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Небесная энциклопедия

Космические корабли и станции, автоматические КА и методы их проектирования, бортовые комплексы управления, системы и средства жизнеобеспечения, особенности технологии производства ракетно-космических систем

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Мониторинг СМИ

Мониторинг СМИ и социальных сетей. Сканирование интернета, новостных сайтов, специализированных контентных площадок на базе мессенджеров. Гибкие настройки фильтров и первоначальных источников.

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Поддерживает ввод нескольких поисковых фраз (по одной на строку). При поиске обеспечивает поддержку морфологии русского и английского языка
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Применить Всего найдено 3972. Отображено 100.
07-03-2013 дата публикации

Compressor end head heating arrangement

Номер: US20130058769A1
Автор: Giusepe Sassanelli, Manuele Bigi, Suresh Devanbu
Принадлежит: Individual

A compressor end head for providing a thermal barrier near a mechanical seal includes an inner end head and an outer end head. The outer end head includes an opening in the center for enclosing the inner end head, an outlet and grooves alongside surfaces radially adjacent the opening. The inner end head has an opening in the center, an inlet, grooves in the opening for enclosing an end portion of a compressor shaft and a flow path along an outer surface.

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Номер записи: 1
23-05-2013 дата публикации

Expandable impeller pump

Номер: US20130129503A1
Автор: Boris Leschinsky, David A. Boger, Gregory P. Dillon, James P. Runt, Justin M. Walsh, Mark W. McBride, Robert F. Kunz, Robert L. Campbell, Stephen A. Hambric, Thomas M. Mallison
Принадлежит: PENN STATE RESEARCH FOUNDATION, Thoratec LLC

An impeller includes a hub, and a plurality of blades supported by the hub, the blades being arranged in at least two blade rows. The impeller has a deployed configuration in which the blades extend away from the hub, and a stored configuration in which at least one of the blades is radially compressed, for example by folding the blade towards the hub. The impeller may also have an operational configuration in which at least some of the blades are deformed from the deployed configuration upon rotation of the impeller when in the deployed configuration. The outer edge of one or more blades may have a winglet, and the base of the blades may have an associated indentation to facilitate folding of the blades.

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Номер записи: 2
06-06-2013 дата публикации

Abradable seal with axial offset

Номер: US20130142628A1
Автор: Nuo Sheng, Roderick Mark Lusted, Vittorio Michelassi
Принадлежит: Individual

A sealing system for a centrifugal compressor includes a stator having a seal, a seal disposed in the seal housing and having an abradable portion along an inner circumference, a rotor having a plurality of rotor teeth configured to rotate within the inner circumference of the seal and configured to create rub grooves within the abradable portion, and a first spring disposed between the stator and the seal and configured to facilitate axial movement of the seal relative to the seal housing.

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Номер записи: 3
04-01-2018 дата публикации

Ring section pump having intermediate tie rod combination

Номер: US20180003177A1
Автор: Abhi N. GANDHI, Daniel S. Miller, Paul W. Behnke
Принадлежит: ITT Manufacturing Enterprises LLC

A ring section pump features a low-pressure end configured to receive fluid to be pumped into the ring section pump; a high-pressure end configured to provide the fluid to be pumped from the ring section pump; and an intermediate tie rod combination having a intermediate flange with upper tie rods configured to couple together the intermediate flange and the high-pressure end and with lower tie rods configured to couple together the intermediate flange and the low-pressure end. The low-pressure end has an inlet flange; the high-pressure end has an outlet/discharge flange; and the upper tie rods couple together the intermediate flange and the outlet/discharge flange and the lower tie rods couple together the intermediate flange and the inlet flange.

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Номер записи: 4
03-01-2019 дата публикации

Stop valve and steam turbine

Номер: US20190003330A1
Автор: Makio Morimoto
Принадлежит: Mitsubishi Heavy Industries Compressor Corp

A stop valve includes: a valve seat in a fluid flow path; a valve disc that contacts the valve seat and that closes the fluid flow path; a valve stem that extends along a center axis includes a first end, in a direction of the center axis, that is connected to the valve disc; a spindle that extends along the center axis and comprises an end surface of a first end, in the direction of the center axis, that faces an end surface of a second end of the valve stem, in the direction of the center axis; and a connector that connects the second end of the valve stem to the first end of the spindle.

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Номер записи: 5
13-01-2022 дата публикации

TURBO BLOWER CAPABLE OF OPERATING IN SURGE AREA

Номер: US20220010801A1
Автор: KIM Minsoo
Принадлежит: TURBOWIN CO., LTD.

