Abstract: An electrical power generating system is driven by a multi-spool gas turbine engine including at least first and second spools. The first spool comprises a turbine and a compressor mounted on a first shaft; the second spool has at least a turbine mounted on a second shaft that is not mechanically coupled to the first shaft. A main generator is coupled with one of the spools, and an auxiliary generator/motor is also coupled with one of the spools. Speed control of each of the generators is employed for controlling operation of the engine. The auxiliary generator/motor can operate in either a generation mode to extract power from its spool or a motor mode to inject power into its spool.

Abstract: A gas turbine installation which includes a compressor which compresses supplied air and discharges the same, a combustor which combusts the compressed air obtained from the compressor and fuel and produces combustion gas, a turbine which is driven by combustion gas provided from the combustor, a regenerative heat exchanger which heats all or a part of the compressed air being supplied from the compressor to the combustor by making use of the heat of the exhaust gas exhausted from the turbine and a plurality of water spraying devices which are provided at positions from an intake air chamber of the compressor to the outlet of low temperature side gas flow passage in the regenerative heat exchanger and is characterized in that the regenerative heat exchanger is constituted by connecting in series a plurality of heat exchangers having different heat transfer surface configurations.

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 recuperated gas turbine engine system and associated method employing catalytic combustion, wherein the combustor inlet temperature can be controlled to remain above the minimum required catalyst operating temperature at a wide range of operating conditions from full-load to part-load and from hot-day to cold-day conditions. The fuel is passed through the compressor along with the air and a portion of the exhaust gases from the turbine. The recirculated exhaust gas flow rate is controlled to control combustor inlet temperature.

Abstract: A compressed air energy storage system comprises a cavern (1) for stored compressed air and a system for providing the compressed air to a power train (3, 5), this system including a recuperator (7) and a first valve arrangement (8) that controls the flow of the compressed air from the recuperator and to the power train (3, 5). A system for warm-keeping of the power train (3, 5) during stand-by operation of the compressed air energy storage system comprises the recuperator (2) and/or an auxiliary electrical air heater (11) and a second valve arrangement (10, 13) for controlling the airflow for warm-keeping. The system for warm-keeping of the power train allows improved temperature control and avoids disadvantages associated with a warm-keeping system having a combustor.

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 turbine inlet air-cooling system improves turbine performance and efficiency. A dehumidifier receives process airflow and reduces a moisture content of the process airflow. An indirect evaporative cooler receives the process airflow from the dehumidifier and is driven by the process airflow from the dehumidifier such that a first portion of the process airflow is contacted directly with water and a second portion of the process airflow is cooled without any addition of moisture. A direct evaporative cooler receives the second portion of the process airflow, which is contacted directly with water to provide evaporative cooling. Subsequently, the direct evaporative cooler outputs the second portion of the process airflow to the turbine.

Abstract: The flow path of the exhaust of a recuperator of a microturbine engine system is routed to insulate the turbine exhaust in the recuperator. The recuperator is encapsulated for defining a passage for flowing the exhaust over the outer diameter of the recuperator so as to insulate the heat within the recuperator. A by-pass system that is operable mechanically or automatically directs turbine exhaust to by-pass the recuperator is disclosed in another embodiment. The by-pass serves to trim the efficiencies of the original manufactured microturbine engines so that all the engines attain a given preselected matching efficiency level. The by-pass can also be utilized to control the temperature of a boiler, chiller or other elements incorporated in the microturbine system by controlling the turbine exhaust to by-pass the recuperator.

Abstract: A piping guides exhaust gas of a gas turbine to a heat recovery steam generator (HRSG). The piping is provided at an outlet of the exhaust gas and is branched into two portions at a branch portion upstream of the HRSG, with one portion being connected to a high-pressure superheater provided in the HRSG and the other portion being connected to a regenerator. Exhaust gas supplied to the high-pressure superheater superheats saturated steam generated by a high-pressure evaporator in the HRSG. Exhaust gas supplied to the regenerator is heat-exchanged with combustion air generated by a compressor in the gas turbine. The exhaust gas having been heat-exchanged is supplied to between the high-pressure superheater and the high-pressure evaporator via another piping extending between the regenerator and the HRSG.

