Abstract: Systems and methods are provided for generating and using decarbonized fuel for power generation. In particular, the integrated systems and methods are provided for generating a synthesis gas, removing carbon dioxide from the synthesis gas and using the synthesis gas for producing power.

Abstract: An apparatus is provided for supplying electrical power and cooling for an aircraft. The apparatus includes a cooling turbine coupled to a shaft, a compressor coupled to the shaft, and including an input for receiving engine bleed air or ambient air, and an output for discharging compressed air, a flywheel coupled to the shaft, a power turbine coupled to the shaft, and a starter generator coupled to the shaft between the compressor and the power turbine.

Abstract: A gas turbine engine installation is provided that has a flexible printed circuit board (FPCB) harness to transfer electrical signals, including electrical power, around a gas turbine engine. The FPCB harness is held to the gas turbine engine installation using clips. The clips have a jaw that has two sets of opposing teeth extending from a base, and a mouth through which the FPCB harness is inserted. The teeth point in a direction that has a component from the mouth to the teeth. This means that the force required to insert the FPCB harness into the clip is lower than the force required to pull the FPCB harness out of the clip in the opposite direction. This means that the FPCB harness can be secured in place whilst aiding ease of assembly.

Abstract: A turbine includes a rotor having at least two rotor members for rotating in a plane, the rotor members being substantially diametrically arranged and attached to an axis situated substantially transversely to the plane, and drive unit coupled to the axis, wherein the rotor members include a fluid contact member, that is hingingly connected to an arm which is attached to the axis, characterized in that the fluid contact members are adapted to hinge between a fluid-active position in which the members project transversely to the plane and a fluid-transparent position in which the members extend mainly parallel to the plane.

Abstract: An auxiliary power unit includes a turbomachine coupled to a generator. A flow path is arranged through the generator and is configured to provide fluid to the generator. A deprime valve is arranged in the flow path and is configured to pulse fluid flow to the generator in response to a command. A controller is configured to send the command to the deprime valve to pulse the fluid flow throughout operation of the auxiliary power unit.

Abstract: The invention relates to a fluid separator 40 having first and second inlets, a turbine and a separation chamber having a centrifugal separation member. The first inlet is in direct fluid communication with a turbine inlet, and in use delivers high pressure vent air flow from a first gas turbine engine bearing housing to the turbine. The second inlet is in direct fluid communication with the centrifugal separation member, and in use delivers low pressure vent air flow from a second gas turbine engine bearing housing to the centrifugal separation member. An outlet of the turbine is in direct fluid communication with the centrifugal separation member. The centrifugal separation member is driven by the turbine.

Abstract: Combined cycle efficiency can be improved by heating fuel in a gas turbine fuel line in two stages using (i) hot water from an HP economizer of a heat recovery steam generator (HRSG) in a second stage and (ii) hot water from an IP economizer of the HRSG and water output flow from the second stage in a first stage. Efficiency may be further improved by adding one or more fuel preheaters using hot water from the IP feedpump and sequential injections of hot water into the fuel.

Abstract: This invention discloses systems and methods for control of a gas turbine or a gas turbine generator, where the gas turbine is connected to a dryer vessel in which gas turbine exhaust gases are used to heat treat a material in the dryer vessel. The control system comprises one or more sensors for temperature, moisture and/or flow rate in the dryer vessel and/or of the material inside, entering and/or exiting the dryer vessel and a controller responsive to the sensor for controlling the fuel and/or air flow into the gas turbine. This control system and method enables providing the appropriate heat output from the gas turbine to meet the process heat required for the desired material treatment. Optionally, the gas turbine can be a liquid fuel turbine engine, or a reciprocating engine can be substituted for the turbine engine.

Abstract: An air starter for turbomachine, including a forward casing, an aft casing, an annular exhaust flow path opening up between an aft end of the forward casing and a forward end of the aft casing, and a cylindrical outlet mesh of the exhaust flow path is disclosed. The forward and aft ends of the outlet mesh include devices for axially retaining the forward casing and the aft casing respectively to the mesh. At least one of the devices for axially retaining one of the casings to the mesh enables a relative rotation of the mesh and this casing.

