Abstract: A method for producing hydrogen by thermochemical splitting of water includes injecting one or more feed streams of water into a reaction chamber. The method further includes using heat from a subterranean heat source to carry out the thermochemical splitting of water to form hydrogen and oxygen in the reaction chamber. The formed products are subsequently removed from the reaction chamber.

Abstract: A power plant including a compressor, a combustion chamber and a turbine, and a compressor air line, which connects the compressor to the combustion chamber, a first heat exchanger connected into the compressor air line and into an exhaust line branching off the turbine. A first expander is arranged between the first heat exchanger and the combustion chamber in the compressor air line, and the first expander and the compressor are arranged on a common shaft.

Abstract: A cooling system configured to reduce a temperature within a gas turbine engine in a shutdown mode of operation includes a first gas turbine engine including a compressor having a bleed port. In a first operating mode of the gas turbine engine, the compressor bleed port is configured to channel a high pressure flow of air from the compressor. During a shutdown mode of operation, the compressor bleed port is configured to channel an external flow of cooling air into the compressor. The cooling system also includes a source of cooling air and a conduit coupled in flow communication between the compressor bleed port and the source of cooling air. The source of cooling air configured to deliver a flow of cooling air into the compressor through the compressor bleed port.

Abstract: A gas turbine engine includes a compressor section having a high pressure compressor and a core casing surrounding the compressor section and defining an inlet. The gas turbine engine also includes a cooling system for cooling air in or to the compressor section. The cooling system includes a fluid tank for storing a volume of cooling fluid and a fluid line assembly in fluid communication with the fluid tank. The fluid line assembly includes an outlet positioned upstream of the high pressure compressor and downstream of the inlet defined by the core casing for injecting cooling fluid into an airflow upstream of the high pressure compressor.

Abstract: The combustion device includes: a compressor that compresses combustion air; a combustor that combusts the compressed combustion air and fuel ammonia; and an ammonia injector that injects the fuel ammonia into the combustion air during or before compression of the combustion air by the compressor and cools the combustion air.

Abstract: Power output and thermal efficiency of combustion turbine depend on the compressor inlet air temperatures. The lower the temperature, the higher is the power output and thermal efficiency. This system employs a gas turbine in a simple or combined cycle configuration for electrical power generation with an air inlet receiving chilled air. Air is chilled using a plurality of interconnected channels containing a fluid and comprising a plurality of coils, an ambient air inlet in fluid communication with the plurality of coils, a chiller unit, an accumulator tank with an at least one entrance and an exit in fluid communication with the plurality of interconnected channels; a pump, shutoff valves, and a control valve. The electric energy storage system has a charging and discharging cycles.

Abstract: There is provided a fluid detection device that detects a flow velocity or a flow rate of a fluid flowing through a piping, the fluid detection device including: a sound detection unit that detects a sound from the piping, and outputs a frequency signal; a signal processing unit that calculates a strength ratio of the frequency signal on the basis of the frequency signal and a predetermined reference frequency signal; and a data conversion unit that obtains the flow velocity or the flow rate on the basis of the strength ratio of the frequency signal and a predetermined fluid characteristic function.

Abstract: A reverse flow gas turbine engine has a low pressure (LP) spool and a high pressure (HP) spool arranged sequentially in an axial direction. The LP spool comprises an LP compressor disposed forward of an LP turbine and drivingly connected thereto via an LP compressor gear train. The HP spool comprises an HP compressor in flow communication with the LP compressor, and an HP turbine disposed forward of the HP compressor and drivingly connected thereto via an HP shaft.

Abstract: By using a combustion flue gas (18) from a power turbine (16), a high-pressure secondary compressed air (12C) is subjected to heat exchange in a first heat exchange unit (19A) of an exhaust heat recovery device (19), and by using resultant heat-exchanged flue gas (18A), a low-pressure primary compressed air (12A) is subjected to heat recovery in a second heat exchange unit (19B) of a saturator (31). Then, a primary compressed air (12B) that has been subjected to heat recovery in the second heat exchange unit (19B) is introduced into a secondary air compressor (22) to increase the pressure of the air, and then the high-pressure air is subjected to heat recovery in the first heat exchange unit (19A), producing a secondary compressed air (12D). The secondary compressed air (12D) is introduced into a combustor (14) and combusted using fuel.

