Abstract: The present disclosure relates to a method for improving aerdynamic stability of a working fluid flow through a compressor of a turbomachine, in particular through a compressor of gas turbine used for power production, particularly against rapidly changing aero speed of the compressor. The method comprises to introduce a first water mass flow to the working fluid flow of the compressor. Furthermore, the disclosure relates to a turbomachine, in particular a gas turbine, which can be driven according to the above method.

Abstract: A water treatment and pressurization system for the adiabatic cooling of comburent air destined for plants using gas turbines (15), run by measuring, control and regulation units, comprising a lifting and pressurizing station (16) of vaporization water at a varying flow-rate for a maximum operating pressure, preferably up to 120 bar, associated with a series of nozzles (20) situated on nozzle-holder ramps (12) downstream of which there is at least one housing unit (44) for humidity and temperature probes (52-55). The lifting station (16) comprises at least two pumps (22) with relative auxiliaries devices connected to nozzle-holder collectors (39).

Abstract: A method and system augments shaft output of gas turbine engines that can be used in multiple modes of operation. The system comprises a washing unit capable of injecting atomized water into the gas turbine engine, thereby obtaining a release of fouling material from the at least one compressor blade; and at least one water injection unit capable of injecting atomized water into the air stream of the gas turbine engine's inlet duct or at the gas turbine, under the control of a computational fluid dynamic model, in order to increase a mass flow of said air flow, wherein the power output from said gas turbine engine can be augmented.

Abstract: Disclosed is a combustor including a baffle plate having at least one through baffle hole and at least one fuel nozzle extending through the at least one through baffle hole. At least one diluent shroud is affixed to the at least one baffle plate and is configured to guide a diluent flow toward a mixing chamber of the at least one fuel nozzle. Further disclosed is a method for introducing a diluent flow into a mixing chamber of a fuel nozzle including urging the diluent flow from a plenum through a baffle plate gap between a baffle plate and an outer surface of the fuel nozzle. The diluent flow is directed via at least one diluent shroud extending from the baffle plate toward a plurality of air swirler holes extending through a fuel nozzle tip. The diluent flow is flowed through the plurality of air swirler holes into the mixing chamber.

Abstract: A method and system augments shaft output of gas turbine engines that can be used in multiple modes of operation. The system comprises a washing unit capable of injecting atomized water into the gas turbine engine, thereby obtaining a release of fouling material from the at least one compressor blade; and at least one water injection unit capable of injecting atomized water into the air stream of the gas turbine engine's inlet duct or at the gas turbine, under the control of a computational fluid dynamic model, in order to increase a mass flow of said air flow, wherein the power output from said gas turbine engine can be augmented.

Abstract: Disclosed is a combustor including a baffle plate having at least one through baffle hole and at least one fuel nozzle extending through the at least one baffle hole. A circumferentially adjustable collar is located at the at least one baffle hole between the baffle plate and the at least one fuel nozzle. A plurality of openings at the collar are configured to meter a flow of diluent between the baffle hole and the at least one fuel nozzle. Further disclosed is a method for providing diluent to a combustor including providing a plurality of openings disposed at a circumferentially adjustable collar between a baffle plate and at least one fuel nozzle extending through a through hole in the baffle plate. The diluent is flowed through the plurality of openings toward at least one airflow hole in the at least one fuel nozzle.

Abstract: Disclosed is a combustor including a baffle plate having at least one through baffle hole and at least one fuel nozzle extending through the at least one baffle hole. A plurality of injection holes extend through the at least one fuel nozzle and are configured to meter a flow of diluent into the combustor. Further disclosed is a method for providing diluent to a combustor including providing a plurality of openings located at at least one fuel nozzle extending through a through hole in a baffle plate. The diluent is flowed through the plurality of openings toward at least one airflow opening in the at least one fuel nozzle.