The present disclosure relates to a turbo blower capable of operating in a surge area and, more particularly, to a turbo blower capable of operating in a surge area, the turbo blower increasing consistency of performance thereof and efficiency by preventing suspension thereof due to a temporarily generated surge by operating even in a surge area for a predetermined time in addition to a normal area in which the turbo blower normally operates. 1{'b': 100', '200', '100', '100, 'a turbo blower machine unit () increasing pressure of external air flowing inside and then discharging the external air; and a turbo blower control unit () driving the turbo blower machine unit () such that the turbo blower machine unit () is stably operated for a predetermined time even in a surge area (SR),'}{'b': '100', 'wherein the turbo blower machine unit () that suctions air, increases the pressure of the air, and then discharges the air includes{'b': '110', 'a body housing () having a predetermined size in which a predetermined space is formed;'}{'b': 120', '110, 'an air inlet () formed on a side of the body housing ();'}{'b': 130', '110', '120, 'a turbo blower () disposed in the body housing () and suctioning and discharging air flowing into the air inlet ();'}{'b': 140', '130', '130', '110, 'an air discharge cone pipe () coupled to the turbo blower () and sending the air discharged through the turbo blower () to the body housing ();'}{'b': 150', '110, 'a turbo blower silencer () suppressing and decreasing noise generated from the inside of the body housing ();'}{'b': '160', 'the electric valve () of which the degree of opening/closing is automatically controlled due to a surge; and'}{'b': 170', '130', '130', '140', '140', '130', '132', '130', '130, 'a blow-off valve () being automatically opened/closed in accordance with the status of the turbo blower (), discharging air temporarily increased in pressure to the outside in order to prevent backflow of air increased in pressure and ...

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Номер записи: 6
20-01-2022 дата публикации

ACCELERATED AND-OR REDIRECTED FLOW-INDUCING AND-OR LOW PRESSURE FIELD OR AREA-INDUCING ARRANGEMENT, THEIR USE WITH TURBINE-LIKE DEVICES AND METHOD FOR USING SAME

Номер: US20220018323A1
Автор: Schurtenberger Walter
Принадлежит:

An accelerated and/or redirected flow arrangement, optimally serving as a wildlife and/or debris excluder (WDE), is used in combination with a turbine-like device having an inlet end and an outlet end for fluid flowing therethrough, e.g., a hydro-turbine. The arrangement includes at least a forward part designed to be placed in front of a fluid inlet of a turbine-like device and configured to produce at least one of the following effects on the fluid: (a) imparting a re-direction of the fluid; and/or (b) accelerating the flow velocity of the fluid, as it flows through the forward part. Turbine-like devices having both a forward part and a rearward part of flow arrangement are disclosed, as well as a method of enhancing turbine performance. 130-.31. A combination comprising a hydro-kinetic turbine device in combination with an accelerated and/or redirected flow-inducing arrangement ,the turbine device having a fluid inlet end and a fluid outlet end for fluid flowing therethrough, defining a direction of fluid flow through the device, an accelerator shroud section that has a longitudinal central axis and defines within its cross-section a fluid flow area and includes a rotor assembly that is mounted within the accelerator shroud for rotation around the longitudinal central axis, and includes a plurality of rotor blades extending radially outwardly within the accelerator shroud;the flow-inducing arrangement comprising (1) a forward deflector positioned in front of the fluid inlet end of the turbine device and (2) a rear deflector positioned downstream of the rotor assembly, the forward deflector being configured so as to produce at least one of the following effects on the fluid flowing through the turbine-device: (a) imparting a re-direction of the fluid as it passes through the forward deflector; and/or (b) accelerating the flow velocity of the fluid as it flows through the forward deflector,wherein the forward deflector comprises a conically shaped forward array of ...

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Номер записи: 7
10-01-2019 дата публикации

SYSTEMS AND METHODS FOR COOLING COMPONENTS OF A GAS TURBINE

Номер: US20190010869A1
Автор: Kerth Jason M.
Принадлежит:

Systems and methods for cooling one or more components of a gas turbine are provided. One system may include an expansion device and one or more conduits. The expansion device may be operatively coupled to the gas turbine and configured to convert a pressure drop of a stream of compressed process fluid to mechanical energy. The expansion device may be further configured to at least partially drive the gas turbine with the mechanical energy. The one or more conduits may fluidly couple the expansion device and the gas turbine. The one or more conduits may be configured to direct an expanded stream of the compressed process fluid to the one or more components of the gas turbine to cool the one or more components. 1. A gas turbine assembly , comprising: a combustor configured to receive a first stream of a compressed process fluid, mix a fuel with the first stream of the compressed process fluid to form a mixture, and combust the mixture to form a combustion product, and', 'a power turbine configured to receive and expand the combustion product to convert a pressure drop of the combustion product to mechanical energy;, 'a gas turbine comprising'}an expansion device configured to receive and expand a second stream of the compressed process fluid to convert a pressure drop of the second stream of the compressed process fluid to mechanical energy, the expansion device operatively coupled to the power turbine and configured to at least partially drive the power turbine with the mechanical energy converted from the pressure drop of the second stream of the compressed process fluid; anda plurality of conduits fluidly coupling the power turbine and the expansion device and configured to direct the second stream of the compressed process fluid expanded in the expansion device to the power turbine to cool one or more components of the power turbine.2. The gas turbine assembly of claim 1 , wherein the power turbine comprises a plurality of stages claim 1 , each stage comprising a ...