Abstract: A gas turbine engine includes a fan section including a fan hub. A speed reduction device includes a star gear system. A turbine section is connected to the fan section through the speed reduction device. A first fan bearing for supporting rotation of the fan hub is connected forward of the speed reduction device. A second fan bearing for supporting rotation of the fan hub is connected aft of the speed reduction device. A first outer race of the first fan bearing is attached to the fan hub.

Abstract: A method for cooling down a gas turbine, wherein the gas turbine is run down from the power operation thereof to cool-down operation, and wherein a liquid is sprayed into air sucked in by a compressor of the gas turbine during the cool-down operation, and wherein the liquid is sprayed into the sucked-in air in dependence on a humidity of the sucked-in air, a flow velocity of cooling air flowing in the gas turbine in the region of at least one flow-guiding component of the gas turbine, which component is to be cooled, and a temperature difference between a temperature of the sucked-in air and a temperature of the at least one flow-guiding component of the gas turbine.

Abstract: A hydraulic fracturing system for fracturing a subterranean formation is disclosed. In an embodiment, the system may include a plurality of electric pumps configured to pump fluid into a wellbore associated with a well at a high pressure; at least one turbine generator electrically coupled to the plurality of electric pumps so as to generate electricity for use by the plurality of electric pumps, each turbine generator having at least one air intake channel; and an air chiller system associated with the at least one turbine generator, the air chiller system comprising: a chiller unit configured to chill a fluid; and at least one coil in fluid communication with the chiller unit and positioned adjacent to the at least one air intake channel, wherein the air chiller system is configured to increase a power output of the at least one turbine generator.

Abstract: A method of operating a turbine assembly is provided. The method includes receiving a flow of air at a filter house that includes a first heat exchanger. The temperature of the air is controlled with the first heat exchanger by one of selectively cooling the air and by selectively heating the air. The air is then channeled from the first heat exchanger to a second heat exchanger to facilitate cooling the air.

Abstract: An object of the present invention is to provide a method and a system for implementing the method so as to alleviate the disadvantages of a reciprocating combustion engine and gas turbine in electric energy production. The invention is based on the idea of arranging a combustion chamber (10) outside a gas turbine (22) and providing compressed air to the combustion chamber (10) in order to carry out a combustion process in controlled and optimal conditions.

Abstract: In one or more of the inventive aspects, when a gas turbine system of a power plant operates at part load, a moisture content of fuel gas provided to the gas turbine system may be controlled so as to minimize combustion dynamics and/or to comply with emission requirements. The fuel gas moisture content may be controlled by modulating a flow of heated water to a fuel moisturizer. By using heated water from a heat recovery steam generator to moisturize the fuel gas, heat energy from the water may be transferred to the fuel gas, and the overall mass flow may be enhanced to thereby increase overall combined cycle efficiency.

Abstract: A staged dry out process and control system for an evaporative media cooling system having a plurality of media stages that are selectively activated and deactivated by a control system is disclosed. The staged dry out process ensures that wet media stages are appropriately dried with minimal disruption to the staging strategy implemented by the control system. In one aspect, the staged dry out process monitors deactivated media stages to determine if the media stages reach a dry state before being activated. In another aspect, the staged dry out process locks out a media stage that has been in a wet state beyond a predetermined maximum time limit until the media stage attains a dry state. With this strategy the cooling system can operate without being required to completely shut down for a drying process.

Abstract: Embodiments of the invention can provide systems and methods for determining a target exhaust temperature for gas turbines. In one embodiment of the disclosure, there is disclosed a method for determining a target exhaust temperature for a gas turbine. The method can include determining a target exhaust temperature based at least in part on a compressor pressure condition; determining a temperature adjustment to the target exhaust temperature based at least in part on steam humidity; and changing the target exhaust temperature based at least in part on the temperature adjustment.

Abstract: A method for controlling an exhaust gas recovery system for an engine includes generating a signal to control exhaust gas flow through an exhaust gas heat exchanger, and generating a diagnostic code based on a difference between coolant temperature downstream of the exhaust gas heat exchanger and coolant temperature downstream of the engine. A vehicle has an engine, and an exhaust heat recovery system with an exhaust gas heat exchanger, a first temperature sensor downstream of the engine, and a second temperature sensor downstream of the exhaust gas heat exchanger. A controller for the vehicle is configured to: (i) generate a signal to control exhaust gas flow through the exhaust gas heat exchanger, and (ii) generate a diagnostic code based on a difference between coolant temperature measured by the first and second temperature sensors.

