Abstract: Concepts and technologies described herein provide for the detection of aircraft contrails through the identification of contrail shadows in real time imagery provided during a flight. According to one aspect of the disclosure provided herein, an antisolar point is located on a surface from the perspective of the aircraft in flight. Real time imagery encompassing the antisolar point is received and analyzed for a contrail indicator. When the contrail indicator is detected, it is determined that the aircraft is creating a contrail.

Abstract: A catcher for a gas turbine engine includes a central hub, a plurality of struts, and a first ring. The plurality of struts are connected to and extend outward from the central hub. The first ring is connected to a mid-section of the plurality of struts and extends therebetween.

Abstract: An exhaust plume cooling device for cooling an exhaust gas plume to reduce deleterious heat effects on impinged and surrounding surfaces. The device is supportable in a position downstream of an exhaust nozzle of an exhaust gas plume-producing engine and configured to periodically interrupt the flow of exhaust gases.

Abstract: A system includes a catalyst system having at least one catalyst to treat an exhaust gas from a gas turbine system, and a thermal storage system having at least one storage tank to store thermal energy in a medium, wherein the system is configured to transfer heat from the medium to the at least one catalyst.

Abstract: A microscale energy cogeneration system includes at least a micro/nano-turbine set for converting fuel into mechanical energy, and a generator for converting mechanical energy produced by said micro/nano-turbine into electrical energy in the range of 1 to 5 kWh. The system further includes an exhaust passage downstream from said micro/nano-turbine delivering high temperature exhaust air from said micro/nano-turbine. At least one heat exchanger receives high temperature exhaust air from said exhaust passage for heat transfer. Said heat exchanger may be used to heat water and/or air of a house. A water heating system may be coupled to the heat exchanger for convening tap water into hot water and/or cool heating air into hot air. The portable micro/nano-turbine set may be scaled up by interconnecting several units at the same time and/or interconnecting different units of different users for balancing out the energy demand of those users.

Abstract: The present application thus provides a gas turbine engine system. The gas turbine engine system may include a gas turbine engine, a nitrogen oxides reduction system in communication with a flow of combustion gases downstream from the gas turbine engine, and a nitrogen oxides controller to control the ratio of nitrogen dioxide to nitrogen oxides in the flow of combustion gases entering the nitrogen oxides reduction system.

Abstract: A system is provided that includes a memory storing a turbomachinery degradation model configured to model degradation of a turbomachinery over time. The system also includes a controller communicatively coupled to the memory and configured to control the turbomachinery based on a feedback signal and the turbomachinery degradation model. Moreover, the turbomachinery degradation model is configured to use a target power to derive a control parameter by estimating a modeled power of the turbomachinery, and the controller is configured to use the control parameter to control the turbomachinery.

Abstract: A power plant includes a gas turbine unit adapted to feed flue gases into a boiler of a steam turbine unit, to be then diverted into a recirculated flow and discharged flow. The recirculated flow is mixed with fresh air forming a mixture that is fed into a gas turbine unit compressor. The discharged flow is fed into a CO2 capture unit that is an amine based or chilled ammonia based CO2 capture unit. A cooler for the flue gases can be configured as a shower cooler located upstream of the CO2 capture unit. The plant can also include a washing unit to neutralize ammonia drawn by the flue gases that can be fed with nitric acid gathered at the cooler.

Abstract: In one embodiment, a system is provided that includes a first gas turbine engine. The first gas turbine engine has a first compressor configured to intake air and to produce a first compressed air and a first combustor configured to combust a first mixture to produce a first combustion gas. The first mixture has a first fuel, at least a first portion of the first compressed air, and a second combustion gas from a second gas turbine engine. The first gas turbine engine also includes a first turbine configured to extract work from the first combustion gas.

Abstract: Various embodiments include an exhaust plume mitigation system for a turbine and systems incorporating the exhaust plume mitigation system. In some embodiments, the exhaust plume mitigation system includes: a first conduit fluidly connecting a compressor to an exhaust chamber of the turbine; a first control valve operably connected with the first conduit for regulating flow of compressor air through the first conduit; and a fluid inductor including: a first inlet fluidly connected with the first conduit; a second inlet fluidly connected with ambient; and an outlet fluidly connected with the exhaust chamber.