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Номер записи: 8
09-01-2020 дата публикации

BLADE CONTAINMENT STRUCTURE

Номер: US20200011203A1
Автор: Domala Uma Maheshwar, Jain Manoj Kumar, Jain Nitesh, Kray Nicholas Joseph, Prabhakar Nagamohan Govinahalli
Принадлежит:

A blade containment structure surrounding a fan in a turbofan engine is disclosed. The blade containment structure includes a cellular material to absorb energy and contain fragments of a blade thrown outward; an inner shell; a ductile back sheet spaced radially outward from the inner shell, the ductile back sheet and inner shell cooperating to define a nesting area for the cellular material, wherein the cellular material is bound at its radially inner surface by the inner shell and at its outer surface by the ductile back sheet; and a containment blanket overlaid on the ductile back sheet, the containment blanket being of the type effective to contain fragments of the blade that penetrate through the ductile back sheet. 1. A blade containment structure , comprising:a cellular material to absorb energy and contain fragments of a blade thrown outward;an inner shell;a ductile back sheet spaced radially outward from the inner shell, the ductile back sheet and inner shell cooperating to define a nesting area for the cellular material, wherein the cellular material is bound at its radially inner surface by the inner shell and at its outer surface by the ductile back sheet; anda containment blanket overlaid on the ductile back sheet, the containment blanket being of the type effective to contain fragments of the blade that penetrate through the ductile back sheet.2. The blade containment structure according to claim 1 , wherein the blade containment structure is formed of two or more segments.3. The blade containment structure according to claim 2 , wherein the two or more segments are joined together using joint configurations selected from the group consisting of an offset lap joint claim 2 , a butt joint with splice plates claim 2 , an interlocking lap joint claim 2 , and a flush lap joint.4. The blade containment structure according to claim 3 , wherein the joint configurations are assembled using an adhesive.5. The blade containment structure according to claim 3 , ...

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Номер записи: 9
09-01-2020 дата публикации

POWER PLANT METHODS AND APPARATUS

Номер: US20200011242A1
Автор: Fukuizumi Yasushi, Kukoski Allan, Wu Song
Принадлежит:

A hybrid power plant system including a gas turbine system and a coal fired boiler system inputs high oxygen content gas turbine flue gas into the coal fired boiler system, said gas turbine flue gas also including carbon dioxide that is desired to be captured rather than released to the atmosphere. Oxygen in the gas turbine flue gas is consumed in the coal fired boiler, resulting in relatively low oxygen content boiler flue gas stream to be processed. Carbon dioxide, originally included in the gas turbine flue gas, is subsequently captured by the post combustion capture apparatus of the coal fired boiler system, along with carbon diode generated by the burning of coal. The supply of gas turbine flue gas which is input into the boiler system is controlled using dampers and/or fans by a controller based on an oxygen sensor measurement and one or more flow rate measurements. 1. A power system comprising: a boiler;', 'an oxygen sensor; and', i) a gas turbine flue gas boiler hopper input of said boiler or', 'ii) a gas turbine flue gas mill air supply duct input which is included as part of a mill air supply duct which supplies air to a mill which provides fuel to said boiler;, 'one or more gas turbine flue gas inputs including at least one of], 'a boiler system includinga gas turbine system; anda controller for controlling the supply of gas turbine flue gas to said one or more gas turbine flue gas inputs of said boiler system based on an oxygen level measured by said oxygen sensor.2. The power system of claim 1 , wherein the boiler system includes:a burner; andat least said gas turbine flue gas boiler hopper input for receiving gas turbine flue gas and supplying said received gas turbine flue gas into said boiler at a location beneath the burner.3. The power system of claim 2 , wherein said boiler system further includes:a burner air supply duct which supplies air to a burner of said boiler, said burner air supply duct including a gas turbine flue gas burner air supply ...

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Номер записи: 10
16-01-2020 дата публикации

Variable geometry diffuser ring

Номер: US20200018326A1
Автор: Paul W. Snell
Принадлежит: Johnson Controls Technology Co

A compressor includes an impeller, a diffuser passage having a diffuser vane therein, and a variable geometry diffuser ring positioned between the impeller and the diffuser vane with respect to a flow of a refrigerant through the compressor. The compressor also includes an actuator configured to move the variable geometry diffuser ring in a direction transverse to the flow of the refrigerant, and between a plurality of ring positions including a fully retracted ring position in which the variable geometry diffuser ring does not block the flow of the refrigerant, and at least one protruded ring position in which the variable geometry diffuser ring adjusts an angle of the flow of the refrigerant upstream of the diffuser vane.

