Abstract: An apparatus performs a power cycle involving expansion of compressed air utilizing high pressure (HP) and low pressure (LP) air turbines located upstream of a gas turbine. The power cycle involves heating of the compressed air prior to its expansion in the HP and LP air turbines. Taking into consideration fuel consumption to heat the compressed air, particular embodiments may result in a net production of electrical energy of ˜2.2-2.5× an amount of energy consumed by substantially isothermal air compression to produce the compressed air supply. Although pressure of the compressed air supply may vary over a range (e.g. as a compressed air storage unit is depleted), the gas turbine may run under almost constant conditions, facilitating its integration with the apparatus. The air turbines may operate at lower temperatures than the gas turbine, and they may include features of turbines employed to turbocharge large reciprocating engines.

Abstract: The invention relates to a method for operation of a combined-cycle power plant with cogeneration, in which method combustion air is inducted in at least one gas turbine, is compressed and is supplied to at least one combustion chamber for combustion of a fuel, and the resultant exhaust gas is expanded in at least one turbine, producing work, and in which method the exhaust gas emerging from the at least one turbine is passed through a heat recovery steam generator in order to generate steam, which generator is part of a water-steam circuit with at least one steam turbine, a condenser, a feedwater tank and a feedwater pump, wherein heat is provided by extracting steam from the at least one steam turbine.

Abstract: A system, including a superconductive heat transfer assembly, including, a first superconductive heat transfer pipe, a second superconductive heat transfer pipe, and a superconductive heat transfer contact switch configured to open and close a gap between the first superconductive heat transfer pipe and the second superconductive heat transfer pipe.

Abstract: A system includes a turbine combustor, a turbine driven by combustion products from the turbine combustor, and an exhaust gas compressor. The exhaust compressor is configured to compress and route an exhaust gas from the turbine to the turbine combustor. The system also includes an exhaust gas recirculation (EGR) path extending through the exhaust gas compressor, the turbine combustor, and the turbine, a first exhaust gas (EG) extraction port disposed along the EGR path, and a second EG extraction port disposed along the EGR path.

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

Abstract: A system includes an oxidant compressor and a gas turbine engine. The gas turbine engine includes a combustor section having a turbine combustor, a turbine driven by combustion products from the turbine combustor, and an exhaust gas compressor driven by the turbine. The exhaust gas compressor is configured to compress and route an exhaust flow to the turbine combustor and the oxidant compressor is configured to compress and route an oxidant flow to the turbine combustor. The gas turbine engine also includes an inlet oxidant heating system configured to route at least one of a first portion of the combustion products, or a second portion of the exhaust flow, or any combination thereof, to an inlet of the oxidant compressor.

Abstract: An integrated turbomachine plant is provided and includes a combustor a turbomachine operably connected to the combustor and including a compressor and a turbine expander, a pathway to flow compressed air from the compressor through the turbine expander to heat the compressed air, an additional pathway by which high temperature fluids output from the turbomachine are employed to heat the compressed air and an air separation unit operably connected to the pathway and configured to separate the heated compressed air into oxygen and oxygen-depleted air.

Abstract: A device and a method for using overcapacities in the power grid is provided. In case of an oversupply of energy, the energy is transferred to a thermal storage device directly via a heating element and in the discharge case of the thermal storage device the heat is removed from the thermal storage device and made available to a thermodynamic cycle whereby electrical energy is produced. The heat from the thermal storage device is used to preheat air in an air feed line to a combustion chamber, or fuel is pre-heated using heat from the thermal storage device.

Abstract: A micro gas turbine system (16) having an annular recuperator (24). The recuperator (24) serves to transfer heat from an exhaust stream (27) of the turbine (17) to an air stream (23) compressed by a compressor (19). Passages (1) for the exhaust stream (27) and passages (2) for the air stream (23) are arranged in alternation to each other in the recuperator (24). Adjacent passages (1, 2) are separated from each other by at least one wall (15). A filler (5) is arranged in the passages (1, 2) of at least one fluid stream.