Abstract: An engine wash system for delivering wash liquid to an engine with a lift fan and a main engine, the lift fan including a plurality of inlet guide vanes and a nose cone, and the main engine connected to the lift fan by a shaft, the engine wash system includes a lift fan manifold to deliver wash liquid to the lift fan; and a main engine manifold to deliver wash liquid to the main engine, wherein the lift fan manifold and the main engine manifold can deliver the wash liquid simultaneously.

Abstract: A gas turbine for a gas and steam turbine plant and method for operating a gas turbine is provided. The gas turbine includes a cooling system for cooling inlet air taken from compressor extractions or compressor discharge and introduced to the turbine(s) and/or combustor(s) of the gas turbine which is adapted for flexible operation in a combined cycle application as well as a simple cycle application. The cooling system includes at least a water/steam cooled cooling air cooler for use in a normal combined cycle application. The gas turbine is provided with at least one second cooling air system arranged in a bypass which is operable instead of or parallel to the water/steam cooled cooling air cooler for use in particular in a simple cycle application operation of the gas turbine.

Abstract: Provided is a gas turbine system capable of dealing with a request for output increase even when high-pressure hot water generated using solar thermal energy cannot be used according to the operating state of the gas turbine system. A gas turbine system which sucks in intake air from an air intake duct by a compressor and drives a gas turbine by combustion gas obtained by burning air and fuel by a combustor, said gas turbine system being provided with pipes for generating high-pressure hot water by providing a solar collecting tube that utilizes solar heat and spraying the high-pressure hot water into the intake air sucked in by the compressor, and pipes for spraying normal temperature water into the intake air sucked in by the compressor.

Abstract: A shell air recirculation system for use in a gas turbine engine includes one or more outlet ports located at a bottom wall section of an engine casing wall and one or more inlet ports located at a top wall section of the engine casing wall. The system further includes a piping system that provides fluid communication between the outlet port(s) and the inlet port(s), a blower for extracting air from a combustor shell through the outlet port(s) and for conveying the extracted air to the inlet port(s), and a valve system for selectively allowing and preventing air from passing through the piping system. The system operates during less than full load operation of the engine to circulate air within the combustor shell but is not operational during full load operation of the engine.

Abstract: Variable speed drive controlled discharge pumps are used for pumping chilled water from a chilled water storage tank to coils operatively associated with the air inlet of a gas turbine, wherein the gas turbine is used to generate electricity. Use of the variable speed drive controlled discharge pumps aids is protecting the temperature distribution in the chilled water storage tank so that a thermocline rises with the addition of chilled water during charging of the tank with chilled water, and lowers during discharge of the tank when using the chilled water to cool inlet air at one or more gas turbines operated at a facility.

Abstract: An internally cooled internal combustion piston engine and method of operating a piston engine is provided, with the combination of liquid water injection, higher compression ratios than conventional engines, and leaner air fuel mixtures than conventional engines. The effective compression ratio of the engines herein is greater than 13:1. The engines may employ gasoline or natural gas and use spark ignition, or the engines may employ a diesel-type fuel and use compression ignition. The liquid water injection provides internal cooling, reducing or eliminating the heat rejection to the radiator, reduces engine knock, and reduces NOx emissions. The method of engine operation using internal cooling with liquid water injection, high compression ratio and lean air fuel mixture allow for more complete and efficient combustion and therefore better thermal efficiency as compared to conventional engines.

Abstract: A reformer for use in a gas turbine engine specially configured to treat a supplemental fuel feed to the combustor that includes a reformer core containing a catalyst composition and an inlet flow channel for transporting the reformer fuel mixture, air and steam (either saturated or superheated) into a reformer core. An outlet flow channel transports the resulting reformate stream containing reformed and thermally cracked hydrocarbons and substantial amounts of hydrogen out of the reformer core for later combination with the main combustor feed. Because the catalytic partial oxidation reaction in the reformer is highly exothermic, the additional heat is transferred (and thermally integrated) using one or more heat exchange units for a first and/or second auxiliary gas turbine fuel stream that undergo thermal cracking and vaporization before combining with the reformate. The combined, hydrogen-enriched feed significantly improves combustor performance.