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Номер записи: 11
26-01-2017 дата публикации

SECTIONED GAS TURBINE ENGINE DRIVEN BY SCO2 CYCLE

Номер: US20170022844A1
Автор: Armstrong Michael J., Bastnagel Thomas E., Burns Donald W., Vaisman Igor
Принадлежит:

An apparatus, system, and method for a gas turbine engine may include a sectioned heat exchanger. A heat exchanger may include an inlet manifold configured to receive a working fluid. A plurality of circuits including at least first and second circuits configured to transfer heat with respect to the working fluid. Each of the circuits may have a circuit inlet valve, a circuit heat exchange channel, and a circuit outlet valve. The heat exchanger may further include an outlet manifold configured to pass the working fluid to an outlet. The heat exchanger may include a first sensor configured to measure of first parameter of the first circuit and a second sensor configured to measure a second parameter of at least one of the outlet and the second circuit. A controller may be configured to selectively isolate at least one of the plurality of circuits based on a pressure difference between the first and second parameters. 1. A sectioned heat exchanger system for a gas turbine engine , comprising:an inlet manifold configured to receive a working fluid;a plurality of circuits including at least first and second circuits configured to transfer heat with respect to the working fluid, each of the first and second circuits having a circuit inlet valve, a circuit heat exchange channel, and a circuit outlet valve;an outlet manifold configured to pass the working fluid to an outlet;a first sensor configured to measure a first parameter of the first circuit;a second sensor configured to measure a second parameter of at least one of the outlet and the second circuit; anda controller configured to selectively isolate at least one of the plurality of circuits based on a parameter difference between the first and second parameters.2. The system of claim 1 , wherein the first and second sensors include respective first and second pressure sensors claim 1 , wherein the parameter difference includes a pressure difference.3. The system of claim 1 , wherein the controller is configured to ...

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Номер записи: 12
28-01-2016 дата публикации

ASYMMETRIC DOUBLE-ENTRY TURBINE

Номер: US20160025044A1
Автор: Martinez-Botas Ricardo, Sakai Masakazu
Принадлежит:

An asymmetric double-entry turbine is provided with a turbine housing that includes a first volute, a second volute and a turbine receiving bore. The first volute has a first exhaust gas inlet and a first exhaust gas outlet. The second volute has a second exhaust gas inlet and a second exhaust gas outlet. The turbine receiving bore is in fluid communication with the first exhaust gas outlet and the second exhaust gas outlet for conducting a flow of exhaust gas from the first exhaust gas outlet and the second exhaust gas outlet out in an axial direction. The first exhaust gas outlet has an angular opening amount of more than 180 degrees around the turbine receiving bore. The second exhaust gas outlet has an angular opening amount of less than 180 degrees around the turbine receiving bore. 1. An asymmetric double-entry turbine housing comprising:a first volute having a first exhaust gas inlet and a first exhaust gas outlet;a second volute having a second exhaust gas inlet and a second exhaust gas outlet; anda turbine receiving bore in fluid communication with the first exhaust gas outlet and the second exhaust gas outlet for conducting a flow of exhaust gas from the first exhaust gas outlet and the second exhaust gas outlet out in an axial direction, the first exhaust gas outlet having an angular opening amount of approximately 200 degrees around the turbine receiving bore, and the second exhaust gas outlet having an angular opening amount of approximately 160 degrees around the turbine receiving bore.2. The asymmetric double-entry turbine housing according to claim 1 , whereinthe second volute is disposed radially inward of the first volute with respect to a radial direction of the turbine receiving bore.3. The asymmetric double-entry turbine housing according to claim 1 , whereinthe first volute has a cross sectional area at its upstream end of the first exhaust gas outlet that is greater than a cross sectional area of the second volute at its upstream end of the ...

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Номер записи: 13
10-02-2022 дата публикации

ELECTRIC MACHINE COOLING

Номер: US20220042458A1
Автор: Kristjansson Kolbeinn, Long Stephen Andrew, Morgan Sean, Trawick David Russell
Принадлежит:

An example system comprises an electric machine including a stator and a rotor, a cooling system configured to supply a cooling fluid to cool the electric machine, and a stator tube configured to contain the cooling fluid within a stator portion of the electric machine and prevent the cooling fluid from contacting the rotor. 1. A system comprising:an electric machine including a stator and a rotor;a cooling system configured to supply a cooling fluid to cool the electric machine; anda stator tube configured to contain the cooling fluid within a stator portion of the electric machine and prevent the cooling fluid from contacting the rotor.2. The system of claim 1 , further comprising an engine claim 1 , wherein the cooling system comprises a cooling circuit that includes both the engine and the electric machine claim 1 , and wherein the cooling system is configured to supply the cooling fluid to the engine to cool the engine.3. The system of claim 2 , wherein the electric machine comprises a generator claim 2 , wherein the rotor of the generator coupled to an output shaft of the engine and is configured to be driven by the engine.4. The system of claim 3 , wherein the engine comprises a gas turbine engine.5. The system of claim 1 , wherein the electric machine further comprises one or more bearings claim 1 , and wherein the cooling system is configured to supply the cooling fluid to the one or more bearings.6. The system of claim 5 , wherein the cooling fluid is configured to cool and lubricate the one or more bearings.7. The system of claim 2 , wherein the cooling system comprises:a cooling fluid tank configured to store the cooling fluid;a pump in fluid communication with the fluid tank and configured to move fluid within the cooling circuit to the engine and the electric machine; anda heat exchanger configured to receive the cooling fluid from any of the electric machine, the engine, and the pump, wherein the heat exchanger is configured to remove heat from the ...

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Номер записи: 14
02-02-2017 дата публикации

HYBRID POWER GENERATION SYSTEM USING SOLAR ENERGY AND BIOENERGY

Номер: US20170030226A1
Автор: CHEN Yilong, LIU Wenyan, ZHANG Yanfeng
Принадлежит:

A hybrid power generation system using solar energy and bioenergy, including a solar thermal boiler system, a biomass boiler system, and a turbogenerator system. The solar thermal boiler system includes a trough solar collector, a heat collector, an oil circulating pump, a storage tank for storing heat transfer oil, a solar thermal heater, a solar thermal evaporator, a main pipe transporting saturated steam, and an auxiliary boiler. Heat transfer oil output from a solar light field of the solar thermal boiler system is transmitted through and transfers heat to the solar thermal evaporator and the solar thermal heater, and the heat transfer oil returns to the storage tank for storing heat transfer oil. The heat transfer oil in the storage tank is pumped to the solar light field via the oil circulating pump. 2. The power generation system of claim 1 , wherein waste steam of the turbine is connected to the condenser and is condensed to be a condensate which is collected in a condensate tank; the condensate is pressurized by the condensate pump and is transmitted to the first heater in which the condensate is heated and is transmitted to the deaerator to produce feed water; the feed water output from the deaerator is pumped to the second heater to be heated via the feed water pump; a heating temperature in the second heater is 240° C.±5° C.; the feed water is distributed by a first flow distributer to be two parts: first part of the feed water is transmitted to the biomass boiler system to produce steam claim 1 , and second part of the feed water is transmitted to the solar thermal boiler system; the second part of the feed water is distributed to be part A and part B; the part A is transmitted to the solar thermal heater claim 1 , and the part B is transmitted to the auxiliary boiler; a second flow distributer is adapted to adjust a feed water flow ratio of part A to part B according to an intensity of solar energy; the second part of the feed water which enters the ...

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Номер записи: 15
02-02-2017 дата публикации

POWER GENERATION SYSTEM

Номер: US20170030264A1
Автор: CHEN Yilong, LIU Wenyan, TANG Hongming, ZHANG Yanfeng
Принадлежит:

A power generation system, including: a solar energy concentration system, a biomass gasification device, a gas-powered generator, a steam turbine, a steam-powered generator. The solar energy concentration system is connected to a solar energy heat exchange system. The biomass gasification device is connected to the gas-powered generator. The gas outlet of the gas turbine is connected to the gas exhaust heat system. The second steam outlet of the gas exhaust heat system is connected to the second and the third cylinders of the steam turbine. The first steam outlet of the gas exhaust heat system and the steam outlet of the solar energy heat exchange system are connected to a steam mixing regulating system. The mixed steam outlet of the steam mixing regulating system is connected to the first cylinder of the steam turbine. 2. The system of claim 1 , whereinthe steam mixing regulating system comprises a mixer housing; a steam ejection pipe is protruded from a rear end of the mixer housing into a middle-front part of a cavity of the mixer housing; a front end of the steam ejection pipe is sealed, steam nozzles are distributed on a front part of a pipe wall of the steam ejection pipe, and a first steam inlet for introducing in steam from the gas exhaust heat system is disposed at a rear end of the steam ejection pipe; a water ejection pipe is installed inside the first steam inlet in a rear part of the steam ejection pipe; water nozzles are distributed on a part of the water ejection pipe extended into the steam ejection pipe, and an inlet of the water ejection pipe is disposed at an end thereof outside the steam ejection pipe and connected to a solenoid valve;a second steam inlet for introducing in steam from the solar energy heat exchange system is disposed on an outer wall of a rear part of the mixer housing;a temperature detector is disposed on an outer wall of a front part of the mixer housing; a probe of the temperature detector is extended into the cavity of the ...