Abstract: A turbine system and method of operating is provided. The system includes a compressor configured to generate a compressed low-oxygen air stream and a combustor configured to receive the compressed low-oxygen air stream and to combust a fuel stream to generate a post combustion gas stream. The turbine system also includes a turbine for receiving the post combustion gas stream to generate a low-NOx exhaust gas stream, a heat recovery system configured to receive the low-NOx exhaust gas stream and generate a cooled air stream and an auxiliary compressor configured to generate an oxygen and water vapor deficient cooled and compressed air stream. A portion of the oxygen and water vapor deficient cooled and compressed air stream is directed to the combustor to generate an Oxygen and H2O deficient film on exposed portions of the combustor, and another portion is directed to the turbine to provide a cooling flow.

Abstract: The invention is directed to a process to obtain a compressed gas starting from a starting gas having a lower pressure by performing the following steps: (i) increasing the pressure and temperature of a gas having an intermediate pressure by means of indirect heat exchange against a fluid having a higher temperature to obtain a gas high in pressure and temperature, (ii) obtaining part of the gas high in temperature and pressure as the compressed gas, (iii) using another part of the gas high in temperature and pressure as a driving gas to increase the pressure of the starting gas in one or more stages to obtain the gas having an intermediate pressure for use in step (i). The invention is also directed to a configuration wherein the process can be performed and directed to a process to generate energy using the process.

Abstract: The present invention discloses a novel apparatus and methods for augmenting the power of a gas turbine engine, improving gas turbine engine operation, and reducing the response time necessary to meet changing demands of a power plant. Improvements in power augmentation and engine operation include additional heated compressed air injection, steam injection, water recovery, exhaust tempering, fuel heating, and stored heated air injection.

Abstract: The present invention provides an inductively coupled plasma device with a cylindrical vessel having a first end and a second end, wherein at least a portion of the cylindrical vessel is transparent or semi-transparent to a wave energy. A tangential inlet is connected to or proximate to the first end. A tangential outlet is connected to or proximate to the second end. An electrode housing is connected to the first end of the cylindrical vessel such that a first electrode is (a) aligned with a longitudinal axis of the cylindrical vessel, and (b) extends into the cylindrical vessel. A hollow electrode nozzle is connected to the second end of the cylindrical vessel such that the center line of the hollow electrode nozzle is aligned with the longitudinal axis of the cylindrical vessel. An electromagnetic radiation source that produces a wave energy and is disposed around or within the cylindrical vessel.

Abstract: The present invention discloses a novel apparatus and methods for augmenting the power of a gas turbine engine, improving gas turbine engine operation, and reducing the response time necessary to meet changing demands of a power plant. Improvements in power augmentation and engine operation include additional heated compressed air injection, steam injection, water recovery, exhaust tempering, fuel heating, and stored heated air injection.

Abstract: A regenerative gas turbine combustor is provided that enable to reduce an amount of leakage of compressed air before preheating to compressed air after the preheating. The regenerative gas turbine combustor is such that a compressed air passage between a combustor inner cylinder 10 and a tail cylinder 12, and a combustor outer cylinder 7 is blocked by a division wall 15 at a position between a bleeding port 13 and an injection port 14, and compressed air is preheated in a regenerator 4 and then the compressed air thus preheated is burnt together with fuel. This combustor includes seal rings 17a-17c, a holder 16 installed on the inner circumferential portion of the division wall 15 and having ring grooves 25a-25c for holding the respective seal rings 17a-17c, and gaps 20 provided between the inner circumferential surfaces of the ring grooves 25a-25c and the outer circumferential surfaces of the seal rings 17a-17c.