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: Fuel is oxidized with air in a pressurized reaction chamber containing water. Water, fuel, or both may be communicated into the reaction chamber in a gaseous state, a liquid state, or both. For example, a liquid mixture that includes the water and/or the fuel can be evaporated to form a gas mixture, and the gas mixture can be communicated into the reaction chamber. Additionally or alternatively, the liquid mixture that includes the water and/or the fuel can be communicated into the reaction chamber and evaporated in the reaction chamber. The water and the fuel may be communicated into the reaction chamber separately or in combination.

Abstract: Apparatus includes an ignition system that repeats an ignition cycle by providing hydrogen and oxygen and also provides a control spark with a sufficient amount of energy for igniting a combustible mixture of hydrogen and oxygen. The combustion chamber is immersed in an aqueous fluid, fills with the same or other aqueous fluid, receives the hydrogen and oxygen therein, receive the control spark to ignite the combustible mixture of hydrogen and oxygen to cause a combustion reaction to occur and form steam that yields a specific amount of heat energy, and provides the aqueous fluid from the combustion chamber in response to the substantial increase in pressure on the aqueous fluid contained therein.

Abstract: A method for producing electric energy from solid and liquid fuels is provided. The fuels are first subjected to a gasification process at high pressure, and the scrubbed gasification gas is fed to a gas and steam turbine process. The combustion of the scrubbed gasification gas in the gas turbine chamber does not occur with air, but with a mixture made of the three components oxygen, carbon dioxide and water vapor. As a result, the waste gas of the gas turbine is made only of carbon dioxide and water vapor. After the condensation thereof, technically pure carbon dioxide remains, which can be dissipated by storage in the deep substrate of the atmosphere.

Abstract: Embodiments of the present invention may provide to a gas turbine a fuel gas saturated with water heated by a fuel moisturizer, which receives heat form a flash tank. A heat source for the flash tank may originate at a heat recovery steam generator. The increased mass flow associated with the saturated fuel gas may result in increased power output from the associated power plant. The fuel gas saturation is followed by superheating the fuel, preferably with bottom cycle heat sources, resulting in a larger thermal efficiency gain.

Abstract: A system and method of cooling a rocket motor component includes injecting a high pressure liquid coolant through an injector nozzle into a cooling chamber. The cooling chamber having a pressure lower than the high pressure liquid coolant. The liquid coolant flashes into a saturated liquid-vapor coolant mixture in the cooling chamber. The saturated liquid-vapor coolant mixture is at equilibrium at the lower pressure of the cooling chamber. Heat from the rocket motor component to be cooled is absorbed by the coolant. A portion of the liquid portion of the saturated liquid-vapor coolant mixture is converted into gas phase, the converted portion being less than 100% of the coolant. A portion of the coolant is released from the cooling chamber and the coolant in the cooling chamber is dynamically maintained at less than 100% gas phase of the coolant as the thrust and heat generated by the rocket motor varies.

Abstract: Provided is a fuel flow control method of a gas turbine combustor provided in a humid air gas turbine, by which method NOx generation in the gas turbine combustor is restricted before and after the starting of humidification and combustion stability is made excellent.

Abstract: Systems and methods for mitigation of hot corrosion in steam injected gas turbine. In one embodiment, a steam injection system can provide for automatic injection of steam in a gas turbine for NOx abatement and power augmentation. The system can obtain indications as to whether the steam to be injected meets the requirements of the gas turbine in terms of purity and quality. If the quality or purity is not adequate, steam the injection into the combustor or compressor discharge casing (CDC) is automatically inhibited. The system may also monitor the dynamic pressure oscillations inside the combustor. The system may modulate steam flows modulates to enhance the total steam flow while maintaining the dynamic oscillations within acceptable limits.

Abstract: Methods and systems are provided for inducing combustion dynamics within turbine engines to remove combustion deposits within the turbine engine during operation of the turbine engine.

Abstract: A turbine engine includes an air inlet fluidly coupleable with an air compressor subassembly. The air compressor subassembly is fluidly coupleable with a combustion subassembly. The combustion subassembly generates and combusts ionic hydrogen, and is fluidly coupleable with a mid-turbine subassembly. The mid-turbine subassembly is fluidly coupleable with a rear turbine subassembly. The rear turbine subassembly is fluidly coupleable with an exhaust outlet for exhausting combustion products from said mid-turbine subassembly. The combustion subassembly includes an electrostatic subassembly fluidly coupleable with a combustion chamber subassembly. The combustion chamber subassembly is fluidly coupleable with the mid-turbine subassembly. The air compressor subassembly can compress and humidify air.