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Номер записи: 16
04-02-2016 дата публикации

COMBUSTOR AND GAS TURBINE

Номер: US20160032842A1
Автор: Isono Mitsunori, MIYAUCHI Kotaro, Saito Toshihiko
Принадлежит:

A combustor is provided with a plurality of fuel nozzles that extend in an axial direction of a combustor main body and are capable of injecting fuel from injection holes which are disposed on the combustion chamber side. The combustor is provided with a phase adjusting unit which partially changes the flow path cross-sectional area of at least one fuel nozzle in the axial direction such that phases of flow rate fluctuation of fuel do not match with respect to at least two fuel nozzles among the plurality of fuel nozzles. 1. A combustor comprising:a plurality of fuel nozzles which extend in an axial direction of a combustor main body and are capable of injecting fuel from injection holes which are disposed on the combustion chamber side, anda phase adjusting unit which partially changes a flow path cross-sectional area of at least one fuel nozzle in the axial direction such that phases of flow rate fluctuation of the fuel do not match with respect to at least two fuel nozzles among the plurality of fuel nozzles.2. The combustor according to claim 1 , whereineach of the plurality of fuel nozzles is provided with the phase adjusting unit, andthe phase adjusting units of the fuel nozzles adjacent to each other are disposed to be shifted away from each other in the axial direction.3. The combustor according to claim 1 , whereinthe plurality of fuel nozzles are disposed in a row, andthe phase adjusting units are provided every other fuel nozzle in an array direction in the plurality of fuel nozzles.4. The combustor according to claim 1 , whereinthe fuel nozzle which is provided with the phase adjusting unit has an injection hole having a size corresponding to the magnitude of pressure loss occurring due to the phase adjusting unit.5. The combustor according to claim 1 , whereinthe phase adjusting units make the phases of flow rate fluctuation of the fuel in the fuel nozzles adjacent to each other have opposite phases.6. The combustor according to claim 1 , whereinthe ...

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Номер записи: 17
04-02-2016 дата публикации

Magnetic Gas Engine and Method of Extracting Work

Номер: US20160032907A1
Автор: Muldoon Patrick Craig
Принадлежит:

The present subject matter overcomes the deficiencies in the prior art by introducing or generating charged particles in an air stream and manipulating the air stream with magnetic fields operating on the charged particles. Embodiments of the present subject mater compress the air stream by accelerating charged particles with a moving magnetic field, where the magnetic field has a velocity perpendicular to its flux lines. The increased velocity of the charged particles increases the statistical mean particle velocity and thereby increases the pressure in the air stream. The compressed air stream is then heated and expanded through a second magnetic field. The expansion of the air stream substantially increases the velocity of the air stream and the charged particles therein. The interaction of the high velocity charged particles and the magnetic field imparts a force perpendicular to the flux lines, this force powers the movement of the magnetic field. 1. A method for providing thrust to a craft across subsonic to supersonic regimes receiving an air stream through an inlet, said air stream having a velocity relative to the craft prior to being received in the inlet;', 'compressing the air stream to a static pressure at or below the stagnation pressure associated with the air stream by decelerating the air stream; and', 'compressing the air stream above the stagnation pressure by adding work to the stream via a magnetic or electric field when the relative air stream velocity is subsonic or less than a predetermined Mach number greater than one;', 'heating the air stream and expanding the heated air stream through a nozzle to provide thrust., 'comprising2. The method of claim 1 , wherein the step of compressing the air stream above the stagnation pressure comprises ionizing the air stream to a net charge.3. The method of claim 2 , wherein the step of compressing the air stream above the stagnation pressure comprises the steps of: providing a gas stream having a net ...

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Номер записи: 18
30-01-2020 дата публикации

SHROUDED BLADE ASSEMBLIES

Номер: US20200032669A1
Автор: Roberts Steven D.
Принадлежит: UNITED TECHNOLOGIES CORPORATION

