Abstract: A turbine engine includes a fan, a compressor section having a low pressure compressor section and a high pressure compressor section, a combustor in fluid communication with the compressor section and a turbine section in fluid communication with the combustor. The turbine section includes a low pressure turbine section and a high pressure turbine section. The low pressure compressor section, the low pressure turbine section and the fan rotate in a first direction whereas the high pressure compressor section and the high pressure turbine section rotate in a second direction opposite the first direction.

Abstract: A turbine engine includes a fan, a compressor section having a low pressure compressor section and a high pressure compressor section, a combustor in fluid communication with the compressor section and a turbine section in fluid communication with the combustor. The turbine section includes a low pressure turbine section and a high pressure turbine section. The low pressure compressor section, the low pressure turbine section and the fan rotate in a first direction whereas the high pressure compressor section and the high pressure turbine section rotate in a second direction opposite the first direction.

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: 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 system includes a gas turbine engine that includes a compressor section configured to generate compressed air and a combustor coupled to the compressor section. The combustor is configured to combust a first mixture comprising the compressed air and a first fuel to generate a first combustion gas. The gas turbine engine also includes a turbine section coupled to the combustor. The turbine section is configured to expand the first combustion gas to generate an exhaust gas. The gas turbine engine also includes a boiler coupled to the turbine section. The boiler is configured to combust a second mixture comprising a portion of the first combustion gas and a second fuel to generate a second combustion gas that is routed to the turbine section. In addition, the boiler generates a first steam from heat exchange with the second combustion gas.

Abstract: A system and method of reducing gas turbine nitric oxide emissions includes a first combustion stage configured to burn air vitiated with diluents to generate first combustion stage products. A second combustion stage is configured to burn the first combustion stage products in combination with enriched oxygen to generate second combustion stage products having a lower level of nitric oxide emissions than that achievable through combustion with vitiated air alone or through combustion staging alone.

Abstract: A gas turbine engine includes an intercooling turbine section to at least partially drive one of a low spool and a high spool. An intercooling turbine section bypass to selectively bypass at least a portion of a core flow through an intercooling turbine section bypass path around the intercooling turbine section.

Abstract: In method for operating a gas turbine (11), the compressed air is fed to a combustor (18, 19) for the combustion of a coal syngas, and the resulting hot gases are expanded in a subsequent turbine (16, 17). Some of the compressed air is separated into oxygen and nitrogen, and the oxygen is used for producing the syngas. In a first combustor, (18) syngas is combusted and the resulting hot gases are expanded in a first turbine (16), and in a second combustor syngas is combusted, using the gases which issue from the first turbine (16), and the resulting hot gases are expanded in the second turbine (17). The two combustors (18, 19) are operated with undiluted syngas, and the first combustor flame temperature (TF) is lowered compared with the operation with natural gas (TNG), while the second combustor (19) is operated in the normal operation (TNG) for natural gas.

Abstract: A reheat combustor for a gas turbine engine includes a fuel/gas mixer for mixing fuel, air and combustion gases produced by a primary combustor and expanded through a high pressure turbine. Fuel injectors inject fuel into the mixer together with spent cooling air previously used for convectively cooling the reheat combustor. The fuel mixture is burnt in an annular reheat combustion chamber prior to expansion through low pressure turbine inlet guide vanes. The fuel/gas mixer and optionally the combustion chamber define cooling paths through which cooling air flows to convectively cool their walls. The fuel injectors are also convectively cooled by the cooling air after it has passed through the fuel/gas mixer cooling paths. The low pressure turbine inlet guide vanes may also define convective cooling paths in series with the combustion chamber cooling paths.

Abstract: An engine comprises a combustion chamber, an expansion cylinder with a piston adapted for reciprocating motion in the expansion cylinder via combustion products combusted in the combustion chamber, and a transmission associated with the expansion cylinder. The transmission has a guide frame with a first drive wheel rotatably mounted at one end of the guide frame and a second drive wheel rotatably mounted at an opposite longitudinal end of the guide frame. Each of the drive wheels is driven by an inextensible continuous loop. The guide frame has a crank head adapted to reciprocatingly translate along the guide frame. The crank head has a drive connection pivotally connecting the crank head to the loop. The crank head is operatively connected to the piston such that reciprocating motion of the piston results in corresponding reciprocating motion of the crank head, movement of the loop, and corresponding rotation of the drive wheels.

