Abstract: A recuperative air storage plant comprising a gas turbine set and a heat exchanger. In the heat exchanger, exhaust gas heat from the gas turbine set can be transferred to a pressurized stored fluid which flows from a storage volume to a expansion machine. A flow junction with an exhaust gas damper which can be operated in a plurality of positions is arranged in the exhaust gas path of the gas turbine set, upstream of the heat exchanger. This exhaust gas damper makes it possible to divide the exhaust gas mass flow (m0) of the gas turbine set in a variable fashion between a stack and the heat exchanger. In this way it is possible to operate the gas turbine set quickly at high power in the electric power network independently of the heat exchanger and the expansion machine, while the thermal load of the air storage part is slowly increased by incrementally increasing the exhaust gas proportion (m1) which flows to the heat exchanger.

Abstract: A method for recovering energy from bleed air from a compressor of a gas turbine is provided. The method includes directing bleed air from a compressor of a gas turbine into a cooling unit. The bleed air is compressed air from the compressor, and the bleed air is not directed into a combustion chamber of the gas turbine. The method also includes cooling the bleed air within the cooling unit. The method further includes expanding the cooled bleed air within a turbo-expander to generate power.

Abstract: A system for providing air to a compressor of an auxiliary gas turbine engine of an aircraft. A system turbine has an inlet adapted to receive compressed air from the aircraft. A system compressor is mechanically coupled to the system turbine and has an inlet adapted to receive atmospheric air. The outlets of the system turbine and the system compressor are fluidly connectable to the inlet of the compressor of the auxiliary gas turbine engine. A method includes providing compressed air from an aircraft to an inlet of a system turbine mechanically coupled to a system compressor. The method includes providing atmospheric air to an inlet of the system compressor. The method includes providing the inlet of the compressor of an auxiliary gas turbine engine with air from an outlet of the system turbine and with air from an outlet of the system compressor.

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: Combined apparatus for heating a fluid and for producing electrical power is comprised of a burner operable to burn a combustible fuel-air mixture to produce gaseous products of combustion; a heat exchanger adapted to receive the products of combustion and to transfer heat therefrom to the fluid; a gas-operated turbine; and an electrical generator that is co-rotatable with the turbine. In operation, gaseous products of combustion are introduced into the turbine after they have passed through at least a portion of the heat exchanger. The products of combustion expand in the turbine to rotate the turbine, which in turn rotates the generator to produce electrical power. The apparatus further includes a compressor that is co-rotatable with the turbine and generator to provide combustion air to the burner and to circulate the products of combustion through the heat exchanger and turbine.

Abstract: A CAES system (10) includes an air storage (18), a compressor (20) supplying compressed air to the air storage, a power generating structure (11, 102), a heat exchanger (24), an auxiliary combustor (27), an air expander (30), and an electric generator (32). The system operates in one of modes a) a main power production mode wherein the auxiliary combustor is inoperable and the power generating structure is operable, to produce power by the air expander, fed by the heated compressed air received from the air storage, in addition to power produced by the power generating structure, or b) a synchronous reserve power mode wherein the auxiliary combustor is operable and the power generating structure is inoperable, with compressed air withdrawn from the air storage being preheated by the auxiliary combustor that feeds the air expander, with the air expander expanding the heated air and the generator providing immediate start-up power.

Abstract: A gas turbine, in particular an aircraft engine and to a method for generating electrical energy in a gas turbine is provided. The gas turbine comprises at least on engine core (18), in which a shaft (19) produces a shaft output. The turbine is equipped with means that generate electrical energy both from the shaft output produced by the engine core (18) and from the compressed air that is dissipated by the engine core (18).

Abstract: A power generation system includes a combustion turbine assembly (11) having a main compressor (12) receiving ambient inlet air, a main expansion turbine (14), a main combustor (16), and an electric generator (15) for generating electric power. An air storage (18?) has a volume for storing compressed air. A source of humidity (23, 34, 42) humidifies the compressed air that exits the air storage and thus provides humidified compressed air. A heat exchanger (24) receives a source of heat and the humidified compressed air so as to heat the humidified compressed air. A air expander (30) expands the heated, humidified compressed air to exhausted atmospheric pressure for producing additional power, and permits a portion of airflow expanded by the air expander to be injected into the combustion turbine assembly for power augmentation. An electric generator (31) is associated with the air expander for producing additional electrical power.

