Abstract: Solutions for clutching turbine wheels are disclosed. In one embodiment, an apparatus includes: a turbine rotor shaft; a plurality of turbine wheels affixed to the turbine rotor shaft; an independent turbine wheel engagably attached to the turbine rotor shaft; and a clutch operably connected to the turbine rotor shaft, the clutch configured to couple and decouple the independent turbine wheel from the turbine rotor shaft.

Abstract: An exemplary igniter assembly for a turbomachine includes an igniter extending along an axis from an igniting end portion to an opposing end portion. The igniting end of the igniter is configured to be received within a bore of a tube. An annular seal restricts flow between the igniting end and the tube.

Abstract: A rotary-wing aircraft includes a retractable port movable between a closed position and an open position to selectively control flow of combustion gases into a bypass passage to change a power distribution between a rotor system and a secondary propulsion system.

Abstract: An object of the present invention is to provide a gas turbine combustor that supports hydrogen-containing gas having a high burning velocity and is capable of performing low NOx combustion without reducing reliability of a burner. A first fuel nozzle is provided upstream of a combustion chamber and supplies fuel for activation and hydrogen-containing gas. The combustor has a primary combustion zone, a reduction zone and a secondary combustion zone. In the primary combustion zone, the fuel supplied from the first fuel nozzle is combusted under a fuel rich condition to form a burned gas containing a low concentration of oxygen. In the reduction zone, a hydrogen-containing gas is injected into the combustion chamber through a second fuel injection hole from a second fuel nozzle so that NOx generated in the primary combustion zone is reduced by an oxygen reaction of the hydrogen.

Abstract: A gas turbine engine has a spool, a towershaft connected to the spool, an impeller pump, and a speed control pump connected to the towershaft and to the impeller pump for driving the impeller pump at a constant speed.

Abstract: A gas turbine engine includes a buffer cooling system having a first heat exchanger, a first passageway, a second passageway and a third passageway. The first heat exchanger exchanges heat with a bleed airflow to provide a conditioned airflow. The first passageway communicates a first portion of the conditioned airflow to a high pressure compressor of the gas turbine engine, the second passageway communicates a second portion of the conditioned airflow to a high pressure turbine of the gas turbine engine, and the third passageway communicates a third portion of the conditioned airflow to a low pressure turbine of the gas turbine engine.

Abstract: A gas turbine engine includes a low spool along an engine axis with a forward fan section and a low pressure turbine section. A high spool along the engine axis with a high pressure turbine section and an aft core driven fan section (CDFS), the aft core driven fan section (CDFS) axially aft of the high pressure turbine section along the engine axis.

Abstract: A convertible gas turbine propulsion system operates in multiple output modes. The convertible gas turbine propulsion system comprises a gas generator, a first power turbine, a secondary propulsion system and an exhaust duct. The gas generator is configured to produce exhaust gas. The first power turbine is aligned with the gas generator to receive the exhaust gas. The secondary propulsion system is in series with the gas generator and the first power turbine. The exhaust duct coaxially extends from the first power turbine to the secondary propulsion system. The exhaust duct includes an exhaust port for opening the exhaust duct to ambient air pressure and permitting exhaust gas to bypass the secondary propulsion system. In various embodiments of the invention, the first power turbine is connected to a first rotary propulsion system, and the secondary propulsion system comprises a second power turbine or a nozzle.

Abstract: A two-shaft gas turbine is capable of starting premixed combustion without extinguishing a flame. The two-shaft gas turbine includes a combustor and a gas generator controller. The combustor has a premix burner that includes combustion regions in which premixed combustion is to be carried out individually. The gas generator controller controls the combustor. In a method for starting the premixed combustion in the combustor, the gas generator controller selects at least one of the combustion regions in which the premixed combustion is to be carried out, on the basis of a fuel-air ratio, and starts premix combustion in the selected combustion region or separately in each of the selected combustion regions. Further, as the fuel-air ratio is increased, the controller increases the number of the selected region in which the premixed combustion is carried out.

Abstract: The disclosure relates to a burner for a combustion chamber of a gas turbine, with an injection device for the introduction of at least one gaseous and/or liquid fuel into the burner, wherein the injection device has at least one body which is arranged in the burner with at least one nozzle for introducing the at least one fuel into the burner, the at least one body being configured as a streamlined body which has a streamlined cross-sectional profile and which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the burner. The at least one nozzle has its outlet orifice at or in a trailing edge of the streamlined body, and with reference to a central plane of the streamlined body, the trailing edge is provided with at least two lobes extending in opposite transverse directions.