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: 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 method for operating a gas turbine engine includes compressing an air stream in a compressor and generating a post combustion gas by combusting a compressed air stream exiting from the compressor in a combustor. The post combustion gas is expanded in a first turbine. The expanded combustion gas exiting from the first turbine is split into a first stream and a second stream. The first stream of the expanded combustion gas is combusted in a reheat combustor. The reheat combustor is cooled using the second stream of the expanded combustion gas.

Abstract: A cogeneration plant is provided that includes a gas turbine, a heat recovery steam generator, a steam turbine and a cooler/condenser. A division module is provided at a division point, via which downstream the heat recovery steam generator the combustion gas is cooled and dehumidified in the cooler/condenser and then divided into a first combustion gas flow and a second combustion gas flow. A second condenser is provided for receiving the second combustion gas flow to separate contained carbon dioxide from contained water by condensation of the water. The cogeneration plant further includes a heater and a compressor for receiving the first combustion gas flow, which is heated, compressed and partly extracted to by-pass the combustor for cooling of the gas turbine before it enters the combustor and mix with the flow of oxygen and fuel to be burned in the gas turbine.

Abstract: A method of power production using a high pressure/low pressure ratio Brayton Power cycle with predominantly N2 mixed with CO2 and H2O combustion products as the working fluid is provided. The high pressure can be in the range 80 bar to 500 bar. The pressure ratio can be in the range 1.5 to 10. The natural gas fuel can be burned in a first high pressure combustor with a near stoichiometric quantity of pressurised preheated air and the net combustion gas can be mixed with a heated high pressure recycle N2+CO2+H2O stream which moderates the mixed gas temperature to the value required for the maximum inlet temperature to a first power turbine producing shaft power.

Abstract: An exemplary burner arrangement and method for operating a burner arrangement are disclosed. During operation of the burner arrangement a hot combustion gas, including combustion air, flows essentially parallel to a burner wall through a mixing chamber, which is delimited by the burner wall, to a combustion chamber. In the mixing chamber the hot combustion gas is mixed with an injected fuel, where cooling air from the outside of the burner wall flows through effusion holes in the burner wall into an interior of the mixing chamber. The cooling air, on the outside of the burner wall, is deflected in a directed manner in its flow direction by means of deflection elements which are in a distributed arrangement.

Abstract: A gas turbine engine test cell has a turbine detuner capable of recovering kinetic energy from exhaust gases emitted by a gas turbine engine while also detuning the exhaust flow to reduce unwanted infrasound. The gas turbine engine test cell includes a test cell building, a thrust frame for mounting the gas turbine engine, and the turbine detuner disposed downstream of the thrust frame for extracting energy from the exhaust gases of the gas turbine engine when in operation. The turbine detuner has an inlet for receiving the exhaust gases, a kinetic energy recovery mechanism (e.g. stator and rotor) for converting the kinetic energy of the exhaust gases into rotary power, and an outlet through which de-energized exhaust gases are emitted after being de-energized by the kinetic energy recovery mechanism. By eliminating the augmentor, the test cell is more compact. The turbine detuner not only reduces infrasound but also recovers otherwise wasted energy.

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 method for operating a gas turbine plant utilizing sequential combustion is provided. The gas turbine plant includes a compressor for compressing inducted combustion air, a first combustion chamber for combustion of a first fuel by utilizing the compressed combustion air, with a first turbine which is connected downstream of the first combustion chamber, and a second combustion chamber for combustion of a second fuel by utilizing the gases which emerge from the first turbine, with a second turbine which is connected downstream of the second combustion chamber. The method provides quick running up with simultaneously low emissions and homogeneous distribution of the turbine inlet temperature is achieved by the second combustion chamber being completely shut down for achieving a low partial load mode of the gas turbine plant.

