828 results about "Power turbine" patented technology

The present invention provides methods and system for power generation using a high efficiency combustor in combination with a CO2 circulating fluid. The methods and systems advantageously can make use of a low pressure ratio power turbine and an economizer heat exchanger in specific embodiments. Additional low grade heat from an external source can be used to provide part of an amount of heat needed for heating the recycle CO2 circulating fluid. Fuel derived CO2 can be captured and delivered at pipeline pressure. Other impurities can be captured.

A combination of SAGD with cogeneration technology for exploiting shallow heavy oil and bitumen reservoirs under primary, secondary and tertiary thermal recovery. Superheated steam is generated by the heat recovery from the exhaust of an above-ground hydrocarbon powered turbine driven electric generator cogeneration plant and is injected through well bores into the hydrocarbon bearing reservoir that is traversed by at least one horizontal producing well bore and one injection well bore to heat the reservoir formation and to induce gravity drainage of the hydrocarbons and allowing their recovery from the horizontal producing well bore. Electrical power that is generated is sold to the electric grid and can be used to offset the fuel costs for the above ground hydrocarbon turbine-driven elector generators.

This disclosure relates to a highly efficient gas turbine engine architecture utilizing multiple stages of intercooling and reheat, ceramic technology, turbocharger technology and high pressure combustion. The approach includes utilizing a conventional dry low NOx combustor for the main combustor and thermal reactors for the reheat apparatuses. In a first configuration, there are three separate turbo-compressor spools and a free power turbine spool. In a second configuration, there are three separate turbo-compressor spools but no free power spool. In a third configuration, all the compressors and turbines are on a single shaft. Each of these configurations can include two stages of intercooling, two stages of reheat and a recuperator to preheat the working fluid before it enters the main combustor.

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. The system may also include integration of a pressure swing reformer (PSR), air-blown auto-thermal reformer (ATR), or oxygen-blown ATR with a gas power turbine system, preferably a combined cycle gas power turbine system. Such systems may be employed to capture and utilize greenhouse gases (GHG) and generate power for use in hydrocarbon recovery operations.

A hybrid aerodynamic thrust system as a prime mover for aircraft or other high-speed vehicles. An arrangement of dual thrust resources to alternately accommodate low and high airspeed regimes. Electromotive force is used in lieu of hot section power turbines to achieve engine air compression or alternately perform thrust work at low velocities.

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.

A drive system for driving a load by a gas turbine. The gas turbine comprises a gas generator having a gas-generator rotor and comprising at least one gas-generator compressor and one high-pressure turbine driving the gas-generator compressor. The gas turbine further comprises a power turbine having a power-turbine rotor, which is torsionally independent of the gas-generator rotor. The load is connected to the power-turbine rotor. The system further comprises an electric motor / generator mechanically connected to the gas-generator rotor and electrically connected to an electric power grid. The electric motor / generator is adapted to function alternatively: as a generator for converting mechanical power from the gas turbine into electrical power; and as a motor for supplementing driving power to the load. A set of movable nozzle guide vanes is arranged at the inlet of the power turbine.

The invention discloses continuous large-power turbine fracturing equipment. The large-power turbine fracturing equipment comprises a turbine engine, a reduction box, a transmission shaft and a plunger pump, wherein the turbine engine and the reduction box are arranged on the same straight line; the reduction box is connected to the plunger pump through a transmission shaft; and an angle of the transmission shaft ranges from 2 degrees to 4 degrees. The continuous large-power turbine fracturing equipment has the beneficial effects that: a chassis T1 material is selected, so that a stable working platform is provided for the equipment; the turbine engine and the reduction box are on the same straight line, the transmission shaft is arranged between the reduction box and the plunger pump, andthe angle of the transmission shaft ranges from 2 degrees to 4 degrees, so that stable and efficient transmission of the turbine engine is guaranteed, and a fault occurrence rate is reduced; a lubricating system driven by an auxiliary power system guarantees that the turbine engine, the reduction box and the plunger pump work under a proper environment; dual lubricating systems guarantee that theplunger pump realizes continuous operation under power of 5000 HP or higher; and the technical means finally can meet continuous large-power operation requirements of the fracturing equipment.

The present invention provides methods and system for power generation using a high efficiency combustor in combination with a CO2 circulating fluid. The methods and systems advantageously can make use of a low pressure ratio power turbine and an economizer heat exchanger in specific embodiments. Additional low grade heat from an external source can be used to provide part of an amount of heat needed for heating the recycle CO2 circulating fluid. Fuel derived CO2 can be captured and delivered at pipeline pressure. Other impurities can be captured.