Abstract: Disclosed is a combustor including a baffle plate having at least one through baffle hole and at least one fuel nozzle extending through the at least one baffle hole. A shroud is disposed between the baffle plate and the at least one fuel nozzle and is affixed to the baffle plate. A plurality of openings in the shroud are configured to meter a flow of diluent between the baffle hole and the at least one fuel nozzle. Further disclosed is a method for providing diluent to a combustor including providing a plurality of openings disposed in a shroud affixed to a baffle plate and disposed between the baffle plate and at least one fuel nozzle extending through a through hole in the baffle plate. The diluent is flowed through the plurality of openings toward at least one airflow opening in the at least one fuel nozzle.

Abstract: In an SEV combustor and a method for reducing emissions in an SEV combustor of a sequential combustion gas turbine, an air/fuel mixture is combusted in a first burner and the hot gases are subsequently introduced into the SEV combustor (1) for further combustion. The SEV combustor (1) includes a chamber having a chamber wall (5) defining a mixing portion (8), for mixing the hot gases with a fuel, and a combustion region (9), at least one inlet (2) for introducing the hot gases into the mixing region (8), at least one inlet (12) for introducing a fuel into the mixing region (8) and at least one inlet (10, 13) for introducing steam into the mixing region.

Abstract: A method for operating a gas turbine engine, including a first compressor, a second compressor, and a turbine, coupled together in serial flow arrangement. The method includes channeling compressed airflow discharged from the first compressor through an intercooler having a cooling medium flowing therethrough, operating the intercooler such that condensate is formed in the intercooler from the compressed airflow, and channeling the condensate to an inlet of the first or second compressor to facilitate reducing an operating temperature of the gas turbine engine.

Abstract: A method and apparatus to heat-activate hydrogen of water for powering rotational, reaction-thrust and projectile-expulsion embodiments (19, 60, 61, 75) of a water engine (10) with hydrogen energy of water which is spray-atomized and electrically heated internally in one or more hydrogen activators (1). Water-hydrogen electrons of the spray-atomized water are heat-activated up to exponentially greater output heat-activation energy than input activation-heat energy added electrically with power generated from forms of the water engine. A minor portion of the output heat-activation energy of the water hydrogen is utilized for generating electrical current for the input activation heat of the spray-atomized water in the hydrogen activators. Net output heat-activation pressure of water-hydrogen is directed from one or more of the hydrogen activators to one or more use chambers (9) of universal-use forms of the water engine. Rotational features of the water engine preferably employ a turbocam drive (20).

Abstract: A fluid delivery skid with a pre-fill system for supplying fluid has one or more stages including a first valve and a second valve, each having an open and closed position. The stages have active and inactive states to provide a desired flow rate of fluid to an apparatus for distribution of the fluid. In an active state, fluid is received in the stage and pressurized with the first valve open and the second valve closed. Further, in an active state, fluid is released with the first valve closed and the second open. In an inactive state, at least the second valve is closed. A control unit is connected to a pump unit and controls operation of the pump to regulate the stages to supply pressure at a level determined to achieve the desired flow rate.

Abstract: A steam cycle power plant (10) is provided that may include a steam source generating steam (40), a steam turbine (24) receiving the generated steam and discharging an exhaust steam, a condenser (44) receiving the exhaust steam and an atomizer (60) for injecting water into the exhaust steam downstream of the steam turbine (24) and upstream of a cooling surface of the condenser (44) effective to reduce a backpressure on the steam turbine (24) and improve a heat rate of the steam turbine (24). The atomizer (60) may include a plurality of symmetrical spaced fluid connections (70) and a plurality of atomizing nozzles (62) affixed proximate at least one exhaust end of the steam turbine (24). The power plant (10) may be a combined cycle power plant including a heat recovery steam generator (40) and a gas turbine engine (12).