Abstract: An apparatus and method converts a power generation combined cycle (CC) power plant to a load management compressed air energy storage (CAES) power plant. The CC power plant includes at least one combustion turbine, a heat recovery steam generator (HRSG) to receive exhaust heat from an associated combustion turbine, a steam turbine associated with the HRSG, and an electric generator associated with the steam turbine. An air storage stores compressed air. At least one compressor supplies the air storage with compressed air so that off peak energy can be converted to compressed air energy stored in the air storage. Compressed air from the storage is received by the HRSG and the HRSG provides heat to compressed air received from the air storage. The steam turbine receives heated compressed air from the HRSG and expands the heated compressed air to produce power.

Abstract: A generator assembly for a gas turbine engine. The assembly includes an electrical generator connected via a first sprag clutch to an accessory gearbox driven by the engine. The generator is also connected by a second sprag clutch to an air turbine connected to engine bleed valves which are selectively open when the engine speed falls below a predetermined level. The clutches are arranged such that the generator is driven at any time by the fastest rotating of the gearbox and turbine.

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: 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, a combustor 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. Pressure reducing structure 28 is constructed and arranged to reduce pressure of compressed air from a source of compressed air to atmospheric pressure and thus to reduce a temperature of the compressed air from the source of compressed air to a temperature below ambient temperature when exhausted from the pressure reducing structure.

Abstract: A power generation system and method includes a first gas turbine system comprising a first combustion chamber configured to combust a first fuel stream of primarily hydrogen that is substantially free of carbon-based fuels. The first gas turbine system also includes a first compressor configured to supply a first portion of compressed oxidant to the first combustion chamber and a first turbine configured to receive a first discharge from the first combustion chamber and generate a first exhaust and electrical energy. The power generation system further includes a second gas turbine system comprising a second combustion chamber configured to combust a second fuel stream to generate a second discharge. The first compressor of the first gas turbine system is configured to supply a second portion of compressed oxidant to the second combustion chamber.

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: An integrated power and cooling machine having an indirect regenerative air cooling feature may be useful for providing power and environmental control to both ground vehicles, such as tanks, and aircraft, such as helicopters and airplanes. The integrated power and cooling machine may prevent contamination of the conditioned supply air by isolating the conditioned supply air from the machine lubricating and heat transport fluid (e.g., operating fluid) that may leak into the conditioned supply air. Furthermore, the integrated power and cooling machine may utilize a lower energy source from the engine, thereby reducing energy consumption and improving system efficiency. In addition, a flow mixing device may enhance airflow to improve cooling performance.

Abstract: A compressed air energy storage power station comprises a first shafting (1) and a second shafting (2). A gas turbo group (11), an electrical machine (12) and a compressor (13) are arranged on the first shafting (1). Switchable clutch elements (14, 15) are arranged between the electrical machine and the gas turbo group or the compressor. The clutch elements allow a connection to be selectively made between the electrical machine and the gas turbo group (11) or the compressor (13). An expansion machine (21) for the power generating expansion of a pressurized storage fluid, an electrical machine (22) and a compressor (23) are arranged on the second shafting (2). Switchable clutch elements (24, 25) are arranged between the electrical machine and the expansion machine or the compressor and allow the electrical machine to be optionally connected to the expansion machine and to the compressor. The electrical machines are operable both as generators and as electric motors.

Abstract: An aircraft accessory system includes an aircraft engine powered direct air turbine driven accessory and an air turbine drivingly directly connected by an air turbine shaft to the accessory. The air turbine includes a variable geometry turbine nozzle in selectable direct flow communication with at least two compressed engine air sources. The two compressed engine air sources may be an HPC interstage bleed and an HPC compressor discharge stage bleed. The variable geometry turbine nozzle may be in selectable direct flow communication with a third compressed engine air source such as a bypass duct or an engine inlet duct. The air turbine includes a turbine exit which may be in selectable direct flow communication with at least two relatively lower pressure engine air sinks. The air sinks may be located in the aft end of a bypass duct and in a divergent section of the exhaust nozzle.

Abstract: The invention relates to a system for driving an accessory, such as a fuel pump or an oil pump in a turboengine, said system comprising an electric motor and further comprising an air turbine associated with said electric motor. Said air turbine is suitable for being fed with a flow of air taken from a compressor of said turboengine and contributing to driving the accessory. The system also includes a valve for controlling the flow of air taken from the compressor, which valve is in the closed position while the turboengine is starting.