Abstract: A power generation system capable of eliminating NOxcomponents in the exhaust gas by using a 3-way catalyst, comprising a gas compressor to increase the pressure of ambient air fed to the system; a combustor capable of oxidizing a mixture of fuel and compressed air to generate an expanded, high temperature exhaust gas; a turbine that uses the force of the high temperature gas; an exhaust gas recycle (EGR) stream back to the combustor; a 3-way catalytic reactor downstream of the gas turbine engine outlet which treats the exhaust gas stream to remove substantially all of the NOx components; a heat recovery steam generator (HRSG); an EGR compressor feeding gas to the combustor and turbine; and an electrical generator.

Abstract: An exhaust collector for a gas turbine engine is disclosed. The exhaust collector includes a front panel, a rear panel, and a side panel. The side panel includes a circumferential portion, a first contoured portion, and a second contoured portion. The circumferential portion extends about the exhaust collector axis with a constant radius. The first contoured portion and the second contoured portion are each between the circumferential portion and the exhaust outlet and include a plurality of curved sections with alternating concavity. Each of the plurality of curved sections extends from the front panel to the rear panel.

Abstract: A gas turbine engine, especially a turbojet or turbofan for an aircraft, includes a combustion section and an exhaust section produces an exhaust gas. The emission products can be reduced by using a gas treatment device with a reactor and an injection device. The reactor produces a nitrogeneous substance such as ammonia. This reducing agent is injected in the gas phase in the exhaust section of the gas turbine engine. By selective non catalytic reaction the Nitrogen oxides of the exhaust gas can be reduced. Furthermore the injection device is arranged such that the temperature window of this reduction process is ranging from 850° C. to 1100° C. The reactor for producing gaseous ammonia can either be a thermal reactor or a high pressure plasma device.

Abstract: An exhaust stack includes an inlet section extending along a first axis and an outlet section extending along a second axis. A co-axial silencer is arranged in one of the inlet section and outlet section. The co-axial silencer includes a plurality of concentric baffles configured and disposed to absorb acoustics generated by fluid flow through the exhaust stack.

Abstract: A compressor compresses air to produce compressed air. A mixture of fuel and the compressed air is combusted in a combustor to produce combustion gas. The combustion gas is supplied to a turbine to obtain rotational power. High-temperature gas accumulated in a space partitioned by an exhaust-side bearing portion that rotatably supports a turbine shaft and an exhaust diffuser is discharged through an exhaust gas passage. The high-temperature gas is sucked into the exhaust gas passage by exhaust gas flowing in the exhaust diffuser.

Abstract: A heat recovery system for use with a gasification system is provided. One system includes a gasification system and an organic Rankine cycle system coupled to the gasification system. The organic Rankine cycle system is configured to receive heated fluid from the gasification system and to deliver cooled fluid to the gasification system. The organic Rankine cycle system is configured to produce power by converting heat energy in the heated fluid.

Abstract: The present invention provides methods and system for power generation using a high efficiency combustor in combination with a CO2 circulating fluid. The methods and systems advantageously can make use of a low pressure ratio power turbine and an economizer heat exchanger in specific embodiments. Additional low grade heat from an external source can be used to provide part of an amount of heat needed for heating the recycle CO2 circulating fluid. Fuel derived CO2 can be captured and delivered at pipeline pressure. Other impurities can be captured.

Abstract: A method and gas turbine are provided for the reliable purging of an exhaust gas recirculation line of the gas turbine with exhaust gas recirculation without the use of additional blow-off fans. A blow-off flow of the compressor is used for the purging of the exhaust gas recirculation line. The gas turbine can include at least one purging line which connects a compressor blow-off point to the exhaust gas recirculation line.

Abstract: A method for operating a gas power plant is provided, having a gas turbine which has a compressor stage and a turbine stage, and is connected to a generator via an axle, wherein the generator is designed to also be operated as a motor, wherein the method involves the operation of the generator as a motor for the rotatory operation of the axle, as well as a simultaneous discharge of the heated gas flow exiting from the turbine stage and routing of said gas flow to a first heat exchanger for the transfer of thermal energy from the gas flow to a heat exchanger fluid, wherein the heat exchanger fluid is provided to either discharge thermal energy to a heat accumulating medium or it can be used an accumulating medium itself for temporary storage.