Abstract: A cogeneration method and device by turbine, particularly by gas turbine, uses a compression section, at least one expansion section, and a combustion chamber. A combustion agent including oxygen is compressed in the compression section; in the combustion chamber, one combustion step is carried out under pressure with a mixture of combustion agent compressed with a fuel; at least some of the hot gases obtained by pressurized combustion are used to effect an exchange with an external facility; and at least one postcombustion step is carried out of a mixture of hot gases coming from combustion with a fuel, prior to the exchange, and at least one other postcombustion step of a mixture of hot gases, coming from the exchange, with a fuel, in order to obtain hot gases that are sent to the expansion section.

Abstract: A method of operating a turbine engine system and a turbine engine system are provided. The method comprises supplying a flow of oxygen to a combustion chamber defined within a plurality of turbines coupled serially together within the turbine engine system, supplying a flow of hydrocarbonaccous fuel to the combustion chambers of each of the plurality of turbines in the turbine engine system, and supplying a working fluid to an inlet of a first turbine engine coupled within the turbine engine system, wherein the working fluid is substantially nitrogen-free and wherein each of the turbines coupled within the turbine engine system is operable with the resulting fuel-oxygen-working fluid mixture.

Abstract: A power-generating system is provided for operating adiabatically and reducing emissions of greenhouse gases contributing to global warming. The system may include gas reactors and/or combustors that burn a fuel and an oxygen-containing gas under substantially adiabatic conditions such that high-pressure combustion products and low pressure combustor housing cooling air are combined to produce a medium pressure working fluid. Higher thermal efficiencies reduce emissions of greenhouse gases. Products of combustion can be processed to further reduce emissions of carbon dioxide and other greenhouse gases from portable and stationary exhaust-producing devices using different fuels. The system may also include solar collectors that pick up a spectrum of solar energy by means of cells containing fluids, aligned to concentrate the solar rays. The collectors may pick up direct and/or diffused solar radiation and can be used to power self-propelled vehicles or function as a roof of a building.

Abstract: A system and method for adding superheat to the hot process gas at the discharge of a compressor drive turbine of a high compression ratio gas turbine or aviation gas turbine. The superheat brings the temperature ratio (T2/T1) of the power output turbine into equality with the pressure ratio (P2/P1)(K?1)/K to effect a highly efficient and adiabatic isentropic expansion across the power output turbine. The added superheat contributes to the output power of the engine less any inefficiency of the output power turbine. All of the variables are brought together to develop the proper superheat levels for obtaining the greatest power output possible at minimum fuel consumption levels.

Abstract: In a method for operating a gas turbine (11) in a combined cycle power plant (40), air, which is used to burn a syngas that is recovered from coal is drawn in by the gas turbine (11) and compressed, is led to a combustor (18, 19), and a portion of the compressed air is separated into oxygen and nitrogen. An improved degree of efficiency is achieved by virtue of the fact that a gas turbine (11) with reheating is used, which includes two combustors (18,19) and two turbines (16, 17), in which, in the first combustor (18) syngas is burned using compressed air, and the resultant hot gases are expanded and in which, in the second combustor, syngas is burned using the gases coming from the first turbine (16) and the resultant hot gases are expanded in the second turbine (17), and that the nitrogen that occurs in the separation of the air is used to cool the gas turbine (11).

Abstract: In a method for operating a gas turbine (11) in a combined cycle power plant (40), air, which is used to burn a syngas that is recovered from coal, is drawn in and compressed by the gas turbine (11), the compressed air is fed into a combustor (18, 19) and such that a portion of the compressed air is separated into oxygen and nitrogen. An improved degree of efficiency is achieved by this method by virtue of the fact that a gas turbine (11) with reheating and two combustors (18, 19) and two turbines (16,17) is used. In the first combustor (18), syngas is burned using the compressed air, and the resultant hot gases are expanded in the first turbine (16). In the second combustor, syngas is burned using the gases coming from the first turbine (16) and the resultant gases are expanded in the second turbine (17) such that the nitrogen that occurs in the separation of the air is led to the gas turbine (11) to be compressed.