Abstract: A turbine engine arrangement incorporates an electrical machine combination which can act as a generator or motor. Thus, the combination during initial turbine engine arrangement start-up acts through this motor to drive shaft rotation. This shaft rotation creates core compressed air which is bled through a valve to an air turbine such that the electrical machine when acting as a motor or generator at low engine loads is appropriately cooled. The arrangement also includes a compressor fan which generates an airflow utilised by the air turbine in order to drive the electrical machine as a generator of electrical power when engine conditions dictate. A duct is provided to direct airflow exhausted from the air turbine to a heat exchanger arranged to exchange heat with a bypass flow from the compressor fan.

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 gas turbine system includes a gas turbine (1, 2, 3) having a compressor (1) and a turbine (2), which via a common shaft (3) drive a generator (4), and a combustion chamber (6), the exit of which is connected to the entry to the turbine (2) of the gas turbine (1, 2, 3), has a fuel feed (8) and receives combustion air from the exit of the compressor (1) of the gas turbine (1, 2, 3) via the high-pressure side of a recuperator (5), the exit of the turbine (2) and the entry to the compressor (1) of the gas turbine (1, 2, 3) being connected via the low-pressure side of the recuperator (5), and a first exhaust-gas turbocharger (ATL2) which sucks in air being connected to different locations (9, 10) of the low-pressure side of the recuperator (4) via the exit of its compressor (13) and the entry to its turbine (14).

Abstract: Plastic parts are formed to have a relatively high wall stiffness by utilizing a pair of spaced plastic plates. One of the plates may be a simple plate. The other plate has a plurality of ribs extending from a base. The ribs are welded to the other plate. Use of the ribs provides a relatively high degree of stiffness to the final molded plastic part, for a relatively lightweight part.

Abstract: A method of operating a turbine arranged in a compressed air energy storage power generation plant comprises an open-loop control of an air mass flow applied within a lower turbine speed range and a closed-loop control of the turbine speed within a higher turbine speed range. The open-loop control comprises the control of the air mass flow by means of air inlet valves and a free development of the turbine speed. The closed-loop control comprises the control of the turbine speed by means of a speed controller, which is acted upon by a speed limiting value determined according to the current air mass flow and a windage calculation. The speed controller activates a static frequency converter in the case that the turbine speed reaches values that are critical with respect to turbine windage or rotor dynamics.

Abstract: A gas turbine and air turbine installation includes a gas turbine to which, downstream of its exhaust gas end, the primary side of a heat exchanger for heating air is connected. In this arrangement, the heat exchanger includes an air turbine connected downstream of its secondary side. By this, a gas turbine and air turbine combined process can be realized which, compared with a pure gas turbine process, is associated with an increase in efficiency and power. The installation concept can be employed particularly advantageously in areas short of water where a conventional gas/steam installation or a steam power installation can hardly be realized because of the requirement for water. Further, a method of operating a power station installation involves waste heat in the exhaust gas of a gas turbine being used to do work to drive an air turbine.

Abstract: A power generation plant with a compressed air energy storage system comprises a means to reduce the pressure of air extracted from a compressed air storage cavern for the use in a combustion turbine. The means to reduce the air pressure comprises at least one expansion turbine and means to control the size of pressure reduction. Furthermore, the expansion turbine is arranged on a rotor shaft that drives a generator. The means for pressure redact, according to the invention, avoid power losses and provide an increased overall efficiency of the power generation plant.

Abstract: An environmental control system includes a turbomachine and an air cycle machine that is driven by shaft power of the turbomachine. The turbomachine includes a compressor, which supplies compressed bleed air to the air cycle machine. Ambient air is compressed by the compressor, and heat of compression is removed by an air-to-air heat exchanger, which envelops the turbomachine. The cooled, compressed air is expanded in the air cycle machine to produce a stream of cooled, conditioned air. Ambient air used by the air-to-air heat exchanger to cool the compressed bleed air is drawn into the turbomachine's exhaust by an eductor.

Abstract: The present invention relates to a turbogroup (1) of a power generating plant. A turbine unit (2), has a turbine (4) and a further fluid-flow machine (6) on a common turbine shaft. A generator unit (3), has a generator (8) on a generator shaft (9). The turbine shaft (5) and the generator shaft (9) are connected to one another. A third radial bearing unit (13) supports the generator shaft (9) on a side of the generator (8) which faces the turbine unit (2). A thrust bearing unit (16) supports the turbine shaft (5) axially between the generator (8) and the additional fluid-flow machine (6). A first radial bearing unit (11) and/or a second radial bearing unit (12) have/has pendulum supports (20) which are in each case supported on a bearing pedestal (21). At least one of the pendulum supports (20) is supported on the associated bearing pedestal (21) via a spring element.