Abstract: The integrated solar-gas turbine cogeneration plant includes a fuel reformer, a plurality of solar collectors, and a gas turbine. The fuel reformer produces syngas to be used as fuel for the gas turbine. One solar collector is operatively connected to both the fuel reformer and the turbine to provide heat for the reforming reaction and to preheat air for a combustion chamber. Exhaust gas from the turbine is directed to the fuel reformer and to a heat recovery steam generator, the former as an additional heat source and the latter to heat the generator. Another solar collector is connected to the generator and heats a portion of the water being fed into the generator in order to help produce steam. The syngas is stored in a fuel storage unit to provide fuel to the gas turbine continuously and to a supplemental heater on the steam generator during low insolation periods.

Abstract: A recuperator disposed in the exhaust duct of a gas turbine engine includes a plurality of recuperator plates arranged in a spaced-apart relationship to define therebetween a plurality of interstices and fluid channels, the plurality of interstices adapted to direct therethrough at least one first stream received at a leading plate edge of the recuperator plates and the plurality of fluid channels adapted to direct therethrough at least one second stream to effect heat exchange between the at least one first stream and the at least one second stream. Each recuperator plate includes, formed at the leading plate edge thereof, a first concavity extending along the leading edge in a direction substantially parallel to a longitudinal axis of the plate. The first concavity extends transversely to a direction of the at least one first stream flowing over each recuperator plate.

Abstract: The present invention provides a plasma arc torch that can be used for lean combustion. The plasma arc torch includes a cylindrical vessel, an electrode housing connected to the first end of the cylindrical vessel such that a first electrode is (a) aligned with a longitudinal axis of the cylindrical vessel, and (b) extends into the cylindrical vessel, a linear actuator connected to the first electrode to adjust a position of the first electrode, a hollow electrode nozzle connected to the second end of the cylindrical vessel such that the center line of the hollow electrode nozzle is aligned with the longitudinal axis of the cylindrical vessel, and wherein the tangential inlet and the tangential outlet create a vortex within the cylindrical vessel, and the first electrode and the hollow electrode nozzle create a plasma that discharges through the hollow electrode nozzle.

Abstract: Provided is a lean fuel sucking gas turbine system including a compressor for compressing a mixed gas having a fuel and air mixed to a concentration of an inflammable limit or lower, thereby producing a compressed gas, a first catalyst combustor for burning the compressed gas by a catalyst reaction, a turbine adapted to be driven by a combustion gas from a second catalyst combustor, and a reproducer for heating the compressed gas to be introduced into the first catalyst combustor with an exhaust gas from the turbine. Between the turbine and the reproducer, there is arranged a duct burner for flame-burning a first auxiliary fuel in the exhaust gas. Thus, it is possible to attain efficient operation of the system while simplifying the entire constitution and to prevent the blow-by of the mixed gas.

Abstract: The present techniques are directed to a system and methods for operating a gas turbine system. An exemplary gas turbine system includes an oxidant system, a fuel system, and a control system. A combustor is adapted to receive and combust an oxidant from the oxidant system and a fuel from the fuel system to produce an exhaust gas. A catalyst unit including an oxidation catalyst that includes an oxygen storage component is configured to reduce the concentration of oxygen in the exhaust gas to form a low oxygen content product gas.

Abstract: Described herein are embodiments of systems and methods for oxidizing gases. In some embodiments, a reaction chamber is configured to receive a fuel gas and maintain the gas at a temperature within the reaction chamber that is above an autoignition temperature of the gas. The reaction chamber may also be configured to maintain a reaction temperature within the reaction chamber below a flameout temperature. In some embodiments, heat and product gases from the oxidation process can be used, for example, to drive a turbine, reciprocating engine, and injected back into the reaction chamber.

Abstract: A method of assembling a turbine engine is provided. The method includes providing a heat exchanger having a curvilinear body. The method also includes coupling the heat exchanger to at least one of a fan casing and an engine casing of the turbine engine. The curvilinear body facilitates reducing pressure losses in airflow channeled into the heat exchanger.