Abstract: A wet compression system for a gas turbine compressor having a bellmouth that includes a plurality of nozzles for spraying a fine spray of liquid disposed within an aft section of the bellmouth. The aft section of the bellmouth may include a downstream half of the bellmouth, and the nozzles may be connected to a plurality of struts, each of the struts comprising a structural member that connects an inner diameter casing of the bellmouth to an outer diameter casing of the bellmouth. In some embodiments, the nozzles may be positioned on a leading edge of at least one of the struts and a minimum clearance of at least approximately 0.2 m may be maintained between the nozzles and the inner diameter casing of the bellmouth. In other embodiments, the nozzles may be positioned on a trailing edge of at least one of the struts and a minimum clearance of at least approximately 0.05 m may be maintained between the nozzles and the inner diameter casing of the bellmouth.

Abstract: Carbon dioxide (152) is removed following compressor (130) which compresses a mixture of compressed air (132) and recirculated exhaust gas (118?) from a gas turbine (120). The carbon dioxide depleted gas (136) is humidified (180, 114) and fed to the combustor (110).

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

Abstract: Method for efficient energy transformation by means of a gaseous medium comprising steam, said steam being produced from a first fluid medium, energy for heating the first fluid medium being provided by burning a fuel, comprising the steps of: mixing the steam with exhaust gas from combustion of said fuel; introducing said mixture into a cavity; and bringing said steam and exhaust gas mixture into contact with a cold second fluid medium within said cavity such that a supersonic shock wave is created. The invention also relates to a device and a system for efficient energy transformation by means of a gaseous medium comprising steam.

Abstract: A drive device for an aircraft comprises a gas turbine apparatus for generating a first drive energy and electric motor for generating a second drive energy. The gas turbine apparatus and the electric motor are set up in such a way that the drive unit may be provided with at least one of the first drive energy and the second drive energy. The drive unit is set up to generate propulsion using at least one of the first drive energy and the second drive energy.

Abstract: A turbomachine includes a compressor portion that generates a cooling airflow. The compressor portion includes a plurality of compressor stages. The turbomachine further includes a turbine portion operatively connected to the compressor portion. The turbine portion includes a plurality of turbine stages. A conduit fluidly connects at least one of the plurality of compressor stages with at least one of the plurality of turbine stages and delivers a portion of the cooling airflow from the compressor portion to the turbine portion. An injector port is connected to the conduit and a secondary fluid generation system. The secondary fluid generation system delivers an amount of dry secondary fluid into the cooling airflow passing from the compressor portion to the turbine portion. The amount of dry secondary fluid replaces a portion of the cooling airflow passing to the turbine portion.

Abstract: The invention relates to a method for producing a gaseous medium comprising steam, said steam being produced from a first fluid medium, energy for heating the first fluid medium being provided by burning a fuel, comprising the steps of mixing the steam with exhaust gas from combustion of said fuel characterised by the steps of prior to mixing the steam with exhaust gas, injecting fluid into the steam. The invention further relates to a device for producing a gaseous medium comprising steam. The invention also relates to a further method for producing a gaseous medium comprising steam The invention still further relates to a further device for producing a gaseous medium comprising steam. The invention finally relates to a turbine configuration.

Abstract: A cooling system for a gas turbine engine including a compressor, a combustor and a high-pressure turbine, coupled together in serial flow arrangement. The cooling system includes a storage tank, a working fluid stored within the storage tank, and a manifold coupled to the channel that supplies cooling air to the high pressure turbine. The working fluid is discharged from the manifold into the turbine cooling air supply channel, thereby reducing the temperature of the compressed cooling airflow channeled to the high pressure turbine.

Abstract: An advanced humid air turbine power plant capable of suppressing condensation of moisture in a cooling channel, which is provided to cool a high-temperature component of a gas turbine, in a start up stage, a coast down stage, and a load varying state of the gas turbine. In the advanced humid air turbine power plant comprising a compressed air supply line for supplying compressed air generated by a compressor to the high-temperature component of the gas turbine, and a humidified air supply line for supplying humidified air generated in a humidifying tower to the high-temperature component of the gas turbine, the power plant further comprises valves capable of adjusting respective air flow rates in the compressed air supply line and the humidified air supply line.