Abstract: In order to desirably prevent leakage of a working fluid from the tip clearance to reduce loss of a heat drop of the working fluid, a first corresponding blade of a second stationary blade row, which corresponds to a first reference blade of a first stationary blade row, is disposed in a position distant by 2L from the position of a lower end of a rotor blade in the direction of movement of the rotor blades when the rotor blade makes the closest approach to a lower end of the first reference blade. It should be noted that L is a value obtained by multiplying the average time T required for the high-pressure working fluid to pass through the rotor blade by the traveling speed U of the rotor blade. On the other hand, a second corresponding blade of the second stationary blade row, which corresponds to a second reference blade of the first stationary blade row, is disposed in a position of a lower end of a rotor blade when the rotor blade makes the closest approach to a lower end of the first reference blade.

Abstract: A thermal power plant with sequential combustion and reduced CO2 emissions is disclosed, which includes the following components, which are connected in series via in each case at least one flow passage (S): a combustion feed air compressor unit, a first combustion chamber, a high-pressure turbine stage, a second combustion chamber and a low-pressure turbine stage. The second combustion chamber and/or the low-pressure turbine stage can be supplied with a cooling gas stream for cooling purposes. A method for operating a thermal power plant of this type is also disclosed.

Abstract: A turbine engine includes a compressor, a combustor fluidly connected to the compressor and a first turbine operated by a combustion product formed in the first combustor. The turbine engine also includes a reheat chamber in which air, fuel, and exhaust gases from the first turbine are ignited to form a combustion product used to drive a second turbine. The engine further includes a controller that regulates at least one of an amount of fuel and compressed air delivered to the combustor and an amount of fuel, compressed air and exhaust gases delivered to the reheat chamber based on at least one turbine engine parameter measured by a sensor.

Abstract: The invention relates to a device for producing electrical power in a multi-spool gas turbine engine comprising at least one first rotary spool (69), for example a low-pressure spool, and a second rotary spool (24), for example a high-pressure spool, and driving an electrical machine (10). The device is one wherein, with the electrical machine (10) being of the twin-rotor type with a first rotor (13) and a second rotor (14), the first rotor (13) is mechanically connected to the first rotary spool (69) and the second rotor is mechanically connected to the second rotary spool (24).

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.

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 system and method for adding superheat to the hot process gas at the discharge of a compressor drive turbine of a high compression ratio gas turbine or aviation gas turbine. The superheat brings the temperature ratio (T2/T1) of the power output turbine into equality with the pressure ratio (P2/P1)(K?1)/K to effect a highly efficient and adiabatic isentropic expansion across the power output turbine. The added superheat contributes to the output power of the engine less any inefficiency of the output power turbine. All of the variables are brought together to develop the proper superheat levels for obtaining the greatest power output possible at minimum fuel consumption levels.

Abstract: A synchronizing stationary clutch system for compression braking in a two spool gas turbine engine is provided by the present invention. The synchronizing stationary clutch system allows the two shafts of a two spool gas turbine engine to be reliably coupled at any given speed of either shaft. This coupling ability is useful to a gas turbine engine functioning in a land vehicle for the purpose of slowing the forward momentum of a rolling vehicle. The clutch system may also allow the use of auxiliary power from an electrical motor to start the engine.

Abstract: Systems and methods for supplementing a power system to achieve consistent operation at varying altitudes are disclosed herein. A hybrid power system comprising a single power source driving multiple generators may implement a power recovery turbine to drive a supercharger compressor, which may provide compressed air at increased altitudes. The supplemental power system disclosed herein provides necessary shaft horsepower at high altitudes to drive a generator and produce cooling air.