Abstract: An apparatus performs a power cycle involving expansion of compressed air utilizing high pressure (HP) and low pressure (LP) air turbines located upstream of a gas turbine. The power cycle involves heating of the compressed air prior to its expansion in the HP and LP air turbines. Taking into consideration fuel consumption to heat the compressed air, particular embodiments may result in a net production of electrical energy of ˜2.2-2.5× an amount of energy consumed by substantially isothermal air compression to produce the compressed air supply. Although pressure of the compressed air supply may vary over a range (e.g. as a compressed air storage unit is depleted), the gas turbine may run under almost constant conditions, facilitating its integration with the apparatus. The air turbines may operate at lower temperatures than the gas turbine, and they may include features of turbines employed to turbocharge large reciprocating engines.

Abstract: The present application provides a gas turbine system. The gas turbine system may include a gas turbine engine producing a flow of exhaust gases, a heat recovery steam generator with a reheater and an evaporator in communication with the flow of exhaust gases, and a gas flow control system for diverting a first portion of the flow of exhaust gases away from the reheater and towards the evaporator.

Abstract: An apparatus performs a power cycle involving expansion of compressed air utilizing high pressure (HP) and low pressure (LP) air turbines located upstream of a gas turbine. The power cycle involves heating of the compressed air prior to its expansion in the HP and LP air turbines. Taking into consideration fuel consumption to heat the compressed air, particular embodiments may result in a net production of electrical energy of ˜2.2-2.5× an amount of energy consumed by substantially isothermal air compression to produce the compressed air supply. Although pressure of the compressed air supply may vary over a range (e.g. as a compressed air storage unit is depleted), the gas turbine may run under almost constant conditions, facilitating its integration with the apparatus. The air turbines may operate at lower temperatures than the gas turbine, and they may include features of turbines employed to turbocharge large reciprocating engines.

Abstract: A gas turbine plant is provided with exhaust gas recirculation and includes a main gas turbine having a main compressor and main turbine driving a main generator, and a combustion chamber, with an outlet connected to the inlet of the main gas turbine, has a fuel feed, and via the recuperator's high-pressure side obtains combustion air from the main gas turbine's compressor outlet. The outlet of the main turbine and the inlet of the main compressor are connected via the recuperator's low-pressure side and a cooler for exhaust gas recirculation. On the recuperator's low-pressure side, a charging unit, with a compressor and a turbine is arranged, and draws in air via an air intake and by the outlet of its compressor is connected to the recuperator's low-pressure side outlet and by the inlet of its turbine is connected to a surplus-gas extraction line on the recuperator's low-pressure side.

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: 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: An integrated absorption refrigeration and dehumidification system includes an absorber containing an absorption solution, an after-cooler having a flow path to receive the solution and a flow path to receive a warm fluid, the flow paths being thermally coupled to separate a refrigerant from the solution, and an auxiliary heat exchanger having a flow path to receive the solution from the after-cooler and a flow path to receive a warm fluid, the flow paths being thermally coupled to separate more refrigerant from the solution. The system also includes a condenser positioned to receive and cool the refrigerant from the auxiliary heater, an expansion valve positioned to receive the refrigerant from the condenser, an evaporator positioned to receive the refrigerant from the expansion valve and the warm fluid from the after-cooler, and a separator to remove condensate from the warm fluid from the after-cooler or a cool fluid from the evaporator.

Abstract: An annular design heat exchanger is formed from an arrangement of wedge-shaped stacks of wafers. Each wafer includes sheets of material separated by peripheral and supporting walls that define interior flow channels through which a first fluid can flow. Holes in the sheets provide inlets and outlets to the channels, and walls surrounding the holes mate with neighboring wafers in the stack, forming integral inlet and outlet manifolds, while ensuring uniform spacing between the wafers. A second fluid can flow around the manifolds and through the spaces between the wafers in a counterflow pattern. In the annular assembly, the manifolds are oriented substantially axially, and the flow channels are oriented substantially radially. The heat exchanger can be formed from a ceramic material, and can be incorporated into an engine assembly or a heat-recirculating combustor.