Abstract: A combustor for a turbine engine includes a first liner defined about an axis with a first row of first combustion air holes, one of the first combustion air holes is defined along each of a multiple of fuel injector zero pitch lines. A second liner defined about the axis with a second row of second combustion air holes, each of the second combustion air holes circumferentially offset relative to each of the multiple of fuel injector zero pitch lines.

Abstract: The disclosure relates to a burner for a combustion chamber of a gas turbine, with an injection device for the introduction of at least one gaseous and/or liquid fuel into the burner, wherein the injection device has at least one body which is arranged in the burner with at least one nozzle for introducing the at least one fuel into the burner, the at least one body being configured as a streamlined body which has a streamlined cross-sectional profile and which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the burner. The at least one nozzle has its outlet orifice at or in a trailing edge of the streamlined body, and with reference to a central plane of the streamlined body, the trailing edge is provided with at least two lobes extending in opposite transverse directions.

Abstract: An exemplary gas turbine engine includes a turbine section operative to impart rotational energy to a compressor section. The turbine section includes at least a low-pressure turbine and a high-pressure turbine, and a number of stages in the low pressure turbine is from three to five.

Abstract: One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique aircraft. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and gas turbine engine powered aircraft. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: A free-turbine turboshaft engine including a gas generator including at least one compressor supplied with air, a combustion chamber receiving the compressed air at the output of the compressor, and at least one generator turbine mechanically connected to the compressor by a drive shaft and driven by gases from combustion of fuel carried out in the combustion chamber, and including a free turbine supplied by the gases from the combustion after passing through the generator turbine and which drives a power shaft positioned non-coaxially relative to the drive shaft of the gas generator and supplying the power of the turboshaft engine via a reduction gear. The combustion chamber is a substantially cylindrical or frusto-conical chamber, coaxial with the axis of the generator turbine, and includes a single injector.

Abstract: A gas turbine engine, in which gases flow upstream to downstream, including a combustion chamber, a high-pressure turbine placed downstream from the combustion chamber, arranged so as to receive combustion gases from the combustion chamber, a free turbine, and an exhaust-gas guide cone attached to the free turbine downstream from the free turbine, the turbine engine emitting sound waves during operation. The guide cone includes a sound suppressor, for example with a Helmholtz resonator structure, with a resonant cavity and a resonator neck in communication with an opening, arranged so as to suppress the sound waves emitted by the turbine engine.

Abstract: A electrical power plant with a gas turbine engine that drives two electric high speed generators connected on the two ends of the engine rotor shaft in a direct drive relation without the need for a gear box. The high speed generators can be of the same or different power rating and connected in series such that the total power output can easily be changed without the need to redesign larger high speed generators. Because the generators use permanent magnets, they can be operated as motors to drive two or more compressors. A turbine can be used to drive two or more high speed generators connected in series. Since the high speed generator/motors have thrust bearings, the thrust bearing in the turbomachine can be eliminated.

Abstract: A turbine engine includes a turbine section having a first turbine portion and a second turbine portion arranged along a central axis. A re-heat combustor is arranged between the first and second turbine portions. The re-heat combustor includes a combustion duct having a curvilinear flow portion. The curvilinear flow portion provides an increased residence time of combustion products passing through the re-heat combustor.

Abstract: A two-shaft gas turbine is capable of starting premixed combustion without extinguishing a flame. The two-shaft gas turbine includes a combustor and a gas generator controller. The combustor has a premix burner that includes combustion regions in which premixed combustion is to be carried out individually. The gas generator controller controls the combustor. In a method for starting the premixed combustion in the combustor, the gas generator controller selects at least one of the combustion regions in which the premixed combustion is to be carried out, on the basis of a fuel-air ratio, and starts premix combustion in the selected combustion region or separately in each of the selected combustion regions. Further, as the fuel-air ratio is increased, the controller increases the number of the selected region in which the premixed combustion is carried out.

Abstract: A jet engine, in particular for an aircraft, having a high-pressure compressor that is situated inside a compressor housing, the high-pressure compressor having blade elements that, through their rotational motion, compress air flowing into the high-pressure compressor via an intake channel, the high-pressure compressor having a plurality of compressor stages on which the blade elements are situated, and the jet engine also having an integrated electric motor/generator unit, wherein the motor/generator unit is situated in the rotational plane of the at least first compressor stage of the high-pressure compressor, and includes a stator that extends around the periphery of the compressor housing, as well as a runner that is formed by the blade elements of the at least first compressor stage, and that the motor/generator unit has an output power of 100 kVA to 150 kVA.