Abstract: An integrated gasification combined cycle power generation system (100). In one embodiment, shown in FIG. 1, a gasifier (108) is configured to generate synthetic gas (117) from a carbonaceous material (106) and an oxygen supply (109) with a cleaning stage (120) positioned to receive synthetic gas (117) from the gasifier (108) and remove impurities therefrom. A gas turbine combustion system (2) including a turbine (123) is configured to receive fuel (128) from the gasifier (108) and a first air supply (131) from a first air compressor (130). A steam turbine system (4) is configured to generate power with heat recovered from exhaust (140) generated by the gas turbine system (2) and an ion transport membrane air separation unit (110) includes a second air compressor (114) for generating a second air supply (113).

Abstract: A method of controlling variable extraction flow in a combustion turbine engine, wherein extraction flow comprises a supply of compressed air extracted from the compressor and supplied to the turbine through extraction conduits, and wherein the extraction conduits includes a variable extraction orifice, the method comprising the steps of: measuring a plurality of turbine engine operating parameters; monitoring, by a control unit, the measured operating parameters of the combustion turbine engine; setting the variable extraction orifices to a setting that allows an approximate maximum level of extraction flow; calculating, by the control unit, at least one calculated operating parameter based upon model-based control and the measured operating parameters, including at least a current turbine inlet temperature and a maximum turbine inlet temperature; and manipulating the setting for the supply of fuel to the combustor such that an increased and/or maximum level of engine output is determined by comparing the va

Abstract: A gas turbine engine and an accessory gear box (AGB) are provided for. The gas turbine engine comprises a drive shaft, a compressor, a combustor and an exhaust turbine, where the exhaust turbine and the compressor are coaxially connected by the drive shaft. The gas turbine engine further comprises an engine casing of varying diameters circumferentially enveloping the compressor, the combustor and the exhaust turbine with a waist located between the compressor and the combustor. The gas turbine engine also includes an accessory gear box (AGB) attached to the engine casing at the waist, the AGB comprising a gear rotating on an axis extending in a transverse direction relative to that of the drive shaft.

Abstract: The present application and the resultant patent provide a feed injector nozzle for a gasification system with a reaction zone therein. The feed injector nozzle may include a number of tubes extending towards the reaction zone. The tubes may define a number of passages therebetween. A cooling water channel may extend through one of the tubes. The cooling water channel may include a first side adjacent to one of the passages and a second side adjacent to the reaction zone. The first side may include a first side thickness and the second side may include a second side thickness with the first side thickness being less than or equal to the second side thickness.

Abstract: A system for managing fuel temperature in an engine includes a source of hot pressurized air and a turbine for converting hot pressurized air into cool expanded air. The system further includes a fuel tank for storing fuel, a fuel conduit fluidly connected to the fuel tank, and a first heat exchanger located on the fuel conduit. The first heat exchanger places the cool expanded air from the turbine in a heat exchange relationship with the fuel, thereby cooling the fuel.

Abstract: The device according to the invention comprises at least one main reservoir (130A, 130B), the or each main reservoir (130A, 130B) being designed to contain a first batch of fuel. It comprises at least one feed line (144C, 144D) for supplying a propulsion engine (16A, 16B) of the aircraft with the first batch of fuel contained in the main reservoir (130A, 130B). The device (18) comprises at least one auxiliary reservoir (132), designed to contain a second batch of fuel separate from the first batch of fuel, the auxiliary reservoir (132) being connected to the main reservoir (130A, 130B). The device (18) comprises an intake line (160) for bringing the second batch of fuel contained in the auxiliary reservoir (132) toward a combustion chamber of the aircraft independent of the or each engine (16A, 16B) of the aircraft.

Abstract: A method is provided for operating a power plant, having a waste heat-generating gas turbine unit and also rooms which are to be air conditioned. Waste heat, which is discharged directly to the outside of the gas turbine unit, is used for heating the rooms which are to be air conditioned. A gas turbine for carrying out the method is also provided.

Abstract: A power generation system is provided and includes a compressor to increase a pressure of inlet ambient air and a turbine downstream from the compressor having a first stage and additional stages downstream from the first stage, the first stage structurally incorporating a combustor in which the compressed ambient air is mixed with fuel and in which the mixture is combusted to generate high temperature exhaust gas from which mechanical energy is derived in the first and additional stages.

Abstract: A power plant and method of operation is provided. The power plant comprises at least one main air compressor, an oxidizer unit configured to deliver a compressed oxygen-rich gas flow to at least one gas turbine assembly. Each assembly comprises a turbine combustor for mixing the compressed oxygen-rich gas flow with a recirculated gas flow and a fuel stream to burn a combustible mixture and form the recirculated gas flow. The assembly also comprises a recirculation loop for recirculating the recirculated gas flow from a turbine to a turbine compressor. The assembly further comprises a recirculated gas flow extraction path for extracting a portion of the recirculated gas flow from the assembly and delivering this to a gas separation system. The gas separation system separates the portion of the recirculated gas flow into a nitrogen portion and a carbon dioxide portion.