Abstract: A micro turbine (10) has a recuperator (20). During startup, an alternator (26) acts as a motor to turn the turbine rotor (32) and compressor rotor (34) of gas turbine (40). The speed of the gas turbine (40) and a fuel control valve (42) are controlled in order to prevent the rate of change of temperature at a gas turbine exhaust sensor (74) and/or a recuperator sensor (80) from exceeding a predetermined value in order to reduce thermal shock on the recuperator during startup. Controlled shutdown sequences are also provided.

Abstract: An engine comprising an isothermal air compressor (1) into which liquid is sprayed as the air is compressed. A combustion chamber (4) receives and expands the compressed air from which the liquid has been removed, to generate power. A precompressor (21, 27) compresses the air upstream of the isothermal compressor. The compressed air from the isothermal compressor receives heat from the exhaust gas from the combustion chamber in a primary heat exchanger (3). A secondary heat exchanger (31, 45) transfers heat recovered from a part of the engine to the compressed air from the isothermal compressor (1) upstream of the primary heat exchanger (3).

Abstract: A combustion air delivery system comprising a compressor operable to provide a stream of compressed air and a bypass duct positioned to divide the stream of compressed air into a bypass flow stream and a primary flow stream. A recuperator is operable to preheat the primary flow to produce a flow of preheated compressed air. A premix chamber receives the bypass flow stream and mixes the bypass flow stream with a flow of fuel to produce a fuel-air flow. A can member at least partially defines a primary zone that receives the fuel-air flow and includes an aperture sized to admit a predetermined portion of the flow of preheated compressed air. The fuel-air flow and predetermined portion of the flow of preheated compressed air mix in the primary zone to produce a combustible flow. An igniter is operable to ignite the combustible flow.

Abstract: An improved turbine engine topology, wherein the improvement comprises a repositioning, with respect to a conventional intercooled regenerative turbine engine topology, of exhaust gas output from a low pressure turbine stage to a regenerator, to an exhaust gas output from a high pressure turbine stage to the regenerator. The engine topology may additionally employ, as an intermediate stage between the high pressure turbine and the low pressure turbine, a feedback control system, whereby the exhaust gas output from the high pressure turbine stage to the regenerator flows through the feedback control. The engine topology may advantageously also employ an additional cooler and an additional exhaust gas output in the feedback control, whereby exhaust gas flows from the feedback control through the additional cooler to a high pressure compressor stage, or the exhaust gas can flow from the feedback control through a bottoming cycle to the high pressure compressor stage.

Abstract: A method for exchanging heat between a first fluid and a second fluid. The method includes providing a heat exchanger having a stack of at least two layers of support structures, wherein each support structure layer is formed from a lattice of support members, and substantially fluidly separating the at least two support structure layers using at least one barrier such that each layer defines a fluid passageway. The method also includes directing a flow of first fluid through a first of the fluid passageways, and directing a flow of second fluid through a second of the fluid passageways that is adjacent the first fluid passageway to facilitate exchanging heat between the first and second fluids.

Abstract: A low or no pollution power generation system is provided. The system has an air separator to collect oxygen. A gas generator is provided with inputs for the oxygen and a hydrocarbon fuel. The fuel and oxygen are combusted within the gas generator, forming water and carbon dioxide. Water or other diluents are also delivered into the gas generator to control temperature of the combustion products. The combustion products are then expanded through at least one turbine or other expander to deliver output power. The combustion products are then passed through a separator where the steam is condensed. A portion of the water is discharged and the remainder is routed back to the gas generator as diluent. The carbon dioxide can be conditioned for sequestration. The system can be optimized by adding multiple expanders, reheaters and water diluent preheaters, and by preheating air for an ion transfer membrane oxygen separation.