Abstract: A recuperator includes a heating gas duct; an inlet manifold; a discharge manifold; and a once-through heating area disposed in the heating-gas duct through which a heating gas flow is conducted. The once-through heating area is formed from a plurality of first single-row header-and-tube assemblies and a plurality of second single-row header-and-tube assemblies. Each of the plurality of first single-row header-and-tube assemblies including a plurality of first heat exchanger generator tubes is connected in parallel for a through flow of a flow medium therethrough and further includes an inlet header connected to the inlet manifold. Each of the plurality of second single-row header-and-tube assemblies including a plurality of second heat exchanger generator tubes is connected in parallel for a through flow of the flow medium therethrough from respective first heat exchanger generator tubes, and further includes a discharge header connected to the discharge manifold.

Abstract: A counter-rotating blade stage in lieu of a stator stage may compensate for relatively low rotational speed of a gas turbine engine spool. A first spool may have at least two compressor blade stage and at least two turbine blade stage. A combustor is located between the at least two compressor blade stage and the at least two turbine blade stage along a core flowpath. The at least two counter-rotating compressor blade stage is interspersed with the first spool at least two compressor blade stage. A transmission couples the at least two additional compressor blade stage to the first spool for counter-rotation about the engine axis.

Abstract: A power generation system includes at least one turbine system. The turbine system includes a compressor section comprising at least one stage, configured to supply a compressed oxidant and a combustion chamber configured to combust the compressed oxidant and a fuel stream comprising carbon-based fuels and to generate a hot flue gas. The turbine system further includes an expander section having an inlet for receiving the hot flue gas comprising at least two stages. The two stages include a high-pressure expander configured to generate an expanded exhaust gas rich in CO2. The high-pressure expander fluidly coupled to a low-pressure expander configured to generate a final exhaust and electrical energy. A CO2 separation system is fluidly coupled to the high-pressure expander for receiving the expanded exhaust gas from the high-pressure expander and providing a CO2 lean gas that is then fed to the low-pressure expander.

Abstract: On a two-shaft gas turbine, on at least one of an inner peripheral side or an outer peripheral side of a main flow passage, an outlet of a high-pressure turbine is lower than an inlet of a low-pressure turbine, an outer periphery of a flow channel that connects the outlet of the high-pressure turbine and the inlet of the low-pressure turbine includes a first casing shroud that is supported by a casing and located on an outer peripheral side of a final-stage rotor vane of the high-pressure turbine, and an initial-stage stator vane of the low-pressure turbine, and a connection position of the first casing shroud and the initial-stage stator vane of the low-pressure turbine is closer to the inlet of the initial-stage stator vane of the low-pressure turbine than the outlet of the final-stage rotor vane of the high-pressure turbine.

Abstract: A gas turbine includes a compressor for compressing the combustion air, at least one combustion chamber, in which a fuel is burned while compressed combustion air is supplied, and at least one first turbine arranged downstream of the combustion chamber and in which the hot combustion gases from the combustion chamber are expanded to perform work. Part of the compressed combustion air is branched off, cooled in a cooling air cooler, brought to a lower cooling air pressure by a second turbine and supplied to the gas turbine for cooling purposes.

Abstract: A power plant for burning a fuel in a low pressure combustion chamber to produce electrical power. A first compressor supplies compressed air through a first heat exchanger to add heat to the compressed air. The heated compressed air is passed through a first turbine to drive a first electric generator. The first turbine outlet is passed through a second heat exchanger in series with the first heat exchanger to further heat the compressed air. The compressed air is then passed through a second turbine to drive a second electric generator and produce electric power. The outlet from the second turbine is passed through a first combustor to produce the hot gas flow through the second heat exchanger. The outlet from the second heat exchanger is passed through a second combustor before passing through the first heat exchanger. The outlet from the first heat exchanger is passed through a heat recovery steam generator to generate steam to drive another turbine and another generator.