Abstract: A system includes a compressor configured to compress a gaseous stream, an exhaust gas cooler configured to cool an exhaust gas from combustion with a cooling water, and a water injection system configured to inject the cooling water from the exhaust gas cooler into at least one of a compressor inlet of the compressor, a stage of the compressor, between stages of the compressor, or an inlet duct coupled to the compressor inlet of the compressor, or any combination thereof.

Abstract: A combustor of a gas turbine engine is fed with liquid ammonia and that liquid ammonia is burned to drive a turbine. Inside the exhaust passage of the gas turbine engine, an NOX selective reduction catalyst is arranged. Inside the intake air which flows into the compressor, liquid ammonia is fed. This liquid ammonia is used to cool the intake air. The NOX which is contained in the exhaust gas is reduced by the unburned ammonia which is exhausted into the exhaust passage by the NOX selective reduction catalyst.

Abstract: A gas turbine facility 10 of an embodiment has a combustor 20 combusting fuel and oxidant, a turbine 28 rotated by combustion gas exhausted from the combustor 20, a heat exchanger 25 cooling the combustion gas from the turbine 28, a pipe 46 guiding a part of the combustion gas to the combustor 20 via the heat exchanger 25, and a pipe 45 exhausting a remaining part of the combustion gas to an outside. Further, the facility has a pipe 40 supplying fuel to the combustor 20, a pipe 41 supplying oxidant to the combustor 20 via the heat exchanger 25, and a pipe 42 branched from the pipe 41, bypassing the heat exchanger 25, and coupled to the pipe 41, so as to introduce the oxidant into the pipe 41.

Abstract: Embodiments of the present disclosure are directed towards a system including a gas turbine engine configured to produce exhaust gas, a selective catalytic reduction system configured to produce processed exhaust gas from the exhaust gas, and a control system. The control system includes a first controller configured to regulate operation of the selective catalytic reduction system, a second controller configured to regulate operation of the gas turbine engine, and an optimizer configured to coordinate operation of the first controller and the second controller to simultaneously maximize a first level of an emissions compound in the exhaust gas and regulate injection of a reductant into the selective catalytic reduction system to reduce a second level of the emissions compound in the processed exhaust gas to a first desired level of the emissions compound in the processed exhaust gas.

Abstract: Embodiments of the present disclosure are directed towards a system including a gas turbine engine, a selective catalytic reduction system, and a control system configured to regulate operation of the selective catalytic reduction system based at least partially on preset variations in an emissions compound of exhaust gases produced by the gas turbine engine.

Abstract: An exhaust mixer for a gas turbine engine where each outer lobe has at the downstream end a circumferential offset in a direction corresponding to that of the swirl component of the flow entering the mixer. The mixer has a crest line having at least a downstream portion curved with respect with respect to a circumferential direction of the mixer and/or a center line at the downstream end tilted with respect to a radial line extending to the tip of the outer lobe to define the circumferential offset. A method of mixing a core flow and a bypass flow surrounding the core flow with an annular mixer is also provided.

Abstract: A system for reducing emissions includes a gas production source that produces nitrogen oxides, sulfur oxides, hydrogen sulfide, sulfuric acid, nitric acid, formaldehyde, benzene, metal oxides, or volatile organic compound emissions. An exhaust plenum is downstream from the gas production source, and structure for dispersing a solvent is in the exhaust plenum. A collection tank is in fluid communication with the exhaust plenum to receive the solvent from the exhaust plenum, and a heat source is in the exhaust plenum downstream from the structure for dispersing the solvent. A method for reducing emissions from a gas production source includes flowing exhaust gases through an exhaust plenum, dispersing a solvent through a nozzle in the exhaust plenum, collecting the dispersed solvent in a collection tank, and heating the exhaust gases flowing through the exhaust plenum downstream from the nozzle.

Abstract: Advanced gas turbines and associated components, systems and methods are disclosed herein. A gas turbine configured in accordance with a particular embodiment includes a rotor operably coupled to a shaft and a stator positioned adjacent to the rotor. A coolant line extends at least partially through the stator to transfer heat out of an air flow within a compressor section of the gas turbine.

