanda profile and to entrain additional fluid flow to create a high velocity fluid flow; wherein the high velocity fluid flow is directed to an end use system through a flow path in flow communication with the device.

Abstract: A thrust generator is provided. The thrust generator is configured to introduce a motive fluid along a Coanda profile and to entrain additional fluid to create a high velocity fluid flow, wherein the high velocity fluid flow is configured to generate thrust for counter-acting a torque generated by a rotating component.

Abstract: The low emission combustor includes a combustor housing defining a combustion chamber having a plurality of combustion zones. A liner sleeve is disposed in the combustion housing with a gap formed between the liner sleeve and the combustor housing. A secondary nozzle is disposed along a centerline of the combustion chamber and configured to inject a first fluid comprising air, at least one diluent, fuel, or combinations thereof to a downstream side of a first combustion zone among the plurality of combustion zones. A plurality of primary fuel nozzles is disposed proximate to an upstream side of the combustion chamber and located around the secondary nozzle and configured to inject a second fluid comprising air and fuel to an upstream side of the first combustion zone. The combustor also includes a plurality of tertiary coanda nozzles. Each tertiary coanda nozzle is coupled to a respective dilution hole.

Abstract: A low emission combustor includes a combustor housing defining a combustion chamber. A secondary nozzle is disposed along a centerline of the combustion chamber and configured to inject air or a first mixture of air and fuel on a downstream side of the combustion chamber. The secondary nozzle includes an air inlet configured to introduce a first fluid including air, a diluent, or combinations thereof into the secondary nozzle. At least one fuel plenum is configured to introduce a second fluid including a fuel, another diluent, or combinations thereof into the secondary nozzle and over a predetermined profile proximate to the fuel plenum. The predetermined profile is configured to facilitate attachment of the second fluid to the profile to form a fluid boundary layer and to entrain incoming first fluid through the fluid boundary layer to promote mixing of the first fluid and the second fluid and fuel to produce the first fluid.

Abstract: A turbine system is provided. The turbine system includes a compressor configured to compress ambient air and a combustor configured to receive compressed air from the compressor, and to combust a fuel stream to generate an exhaust gas. The turbine system also includes a turbine for receiving the exhaust gas from the combustor to generate electricity; wherein a first portion of the exhaust gas is mixed with the ambient air to form a low-oxygen air stream, and wherein the low-oxygen air stream is compressed using the compressor, and is directed to the combustor for combusting the fuel stream to generate a low-NOx exhaust gas.

Abstract: A thrust generator is provided. The thrust generator includes an air inlet configured to introduce air within the thrust generator and a plenum configured to receive exhaust gas from a gas generator and to provide the exhaust gas over a Coanda profile, wherein the Coanda profile is configured to facilitate attachment of the exhaust gas to the profile to form a boundary layer and to entrain incoming air from the air inlet to generate thrust.