Abstract: A turbine engine particularly suited for VTOL aircraft is disclosed. According to various embodiments, the core of the turbine engine includes two spools—a low pressure (LP) spool and a high pressure (HP) spool—where the LP spool is independently mounted remote to the HP spool. The engine may be modulated for operation by a modulation diverter valve assembly and through the fuel flow to the engine. The power output from the engine can be modulated from high levels to low levels and vice versa through control of the air flow through the engine using the modulation diverter valve assembly. In lift mode operation both the LP and HP spools may be operational, while during the forward flight cruise mode of operation the HP spool is operational and the LP spool may or may not be operational depending upon the power required for the flight condition. For HP spool only operation, the LP spool may be shut down using the modulation diverter valve assembly and an inlet flow diverter valve assembly.

Abstract: In order to provide a high electric power for an aircraft via a generator driven by the engine, an additional free turbine is included in the hot-gas flow of the engine, which—equipped with generator-starter magnets (9) and surrounded by annularly arranged generator-starter coils (12)—forms a generator-starter turbine (5) and is connected to the high-pressure shaft (1) via an overrunning clutch (15), and hence, is also used for starting the engine.

Abstract: A power generation system includes first and second turbines. The first turbine including a low-pressure compressor (14) and a high-pressure compressor (16). A combustion chamber (22) combusts compressed oxidant and a fuel stream to generate a hot flue gas (31). The first turbine further includes a high-pressure expander (20) for receiving the flue gas and generating a CO2 rich exhaust gas. A low-pressure expander (22) generates a first final exhaust (52) and electrical energy. A CO2 separation system receives exhaust gas (38) and provides a CO2 lean gas fed to low-pressure expander (22). The second turbine including a compressor section (64) configured to discharge a recycle stream (71) from a high pressure compressor (70) to a second combustion chamber (72) and supply a split stream (84) from a low-pressure compressor (68) to high pressure compressor (16) of the first turbine.

Abstract: A turbine combustion chamber is provided with deflectors on the cold side generating vortices in a secondary gas flow into the chamber, thereby confining the flame front under variable operating conditions and cooling the chamber walls. The high-speed cantilever shaft has a longitudinal duct and an array of fine orifices in the wall of the shaft for directing pressurized oil jets that impinge on the shaft bearings with little relative speed to increasing wetting of the bearing components. Oil is supplied to the duct by means of a positive-displacement pump directly driven by the output shaft. The pump output pressure is monitored to signal the end of the start-up sequence when the turbine reaches sufficient speed. The turbo-engine further includes devices for decoupling vibrations between the three systems thereof, including a loosely-mounted removable spline pivotable at both ends for coupling the high-speed shaft to the step-down gearbox.

Abstract: A turbine engine includes a turbine section having a first turbine portion and a second turbine portion arranged along a central axis. A re-heat combustor is arranged between the first and second turbine portions. The re-heat combustor includes a combustion duct having a curvilinear flow portion. The curvilinear flow portion provides an increased residence time of combustion products passing through the re-heat combustor.

Abstract: A method of reducing gas turbine engine distortion includes coupling a core gas turbine engine to a power turbine, coupling the power turbine to a thrust bearing support assembly through a frusto-conically shaped structural support such that the net axial thrust of the coupled core gas turbine engine and power turbine reacts through the thrust bearing support assembly at engine centerline to facilitate minimizing distortion of the core gas turbine engine casing, and supporting the thrust bearing support assembly such that all of the remaining thrust generated by the core gas turbine engine and the power turbine is reacted to ground.

Abstract: A convertible gas turbine propulsion system operates in multiple output modes. The convertible gas turbine propulsion system comprises a gas generator, a first power turbine, a secondary propulsion system and an exhaust duct. The gas generator is configured to produce exhaust gas. The first power turbine is aligned with the gas generator to receive the exhaust gas. The secondary propulsion system is in series with the gas generator and the first power turbine. The exhaust duct coaxially extends from the first power turbine to the secondary propulsion system. The exhaust duct includes an exhaust port for opening the exhaust duct to ambient air pressure and permitting exhaust gas to bypass the secondary propulsion system. In various embodiments of the invention, the first power turbine is connected to a first rotary propulsion system, and the secondary propulsion system comprises a second power turbine or a nozzle.

Abstract: A gas turbine engine, in particular a turboshaft engine, includes a spool having a turbine and a gas generator compressor mounted thereto, a source of heat positioned between the turbine and the compressor, a first shaft and a free turbine mounted to the first shaft, and a control system for transferring power between the spool and the shaft. The operating speed of the gas generator compressor is re-matched in order to improve the efficiency and surge margin of the gas generator compressor and to improve the transient performance of the gas turbine engine.