Abstract: The flow path of the exhaust of a recuperator of a microturbine engine system is routed to insulate the turbine exhaust in the recuperator. The recuperator is encapsulated for defining a passage for flowing the exhaust over the outer diameter of the recuperator so as to insulate the heat within the recuperator. A by-pass system that is operable mechanically or automatically directs turbine exhaust to by-pass the recuperator is disclosed in another embodiment. The by-pass serves to trim the efficiencies of the original manufactured microturbine engines so that all the engines attain a given preselected matching efficiency level. The by-pass can also be utilized to control the temperature of a boiler, chiller or other elements incorporated in the microturbine system by controlling the turbine exhaust to by-pass the recuperator.

Abstract: A wide-angle diffuser for a combustion turbine system having a turbine provides multiple expanding flow paths for the turbine exhaust. Each flow path is arranged to have the ideal diffusion angle for the given flow thus allowing for complete and efficient expansion of the turbine exhaust with a shorter length diffuser. An inner tube having an ideal diffusion angle is surrounded by a plurality of frustoconical tubes having larger opening angles producing a plurality of interstitial flow paths.

Abstract: The invention provides a gas turbine combustor in which the size of a combustor outer casing can be reduced. A transition inner duct and a transition outer duct are disposed in a main housing, inlet openings for a fluid to cool the transition inner duct are formed at ends of the transition outer duct on both sides nearer to the combustor liner and the turbine, and the transition outer duct is formed as an extraction flow passage for extracting the cooling fluid having flown in through the inlet openings to a recuperator. A partition member is also provided to prevent the fluid in the main housing and the fluid in the combustor outer casing from mixing with each other.

Abstract: A direct fired absorption chiller is combined with a microturbine engine that operates to power another medium includes a by-pass valve interconnecting the discharge end of the recuperator and the discharge end of the turbine so as to maintain a constant heat delivered to the chiller. A temperature monitoring sensor actuates the by-pass valve to assure that the proper heat is maintained in the chiller. In the preferred embodiment the microturbine powers an electrical generating system.

Abstract: A method of combustor cycle air flow adjustment for a gas turbine engine according to the present invention solves the problem of a higher flame temperature in the combustor, thereby affecting the emission levels when a heat-recuperated air flow cycle is used to increase the compressed air temperature. In low emission combustors this impact is severe because emission levels are significantly dependent on the primary combustion zone flame temperature. The method of the present invention includes a step of changing a geometry of an air flow passage and thereby changing distribution of a total air mass flow between an air mass flow for combustion and an air mass flow for cooling in order to ensure that flame temperature in a primary combustion zone of a combustor are maintained substantially the same whether the gas turbine engine is manufactured to operate as a simple air flow cycle engine or as a heat-recuperated air flow cycle engine.

Abstract: The microturbine engine that is typically utilized to power an electrical generating system and/or boiler, chiller and the like includes a second boiler and a by-pass system for providing heated water at two different levels or where one of the boilers provides steam. The turbine exhaust is utilized as the heat transport medium and is directly connected to one of the boilers while the other is connected to the recuperator. The system can optionally provide cooling to the electrical and electronic components of the system by providing a water circuit for leading water into the electric and electronic components prior to feeding the boilers. The system is designed to assure that the delta heat difference between the medium being heated and the waste heat of the turbine is sufficient so that the heat exchange will be done efficiently.

Abstract: A direct fired absorption chiller is combined with a microturbine engine that operates to power another medium includes a by-pass valve interconnecting the discharge end of the recuperator and the discharge end of the turbine so as to maintain a constant heat delivered to the chiller. A temperature monitoring sensor actuates the by-pass valve to assure that the proper heat is maintained in the chiller. In the preferred embodiment the microturbine powers an electrical generating system.

Abstract: An environmental control system includes a turbomachine and an air cycle machine that is driven by shaft power of the turbomachine. The turbomachine includes a compressor, which supplies compressed bleed air to the air cycle machine. Ambient air is compressed by the compressor, and heat of compression is removed by an air-to-air heat exchanger, which envelops the turbomachine. The cooled, compressed air is expanded in the air cycle machine to produce a stream of cooled, conditioned air. Ambient air used by the air-to-air heat exchanger to cool the compressed bleed air is drawn into the turbomachine's exhaust by an eductor.