A rotor system for a gas turbine engine may comprise a shrouded blade assembly. The shrouded blade assembly may include a blade configured to rotate about a central longitudinal axis of the gas turbine engine, an inner diameter shroud located at a proximal end of the blade, and a blade tip shroud located at a distal end of the blade. A radial seal assembly may be located radially outward of a distal surface of the blade tip shroud. 1. A rotor system for a gas turbine engine , comprising: a blade configured to rotate about a central longitudinal axis of the gas turbine engine;', 'an inner diameter shroud located at a proximal end of the blade; and', 'a blade tip shroud located at a distal end of the blade; and, 'a shrouded blade assembly comprisinga radial seal assembly located radially outward of a distal surface of the blade tip shroud.2. The rotor system of claim 1 , wherein the radial seal assembly comprises a non-contact radial seal.3. The rotor system of claim 2 , wherein the non-contact radial seal comprises a shoe and a housing supporting the shoe claim 2 , wherein the shoe is configured to translate towards the distal surface of the blade tip shroud in response to a pressure differential between a forward end of the shoe and an aft end of the shoe.4. The rotor system of claim 3 , wherein the non-contact radial seal is configured to maintain a predetermined clearance between a proximal edge of the shoe and the distal surface of the blade tip shroud.5. The rotor system of claim 4 , wherein the non-contact radial seal is configured such that at the predetermined clearance an equilibrium is established preventing the shoe from translating radially inward.6. The rotor system of claim 3 , further comprising a support structure located radially outward of the radial seal assembly claim 3 , wherein the housing is contacting the support structure.7. The rotor system of claim 1 , wherein an axial length of the blade tip shroud is greater than a chord of the blade.8. ...

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Номер записи: 19
19-02-2015 дата публикации

MULTI-PULSE GAS GENERATOR AND OPERATION METHOD THEREOF

Номер: US20150047316A1
Автор: IEKI Katsunori, MIHARA Chiyako, SUZUKI Tasuku
Принадлежит:

A multi-pulse gas generator includes a pressure vessel, an outer propellant arranged in the pressure vessel and which has a tubular shape, an intermediate propellant arranged inside the outer propellant and which has a tubular shape, an inner propellant arranged inside the intermediate propellant and which has a tubular shape, an internal structure arranged inside the inner propellant and fixed to the pressure vessel, a first barrier membrane arranged between the outer propellant and the intermediate propellant so as to isolate the outer propellant and the intermediate propellant from each other, and a second barrier membrane arranged between the intermediate propellant and the inner propellant so as to isolate the intermediate propellant and the inner propellant from each other. The outer propellant is supported on its outer surface by the pressure vessel. The inner propellant is supported on its inner surface by the internal structure. 1. A multi-pulse gas generator comprising:a pressure vessel;an outer propellant disposed in the pressure vessel and having a tubular shape;an intermediate propellant disposed inside the outer propellant and having a tubular shape;an inner propellant disposed inside the intermediate propellant and having a tubular shape;an internal structure disposed inside the inner propellant and fixed to the pressure vessel;a first barrier membrane disposed between the outer propellant and the intermediate propellant so as to isolate the outer propellant and the intermediate propellant from each other; anda second barrier membrane disposed between the intermediate propellant and the inner propellant so as to isolate the intermediate propellant and the inner propellant from each other,wherein said outer propellant is supported on its outer surface by the pressure vessel, andwherein said inner propellant is supported on its inner surface by the internal structure.2. The multi-pulse gas generator according to claim 1 , further comprising:a third ...

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Номер записи: 20
15-02-2018 дата публикации

SYSTEM AND METHOD FOR GENERATING ELECTRIC ENERGY

Номер: US20180045079A1
Автор: Erämaa Timo, Salminen Heikki J.
Принадлежит: Finno Energy Oy

An object of the present invention is to provide a method and a system for implementing the method so as to alleviate the disadvantages of a reciprocating combustion engine and gas turbine in electric energy production. The invention is based on the idea of arranging a combustion chamber outside a gas turbine and providing compressed air to the combustion chamber in order to carry out a combustion process supplemented with high pressure steam pulses. 1. An electric generator system havinga turbine in connection with a generator and a compressor for converting energy fed to the turbine into electric energy with the generator and for using the energy fed to the turbine to compress air with the compressor,a combustion chamber outside said turbine, wherein the combustion chamber is arranged to receive compressed air from the compressor and fuel from a fuel tank to initiate a combustion process and output combustion products into the turbine for rotating the rotor of the turbine, the combustion process within the combustion chamber being a cyclic combustion process, each cycle comprising a compression phase and an expansion phase,one or more controllable fuel input valves for providing fuel to the combustion chamber,one or more controllable air input valves for providing compressed air to the combustion chamber,wherein the combustion chamber comprises an open output which is not controlled by a closing valve.2. An electric generator system as claimed in claim 1 , wherein in that the compressor is a first screw compressor and the system further comprises a second screw compressor connected in series with the first screw compressor.3. An electric generator system as claimed in claim 1 , wherein the system further comprises an air tank for accumulating compressed air from the compressor and for providing the compressed air to the combustion chamber.4. An electric generator system as claimed in claim 1 , wherein the fuel used in the system is one of the following group: ...

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Номер записи: 21
19-02-2015 дата публикации

TURBINE HOUSING

Номер: US20150050131A1
Автор: COULOMBE Joseph Gerald Jimmie, SLOSS Clayton A.
Принадлежит: WESCAST INDUSTRIES, INC.