Abstract: Systems and methods for supplementing a power system to achieve consistent operation at varying altitudes are disclosed herein. A hybrid power system comprising a single power source driving multiple generators may implement a power recovery turbine to drive a supercharger compressor, which may provide compressed air at increased altitudes. The supplemental power system disclosed herein provides necessary shaft horsepower at high altitudes to drive a generator and produce cooling air.

Abstract: In a power generation plant having at least one gas turbine cycle with heat-recovery boiler (4) and at least one steam turbine cycle operated via the heat-recovery boiler (4), the gas turbine cycle being designed to be semi-closed and essentially free of emissions and essentially comprising a compressor (1), a combustion chamber (2) arranged downstream of the compressor (1), a gas turbine (3) arranged downstream of the combustion chamber (2), a heat-recovery boiler (4) arranged downstream of the gas turbine (3), and at least one generator (8) coupled to the gas turbine (3), modes of operation with the gas turbine cycle stopped and start-up using fresh air are made possible by first means (12) being arranged which alternatively or additionally allow hot gas to be fed into the hot-gas path (23) between gas turbine (3) and heat-recovery boiler (4), and by second means (15) being arranged which alternatively or additionally allow exhaust gas to be expelled from the exhaust-gas path (40) downstream of the heat-rec

Abstract: In a reheat gas turbine engine for power generation, fuel is burnt with compressed air from a compressor in a first or primary combustor, the combustion products are passed through a high pressure turbine, the exhaust of the high pressure turbine is then burnt together with further fuel in a reheat combustor to consume the excess air, and the exhaust of the second combustor is passed through a lower pressure turbine. Excess air is supplied to the first combustor, thereby enabling so-called “lean burn” combustion for production of low levels of pollutants in the exhaust of the engine. Some turbine components of the turbines, e.g., blades or vanes, are cooled by cooling air supplies tapped off from the compressor.

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: There is provided a low-emission, staged-combustion power generation system and associated method for generating power. The power generation system and method combust a carbonaceous fuel with an oxidizing fluid, both of which are substantially free of nitrogen and sulfur, to generate power, for example, in the form of electricity, without the formation of nitrous oxides (NOx) and sulfur oxides (SOx). Efficiency is enhanced using a multi-staged combustion, in which the carbonaceous fuel is partially combusted before passing through a first power take-off device and subsequently reheated and passed through one or more additional power take-off devices. Additionally, exhaust gases from one or more of the power take-off devices can be extracted and processed to provide quantities of useful products such as hydrogen and methanol.

Abstract: An oxygen fired power generation system is disclosed. The power generation system has a high pressure combustor having a water recycle temperature control subassembly, and an intermediate pressure combustor having a CO2 recycle temperature control subassembly. Thus, a first energy cycle utilizes a first energy source operatively associated with a corresponding first heat sink, and a first inert agent to provide energy transfer therebetween and temperature control during operation of the first energy source. In like fashion, a second energy cycle utilizes a second energy source operatively associated with a corresponding second heat sink, and a second inert agent to provide energy transfer therebetween and temperature control during operation of the second energy source. The first and second energy sources are not identical, the first and second heat sinks are not identical and the first and second inert agents are not identical.

Abstract: An APU system includes a gas turbine engine having a low pressure spool, a high pressure spool and an electrical generator. The electrical generator is driven by the high pressure spool which is governed to a constant speed. Conversely, the low pressure spool is not governed at all, but is allowed to seek a speed that balances the power developed by the low pressure turbine (LPT) and power absorbed by the low pressure compressor (LPC). A step increase/decrease in electrical power demand is met with a step increase/decrease in fuel flow, which results in an overshoot/undershoot of the new equilibrium turbine inlet temperature TIT. The TIT returns to the new equilibrium when the LP spool has achieved it's new shaft speed and new equilibrium power balance. The HP Spool and generator maintain essentially constant speed and frequency, while the LP Spool responds to restore equilibrium.