Abstract: The annular recuperator for use with a microturbine includes an involuted shaped inner member with a portion thereof being corrugated and an involuted shaped outer member also with a portion thereof being corrugated and spaced therefrom to define a cell. The end portions of both the inner and outer members is planar and define a header for admitting and discharging the fluid flowing in the cell. The edges of the inner and outer members are sealed and an inlet and outlet are fluidly connected to the respective headers. The cells are circumferentially mounted side by side and abut each other but leaving sufficient space for another medium to flow through the space and be place in indirect heat exchange with the fluid flowing in the cell.

Abstract: Turbojet powerplant with at least one compressor (1), at least one combustion chamber (2), a high-pressure turbine (3) and a low-pressure turbine (4), characterised in that a heat exchanger (5) is arranged between the compressor (1) and the combustion chamber (2), in that at least one hot-gas line (6) branches off from an area downstream of the high-pressure turbine (3) and is connected to the heat exchanger (5), and in that at least one cold-gas line (7) connects the heat exchanger (5) with an area upstream of the low-pressure turbine (4).

Abstract: Combustion turbines and other types of turbines, whether axial or radial flow, have significant amounts of kinetic energy left in the exhaust gas (working fluid) after the working fluid has been fully expanded to atmosphere. This invention eliminates the exhaust loss typical to both impulse and reaction stages by using externally and rotating nozzles attached to the periphery of the turbine wheel. These nozzles are perpendicular and circumferential to the turbine's centerline. The external rotating nozzles turn the wheel by the production of thrust that create a rotating torque on the turbine's centerline. By controlling the turbine's wheel translational speed to equal the working fluid velocity exiting the nozzle, the exhaust gas (exit) loss is eliminated. In addition, other losses associated with conventional stationary nozzles turbines such as cosine losses, clearance losses and potential “stall” are eliminated.

Abstract: A gas turbine installation which includes a compressor which compresses supplied air and discharges the same, a combustor which combusts the compressed air obtained from the compressor and fuel and produces combustion gas, a turbine which is driven by combustion gas provided from the combustor, a regenerative heat exchanger which heats all or a part of the compressed air being supplied from the compressor to the combustor by making use of the heat of the exhaust gas exhausted from the turbine and a plurality of water spraying devices which are provided at positions from an intake air chamber of the compressor to the outlet of low temperature side gas flow passage in the regenerative heat exchanger and is characterized in that the regenerative heat exchanger is constituted by connecting in series a plurality of heat exchangers having different heat transfer surface configurations.

Abstract: A recuperator support includes a first pivot mount that defines a first pivot axis and a floating pivot mount that defines a floating pivot axis. The recuperator is coupled to the pivot mounts and pivotal about the pivot axes. The floating pivot mount accommodates thermal growth of the recuperator. The first pivot mount may be mounted to a frame such that the first pivot axis is fixed with respect to the frame.

Abstract: A gas turbine installation which includes a compressor which compresses supplied air and discharges the same, a combustor which combusts the compressed air obtained from the compressor and fuel and produces combustion gas, a turbine which is driven by combustion gas provided from the combustor, a regenerative heat exchanger which heats all or a part of the compressed air being supplied from the compressor to the combustor by making use of the heat of the exhaust gas exhausted from the turbine and a plurality of water spraying devices which are provided at positions from an intake air chamber of the compressor to the outlet of low temperature side gas flow passage in the regenerative heat exchanger and is characterized in that the regenerative heat exchanger is constituted by connecting in series a plurality of heat exchangers having different heat transfer surface configurations.

Abstract: The invention relates to a method for starting a power plant (1), in particular a gas storage power plant, with the following steps: S1: ignition of an auxiliary combustion chamber (19), S2: operation of the auxiliary combustion chamber (19) in such a way that the consequently heated gas introduced into a first flow path (13) has a temperature which is below a self-ignition temperature of a fuel/oxidizer/gas mixture delivered to the main combustion chamber (5) for starting the latter, S3: operation of the auxiliary combustion chamber (19) according to step S2, until a recuperator (12) has a predetermined preheating temperature, S4: Starting of a turbine (3) and ignition of the main combustion chamber (5).