Abstract: The invention relates in particular to a method for converting thermal energy from carbonaceous raw materials into mechanical work, having at least one first (4) and one second (6) device for storing and releasing thermal energy connected to least intermittently alternatingly in a turbine branch (T) having a gas turbine (8) connected downstream thereof, comprising the steps of: a) combusting a gas in a gas combustor (2); b) passing the smoke gases (3) arising in the gas combustor (2) through a device (4, 6) for storing thermal energy; and c) feeding the hot air released by at least one device (4, 6) into the gas turbine (8), wherein the hot air (7) released by the gas turbine (8) is fed to at least one heat exchanger ( ) connected downstream of the gas turbine (8).

Abstract: Embodiments of a process for discharging amine byproducts formed in an amine-based solvent are provided. The process comprises the steps of contacting the amine-based solvent with flue gas comprising carbon dioxide, oxygen, nitrogen, NOx, SOx, or mixtures thereof to form a carbon dioxide-laden amine-based solvent that contains the amine byproducts. Carbon dioxide is separated from the carbon dioxide-laden amine-based solvent to form a carbon dioxide-depleted amine-based solvent. The amine byproducts from the carbon dioxide-depleted amine-based solvent are fed to an algae source.

Abstract: There is provided an axial bearing load distribution system for a gas turbine engine of the type having a low pressure rotor supported by axial bearings. The system comprises a line having an inlet end positioned in a high-pressure compressor gas path downstream of any compressor stage provided with a variable geometry. The line is adapted to sense static pressure in the high-pressure compressor gas path. The line has an outlet end producing the static pressure. An air-tight pressure actuator is operatively connected to the outlet end and to one of the axial bearings to exert a force on the axial bearing proportionally to a pressure of the outlet end.

Abstract: In some implementations, a system may include a compressor, a heat exchanger and an ITM. The compressor is configured to receive an air stream and compress the air stream to generate a pressurized stream. The heat exchanger is configured to receive the pressured stream and indirectly heat the pressurized stream using heat from an oxygen stream from an Ion Transport Membrane (ITM). The ITM is configured to receive the heated pressurized stream and generate an oxygen stream and the non-permeate stream, wherein the non-permeate stream is passed to a gas turbine burner and the oxygen stream is passed to the heat exchanger.

Abstract: The invention relates to a thermodynamic circuit with a working medium comprising at least two substances with non-isothermal evaporation and condensation whereby the working medium can decompose above a given temperature. According to the invention, the heat from heat sources at temperatures above the decomposition temperature of the working medium may be made useful with little complexity and with high operational security, whereby the heat from the heat source is transferred in a first step to a hot liquid circuit and, in a second step, from the hot liquid circuit to the circuit with the working medium comprising at least two substances with non-isothermal evaporation and condensation. The heat introduced to the circuit with the working medium comprising at least two substances with non-isothermal evaporation and condensation can be reduced by means of the intermediate hot liquid circuit, such that a decomposition of the working medium can be avoided.

Abstract: A permanent magnet alternator includes a permanent magnet alternator stator attached to a housing. A shaft is rotatable with respect to the housing with a permanent magnet alternator rotor attached to the shaft. The permanent magnet alternator rotor is positioned with respect to the permanent magnet alternator stator so as to generate electricity when the shaft rotates. A cooling fan is also attached to the shaft and is positioned in a gas flow path for flowing air through the gas flow path.

Abstract: The present invention relates to (with reference to FIG. 2) a gas turbine system comprising: a gas compressor (210); an upstream heat source, e.g. a fuel cell (212), which receives gas compressed by the compressor (210) and heats the gas passing therethrough (and when a fuel cell generates electrical power); an intermediate turbine (220) which receives the gas previously heated in the upstream heat source and which is connected to and drives the compressor (210); and an output turbine (240) which receives gas output by the intermediate turbine (220). Expanded gas leaving the intermediate turbine passes to the output turbine through either or both of a downstream combustion chamber and/or a downstream fuel cell, whereby the expanded gas is reheated prior to expansion in the output turbine (240). Preferably the system is configured such that the temperature of the gas received by the output turbine (240) is higher than the temperature of the gas received by the intermediate turbine (220).