Abstract: A power generation system and method of generating power with reduced NOx emission includes a gas turbine system. The turbine system includes a compressor configured to receive a feed oxidant stream and supply a compressed oxidant stream to a combustion chamber and an expander configured to receive a discharge stream from the combustion chamber and generate an exhaust stream comprising carbon dioxide and electrical energy. The system further includes an exhaust gas recirculation system configured to generate a recycle stream, wherein the recycle stream is mixed with a fresh oxidant to generate the feed oxidant stream. The exhaust gas recirculation system includes an exhaust gas recirculation control loop to control a pilot ratio (diffusion to total fuel ratio) based on received feedback related to combustion parameters. The control loop configured to control the pilot ratio required to keep NOx in its minimum ratios with improved flame stability.

Abstract: A gas turbine engine recuperator system includes a heat recuperator positioned in a gas turbine exhaust gas duct for recovering heat from turbine exhaust gases to preheat a compressor flow being supplied to the combustor. A continuous bleed flow of the turbine exhaust gases is provided to bypass the heat recuperator. The continuous bleed flow of the turbine exhaust gases is adjustable to reduce turbine exhaust gas pressure loss at a high engine operation level and to provide efficient heat recovery at low and/or medium engine operation levels.

Abstract: A recuperated micro gas turbine combustor has a casing, liner, fuel injector and a flame stabilization device. This flame stabilization device is characterized by a swirl strength and air passage geometry as such that the pressure loss over the device is less than 1.5%. The flame stabilization device and the fuel injector form together with the liner inlet/head hardware a single burner.

Abstract: Systems and methods for improving the efficiency of a power generation facility utilize heat energy to preheat inlet-air that is supplied to the compressor of a turbine or to preheat fuel that is burned in the turbine. The heat energy used to preheat the inlet-air can be drawn from a heat recovery steam generator (HRSG) that produces steam using at least part of the exhaust gas of the turbine. The heat energy can be obtained from one or more predetermined points within the HRSG, such as a feed water line exiting a drum of the HRSG or a feed line connecting an economizer of the HRSG to a drum of the HRSG. The fluid drawn from the predetermined point passes through a heat exchanger or a preheater to remove the heat energy used for preheating. The fluid is then returned to the HRSG immediately downstream from the point from which it was drawn.

Abstract: A heat recuperator includes a plurality of channel walls composed substantially of thermally-conductive material and supported in spaced-apart relation, defining fluid channels and interstices therebetween. The fluid channels receive at least one primary fluid flow and the interstices receive at least one secondary fluid flow so as to effect heat exchange between the two flows. In use, the plurality of channel walls are deformable by pressure differential between the primary and secondary fluid flows. When at least some of the channel walls are in a deformed state, the plurality of channel walls are stabilized through press fit engagement of mutually opposed contact regions formed in adjacent pairs of the channel walls.

Abstract: Systems, methods, and computer program products are disclosed that overcome the deficiencies of traditional steam engines and internal combustion engines. In an embodiment, a system is disclosed for generating reaction products having elevated temperature and pressure. The system comprises a first chamber including a reactor to decompose hydrogen peroxide to generate oxygen and water vapor. The system further comprises a second chamber including a reactor to catalytically combust a mixture of the generated oxygen and a fuel to generate reaction products having elevated temperature and pressure. The system further comprises a passageway to receive reaction products exiting the second chamber and to channel the reaction products to come into contact with external surfaces of the first and second chambers to thereby transfer heat to the first and second chambers, and an outlet to allow the reaction products to exit the system.

Abstract: A gas turbine engine system includes a gas turbine engine using vaporized liquefied gas as fuel. The gas turbine engine is configured to ingest intake air from an intake port and direct exhaust gases to an exhaust port. The gas turbine engine system also includes a heat exchanger with a heat transfer fluid therein. The heat exchanger is configured to create at least a part of the fuel by heating the liquefied gas. The gas turbine engine system also includes an intake air temperature control circuit. The intake air temperature control circuit includes conduits configured to direct the heat transfer fluid to the intake port and the exhaust port. The gas turbine engine system also includes a control system configured to selectively direct the heat transfer fluid to one of the intake port and the exhaust port.