Abstract: A mixture of air and fuel is received into a reaction chamber of a gas turbine system. The fuel is oxidized in the reaction chamber, and a maximum temperature of the mixture in the reaction chamber is controlled to be substantially at or below an inlet temperature of a turbine of the gas turbine system. The oxidation of the fuel is initiated by raising the temperature of the mixture to or above an auto-ignition temperature of the fuel. In some cases, the reaction chamber may be provided without a fuel oxidation catalyst material.

Abstract: A combustion burner 10A according to one embodiment of the present invention includes: a fuel nozzle 110; a burner tube 120 forming the air passage 111 between the burner tube 120 and the fuel nozzle 110; swirler vanes (swirler vanes) 130 arranged in a plurality of positions in the circumferential direction on the external circumferential surface of the fuel nozzle 110, each extending along the axial direction of the fuel nozzle 110, and gradually curving from upstream toward downstream; and a liquid fuel injecting hole 133A from which a liquid fuel is injected to a surface of each of the swirler vanes 130. The combustion burner 10A also includes multi-purpose injecting holes 11-1 to 11-3 as a cooling unit that cools a part of a vane pressure surface 132a of the swirler vane 130 on which the liquid fuel LF hits.

Abstract: A preferred of operating a gas turbine engine having an inlet for receiving a stream of air to be compressed includes providing a first and a second set of interchangeable spray nozzles. Each of the nozzles in the first set is capable of discharging fluid supplied to the nozzle at a first pressure at a first flow rate. Each of the nozzles in the second set is capable of discharging fluid supplied to the nozzle at the first pressure at a flow rate that is different from the first flow rate.

Abstract: This wet compression invention with a vaporizable fluid mist demonstrates major performance improvements over the relevant art in achieving a high degree of saturation, providing sensible cooling, strongly reducing the temperature increase due to compression work, reducing excess diluent air flow for downstream combustion, reducing compression noise, and increasing the achievable compressor pressure ratio.

Abstract: Provided in one embodiment is a two-shaft gas turbine that exhibits improved reliability, output power, and efficiency. The turbine operates stably by establishing a balance between the driving force of a compressor and the output power of a high-pressure turbine in the case where the two-shaft gas turbine is applied to a system, in which the flow rate of a fluid flowing into a combustor is higher than a simple cycle gas turbine. A portion of the fluid driving the high-pressure turbine is allowed to flow not into the high-pressure turbine but into a low-pressure turbine.

Abstract: Disclosed is a water-injection type scroll air compressor whose pre-stopping operation time for drying can be reduced while enhancing compressor efficiency. The compressor body 1 includes a water supply line 24 for supplying water to a water feeder 23 connected to an air suction line 2. The water supply line 24 is provided with a control valve 27 that can control a flow rate of the water. A controller 28 conducts driving control of the control valve 27 in a 5×10?5 to 40×10?5 range of an injected-water volume ratio (more specifically, a volume ratio between an intake air flow rate and injected-water flow rate in the water feeder 23 of the suction line 2) and at the same time, in an injected-water volume ratio range of the compressor characterized so that an increase rate of overall adiabatic efficiency of the compressor per 1×10?5 increase rate of the injected-water volume ratio stays less than 2% of an original or initial value.

Abstract: A method of controlling a combustor of a gas turbine is disclosed. The method includes operatively disposing a combustor can in a combustor of a gas turbine. The combustor can comprising a plurality of combustor fuel nozzles, each having a fuel injector and configured to selectively provide a liquid fuel, a liquid fluid or liquid fuel and liquid fluid to a fuel injector nozzle that is configured to provide, respectively, a plurality of liquid fuel jets, a plurality of liquid fluid jets or a combination thereof, that are in turn configured to provide an atomized liquid fuel stream, an atomized liquid fluid stream, or an atomized and emulsified liquid fuel-liquid fluid stream, respectively. The method also includes selectively providing an amount of fuel, fluid or a combination thereof to the fuel injector nozzle to produce an atomized fuel stream, atomized fluid stream, or an atomized and emulsified fuel-fluid stream, respectively.