Abstract: A gas turbine engine is provided comprising an outer shell, a compressor assembly, at least one combustor assembly, a turbine assembly and duct structure. The outer shell includes a compressor section, a combustor section, an intermediate section and a turbine section. The intermediate section includes at least one first opening and at least one second opening. The compressor assembly is located in the compressor section to define with the compressor section a compressor apparatus to compress air. The at least one combustor assembly is coupled to the combustor section to define with the combustor section a combustor apparatus. The turbine assembly is located in the turbine section to define with the turbine section a turbine apparatus.

Abstract: The carbon-free gas turbine is a power-producing turbine driven by the combustion of hydrocarbon fuels with oxygen. The carbon-free gas turbine includes at least one combustor for combusting gaseous fuel with oxygen. The at least one combustor includes a housing containing at least one oxygen transport reactor. The oxygen transport reactor includes an outer wall and an inner cylindrical ion transport membrane. The membrane receives pressurized air and separates gaseous oxygen therefrom, transporting the oxygen into a central region thereof for combustion with the gaseous hydrocarbon fuel, producing gaseous carbon dioxide and water vapor. A first turbine is driven by the gaseous carbon dioxide and water vapor produced by the at least one combustor and drives a first compressor. The first compressor provides the pressurized air supplied to the at least one combustor. A second turbine is driven by pressurized nitrogen gas resulting from the combustion.

Abstract: A combined heat and power plant in which air is compressed in a compressor, the compressed air is reacted with a fuel, producing high temperature, high pressure combustion products, the combustion products heat a first heat load whereby the combustion products are cooled to a temperature suitable for entry into an expander, and the cooled, high pressure combustion products are expanded in the expander which provides turning power to a power load such as a generator. Less than substantially 200% excess air and preferably less than substantially 20% excess air is compressed. The exhaust gas from the expander may optionally heat a second heat load. The first heat load may be the heating of a hydrocarbon and steam to promote steam methane reforming to form syngas. The second heat load may be a combination of boiling steam for reforming a hydrocarbon and heating a building or the like.

Abstract: A positive displacement power extraction compensation device is used to start and control the operation of engines. The device includes a positive displacement fixed vane compressor having a rotor connected with a drive shaft, a combustor connected with the compressor and a positive displacement power extraction device also having a rotor connected with a drive shaft. The compressor and power extraction devices are configured to displace unequal volumes of air at a given speed, so that combustion gases from the combustor exert less force on the compressor drive shaft as on the power extraction device drive shaft.

Abstract: In certain exemplary embodiments, a system includes a gas turbine system having a turbine, combustor, and a compressor. The system also includes an output flow path from the gas turbine system. The system further includes a blast furnace coupled to the output flow path, wherein output flow path is configured to deliver heated air or exhaust gas from the gas turbine system directly to the blast furnace as a blast heat source.

Abstract: Gas turbine engine accessories are mounted on an accessory gearbox therefor which is in turn mounted on a case of the engine such that the accessories extend from the gearbox in directions generally parallel to circumferential tangents to the engine case for compactness, ease in installation and removal of the accessories, reduction of the weight in lines extending from the accessories and minimization of the risk of damage to such accessories and gearbox from the fan blades which may separate from a fan hub upon encountering birds, ice, or other foreign objects.

Abstract: Hybrid gas-turbine electric vehicles and methods for operating hybrid gas-turbine electric vehicles are provided that make use of the gas-turbine for efficiently providing cooling for the vehicle.

Abstract: A desalination and minerals extraction process includes a desalination facility fluidly coupled to a minerals extraction facility. The desalination facility includes a nanofiltration membrane section producing a first tailings stream and a reverse osmosis membrane section producing a second tailings stream and a desalinated water outlet stream from an inlet feed stream. The extraction facility produces at least one mineral compound, an extraction tailings stream, and a second desalinated water outlet stream. At least one of the first tailings stream and the second tailings stream is fed into the extraction facility. In certain exemplary embodiments, a natural gas combined cycle power unit supplies power to at least one of the desalination facility and the extraction facility. In certain exemplary embodiments, the extraction tailings stream is recycled into the desalination facility and there are no extraction tailings streams or desalination tailings streams discharged into the environment.