Abstract: In a method for operating a gas turbine, NOx is removed from the exhaust gases of the gas turbine by means of a selective catalysis device with the addition of NH3. The method achieves an extremely low NOx content while simultaneously achieving economic consumption of NH3 and avoiding NH3 in the exhaust gas by maintaining the NOx content of the exhaust gas at a constant level via a regulated return of a portion of the exhaust gas in varying operating conditions of the gas turbine, and by adjusting the addition of the NH3 in the selective catalysis device to the constant NOx level.

Abstract: A system includes a gas turbine engine that includes a combustor section having one or more combustors configured to generate combustion products and a turbine section having one or more turbine stages between an upstream end and a downstream end. The one or more turbine stages are driven by the combustion products. The gas turbine engine also includes an exhaust section disposed downstream from the downstream end of the turbine section. The exhaust section has an exhaust passage configured to receive the combustion products as an exhaust gas. The gas turbine engine also includes a mixing device disposed in the exhaust section. The mixing device is configured to divide the exhaust gas into a first exhaust gas and a second exhaust gas, and to combine the first and second exhaust gases in a mixing region to produce a mixed exhaust gas.

Abstract: A gas turbine having an exhaust gas diffuser connected to a turbine unit is provided, wherein the gas diffuser channel of the gas diffuser is delimited on the outside by a channel wall and has a plurality of hollow supporting fins extending inward for fastening a radial bearing of the gas turbine, wherein at least one blow-off line for blow-off air having at least one pipeline ends at the outlet side on the exhaust gas diffuser and the end of the exhaust gas diffuser on the inlet side is connected to a compressor of the gas turbine. In order to at least partially compensate for incorrect incident flow of the supporting fins, more particularly in partial load operation, the supporting fins have a hub on the inner end thereof, the axial end of said hub having additional openings for blowing out the blow-off air in the diffuser channel.

Abstract: A heating system (50) for heating a cabin (2) of an aircraft (1), said heating system including an annular heat exchanger (10) positioned around an exhaust pipe (21) of a turbine engine (20), and through which a heat transfer fluid (14) and ambient air (25) flow. Said heat exchanger (10) is provided with a rear casing situated at an outlet of said heat exchanger (10) and directing the ambient air (25) exiting form said heat exchanger (10) towards said exhaust gas (15) exiting via said exhaust pipe (21). Said exhaust gas (15) then generates a flow of ambient air (25) through said heat exchanger (10) by the “Coanda” effect. Said ambient air (25) flowing through said heat exchanger (10) is thus heated by convection from said pipe (21), and said heat transfer fluid (14) is heated firstly by radiation from said pipe (21) and secondly by convection between said heat transfer fluid (14) and said ambient air (25).

Abstract: A system for reducing harmful substances in engine exhaust gases includes a fuel cell, which is adapted to generate electrical energy and a steam-containing fuel cell exhaust gas during operation. A fuel tank serves to store fuel which is to be supplied to an engine during operation. A condensing device is connected to an exhaust gas outlet of the fuel cell so that steam-containing fuel cell exhaust gas is supplyable to the condensing device. The condensing device is adapted to convert the steam contained in the fuel cell exhaust gas into the liquid state of aggregation by means of condensation and to introduce the water obtained as a result of the condensing process into the fuel in order to form a water/fuel mixture. A water/fuel mixture line is connected to the engine so that a water/fuel mixture is supplyable to the engine.

Abstract: A system including an energy unit with an outlet for flue gases is disclosed. The system comprises a regulating nozzle for injecting water into the flue gases from the outlet, a condenser apparatus for extracting water from flue gases, a pump for pumping water from the condenser apparatus to the regulating nozzle, the water devoid of any chemical treatment, and a processor for receiving sensor data, calculating target water content of the flue gases at 100% humidity and a dew point of the flue gases and, calculating an amount of water to inject into the flue gases for: 1) increasing a water content of the flue gases to 100% humidity; 2) lowering a temperature of the flue gases to below the dew point and 3) such that the water is absorbed by the flue gases, and transmitting control signals to the regulating nozzle to inject said amount of water.

Abstract: Methods of one or more embodiments include delivering hydrogen sulphide-containing exhaust gases to a current generation device where the gases are burnt, preferably with air being supplied. The energy released during combustion is employed at least partially for current generation. One or more embodiments also include an apparatus for current generation in which supplied hydrogen sulphide-containing exhaust gases are burnt, preferably with air being supplied.