Abstract: A compressor having a front fan, which rotates to compress intake air, a single-stage low-pressure compressor which is disposed behind the front fan to compress intake air, and a single-stage high-pressure compressor which compresses the compressed air compressed by the low-pressure compressor; a ratio (RH/RL) of a pressure ratio (RH) of the high-pressure compressor to a pressure ratio (RL) of the low-pressure compressor is within a range of 4.5 to 6.0.

Abstract: A combustion turbine power generation system (10) includes a combustion turbine assembly (11) including a main compressor (12) constructed and arranged to receive ambient inlet air, a main expansion turbine (14) operatively associated with the main compressor, combustors (16) constructed and arranged to receive compressed air from the main compressor and to feed the main expansion turbine, and an electric generator (15) associated with the main expansion turbine for generating electric power. A compressed air storage (18) stores compressed air. A heat exchanger (24) is constructed and arranged to receive a source of heat and to receive compressed air from the storage so as to heat compressed air received from the storage. An air expander (28) is associated with the heat exchanger and is constructed and arranged to expand the heated compressed air for producing additional electric power.

Abstract: After passing into reaction section R, the hydrocarbon feedstock C mixed with hydrogen H is expanded in device D. The expansion is brought about by a single-phase turbine until a gas volume ratio of 5% is reached, then expansion is brought about in a two-phase turbine of the rotodynamic type.

Abstract: A power generation system includes a first turbine system. The first turbine system includes a first compressor section comprising at least two stages. The two stages includes a first low pressure compressor fluidly coupled to a first high pressure compressor configured to supply a first portion of compressed oxidant and a second portion of compressed oxidant A first combustion chamber is configured to combust said first portion of compressed oxidant and a first fuel stream comprising carbon-based fuels and to generate a first hot flue gas. The first turbine system further includes a first expander section having an inlet for receiving said first hot flue gas and generating a first expanded exhaust gas rich in CO2. The first high-pressure expander is fluidly coupled to a first low-pressure expander configured to generate a first exhaust and electrical energy.

Abstract: A power generation system includes at least one turbine system. The turbine system includes a compressor section comprising at least one stage, configured to supply a compressed oxidant and a combustion chamber configured to combust the compressed oxidant and a fuel stream comprising carbon-based fuels and to generate a hot flue gas. The turbine system further includes an expander section having an inlet for receiving the hot flue gas comprising at least two stages. The two stages include a high-pressure expander configured to generate an expanded exhaust gas rich in CO2. The high-pressure expander fluidly coupled to a low-pressure expander configured to generate a final exhaust and electrical energy. A CO2 separation system is fluidly coupled to the high-pressure expander for receiving the expanded exhaust gas from the high-pressure expander and providing a CO2 lean gas that is then fed to the low-pressure expander.

Abstract: A method facilitates assembling a gas turbine engine including a compressor and a rotor assembly coupled in axial flow communication downstream from the compressor. The method comprises coupling a bypass system in flow communication with the compressor to channel a portion of flow discharged from the compressor towards the rotor assembly is channeled through the bypass system, and coupling a downstream end of the bypass system within the gas turbine engine such that the flow entering the bypass system flows past the rotor assembly and is discharged downstream from the rotor assembly.

Abstract: A method of assembling a turbine engine is provided. The method includes providing a bushing including at least one retaining mechanism formed integrally therewith, coupling a shim to the bushing such that at least one retainer extending from the shim is received within the bushing retaining mechanism, and coupling the bushing and shim within the turbine engine to facilitate aligning a first engine component relative to a second engine component.

Abstract: Provided are apparatus and methods for manufacturing semiconductor devices and more specifically exhaust system apparatus and methods used in conjunction with a plurality of semiconductor processing chambers. The overall apparatus includes a plurality of process modules in which a semiconductor process is performed and an exhaust module to which the process modules are independently connected by fluid exhaust lines. The exhaust module amplifies an exhaust functionality of the system by more effectively and reliably drawing exhaust material from the process modules to be efficiently and effectively exhausted from the system.

Abstract: A bleed air power assist system is coupled to a gas turbine engine that includes a high pressure turbine, a low pressure turbine, and an electrical generator driven by the high pressure turbine. The bleed air power assist system selectively bleeds air discharged from the high pressure turbine and supplies it to an air turbine that is also coupled to the generator. Thus, the system selectively reduces the power extracted from the high pressure turbine. This, coupled with the bleed air that is diverted from the low pressure turbine, allows the low pressure spool to run at lower speeds when high engine thrust is not needed or desired, but when the generator is still needed to supply high electrical loads.