Abstract: A gas turbine power plant and a method for operating a gas turbine power plant are provided. The power plant includes a gas turbine installation which may supply a mains supply network with electric power and includes a compressor and an associated first gas turbine. Differing from previous gas turbine installations, the compressor of the gas turbine installation and the first gas turbine of the gas turbine installation are decoupled from each other. A second turbine is provided which drives compressor. As a result, the compressor of the gas turbine installation is operated independently of the first gas turbine. Influences on the mains supply network side, such as generating deficiencies in the main supply network, which act upon the first gas turbine as a result of speed reduction, are also not able to have an impact upon the compressor which is decoupled from the first gas turbine.

Abstract: A system includes a gas production source configured to produce a gas stream comprising nitrogen oxides (NOx) and a hydrocarbon injector disposed downstream of the gas production source and configured to inject a hydrocarbon into the gas stream. The hydrocarbon is configured to oxidize molecules of the NOx in the gas stream to produce a higher order compound of nitrogen and oxygen (NyOz). The system also includes a removal device disposed downstream of the hydrocarbon injector. The removal device is configured to remove the NyOz from the gas stream via absorption or reaction.

Abstract: A machine for recovering power from a flow of compressed gas, for example, natural gas includes a turbo-expander having a turbo-expander wheel, and a generator having a rotor able to be driven by the turbo-expander wheel and a stator about the rotor. The turbo-expander and the generator are housed in a length of pipe. The turbo-expander wheel has an obverse side facing the generator. There is a flow passage for the flow of expanded gas that places the obverse side of the wheel in gas flow communication with an outer surface of the stator. This outer surface typically carries fins to facilitate cooling of the stator by expanded gas from the turbo-expander.

Abstract: A gas turbine power generation plant including: a solid fuel gasifier for the production of a fuel gas stream, an arrangement for fuel gas treatment, a combustor for receiving the fuel gas stream and for the production of a flue gas stream, a gas turbine unit having an inlet for said flue gas stream and being mechanically coupled to an electric generator for the extraction of useful work; a compressor unit for the supply of compressed oxygen to the combustor. A steam generator is arranged for heat recovery in the flue gas stream downstream of the turbine unit positioned for water recovery in the flue gas stream, said condenser having a connection for water supply to the steam generator, and the steam generator is connected for supply of steam to the combustor for contributing as process gas. The invention also concerns a method for operating a power plant and an arrangement and a method for fuel gas treatment.

Abstract: A by-pass turbofan gas turbine engine, has a by-pass fan, a generally annular core engine duct, a generally annular by-pass duct situated in a generally coaxial relationship with the core engine duct coupled to the by-pass fan, an upstream axial compressor coupled to the core engine duct, a downstream radial compressor coupled to the upstream compressor, a generally annular recuperator with a cool side inlet coupled to the downstream compressor, a generally annular combustor coupled to a cool side outlet of the recuperator, a radial turbine coupled to the combustor and a warm side inlet of the recuperator coupled to the radial turbine, at least one exhaust nozzle coupled to a warm side outlet of the recuperator that discharges into the by-pass duct and a propelling nozzle coupled to the by-pass duct.

Abstract: An integrated turbomachine plant is provided and includes a combustor a turbomachine operably connected to the combustor and including a compressor and a turbine expander, a pathway to flow compressed air from the compressor through the turbine expander to heat the compressed air, an additional pathway by which high temperature fluids output from the turbomachine are employed to heat the compressed air and an air separation unit operably connected to the pathway and configured to separate the heated compressed air into oxygen and oxygen-depleted air.