Abstract: A gas turbine and air turbine installation includes a gas turbine to which, downstream of its exhaust gas end, the primary side of a heat exchanger for heating air is connected. In this arrangement, the heat exchanger includes an air turbine connected downstream of its secondary side. By this, a gas turbine and air turbine combined process can be realized which, compared with a pure gas turbine process, is associated with an increase in efficiency and power. The installation concept can be employed particularly advantageously in areas short of water where a conventional gas/steam installation or a steam power installation can hardly be realized because of the requirement for water. Further, a method of operating a power station installation involves waste heat in the exhaust gas of a gas turbine being used to do work to drive an air turbine.

Abstract: A supercharger arrangement, having a first rotor assembly, including a first compressor with a first compressor inlet and a first compressor outlet, and a second compressor with a second compressor inlet and a second compressor outlet. The supercharger arrangement also having a second rotor assembly, including a third compressor with a third compressor inlet and a third compressor outlet, and a fourth compressor with a fourth compressor inlet and a fourth compressor outlet; and a first inter-stage conduit that communicates the first compressor outlet with the fourth compressor inlet so that flow from the first compressor feeds into the fourth compressor.

Abstract: A jet engine assembly having a jet engine and an unsteady flow ejector. The unsteady flow ejector segregates the exhaust flow from the jet engine into a plurality of rotating high velocity, low density jets and a plurality of rotating low pressure voids. The low pressure voids are employed to entrain at least a portion of a secondary flow of air which is mixed with the jets to produce a mixed flow having a relatively higher flow rate and a relatively lower velocity than the exhaust flow. A method for attenuating the noise that is produced by the exhaust flow of a jet engine is also provided.

Abstract: An aircraft gas turbine engine is provided with low observable fan features which reduce the radar signature of the engine and its aircraft. An aircraft gas turbine engine fan section has in direct serial flow relationship an inlet having fixed high swirl angle inlet guide vanes, a first stage of first fan rotor blades, a stage of first variable angle stator vanes, and a fan bleed. The inlet guide vanes are angled to block the linear line of sight of the rotating fan blades through the inlet and include a RAM treatment which preferably is a coating of a radar absorbing material on the surface of the inlet guide vanes. The exemplary embodiment has a multi-stage fan section with the mid-stage fan bleed disposed between the first and second stages of fan rotor blades.

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: A means for eliminating a frozen or near frozen state in a drain of the condensed water generated by the action of an exhaust gas heat exchanger is provided. The condensed water separated from the exhaust gas in a silencer (31) is passed through a waste water trap provided with the joint (34) and discharged to the outside. The joint (34) also has a passage provided therein for circulating a heat transfer medium through an externally (separately) installed heat exchanger (52A). When the engine (2) is started, it is judged, based on the temperature of the waste water trap or the water measured by a sensor (53), whether the frozen state is present or not. When it is judged that the frozen state is present, a water pump 10 is switched on for circulating the heat transfer medium through the waste water trap.

Abstract: The device involves the placement of an air pump turbine and the aircraft outflow valve in a duct through which all the air flows, with the turbine shaft attached to that of an electric generator, to a hydraulic pump, and to the N2 and accessory gearbox inside the engine, the air is also sent through a duct to strike inclined against the tips of the fan blades and against the tips of the first stage of the low speed compressor blades of the turbine engine.

Abstract: A two stage expansion and single stage combustor compressed air energy storage cycle that employs a heat exchanger to raise the temperature of the compressed air before it enters a high pressure expander. A combustor heats the exhaust from the high pressure expander and creates a working gas to drive a low pressure expander. The exhaust from the low pressure expander is supplied to the heat exchanger to raise the temperature of the compressed incoming air. A portion of the exhaust of the high pressure expander is cooled and employed in a cooling circuit within the low pressure expander. A starter valve in the compressed air input circuit finely tunes the incoming air during startup. The startup air flow is heated by an auxiliary duct burner until the low pressure turbine exhaust reaches operating temperature and is sufficient to heat the incoming air under normal operating conditions.

Abstract: An impeller is directly driven by an output shaft of a core engine. The airflow produced by the impeller rotates an air turbine and a fan disposed integrally with the air turbine. The impeller and the air turbine form a fluid coupling which serves also as a speed reducing mechanism. The rotational speed of the fan can be reduced to be lower than that of the output shaft while retaining efficiency of the core engine. The outer diameter of the fan can be increased, raising a bypass ratio.