Abstract: A recuperated gas turbine engine. The gas turbine engine includes a heat exchanger, and gas turbine (including compressor, can-type combustor and turbine). The heat exchanger includes a compressed air passageway and a turbine exhaust gas passageway adjacent to each other within the casing which extend spirally throughout the heat exchanger and towards an inner cylindrical chamber in which the combustor is positioned approximately to the center of the casing. Improved engine fuel efficiency is achieved by preheating the compressed air before it reaches the combustor with the higher-temperature exhaust gas. A can-type combustor is used for alleviating heat-dissipation issues to improve efficiency of the combustion. A concentric back-to-back rotor arrangement significantly shortens the length of a conventional engine turbine rotor which improves on the operational stability of a gas turbine engine.

Abstract: An integrated-cycle power system and method, comprising thermal transfer assembly, recuperating heat exchanger assembly, heat integrator, thermal conduit assembly and gas turbine. The thermal transfer assembly receives heat emitted from the effluent of a heat source, wherein the heat is preferably in the form of high temperature gas. Within the thermal transfer assembly, the energy of the high temperature gas is transferred to a conductive medium carried within a thermal conduit assembly. Due to a thermal potential between the augmenting heat source effluent and the heat integrator, the augmenting heat-source energy is transferred to the heat integrator, wherein energy from a novel recuperating heat exchange assembly is integrated therewith and introduced into the combustion chamber of a gas turbine. The recuperating heat exchanger assembly receives exhaust heat from the gas turbine and recuperates this energy via the heat integrator back into the combustion chamber of the gas turbine.

Abstract: The invention relates to a method of operating a gas turbine installation (1), compressed fresh air (6, 19, 38) is branched off after a compressor (2) and supplied to an evaporator device (14), in the evaporator device (14) feed water (17, 26, 28) is evaporated, while heat is supplied, and is mixed with the fresh air (6, 19, 38) in order to generate a steam/air mixture (22, 37), the steam/air mixture (22, 37) is fed back upstream of a gas turbine (10), the heat required for the evaporation of the feed water (17, 26, 28) is at least partially extracted from an exhaust gas (12) of the gas turbine (10). In order to improve the efficiency of the gas turbine installation (1), the feed water (17, 26, 28) runs down along a wall arrangement (39) heated by the exhaust gas (12) and is subjected to the fresh air (6, 19, 38). The feed water (17, 26, 28) evaporates and mixes with the fresh air (6, 19, 38), by which means the steam/air mixture (22, 37) forms for the recirculation.

Abstract: A heat exchanger for a turbine is provided wherein the heat exchanger comprises a heat transfer cell comprising a sheet of material having two opposed ends and two opposed sides. In addition, a plurality of concavities are disposed on a surface portion of the sheet of material so as to cause hydrodynamic interactions and affect a heat transfer rate of the turbine between a fluid and the concavities when the fluid is disposed over the concavities.

Abstract: In a method which, owing to improved environmental properties, allows production of power, power and thermal energy, power and cold, or power, thermal energy and cold, a system includes a compression unit is used for pressurizing a working fluid containing oxygen, preferably air. The system further comprises a combustion unit which downstream of the compressing unit, as seen in the direction of flow of the working fluid, is arranged to supply a first amount of heat to the working fluid by substantially complete combustion of a fuel in the working fluid. An expansion unit is arranged to produce mechanical work during expansion of the working fluid. A heat recovery unit is arranged downstream of the expansion unit to divert a second amount of heat from the working fluid at a pressure above atmospheric pressure.

Abstract: A recuperator (10) in a thermal power installation such as, for example, a gas turbine installation or air storage power installation, having turbines (15a, 15b) and a generator (G), has sectors (S1-S4) with tubes for the circulation of air. Hot exhaust gases from the turbines (15a, 15b) are supplied to the recuperator (10) for the purpose of heating the air flowing through the sectors (S1-S4). According to the invention, the recuperator (10) has one or a plurality of external heat storage devices (HS1, HS2, HS3) which are connected between the (S1-S4) of the recuperator (10) and are heated during the normal operation of the power installation. During an outage period of the power installation, air is circulated through the installation components (10, 15a, 15b, 19), a temperature distribution being maintained in these components with temperature differences which are smaller than a critical magnitude with respect to transient thermal stresses in the components of the recuperator.