The invention discloses a double-vehicle-mounted gas turbine generator set. According to the double-vehicle-mounted gas turbine generator set, the whole generator set is in a double-vehicle mode so asto facilitate transportation and movement; a gas turbine, a generator, a gearbox, an air inlet system, a starting lubricating system, a fire extinguishing system, a cabin cooling system and a controlsystem are reasonably arranged in a silent cabin, so that the space layout is effectively optimized, and the space guarantee is provided for the double-vehicle of the high-power gas turbine; the power of the gas turbine is large, and the output power is also large; and in the same unit area, compared with the simultaneous use of existing low-power multi generators, the power density through usingthe double-vehicle-mounted gas turbine generator set is larger, and the occupied area is effectively reduced. By adoption of a hydraulic leveling mechanism, the height of the double-vehicle can be effectively matched; and an adjusting mechanism of an exhaust system can be used for adjusting the movement of a second transportation tool in the horizontal direction, so that rapid installation and butt joint on site are realized without hoisting and ground hardening.

A power generation system includes a first compressor, a second compressor, a combustor configured to receive compressed air from the second compressor to produce an exhaust stream, a first turbine, and a power turbine. The first turbine is configured to receive the exhaust stream, generate a rotational power from the exhaust stream, output the rotational power to a second compressor, and output the exhaust stream. The system includes a coupling device configured to couple and decouple the first compressor to / from a second turbine, an electrical generator coupled to an output of the power turbine and configured to output electrical power, and a controller configured to cause the coupling device to mechanically decouple the second turbine from the first compressor, and cause the coupling device to direct compressed air from an air storage cavern to an inlet of the second compressor.

A counter-flow system for use in a turbine for selecting various mixtures of fluids for use with the system. The system may be used for a combustor for a gas powered turbine which employs a heat exchanger to combust a fuel without the emission of undesired chemical species. A gas powered turbine requires expanding gases to power the turbine blades. Fuel is combusted to produce the required gases. An oxidizer is introduced into the counter-flow system in a first direction before a first portion of fuel is introduced into the oxidizer. The fuel and oxidizer mixture is then flowed through a second pathway wherein the fuel and oxidizer mixture obtains a selected amount of thermal energy. Moreover, in a second pathway an equivalence ratio of the fuel and oxidizer mixture may be altered from the original fuel and oxidizer mixture.

An inside out generator disposed aft of the low-pressure turbine spool to generate power for the electrical demands of an aircraft system. The low-pressure turbine discharge flow is used to drive the power turbine, which is coupled to the generator. The generator is able to extract power at idle conditions of the aircraft engine from ducting the discharge through the inside out generator. The system eliminates the placement of a generator in the hot gas path of the discharge, and enables the injection of power directly to the accessory gear box of the engine.

A power and cooling management system configured to flexibly couple various adaptive modules to an integrated power and cooling unit to suit any aircraft platform is provided. The integrated power and cooling unit has a compressor, a power turbine, a cooling turbine and an integral starter generator mounted to the shaft of the power and cooling turbine. The integrated power and cooling unit may be pneumatically and / or pneumatically coupled to an adaptive module that comprises an additional compressor and an additional turbine or electrically coupled to a fuel cell which provides the main power after entering the full operation mode. When the engine includes an integral starter generator mounted thereto, the integral starter generator of the integrated power and cooling unit is operative to receive electric power from the engine mounted generator. Alternatively, a motor / generator may be mounted to the shaft of the additional turbine of the adaptive module.

An aeroderivative gas turbine including an air intake plenum; a compressor with a compressor air intake in fluid communication with the air intake plenum; a combustor; a high pressure turbine; a power turbine. A forced air-stream generator is arranged in fluid communication with the air intake plenum. A shutter arrangement is provided in a combustion-air flow path, arranged and controlled to close the combustion-air flow path for pressurizing said air intake plenum by means of the forced air-stream generator to a pressure sufficient to cause pressurized air to flow through the aeroderivative air turbine.

An integrated environmental control system for an aircraft compartment and aircraft power system comprises first and second air compressors, an auxiliary power unit, and first and second environmental control systems. The first and second compressors receive and compress airflow from the aircraft exterior. The auxiliary power unit comprises a first shaft rotatably mounting a power turbine, a third air compressor to compress airflow from the aircraft exterior, and a first cooling turbine to cool the airflow. Each environmental control system comprises a first heat exchanger, a recycling heat exchanger, and a second shaft rotatably mounting a fourth compressor and a second cooling turbine for compressing and cooling the airflow. The first heat exchanger receives airflow from the first, second, and third air compressors and forwards airflow to the aircraft compartment. The recycling heat exchanger receives airflow from the aircraft compartment and recirculates airflow back to the aircraft compartment.

Herein provided are methods and systems for operating a gas-turbine engine comprising a gearbox and a power turbine coupled to the gearbox. A first torque at the gearbox is obtained via a sensor. A second torque at the power turbine is determined based on the first torque. A power at the power turbine is determined based on the second torque. Operation of the engine is controlled based on the power.

The present invention provides methods and system for power generation using a high efficiency combustor in combination with a CO2 circulating fluid. The methods and systems advantageously can make use of a low pressure ratio power turbine and an economizer heat exchanger in specific embodiments. Additional low grade heat from an external source can be used to provide part of an amount of heat needed for heating the recycle CO2 circulating fluid. Fuel derived CO2 can be captured and delivered at pipeline pressure. Other impurities can be captured.