Abstract: A land based gas turbine apparatus includes an integral compressor; a turbine component having a combustor to which air from the integral compressor and fuel are supplied; and a generator operatively connected to the turbine for generating electricity; wherein hot gas path component parts in the turbine component are cooled entirely or at least partially by cooling air or other cooling media supplied by an external compressor. A method is also provided which includes the steps of supplying compressed air to the combustor from the integral compressor; and supplying at least a portion of the cooling air or other cooling media to the hot gas path parts in the turbine component from an external compressor.

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

Abstract: An industrial gas turbine engine capable of operating at higher temperatures than air cooled nickel based alloy airfoils in the turbine. The engine burns stoichiometric or rich to produce a hot gas stream that is mostly without oxygen, and the turbine airfoils are made from a high temperature resistant material such as a refractory material that also has poor oxidation resistance. A second small gas turbine engine is used to compress nitrogen gas that is used to pass through the turbine airfoils for cooling where the film cooling nitrogen gas is injected into the hot gas stream but without igniting the fuel rich gas stream.

Abstract: A system includes a sulfur recovery unit including a thermal reactor having an acid gas inlet and an air inlet. The acid gas inlet is configured to receive a flow of acid gas, and the air inlet is configured to receive an air flow of pressurized air extracted from a gas turbine compressor of a gas turbine engine.

Abstract: In certain embodiments, a carbon capture integrated gasification combined cycle (IGCC) system includes a supplemental gas turbine engine configured to burn a high-hydrogen syngas to generate power only for an auxiliary load.

Abstract: This invention discloses systems and methods for control of a gas turbine or a gas turbine generator, where the gas turbine is connected to a dryer vessel in which gas turbine exhaust gases are used to heat treat a material in the dryer vessel. The control system comprises one or more sensors for temperature, moisture and/or flow rate in the dryer vessel and/or of the material inside, entering and/or exiting the dryer vessel and a controller responsive to the sensor for controlling the fuel and/or air flow into the gas turbine. This control system and method enables providing the appropriate heat output from the gas turbine to meet the process heat required for the desired material treatment. Optionally, the gas turbine can be a liquid fuel turbine engine, or a reciprocating engine can be substituted for the turbine engine.

Abstract: The present invention provides a combustor for an aerospace gas turbine engine comprising two stages wherein each stage defines an inlet and an exit. The second stage inlet is in fluid communication with the first stage exit such that a first flowpath is defined and it passes substantially through the second stage. A plurality of flow channel tubes is positioned within the second stage and each flow channel tube passes sealingly through a header plate positioned upstream of the second stage inlet thereby defining a second flowpath that also passes substantially through the second stage. The first flowpath exit and the second flowpath exit are positioned adjacent and proximate to one another to provide for the generation of microflames or microflame jets exiting the second stage from between and around the flow channel tube exits. The first stage of the combustor provides a gasifier and a reformer.

Abstract: A system for power generation comprises an engine operative to output an exhaust gas, a carbon capture means operative to remove carbon dioxide (CO2) from the exhaust gas and output the CO2, and a compressor operative to receive the CO2 and output compressed CO2 that cools a component of the engine.

Abstract: A reformation power plant generates clean electricity from carbonaceous material and high pressure CO2 which can be easily sequestered or utilized for a beneficial purpose, such as fuel production. The reformation power plant design utilizes a reformation process that reforms carbonaceous fuel with super-heated steam into a high-pressure gaseous mixture that is rich in carbon dioxide and hydrogen gas. This high-pressure gas exchanges excess heat with the incoming steam from a boiler and continues onward to a condenser. Once cooled, the high-pressure gas goes through a methanol separator, after which the CO2-rich gas is sequestered underground or beneficially re-used. The remaining hydrogen-rich gas is combusted through a gas turbine. The gas turbine provides power to a generator and also regenerative heat for the boiler. Finally, the generator converts mechanical energy into electricity, which is transferred to the electric grid.

Abstract: This invention relates to a method and plant for combined electric energy and water production, where the method comprises feeding substantially pure oxygen and a hydrocarbon fuel in a stochiometric ratio to a combustor (5), combusting the oxygen and hydrocarbon feed for forming an exhaust gas at comparatively high temperature and pressure, passing the exhaust gas at high temperature and pressure to an expander (7) that runs an electric generator (8) and an exhaust gas compressor (9), passing the exhaust gass exiting the expander to an exhaust gas cooler (11) which cools the gas to a temperature above the steam condensation temperature, passing the exhaust gas exiting the exhaust gas cooler to the exhaust gas compressor for pressurising, and passing the pressurised exhaust gas to an exhaust gas condenser (14) where the exhaust gas is condensed and thus separated into a substantially pure water fraction and a gaseous CO.