Abstract: A turbine power generation system is provided for use with an off-gas fuel source. The system comprises first compression means for compressing air; second compression means for compressing off-gas; combustion means for combusting a mixture of said compressed air and a fuel comprising said off-gas; turbine means for converting energy released from combustion into mechanical energy; transduction means for converting the mechanical energy into electrical energy; a shaft linking the first compression means, turbine means, and transduction means, to allow mechanical energy produced by the turbine means to be used by the transduction means and first compression means; and an off-gas heating means for heating the compressed off-gas to a temperature greater than the gas dew point of the off-gas to ensure that no liquids are formed in the fuel gas supply to the combustor.

Abstract: A recuperated gas turbine engine is disclosed, comprising: a heat exchanger, and gas turbine (including compressor, can-type combustor and turbine); wherein, said heat exchanger comprises a compressed air passageway and a turbine exhaust gas passageway adjacent to each other within the casing which extend spirally throughout said heat exchanger and towards an inner cylindrical chamber in which said combustor is positioned approximately to the center of said casing. Improved engine fuel efficiency is achieved by preheating the compressed air before it reaches the combustor with the higher-temperature exhaust gas. A can-type combustor is used for alleviating heat-dissipation issues to improve efficiency of the combustion. A concentric back-to-back rotor arrangement significantly shortens the length of a conventional engine turbine rotor which improves on the operational stability of a gas turbine engine.

Abstract: The present invention relates to an air humidifier for adding moisture to a working medium of a gas turbine for humidification, and gas turbine electric power generation equipment for driving the gas turbine by the working medium of high moisture to generate electricity. An object of the present invention is to reduce pressure loss of burned exhaust gas of the gas turbine to improve output or efficiency of electric power generation. The invention comprises a humidifier (3), a combustor (5), a turbine (6), a generator (7), and a water recovery unit (10), and further comprises an exhaust gas reheater (11) for heating burned exhaust gas discharged from the water recovery unit by surplus water discharged from the humidifier.

Abstract: In a turbine engine with an annular recuperator surrounding the turbine, exhaust gas is directed from the turbine to the recuperator by a generally curved exhaust dome. A vortex disrupter structure extends from the exhaust dome to a point distal of the turbine to evenly distribute the exhaust gas entering the recuperator and sustain diffusion of the exhaust gas to increase the expansion ratio across the turbine.

Abstract: A compressed air energy storage system comprises a cavern (1) for stored compressed air and a system for providing the compressed air to a power train (3,5), this system including a recuperator (7) and a first valve arrangement (8) that controls the flow of the compressed air from the recuperator and to the power train (3,5). A system for warm-keeping of the power train (3,5) during stand-by operation of the compressed air energy storage system comprises the recuperator (2) and/or an auxiliary electrical air heater (11) and a second valve arrangement (10, 13) for controlling the airflow for warm-keeping. The system for warm-keeping of the power train allows improved temperature control and avoids disadvantages associated with a warm-keeping system having a combustor.

Abstract: An integrated-cycle power system and method, comprising thermal transfer assembly, recuperating heat exchanger assembly, heat integrator, thermal conduit assembly and gas turbine. The thermal transfer assembly receives heat emitted from the effluent of a heat source, wherein the heat is preferably in the form of high temperature gas. Within the thermal transfer assembly, the energy of the high temperature gas is transferred to a conductive medium carried within a thermal conduit assembly. Due to a thermal potential between the augmenting heat source effluent and the heat integrator, the augmenting heat-source energy is transferred to the heat integrator, wherein energy from a novel recuperating heat exchange assembly is integrated therewith and introduced into the combustion chamber of a gas turbine. The recuperating heat exchanger assembly receives exhaust heat from the gas turbine and recuperates this energy via the heat integrator back into the combustion chamber of the gas turbine.