Abstract: A gas turbine plant having a compressor (1), one or more combustion chambers (2), a high-pressure gas turbine (3) and a power turbine (24) includes a device whereby water or water vapor is injected into the flow of the combustion air compressed by the compressor (1). The injection nozzles (22) are arranged in a bend (20) of an external connection housing (18), which consists of a radial housing part (19) connected to the outlet of the compressor (1) and of an axial housing part (21) connected to the intake of the combustion chamber (2).

Abstract: A gas turbine group comprises a device, arranged in a suction-intake duct, for cooling a suction-intake airflow. The device is, for example, a device for injecting a liquid mass flow. The cooling device is activated automatically when a first limit temperature of the ambient air is overshot and is deactivated automatically when a second limit temperature is undershot. Stability of the automatic algorithm can be improved in that the second limit temperature can lie by a specific amount below the first limit temperature. In one embodiment, the limit temperatures are predetermined as a function of the position of an adjustable initial guide blade cascade.

Abstract: The invention proposes a cooling system (42) for a gas turbine (1), with an annular duct extending axially in the compressor (5). In the annular duct, a ring (15) of compressor guide blades (14, 28, 33) and a ring (17) of moving blades (16) fastened to a rotor disk (19) of the rotor (3) are provided, with at least one cooling-air extraction point (34), arranged on the rotor (3), for diverting a cooling-air stream into a cooling-duct system arranged in the rotor (3), and with a turbine unit (8), in which, when the gas turbine (1) is in operation, components subjected to thermal stress by a hot gas (20) can be cooled by the divertible cooling-air stream, and also with a feed line (46) for feeding a liquid (45) into the cooling-air stream.

Abstract: A turbine power plant employs a radial staging of a liquid injection system to provide a uniform fluid distribution, for use in wet compression. The liquid injection system includes a hub to be coupled to an air intake case of a turbine power plant. An annular ring assembly is spaced radially outwardly from the hub. Spray bars are spoked about the hub and the annular ring. The spray bars each include a body portion having an inner end coupled to the hub and an outer end coupled to the ring assembly. The spray bars each have at least two nozzle assemblies along the body portion. The spray bars each define at least two liquid supply manifolds each having an inlet at the annular ring assembly and an outlet at an associated nozzle assembly. The liquid supply manifolds each supply liquid to one or more associated nozzle assemblies.

Abstract: A liquid atomizing arrangement comprises: a line system, at least one pressure atomizer nozzle, at least one line for the liquid to be atomized, and at least one first actuator for setting the atomizing supply pressure and/or the liquid mass flow through the atomizing arrangement. method of operating the liquid atomizing arrangement comprises the steps of measuring the mass flow flowing through the liquid atomizing arrangement, of measuring the atomizing supply pressure upstream of the pressure atomizer nozzle, and of acting upon the first actuator as a function of at least one of these measured values.

Abstract: The injection of finely atomized liquid-droplets into the intake air flow of a compressor is used, for example, to improve the output of a gas turbine. If the atomization is effected via pressure atomizer nozzles, it is advantageous, when the injection device is operated with a portion of the design mass flow, to admit liquid to only some of the atomizer nozzles of the injection device. The atomizer nozzles may be arranged on nozzle tubes, liquid being jointly admitted to all the atomizer nozzles arranged on a respective nozzle tube, operated in such a way that the same mass flow is injected on each side of a symmetry line. To this end, nozzle tubes may be combined to form groups, to which liquid is jointly admitted, and the tubes of a group may be arranged in mirror image to one another relative to the symmetry line.