Abstract: The present invention comprises a highly supercharged, regenerative gas-turbine system. The gas turbine comprises a compressor, a regenerator, a combustor, and an expander. A pre-compressor pressurizes air going into the compressor section of the gas turbine. A cooler lowers the temperature of the air going into the compressor. The compressor pressurizes air, which then flows through the regenerator, which heats the air before it enters the combustor. The combustor further heats the air which then flows through the expander and then the regenerator. A post-expander is preferably located downstream of the regenerator. The post-expander is a second expander that receives high-pressure gas exiting the regenerator. The post-expander preferably drives the pre-compressor. The preferred pre-compressor and post-expander are toroidal intersecting vane machines (TIVMs), which are positive-displacement rotary devices. Numerous alternated embodiments of this basic system are described.

Abstract: Two spool gas turbine engines are often used to drive variable speed loads, such as an electric generator, or the fan/propeller of aircraft engines. The gas turbine engine must be designed to withstand transient speed and temperature conditions which are encountered when sudden changes to the load on the generator, fan, or propeller occur. By adding a relatively small motor/generator to the gas generator spool of the gas turbine engine, the compressor speed and airflow can be quickly adjusted to compensate for external load changes. This reduces the severity and duration of the transient conditions, resulting in decreased operation and reliability problems such as overspeed, compressor surge, and high turbine temperature. The motor/generator may also be used as an engine starting device.

Abstract: A gas turbine engine system comprises a first compression stage; a second compression stage; a combustor; a controller; a first sensor for sensing the speed of the first compression stage and providing a first indication of the sensed speed to the controller; and a second sensor for sensing the speed of the second compression stage and providing a second indication of the sensed speed to the controller, wherein the controller is operable to control the supply of fuel to the combustor in dependence upon the first indication received from the first sensor and the second indication received from the second sensor. This arrangement is particularly useful in controlling the acceleration of an aero-engine from minimum idle.

Abstract: A reheat heat exchanger is provided particularly for use in Rankine cycle power generation systems. The reheat heat exchanger includes a high pressure path between a high pressure inlet and a high pressure outlet. The reheat heat exchanger also includes a low pressure path between a low pressure inlet and a low pressure outlet. The two paths are in heat transfer relationship. In a typical power generation system utilizing the reheat heat exchanger, the high pressure inlet is located downstream from a source of high temperature high pressure working fluid. An expander is located downstream from the high pressure outlet and upstream from the low pressure inlet. A second expander is typically provided downstream from the low pressure outlet. The reheat heat exchanger beneficially enhances the efficiency of power generation systems, particularly those which utilize expanders having inlet temperatures limited to below that produced by the source of working fluid.

Abstract: A power turbine speed control system for a helicopter is disclosed which includes components for generating a power turbine speed signal based upon a demanded rotor speed, a high-order filter for filtering the power turbine speed signal by effectuating a rapid attenuation of main and tail rotor torsional frequencies in the power turbine speed signal without compromising phase at low frequencies, and a governor for providing isochronous power turbine speed and rotor speed control based upon the filtered power turbine speed signal.

Abstract: The invention relates to a method for decreasing the level of carbon dioxide present in the fumes discharged by a power generator burning a mixture of a combustive agent and of a fuel containing hydrocarbons, wherein a gaseous mixture comprising at least part of said combustive agent and at least part of said fumes is compressed, all or part of the carbon dioxide present in the compressed gaseous mixture is eliminated by absorption, a fuel is mixed with the gaseous mixture, the resulting mixture of fuel and gaseous mixture is burnt and the fumes from the combustion process are expanded. The invention also relates to a power generator for implementing said method.

Abstract: A reheat heat exchanger is provided particularly for use in Rankine cycle power generation systems. The reheat heat exchanger includes a high pressure path between a high pressure inlet and a high pressure outlet. The reheat heat exchanger also includes a low pressure path between a low pressure inlet and a low pressure outlet. The two paths are in heat transfer relationship. In a typical power generation system utilizing the reheat heat exchanger, the high pressure inlet is located downstream from a source of high temperature high pressure working fluid. An expander is located downstream from the high pressure outlet and upstream from the low pressure inlet. A second expander is typically provided downstream from the low pressure outlet. The reheat heat exchanger beneficially enhances the efficiency of power generation systems, particularly those which utilize expanders having inlet temperatures limited to below that produced by the source of working fluid.