Abstract: A turbomachine assembly for recovering waste heat generally has a compressor section that is configured to generate a compressed fluid flow and to channel the compressed fluid flow within the turbomachine assembly. A turbine section is coupled to the compressor section via a rotating member such that portions of the rotating member are located within the compressor section and the turbine section, respectively. The turbine section is in flow communication with the compressor section such that the compressed fluid flow is received by the turbine section. At least one heat exchanger is positioned at least partly within the turbine section where the heat exchanger receives waste heat energy. The heat exchanger transfers energy from the waste heat into the compressed fluid flow to increase at least one parameter of the compressed fluid flow contributing to the generation of a power output.

Abstract: A turbine engine shutdown temperature control system configured to foster consistent air temperature within cavities surrounding compressor and turbine blade assemblies to eliminate turbine and compressor blade tip rub during warm restarts of gas turbine engines is disclosed. The turbine engine shutdown temperature control system may include one or more casing temperature control housings extending along an inner surface of a casing at an outer diameter of the casing and at an upper side region of the casing. The upper side region may be positioned above a horizontally extending centerline of the casing. Fluids may be exhausted from one or more exhaust slots in the casing temperature control housing to isolate the upper side region of the casing from buoyancy effects of hot gases within the casing after shutdown of the gas turbine engine.

Abstract: To provide a method for producing a catalyst flow element (100) by means of which robustly constructed catalyst flow elements (100) usable in a broad field of operation are producible, it is proposed that the following method steps be performed in the method: providing a main body (102) including a plurality of flow channels (104); introducing slots (116) into partition walls (110) of the main body (102), which separate the flow channels (104) from one another such that at least two adjacent flow channels (104) are connected together fluidically within the main body (102) in a common end region (130) of the at least two adjacent flow channels (104); and arranging channel closures (118) in the common end region (130) for fluid-tight closure of the common end region (130) while maintaining the fluidic connection between the at least two adjacent flow channels (104) in the common end region (130).

Abstract: A mixer for a confluent-flow nozzle of a turbine engine is provided. The mixer includes: an annular cap designed to be centered on a longitudinal axis of the nozzle and having a stationary upstream portion and a downstream portion that is movable in rotation about the longitudinal axis relative to the stationary portion, the movable portion of the cap terminating at its downstream end in inner lobes alternating circumferentially with outer lobes; and a mechanism which imparts reciprocating rotary motion to the movable portion of the cap.

Abstract: A gas turbine generator set includes a compressor unit including at least one compressor, at least one generator and at least one combustion chamber. Exhaust gases from at least one turbine are recirculated for a further thermal utilization. At least one cooling fluid compressor is configured to compress a cooling fluid including at least one of fresh air and a portion of the recirculated exhaust gases for a cooling of thermally loaded parts.

Abstract: A guide system for translating components of an aircraft engine nacelle includes a track assembly and a slider assembly. The track assembly includes a track guide member and a track liner engaged therewith. The track guide member includes a track channel configured to receive the track liner. The track liner defines an interior surface and includes a projection portion projecting inwardly of the track channel to define a convex surface. The slider assembly translatably engages the track assembly and includes a slider member having a head portion configured to be received within the track channel. The head portion defines a concave surface substantially corresponding to the convex surface of the track liner and is configured to mate therewith. The slider member further includes an extension portion extending from the head portion and outwardly of the track assembly.

Abstract: In a silencer, holes are disposed in one row with intervals to each other along one direction, holes forming the one row are disposed in a plurality of rows in a direction perpendicular to the one direction, and positions of the holes in adjacent rows are shifted in the one direction and disposed in a zigzag pattern. A disposition interval of the holes of an outer edge hole row forming one row in at least two sides opposite to each other in the silencing porous plate is set to be larger than a disposition interval of the holes of a row inside the outer edge hole row.

Abstract: A turbine outlet frozen gas capture apparatus is provided and includes an enclosure divided into first and second chambers, the first chamber being receptive of turbine outlet exhaust including frozen gas, a wheel disposed and configured to be rotatable such that frozen gas received in the first chamber is captured and transported into the second chamber and a heater disposed within the second chamber and configured to vaporize the frozen gas transported therein to thereby produce vaporized gas.