Abstract: The invention relates to a regulation of the temperature of a hot gas of a gas turbine, particularly of a stationary gas turbine used for generating electricity, which comprises an injecting device for injecting a liquid into an airflow, which can be drawn into a compressor and with the aid of which a fuel inside a combustion chamber, which is situated downstream, combusts while producing the hot gas that is subsequently expanded when flowing through the turbine part located downstream. A temperature measuring device is provided that measures the temperature of the airflow before the compressor, whereby the temperature of the hot gas is regulated by the quantity of fuel. The aim of the invention is to provide a regulation with which, during wet compression operation, the serviceable life of the components subjected to the action of hot gas is lengthened.

Abstract: The amount of water to be injected in an intercooler is controlled to cool the compressed gas to the saturation temperature. It is difficult to adjust the amount of the water to be injected, however, since the temperature of the compressed gas at an intercooler outlet is actually higher than the saturation temperature. An intercooling system is configured so as to cool a gas to the saturation temperature without controlling the amount of water injection and thereby maintain the reliability of the compressor while improving the cooling efficiency. The intercooling system is located between a plurality of compression stages of a gas compressor to cool the gas that has been in the compressor. A desired amount of liquid is sprinkled to cool the compressed gas while restraining inflow of the liquid into the compression stages.

Abstract: A high humidity gas turbine equipment includes a turbine; a compressor; a humidifier, which brings the air compressed by the compressor into contact with feed water to humidify the air; a regenerative heat exchanger, which causes the air humidified by the humidifier to be heated by exhaust gas from the turbine; a combustor, which burns the air heated by the regenerative heat exchanger and fuel to generate the combustion gas; a deaerating equipment including a deaerating section, a water storage tank, and a steam generating section, which causes feed water and makeup water in the water storage tank to be heated by exhaust gas from the turbine to evaporate and supplies the steam to the deaerating section; and a feed water supply pipe, through which the feed water and the makeup water in the water storage tank are supplied to the humidifier.

Abstract: An apparatus for supplying water to a misting system for an inlet of a gas turbine, includes a diversion of heated feedwater from a loop and to a pump, the pump providing high-pressure feedwater to the misting system. A combined cycle power plant and a method for supplying water are provided.

Abstract: A combined cycle power plant comprises a gas turbo group and a water/steam circuit A liquid atomization device is arranged, upstream of the compressor, in the intake duct of the gas turbo group. The liquid under pressure, which is intended to be injected into the compressor inflow, is branched off from the water/steam circuit.

Abstract: A gas turbine, a combined cycle plant and compressor by which both augmentation of the power output and augmentation of the thermal efficiency can be realized by injecting liquid droplets into inlet air introduced into an entrance of a compressor with simple equipment which is suitable for practical use. The gas turbine includes a compressor for taking in and compressing gas, a combustor in which fuel is combusted with the gas discharged from the compressor, and a turbine driven by the combusted gas of the combustor. The gas turbine further includes a liquid droplet injection device provided on the upstream side of the compressor for injecting liquid droplets into inlet air to be supplied into the entrance of the compressor to lower the temperature of the inlet air to be introduced into the compressor so that the injected liquid droplets may be evaporated while flowing through the compressor.

Abstract: The invention is intended to maintain turbine reliability when, based on a gas turbine designed for one desired cycle, a gas turbine for another different cycle is manufactured. A channel of a compressor is formed such that a mass flow of a fluid compressed by the compressor changes. Thus, when manufacturing, based on the gas turbine designed for one desired cycle, the gas turbine for another different cycle, turbine reliability can be maintained.

Abstract: A combined power plant that is capable of reducing the time required for restarting is provided.

Abstract: The present invention discloses a method and system for augmenting shaft output of stationary gas turbines that can be used in multiple modes of operation. The system comprises a washing unit (25, 27, 28) adapted to inject a spray (26) of atomized liquid so as to impinge on the compressor blades (12) in order to wet said blades (12), thereby obtaining a release of fouling material from said blades (12); and at least one liquid injection unit (21, 23, 24, 29, 210, 212, 214, 215, 216) adapted to inject a spray (22, 211, 213) of atomized liquid into an air stream of said turbine duct (101) or at the gas turbine (10) in order to increase a mass flow of said air flow, wherein the power output from said gas turbine engine can be augmented. With the invention follows also benefits such as fuel savings and improved environmental performance by reduction of emissions.