Abstract: An integrated oxy-combustion power generation process is provided. This process includes providing an air separation unit for producing at least an oxygen-enriched stream, providing a carbon dioxide recycle stream, which is combined with the oxygen-enriched stream thereby producing a synthetic air stream, providing a gas turbine comprising a gas inlet , a combustor, and a gas outlet, wherein the synthetic air stream is introduced into the gas inlet, providing a fuel stream to the combustor, thereby producing a power output, and a hot exhaust gas stream, which exits the gas outlet, introducing the exhaust gas stream, along with a boiler feed water stream, into a heat recovery steam generator, thereby producing a steam stream and a cooled exhaust gas stream, and separating the cooled exhaust gas stream into an enriched carbon dioxide product stream and the carbon dioxide recycle stream.

Abstract: An internal combustion engine includes in one aspect a source of a pressurized working medium and an expander. The expander has a housing and a piston, movably mounted within and with respect to the housing, to perform one of rotation and reciprocation, each complete rotation or reciprocation defining at least a part of a cycle of the engine. The expander also includes a septum, mounted within the housing and movable with respect to the housing and the piston so as to define in conjunction therewith, over first and second angular ranges of the cycle, a working chamber that is isolated from an intake port and an exhaust port. Combustion occurs at least over the first angular range of the cycle to provide heat to the working medium and so as to increase its pressure.

Abstract: A heating and cooling system for inlet air of a gas turbine engine in a combined cycle power plant having a steam turbine. The heating and cooling system may include a fluid coil positioned about the gas turbine engine, a heat exchanger in communication with the fluid coil, and a condenser in communication with the steam turbine and the heat exchanger such that waste heat from the steam turbine is forwarded to the fluid coil.

Abstract: A gas turbine engine including a compressor, a combustion chamber and a turbine arranged in flow series, wherein the gas turbine engine further includes: one or more combustion zones; a source of steam configured to deliver steam to the combustion chamber; and a liquid water delivery system configured to selectively provide liquid water to one or more of the combustion zones after a start up period of the gas turbine engine. A method of generating power with a gas turbine engine, the gas turbine engine including a compressor, a combustion chamber and a turbine arranged in flow series, wherein the method includes: selectively delivering steam from a source of steam to the combustion chamber; and providing liquid water to one or more combustion zones after a start up period of the gas turbine engine.

Abstract: A compressor-less micro gas turbine has a compressed working medium container for maintaining a gas turbine under pressure. A combustion chamber is in fluid communication with the compressed gas container for receiving a gas from the gas container and heating the gas within the combustion chamber to create an expanded gas. A heater heats the combustion chamber to expand the working gas therein. A turbine in fluid communication with the combustion chamber for receiving the expanded gas. The expanded gas drives the turbine. A generator is operatively coupled to the turbine. The turbine provides a mechanical input to the generator causing the generator to produce electricity.

Abstract: A method is disclosed for directing flow to a combustor embedded in a recuperator while shielding the recuperator from radiative heat transfer from the combustor. The radiation heat shield also serves as a structural component to center the combustor within the recuperator core cavity and to allow motion between the combustor and recuperator as temperatures vary. The disclosure is illustrated by the example a gas turbine engine comprising three turbomachinery spools, an intercooler, a recuperator and a combustor. Thermal efficiency of such an engine can be increased by raising the high pressure turbine inlet temperature. It is a specific goal of the present disclosure to reduce radiative heating of a recuperator by a combustor which is housed substantially inside the recuperator.

Abstract: The present application provides a stoichiometric exhaust gas recovery turbine system. The stoichiometric exhaust gas recovery turbine system may include a main compressor for compressing a flow of ambient air, a turbine, and a stoichiometric exhaust gas recovery combustor. The stoichiometric exhaust gas recovery combustor may include a combustion liner, an extended flow sleeve in communication with the main compressor, and an extraction port in communication with the turbine. The extended flow sleeve receives the flow of ambient air from the main compressor so as to cool the combustion liner and then the flow of ambient air splits into an extraction flow to the turbine via the extraction port and a combustion flow within the combustion liner.