Abstract: A combined cycle power plant including a gas turbine engine having a first compressor providing compressed air for combustion to form a hot working gas, and a turbine section for expanding the hot working gas. A first heat recovery steam generator (HRSG) is provided for receiving an exhaust gas flow from the turbine section to form a reduced temperature exhaust gas and to produce a high pressure steam flow which is provided to a high pressure steam turbine. A second compressor is provided for receiving and compressing the reduced temperature exhaust gas to add energy and form a reheated exhaust gas. A second heat recovery steam generator (HRSG) is provided for receiving and removing heat from the reheated exhaust gas to produce a low pressure steam flow, and a low pressure steam turbine is provided for receiving and expanding the low pressure steam flow.

Abstract: A simple cycle gas turbomachine includes a compressor portion, and a turbine portion having an outlet. At least one combustor is fluidically connected to the compressor portion and the turbine portion. An exhaust member includes an inlet, fluidically connected to the outlet of the turbine portion, a first outlet and a second outlet. A fuel conditioning system includes a heat exchange member provided with a first circuit having an exhaust gas inlet fluidically connected to the second outlet of the exhaust member and an exhaust gas inlet, a second circuit having an inlet fluidically connected to a source of fuel and an outlet fluidically connected to the at least one combustor. A conditioned fluid conduit is fluidically connected between a source of conditioned fluid and one of the combustor assembly and the first outlet of the exhaust member.

Abstract: A gas turbine exhaust diffuser includes a frustoconical portion that defines an interior surface and an axial centerline. In particular embodiments, the interior surface may have a slope greater than 6 degrees, 10 degrees, or 20 degrees with respect to the axial centerline to define an axial cross-sectional area of at least 200 square feet, 240 square feet, or 260 square feet. In other particular embodiments, the interior surface may have an axial length of less than 25 feet or less than 10 feet. A helical turbulator on the interior surface of the frustoconical portion may reduce flow separation between exhaust gases and the interior surface to enhance recovery of potential energy from the exhaust gases.

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 method includes i) identifying a period of operation corresponding to a fuel supply requirement; ii) determining at least one ambient air condition in which the machine will operate during the period; iii) determining a duration of time in which, whilst in the ambient air condition, it is required to achieve a predetermined vapor trail characteristic; iv) determining a resultant fuel composition for use by the machine in the ambient air condition to achieve the characteristic, where the resultant fuel composition includes at least one of the first and second fuel compositions; v) determining the ratio of at least the first and second fuel compositions required for sufficient resultant fuel composition for the duration of time determined in step iii); and vi) producing a first signal indicative of the ratio of at least the first and second fuel compositions required for the duration of time determined in step iii).

Abstract: A cooling system is provided for an aero gas turbine engine. The system has a duct which diverts a portion of a bypass air stream of the engine. A heat exchanger located in the duct receives cooling air for cooling components of the engine. The cooling air is cooled in the heat exchanger by the diverted bypass air stream. After cooling the cooling air, the spent diverted air stream is routed to a tail cone located at the exit of the engine and ejected through a nozzle at the tail cone.

Abstract: The invention relates to a gas turbine power plant, having a gas turbine, a waste heat steam generator following the gas turbine, an exhaust gas recooler, an exhaust gas blower, a carbon dioxide separation plant which separates the carbon dioxide contained in the exhaust gases from these and discharges it to a carbon dioxide outlet. A bypass chimney is arranged in the gas turbine power plant between the outlet of the waste heat steam generator and the exhaust gas blower and is connected to a fail-safe open connection both in the throughflow direction from the exhaust gas line to the bypass chimney and in the throughflow direction from the bypass chimney to the exhaust gas line. The invention relates, further, to a method for operating a gas turbine power plant of this type, in which the exhaust gas blower is regulated.

Abstract: The present techniques are directed to a system and method for generating power and producing liquefied natural gas (LNG). The system includes a power plant configured to generate power, wherein an exhaust gas from the power plant provides a gas mixture including nitrogen and carbon dioxide. The system also includes a dehydration system configured to dehydrate the gas mixture to generate a nitrogen refrigerant stream and a refrigeration system configured to produce LNG from a natural gas stream using the nitrogen refrigerant stream.