A system and process are provided for converting a light hydrocarbon gas to a synthetic heavier hydrocarbon liquid. The system includes an autothermal reformer, a Fischer-Tropsch reactor and a Brayton cycle that are structurally and functionally integrated. In the practice of the process, a mixture of a hydrocarbon feed gas, a compressed air feed and process steam is fed to the autothermal reformer to produce a synthesis gas. The synthesis gas is fed to the Fischer-Tropsch reactor where it is catalytically reacted to produce heavy hydrocarbons. The outlet from the Fischer-Tropsch reactor is separated into water, a low heating value tail gas, and the desired hydrocarbon liquid product. The water is pressurized and heated to generate process steam. The tail gas is heated and fed with compressed air and steam to the Brayton cycle having a combustor and a series of power turbines and compressors. The tail gas and air feed are burned in the combustor to produce a combustion gas that is used to drive a power turbine linked by a shaft to an air compressor, thereby driving the air compressor. The system further includes a plurality of heat exchangers that enable heat to be recovered from the outlet of the autothermal reformer. The recovered heat is used to make the process steam as well as to preheat the hydrocarbon feed gas before it is fed to the autothermal reformer, preheat the synthesis gas before it is fed to the Fischer-Tropsch reactor and preheat the tail gas before it is fed to the combustor.

An aeroderivative gas turbine, including a gas generator, a gas generator rotor, a power turbine section, and a slow turning device, wherein said slow turning device is designed and arranged to keep said rotor in rotary motion after turbine shut-down.

An internal combustion engine having a reciprocating multi cylinder internal combustion engine with multiple valves. At least a pair of exhaust valves are provided and each supply a separate power extraction device. The first exhaust valves connect to a power turbine used to provide additional power to the engine either mechanically or electrically. The flow path from these exhaust valves is smaller in area and volume than a second flow path which is used to deliver products of combustion to a turbocharger turbine. The timing of the exhaust valve events is controlled to produce a higher grade of energy to the power turbine and enhance the ability to extract power from the combustion process.

A gas turbine engine is provided, including an air inlet in fluid communication with a compressor, a combustor, a compressor turbine, and a power turbine. The compressor and compressor turbine may be mounted on a first drive shaft, and the power turbine may be mounted on a second shaft. The engine further includes an engagement mechanism adapted to selectively engage the first drive shaft to the second drive shaft, wherein the first drive shaft and second drive shaft rotate at substantially the same speed when the engagement mechanism is engaged. The disclosed multi-spool gas turbine engine provides improved part power fuel consumption at reduced output shaft speeds. The proposed invention can relate to turbines with two or more gas generator spools.

An integrated power and pressurization management system supplies electrical power and cabin pressurization and cooling air during both airborne and ground operations. The system includes an integral auxiliary power unit (APU) that has a compressor, a motor-generator, and a power turbine all mounted on one shaft. The integral APU can supply compressed air for cabin pressurization and environmental cooling functions, and can generate electrical power for various electrical loads. The system further includes one or more electrically driven compressors.

An integrated power and pressurization management system supplies electrical power and cabin pressurization and cooling air during both airborne and ground operations. The system includes an integral auxiliary power unit (APU) that has a compressor, a motor-generator, and a power turbine all mounted on one shaft. The integral APU can supply compressed air for cabin pressurization and environmental cooling functions, and can generate electrical power for various electrical loads. The system further includes one or more electrically driven compressors.

The present invention relates to an electrical power and cooling system for use in an aircraft having at least one engine. The electrical power and cooling system comprises a single shaft, a power turbine mounted on the shaft for receiving fresh pressurized air from the at least one engine, a cooling turbine mounted on the shaft and receiving the fresh pressurized air from the at least one engine, a generator mounted on the shaft, and a fan mounted on the shaft for creating a flow of cooling air. The system further has a condenser for removing moisture from the air exiting the cooling turbine and a mixing chamber for mixing the cooled dry air with recirculated cabin air. The electrical power and cooling system delivers conditioned air to a cabin and / or a flight deck onboard the aircraft and electrical power to the aircraft's electrical systems.

A directed vapor deposition (DVD) method and system for applying at least one bond coating on at least one substrate for thermal barrier coating systems. The method and system provides for alloy strengthening in high temperature metallic alloys that can be melt or solid state processed to materials that one applies by vapor deposition. The creep strengthened coating contains nanoscopic particles of oxides, nitrides, borides, carbides, and other materials which are formed by reactive codeposition. An approach for reactive codeposition is plasma assisted directed vapor deposition. Accordingly, the resultant structure may be utilized for, but not limited thereto, high temperature coatings, e.g. for protecting rocket or power turbines, or diesel engine components. The resultant structure is has a greatly extended lifetime attributed in part to the elimination of coating spallation by the “rumpling” mechanism.

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.