Abstract: A system including a gas turbine engine having a compressor portion, a combustion portion and an exhaust portion is disclosed. The system includes a first regulating nozzle for injecting water into the compressor portion, a second regulating nozzle for injecting water into the combustion portion, a third regulating nozzle for injecting water into the exhaust portion, and a condenser apparatus for extracting water from flue gases in the exhaust portion. The system further includes a pump for pumping water from the condenser apparatus to the first, second and third regulating nozzles, wherein said nozzles inject water supplied solely from the condenser apparatus, and a processor communicatively coupled to said regulating nozzles, wherein the processor is configured for transmitting control signals to the first, second and third regulating nozzles, and wherein the control signals are configured to command said regulating nozzles to inject predefined amounts of water.

Abstract: An improved method of powering an engine using water as a fuel by separating the hydrogen and oxygen atoms and igniting the hydrogen with high voltage high amperage dc electricity in the compression/combustion chamber of the engine and recycling the exhaust water for reuse.

Abstract: The present invention is a method and system for vertically producing a steam and combustion gas mixture, typically used in enhanced oil recovery processes. The system is a fluid bed up-flow combustor system, including a vertical vessel with fours sections. In a first section, fuel, oxidizer, and possibly water are supplied to the high pressure combustor at a combustion section of a vertical vessel. The combustion gas from the first section flows to a second section for steam generation, where low quality water is injected and turned into steam. Next, the third section is a homogenizer vessel, where any remaining water drops are converted to steam and solid particles and discharged from the vessel. The fourth section located at the bottom of the vessel is a fluid bed, receiving and processing the falling solids from the combustion and the steam generation sections.

Abstract: A power generation system (11) and method of operating such a system (11) including a steam turbine (14). In one embodiment a HRSG (20) includes an evaporator (127) coupled to receive condensate from the steam turbine (14), and a superheater (132) coupled to receive output from the evaporator (127). The HRSG (20) generates steam with thermal energy received from a combustion turbine (28). A flash tank (9) receives water heated in the HRSG (20), outputs a first portion of the water as steam, and outputs a second portion of the water as liquid. A flow line (134) passes steam (51) from the flash tank (9) to a combustion chamber (26) in the combustion turbine (28) to provide power augmentation.

Abstract: A method is disclosed for removing deposits from rotating parts of a gas turbine engine while under full fire or idle speed utilizing a particulate coke composition. The coke composition may be introduced directly into the combustion chamber (combustor) of the gas turbine or, alternatively, anywhere in the fuel stream, water washing system, or the combustion air system. By kinetic impact with the deposits on blades and vanes, the deposits will be dislodged and will thereby restore the gas turbine to rated power output. If introduced into the compressor section, the coke particles impinge on those metal surfaces, cleaning them prior to entering the hot gas section where the process is repeated.

Abstract: The present application provides a compressor for a gas turbine. The compressor may include a number of rotor wheels positioned about a compressor aft section having a low alloy material, a number of inlet guide vanes positioned about a compressor inlet section, and a wet compression system positioned about the compressor inlet section.

Abstract: A moisture removal system for removing water moisture from an air stream and an associated method are provided. The moisture removal system includes one or more packed beds that include a water-entry surface at which liquid water is received and an air-entry surface that is located substantially opposite the water-entry surface and at which the air stream is received. The air stream passes through the one or more packed beds in a direction substantially counter-current to the passage of the liquid water and the liquid water and the air stream contact one another in the one or more packed beds resulting in the removal of at least a portion of the water moisture from the air stream. The moisture removal system can be located upstream of and be operably connected to the inlet of a gas turbine system to which the air stream is delivered from the moisture removal system.

Abstract: A method for cooling inlet air to a gas turbine is provided. For example, a method is described including passing inlet air through a cooling coil that includes an opening for receiving the inlet air and that is operably connected to a gas turbine power plant. The gas turbine power plant may include at least one gas turbine, and at least one gas turbine inlet which receives the inlet air. The method may further include passing circulating water through a water chiller at a first flow rate to reduce the temperature of the circulating water, the water chiller including a conduit through which the circulating water is capable of passing and passing the circulating water having the first flow rate through the cooling coil in an amount sufficient to lower the temperature of the inlet air.