Abstract: The present invention provides a humid air turbine having a compressor, a humidificator for generating humid air by adding moisture to compressed air supplied from the compressor, a combustor, a turbine, a recuperator for effecting heat exchange between exhaust from the turbine and the humid air, an economizer for effecting heat exchange between exhaust from the recuperator and water, and a system for supplying the water heated by the economizer to the humidificator. The humid air turbine includes a temperature measurement device for measuring the temperature of gas discharged from the economizer, and a control device for adjusting the amount of moisture to be supplied to the humidificator in accordance with a temperature signal from the temperature measurement device. The present invention assures low NOx of combustor and flame stability before and after water addition to the humid air turbine.

Abstract: A micro gas turbine system is provided which increases power generation efficiency and output of power generation by means of water spray and which can exercise effective water spray control with simple control. The micro gas turbine system, according to the present invention, including a compressor, a combustor, a regenerative heat exchanger, a generator and a power transducer is provided with a plurality of spray water supply lines which include spray water nozzles and shutoff valves and which supply a prescribed amount of spray water by opening and closing the shutoff valves.

Abstract: A gas turbine, a combined cycle plant and compressor by which both augmentation of the power output and augmentation of the thermal efficiency can be realized by injecting liquid droplets into inlet air introduced into an entrance of a compressor with simple equipment which is suitable for practical use. The gas turbine includes a compressor for taking in and compressing gas, a combustor in which fuel is combusted with the gas discharged from the compressor, and a turbine driven by the combusted gas of the combustor. The gas turbine further includes a liquid droplet injection device provided on the upstream side of the compressor for injecting liquid droplets into inlet air to be supplied into the entrance of the compressor to lower the temperature into the entrance of the compressor to lower the temperature of the inlet air to be introduced into the compressor so that the injected liquid droplets may be evaporated while flowing through the compressor.

Abstract: The present disclosure relates to a method for improving aerdynamic stability of a working fluid flow through a compressor of a turbomachine, in particular through a compressor of gas turbine used for power production, particularly against rapidly changing aero speed of the compressor. The method comprises to introduce a first water mass flow to the working fluid flow of the compressor. Furthermore, the disclosure relates to a turbomachine, in particular a gas turbine, which can be driven according to the above method.

Abstract: A gas turbine system comprises a compressor for compressing air, a combustor for burning the air compressed by the compressor and fuel, a turbine driven by combustion gases produced from the combustor, and a spraying apparatus for adding water to working air at least upstream or in an intermediate stage of the compressor. A rotationally symmetric groove or projection is formed in an inner wall surface defining a channel through which the working air added with the water flows, or in a channel-defining surface of a rotor or a casing of the gas turbine. A larger amount of water can be supplied to the compressor while improving the reliability of the gas turbine.

Abstract: A method for compressing the working fluid during a water/steam combination process in multi-stage turbocompressors comprising intercooling in the individual compressor stages, by the addition of a coolant to the working fluid. The aim of the invention is to provide a technical solution, which is suitable for the efficient intercooling of the working fluid during multi-stage compression and thus for the highest possible reduction of the required compressor power. To achieve this, dispersed water, which is obtained by the pressure atomization of water to form micro-droplets, is used as the coolant. The coolant is added directly to the working fluid in at least one compression stage in a quantity that maintains the thermodynamic equilibrium, and is converted during compression into the state of the working fluid, the evaporation of the coolant takes place at the saturation line.