Abstract: A propeller or propeller drive, the propeller being carried by a support shaft (3) which projects from the body (53) of the missile or vehicle and about which the propeller rotates, the drive unit for the propeller being situated in front of the propeller (23) in the propulsion direction or in the propeller spinner (1). According to the invention it is provided that the drive unit has at least one gas turbine (55), optionally a multiple-stage gas turbine, which is secured to the drive shaft and which drives it or jointly rotates with it, and that the drive shaft (6) is traversed by the support shaft (3) or is mounted thereon in a rotating manner and drives the propeller (23), optionally by way of a gear mechanism (14) situated between the turbine (55) and the propeller (23).

Abstract: A turbine engine compressor has a rotor including rotating compressor discs. Magnets are positioned on the rotating compressor discs. Electrical coils are positioned in a stationary guide vane internal ring so as to create an electric machine providing starting torque to a rotor, and/or generating electrical energy once the rotor is rotating.

Abstract: Methods and systems for low emission power generation in hydrocarbon recovery processes are provided. One system includes integrated pressure maintenance and miscible flood systems with low emission power generation. An alternative system provides for low emission power generation, carbon sequestration, enhanced oil recovery (EOR), or carbon dioxide sales using a hot gas expander and external combustor. Another alternative system provides for low emission power generation using a gas power turbine to compress air in the inlet compressor and generate power using hot carbon dioxide laden gas in the expander. Other efficiencies may be gained by incorporating heat cross-exchange, a desalination plant, co-generation, and other features.

Abstract: Gas pressure and exhaust heat of the combustion exhaust gas exhausted from the internal combustion engine is effectively utilized for generating electricity. Using a turbocharger (8) having a turbine (4) that is driven by gas pressure of the combustion exhaust gas and a compressor (6) that is driven by rotational force generated in the turbine, an air engine (12) generating rotational force by air pressure as a power source, and a generator (14) converting the rotational force generated by the air engine to electric power, the air inspired from outside is compressed by the compressor of the turbocharger and heated by the turbine heat at high temperature, and electricity is generated by the generator using the generated compressed air of high pressure and high temperature as a power source of the air engine. The compressed air thus generated in the turbocharger (8) is shared and distributed for combusting the internal combustion engine (2) and for driving the air engine (12).

Abstract: A gas turbine engine is disclosed that has with two or more compressors. A first one of the compressors include a compressor variable geometry mechanism that may be in the form of adjustable vanes, bleed valves, or the like. A first one of the compressors is turned at a first speed and the second one of the compressors is turned at a second speed. The first speed is maintained approximately constant while the second speed varies and position of the compressor variable geometry mechanism is modulated in accordance with the second speed of the second one of the compressors to regulate surge margin for the first one of the compressors.

Abstract: Provided are gas turbine engines 10, combustion chambers 46 and methods of operation for reducing NOx and CO emissions in aerospace and industrial applications. An upstream compressor 18 provides pressurized air 32 to a combustion chamber having an inner liner 58 and an outer shroud 62 circumscribing a portion of the inner liner 58. The inner liner 58 having a wall 74 with an inwardly facing hot side 76 and an outwardly facing cold side 78. The shroud 62 is spaced from the inner liner 58, forming an annulus 100 for accepting a pressurized air stream 32B therein. Heat transfer features 82, disposed on the cold side 78, exchange heat from the liner wall 74 to the air stream 32B. Methods of operation include introducing fuel and air inside a liner wall 74 without premixing, and producing combustion products without introducing any additional pressurized air adjacent the hot side 76.

Abstract: A gas turbine equipment utilizing high humidity, for preventing generation of white smoke throughout a year, and for restraining radiation of extra heat so as to restrain lowering of heat efficiency, the equipment comprising a humidifying device for humidifying compressed gas for combustion, a heat recovery device for recovering exhaust heat from a gas turbine or the compressed air so as to heat humidifying water in the humidifying device, a recuperator for recovering exhaust heat from the gas turbine and heating the compressed gas for combustion, a dehumidifying device for dehumidifying and recovering moisture in the exhaust gas having passed through the recuperator, and an exhaust gas reheater for heating the exhaust gas after dehumidification, and further comprising a temperature measuring device for measuring a temperature of the exhaust gas passing through the exhaust gas reheater, and a heating temperature adjusting device for increasing the heating temperature of the exhaust gas reheater if a temperatu