Patent application number | Description | Published |
20080309087 | SYSTEMS AND METHODS FOR POWER GENERATION WITH EXHAUST GAS RECIRCULATION - 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. | 12-18-2008 |
20080315042 | THRUST GENERATOR FOR A PROPULSION SYSTEM - 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. | 12-25-2008 |
20090218821 | LOW EMISSION TURBINE SYSTEM AND METHOD - 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-NO | 09-03-2009 |
20090314000 | COANDA PILOT NOZZLE FOR LOW EMISSION COMBUSTORS - 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. A plurality of primary fuel nozzles are disposed proximate on an upstream side of the combustion chamber and located around the secondary nozzle and configured to inject air or a second mixture of air and fuel to an upstream side of the combustion chamber. | 12-24-2009 |
20100011771 | COANDA INJECTION SYSTEM FOR AXIALLY STAGED LOW EMISSION COMBUSTORS - 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. The tertiary coanda nozzles are configured to inject a third fluid comprising air, at least one other diluent, fuel, or combinations thereof to one or more remaining combustion zones among the plurality of combustion zones. | 01-21-2010 |
20100019079 | THRUST GENERATOR FOR A ROTARY WING AIRCRAFT - 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. | 01-28-2010 |
20100034642 | DEVICE FOR ENHANCING EFFICIENCY OF AN ENERGY EXTRACTION SYSTEM - 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. | 02-11-2010 |
20110138766 | SYSTEM AND METHOD OF IMPROVING EMISSION PERFORMANCE OF A GAS TURBINE - 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. | 06-16-2011 |
20110219776 | AERODYNAMIC FLAME STABILIZER - 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. | 09-15-2011 |
20130255267 | SYSTEM AND METHOD OF IMPROVING EMISSION PERFORMANCE OF A GAS TURBINE - A power generation system and method of generating power with reduced NO | 10-03-2013 |
Patent application number | Description | Published |
20110162342 | SYSTEM AND METHOD FOR LOW EMISSIONS COMBUSTION - 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. | 07-07-2011 |
20120103604 | SUBSURFACE HEATING DEVICE - 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. | 05-03-2012 |
20120167570 | SCULPTED TRAILING EDGE SWIRLER COMBUSTION PREMIXER AND METHOD - Methods and devices useable in turbo-engines premixing of compressed air and fuel are provided. A premixer has a mixing part configured to receive a gas flow input in a flow direction and fluid fuel injected substantially perpendicular to the flow direction. The mixing part has a rim configured to define a substantially cylindrical shape. The mixing part also has a swirler with (i) a center body located substantially in a middle of the cylindrical shape along the flow direction, and (ii) a set of vanes extending from the center body towards the rim, the vanes being configured to determine a rotation motion inside a flow that includes the received gas flow and the injected fuel when the flow passes through the mixing part, at least some of the vanes having a trailing edge with a waving profile configured to generate mixing zones inside the flow thereafter. | 07-05-2012 |
20120248217 | BI-DIRECTIONAL FUEL INJECTION METHOD - In certain embodiments, a fuel injector includes a wall separating a fuel passage from an air passage. The fuel injector also includes a fuel injection port extending from a first side of the wall to a second side of the wall for injecting a flow of fuel from the fuel passage into a flow of air in the air passage. In addition, the fuel injector includes first and second feedback lines extending from a downstream end of the fuel injection port to an upstream end of the fuel injection port. The first and second feedback lines are disposed on opposite sides of the fuel injection port. In addition, the first and second feedback lines are disposed entirely within the wall. | 10-04-2012 |
Patent application number | Description | Published |
20110215204 | SYSTEM AND METHOD FOR GENERATING THRUST - 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. | 09-08-2011 |
20120131900 | INLET PARTICLE SEPARATOR SYSTEM - 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. | 05-31-2012 |
20120151932 | TRAPPED VORTEX COMBUSTOR AND METHOD OF OPERATING THEREOF - A trapped vortex combustor includes a trapped vortex cavity having a first surface and a second surface. A plurality of fluidic mixers are disposed circumferentially along the first surface and the second surface of the trapped vortex cavity. At least one fluidic mixer includes a first open end receiving a first fluid stream, a coanda profile in the proximity of the first open end, a fuel plenum to discharge a fuel stream over the coanda profile, and a second open end for receiving the mixture of the first fluid stream and the fuel stream and discharging the mixture of the first fluid stream and the fuel stream in the trapped vortex cavity. The coanda profile is configured to enable attachment of the fuel stream to the coanda profile to form a boundary layer of the fuel stream and, to entrain the incoming first fluid stream to the boundary layer of the fuel stream to form a mixture of the first fluid stream and the fuel stream. | 06-21-2012 |
20120151935 | GAS TURBINE ENGINE AND METHOD OF OPERATING THEREOF - A method for operating a gas turbine engine includes compressing an air stream in a compressor and generating a post combustion gas by combusting a compressed air stream exiting from the compressor in a combustor. The post combustion gas is expanded in a first turbine. The expanded combustion gas exiting from the first turbine is split into a first stream and a second stream. The first stream of the expanded combustion gas is combusted in a reheat combustor. The reheat combustor is cooled using the second stream of the expanded combustion gas. | 06-21-2012 |
20130152599 | HYDROCARBON FILM PROTECTED REFRACTORY CARBIDE COMPONENTS AND USE - A turbine power generation system with enhanced stabilization of refractory carbides provided by hydrocarbon from high carbon activity gases is disclosed. The disclosure also includes a method of using high carbon activity gases to stabilize hot gas path components. | 06-20-2013 |