Abstract: The present invention provides high humidity gas turbine equipment including a compressor compressing air, a combustor combusting the compressed air and a fuel, a gas turbine driven by the combustion gas, a generator driven by the gas turbine to generate power, a humidifier humidifying the compressed air by directly contacting it with hot water, and a regenerative heat exchanger heating the humidified compressed air by exhaust gas of the gas turbine and feeding it to the combustor, heat exchangers generating hot water for the humidifier utilizing a factory exhaust heat medium from the outside, a boiler generating steam to be supplied to the outside utilizing the exhaust gas of the gas turbine, and a boiler generating steam to be supplied to the outside utilizing the compressed air discharged from the compressor.

Abstract: In a method for operating a gas turbine centre in the vicinity of the group nominal full-load conditions, the cooling of the working fluid before and/or during the compression is set in such a way that the respectively attainable full-load power is above the current power. Rapid power demands can therefore be rapidly satisfied by an increase in the turbine inlet temperature or by opening an adjustable inlet guide vane row, whereas the control of the cooling effect, which has a tendency to be more sluggish, is employed to adjust the full-load operating point.

Abstract: Disclosed is a gas turbine power generating system capable of achieving a high output power and a high power generating efficiency under conditions with a small amount of supplied water and less change in design of a gas turbine. A fine water droplet spraying apparatus (11) is disposed in a suction air chamber (22) on the upstream side of an air compressor (2), and a moisture adding apparatus (7) for adding moisture to high pressure air supplied from the compressor (2) is disposed. A regenerator (5) for heating the air to which moisture has been added by using gas turbine exhaust gas as a heat source is also provided. With this configuration, there can be obtain an effect of reducing a power for the compressor (2) and an effect of increasing the output power due to addition of moisture to air (20) for combustion. Further, since the used amount of fuel is reduced by adopting a regenerating cycle, the power generating efficiency is improved.

Abstract: A method for operating a gas turbine engine, including a first compressor, a second compressor, and a turbine, coupled together in serial flow arrangement. The method includes channeling compressed airflow discharged from the first compressor through an intercooler having a cooling medium flowing therethrough, operating the intercooler such that condensate is formed in the intercooler from the compressed airflow, and channeling the condensate to an inlet of the first or second compressor to facilitate reducing an operating temperature of the gas turbine engine.

Abstract: A method for operating a gas turbine installation (1) includes sucking in a gaseous medium (2) by the compressor (3) and compressed in the compressor space, a liquid medium (10) being injected into the gaseous medium (2), so that a two-phase flow comprising a gaseous phase and a liquid phase is formed at least in a subregion of the compressor (3). The gaseous medium (2) is then burnt with fuel (5) in a combustion chamber (6) to form hot gases (7), and the hot gases (7) are expanded in a turbine (8), the hot components of the gas turbine installation (1) being cooled by cooling air (14) of a cooling air system. A measurement is carried out to determine whether a liquid phase is present in a region of the compressor (3) and/or of the cooling air system.

Abstract: Techniques suitable for recovering energy from a high-temperature gas of an ordinary pressure are provided. A turbomachine has a turbine 16 and compressors 20 and 24. A combustor 12 is disposed at a stage above the turbine 16. A power generating system generates power by passing a working fluid for the turbomachine through the combustor 12, the turbine 16 and the compressors 20 and 24 in that order.

Abstract: A closed-loop cooling system is provided for a hydrogen/oxygen based combustor. A combustion reaction between hydrogen and oxygen in the combustor produces steam. The steam is used to generate work from a turbine shaft, which is used to drive a propulsion system for the underwater vessel. After the steam passes through the turbine, the steam is cooled back to liquid water by a condenser that uses a seawater cooling loop to cool the steam into cold water. The cold water is then injected into the combustor, and pumped into passages along the walls of the combustor, thus absorbing the heat. The cold water absorbs this heat until it becomes hot water or steam, which is then injected into the combustor with the hydrogen and oxygen to act as a diluent, thus reducing the reaction temperature of the hydrogen/oxygen combustion reaction. The reaction produces more steam, and the cycle repeats.