Abstract: In various embodiments, the present invention provides a means for improving gas turbine engine performance by applying fluid flow control to the inter-turbine duct joining a high-pressure turbine spool and an associated low-pressure turbine spool, allowing the low-pressure turbine spool to have a relatively larger diameter than the high-pressure turbine spool. One or more unobstructed fluid flow paths between one or more boundary layer suction ports disposed within the upstream end of the outer-body surface of the inter-turbine duct and the suction side of the associated low-pressure turbine nozzle are provided. Advantageously, the natural static pressure difference between these points results in a self-aspirating assembly. The fluid flow control provided by the respective suction and blowing forces generated allows for a relatively larger diameter low-pressure turbine spool and/or relatively fewer low-pressure turbine nozzles to be used than is possible with conventional systems, assemblies, and methods.

Abstract: There is provided a low-emission, staged-combustion power generation system and associated method for generating power. The power generation system and method combust a carbonaceous fuel with an oxidizing fluid, both of which are substantially free of nitrogen and sulfur, to generate power, for example, in the form of electricity, without the formation of nitrous oxides (NOx) and sulfur oxides (SOx). Efficiency is enhanced using a multi-staged combustion, in which the carbonaceous fuel is partially combusted before passing through a first power take-off device and subsequently reheated and passed through one or more additional power take-off devices. Additionally, exhaust gases from one or more of the power take-off devices can be extracted and processed to provide quantities of useful products such as hydrogen and methanol.

Abstract: A method of separating oxygen using a ceramic membrane unit having one or more ceramic membranes, preferably formed of a mixed conducting ceramic, for instance, a perovskite, capable of conducting both oxygen ions and electrons. Oxygen is separated within the ceramic membrane unit under impetus of compressing an incoming oxygen containing feed. The compressor used in the compression is powered by the work of expansion produced by expanding a process stream composed of at least a portion of the retentate produced in the ceramic membrane unit. Prior to expansion, the process stream is cooled to allow the use of less expensive materials in expanders used in the expansion. As a result, expansion of the process stream alone is insufficient to meet the power requirements involved in the compression. Interstage expansion with reheating is used to make up for the power deficit.

Abstract: A method of operating a gas turbine engine comprising a power turbine mounted downstream a compressor, and a compressor turbine mounted downstream the power turbine for rotation in a direction opposite to the rotation direction of the power turbine. Exhaust fluid from the compressor turbine is cooled in a heat exchanger with a compressed fluid downstream the compressor and is then cooled with air in separate heat exchanger before being admitted to the compressor. A part of the compressed fluid heated in the heat exchanger is fed to cool the turbine blades, and the rest of the fluid is fed to a heated fluid source for the turbine. To control the gas turbine engine, a part of fluid is boosted by a booster compressor and is discharged from the engine. The booster compressor is driven by an expanding turbine that rotated under the effect of combustion air that is expanded in the expanding turbine and flows through the expanding turbine under the action of reduced pressure in the heated fluid source.

Abstract: Apparatus for generating power includes a gas turbine unit having a compressor for compressing ambient air and producing compressed air, a combustion chamber to which the compressed air is supplied, a source of relatively high grade fuel for burning in the combustion chamber and producing combustion gases, and a gas turbine connected to generator and to the compressor for expanding the combustion gases and producing exhaust gases. The apparatus further includes a combustor that burns relatively low grade fuel, and produces combustion products, and an indirect contact heat exchanger responsive to the combustion products for heating the compressed air before the latter is applied to the combustion chamber, and for producing cooled combustion products. In addition, an energy converter is provided having an organic working fluid responsive to the exhaust gases for converting heat in the exhaust gases to electricity.

Abstract: A variable cycle gas turbine engine (10) includes first and second compressors (18,16), combustion apparatus (20) and first and second turbines (22,24) operable to drive the first and second compressors (18,16) respectively via interconnecting shafts. The capacity of one of the turbines (24) may be varied, for example by means of guide vanes (32) which can be adjusted to reduce or increase a throat area (40) through which air leaves the guide vanes to impact the turbine. The capacity of the turbine may be increased at low engine speeds, to reduce the pressure ratio across the turbine and across the compressor (16) which it drives, thereby improving the surge margin of the compressor.