Abstract: A method of combustor cycle air flow adjustment for a gas turbine engine according to the present invention solves the problem of a higher flame temperature in the combustor, thereby affecting the emission levels when a heat-recuperated air flow cycle is used to increase the compressed air temperature. In low emission combustors this impact is severe because emission levels are significantly dependent on the primary combustion zone flame temperature. The method of the present invention includes a step of changing a geometry of an air flow passage and thereby changing distribution of a total air mass flow between an air mass flow for combustion and an air mass flow for cooling in order to ensure that flame temperature in a primary combustion zone of a combustor are maintained substantially the same whether the gas turbine engine is manufactured to operate as a simple air flow cycle engine or as a heat-recuperated air flow cycle engine.

Abstract: The invention provides a method of operating a gas turbine arranged in a power generation system and comprising a source of compressed air, a combustor having a combustion chamber and multiple burners. A gas turbine controller controls the activation and deactivation of the single burners and/or burner groups according to a switching criterion that is proportional to the difference between a combustion chamber air inlet temperature and a temperature downstream of the combustion chamber. The switching criterion according to the invention fully accounts for large temperature fluctuations of the combustion chamber inlet air, which then result in only relatively small variations in burner equivalence ratio. The invention is particularly suited for application in compressed air energy power generation plants.

Abstract: An apparatus for supporting the recuperator of a microturbine system in a vertical position above a turbine. The apparatus including a plurality of spring supports supporting the recuperator while simultaneously allowing thermal expansion of the turbine with a minimum amount of force being applied thereto. Thermal expansion of the turbine causes it to lift the recuperator while simultaneously decompressing the springs an amount equal to the amount of thermal expansion experienced by the turbine.

Abstract: A cogenerating recuperated microturbine includes a recuperator, an air compressor and a combustor. The combustor burns a fuel along with the compressed air received from the recuperator to create products of combustion. A turbine generator operates in response to expansion of the products of combustion to generate electricity. The products of combustion then flow through the recuperator to preheat the compressed air. The products of combustion then flow out of the recuperator as an exhaust flow. A heat exchanger is movable into and out of the exhaust flow to selectively heat a fluid in the heat exchanger. The heat exchanger is actuated by a piston-cylinder type actuator that operates under the influence of compressed air selectively bled from the air compressor. The actuator may be a single-acting cylinder used in conjunction with a biasing spring, or may be a double-acting cylinder.

Abstract: In a turbine engine with an annular recuperator surrounding the turbine, exhaust gas is directed from the turbine to the recuperator by a generally curved exhaust dome. A vortex disrupter structure extends from the exhaust dome to a point distal of the turbine to evenly distribute the exhaust gas entering the recuperator and sustain diffusion of the exhaust gas to increase the expansion ratio across the turbine.

Abstract: A power generation plant with a compressed air energy storage system comprises a means to reduce the pressure of air extracted from a compressed air storage cavern for the use in a combustion turbine. The means to reduce the air pressure comprises at least one expansion turbine and means to control the size of pressure reduction. Furthermore, the expansion turbine is arranged on a rotor shaft that drives a generator. The means for pressure redact, according to the invention, avoid power losses and provide an increased overall efficiency of the power generation plant.

Abstract: As the development of gas and steam turbine systems has progressed, the steam turbine section, in particular, has become highly sophisticated and complex by being configured as a three-pressure system. In order to make a gas and steam turbine system of economic interest for medium and low power levels as well, and with high efficiencies, the steam turbine section is configured as a two-pressure system, and the combustion air for the system is compressed in at least two stages. In the process, the combustion air is cooled after at least one compression stage, and is heated at least after the last stage of the two stages.

Abstract: A method and system for generating power include using a cogeneration power system having a gas turbine. The gas turbine has a compressor section for receiving air to be compressed. The compressed air is fed to a combustor section where it is mixed with fuel and the fuel is burned to produce heated combustion gas. The heated combustion gas is expanded in an expander section to generate shaft work which is used to drive a generator or alternator for producing electric power. The heated combustion gas leaves the expander as turbine exhaust which is cooled by transferring at least part of its heat to the air ahead of the combustor.