A turbocharger system may include a turbine housing and a tongue insert. The turbine housing may include an inlet, an outlet, and a gas pathway between the inlet and outlet. The gas pathway may include a volute portion and an inlet portion extending approximately tangent to the volute portion. The turbine housing may be formed from a first material. The tongue insert may be received in the turbine housing and may at least partially define the volute portion and the inlet portion. The tongue insert may be formed from a second material that is more heat resistant than the first material. 1. A turbocharger system comprising:a turbine housing including an inlet, an outlet, and a gas pathway between the inlet and the outlet, the gas pathway including a volute portion and an inlet portion extending approximately tangent to the volute portion, the turbine housing being formed from a first material; anda tongue insert received in a groove in the turbine housing and at least partially defining the volute portion and the inlet portion, the tongue insert being formed from a second material that is more heat resistant than the first material.2. The turbocharger system of claim 1 , wherein the tongue insert includes a depression defining a gap between the tongue insert and the inlet portion.3. The turbocharger system of claim 1 , wherein the groove includes a depression defining a gap between the tongue insert and the inlet portion.4. The turbocharger system of claim 1 , wherein the groove extends through an inlet interface defining the inlet of the turbine housing.5. The turbocharger system of claim 1 , wherein the groove includes an end stop locator that locates the tongue insert relative to the turbine housing.6. The turbocharger system of claim 1 , wherein the tongue insert engages the groove by a press fit.7. The turbocharger system of claim 1 , wherein the turbine housing includes a coolant passage formed therein.8. A turbocharger system comprising:a turbine housing ...

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Номер записи: 22
01-03-2018 дата публикации

SYSTEM AND METHOD FOR REDUCED TURBINE DEGRADATION BY CHEMICAL INJECTION

Номер: US20180058317A1
Автор: Davis, Ekanayake Sanji, JR. Lewis Berkley, Scipio Alston Ilford, Shaffer Jason Brian, WU Edwin
Принадлежит:

A gas turbine injection system having a gas turbine with an inlet section, a compressor section, at least one combustor in a combustion section, and a turbine section is disclosed. Air supply piping, water supply piping, and chemical reactant supply piping is in fluid communication with the injection system. A mixing chamber is in fluid communication with at least one of the water supply piping, air supply piping, and the chemical reactant supply piping to produce a chemical mixture. Chemical mixture supply piping is in fluid communication with the mixing chamber and at least one spray nozzle configured to selectively combine the chemical mixture with the air and inject an atomized chemical mixture into at least one section of the turbine. 1. A gas turbine injection system , comprising:a gas turbine having an inlet section, a compressor section, at least one combustor in a combustion section, and a turbine section;air supply piping in fluid communication with a supply of air and at least one spray nozzle;water supply piping in fluid communication with a supply of water;chemical reactant supply piping in fluid communication with the supply of a chemical reactant;a mixing chamber in fluid communication with the water supply piping and the chemical reactant supply piping, the mixing chamber configured to receive water from the water supply piping and the chemical reactant from the chemical reactant supply piping to produce a chemical mixture; andchemical mixture supply piping in fluid communication with the mixing chamber and the at least one spray nozzle, the at least one spray nozzle configured to selectively combine the chemical mixture with the air and inject an atomized chemical mixture into at least one section of the turbine.2. The injection system of claim 1 , further comprising a retractable manifold in fluid communication with at least one retractable spray nozzle claim 1 , the chemical mixture supply piping claim 1 , and the air supply piping.3. The ...

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Номер записи: 23
01-03-2018 дата публикации

GAS TURBINE ENGINE WITH COLD TURBINE AND MULTIPLE CORE FLOWPATHS

Номер: US20180058376A1
Автор: Kupratis Daniel Bernard, Moon Francis R., Utay Arthur W.
Принадлежит:

A gas turbine engine includes a spool configured to rotate about an axial centerline. The spool includes a fan rotor and a cold turbine rotor. The fan rotor is rotatably driven by the cold turbine rotor. A cold turbine inlet passage is configured to direct an airflow along a radial inward trajectory to the cold turbine rotor. 1. A gas turbine engine , comprising:a spool configured to rotate about an axial centerline, the spool comprising a fan rotor and a cold turbine rotor, and the fan rotor rotatably driven by the cold turbine rotor; anda cold turbine inlet passage configured to direct an airflow along a radial inward trajectory to the cold turbine rotor.2. The gas turbine engine of claim 1 , further comprising a cold turbine outlet passage claim 1 , wherein the cold turbine rotor is configured to:receive the airflow from the cold turbine inlet passage along the radial inward trajectory; anddirect the airflow into the cold turbine outlet passage along an axial trajectory.3. The gas turbine engine of claim 1 , further comprising an airflow regulator configured to regulate the airflow through the cold turbine rotor.4. The gas turbine engine of claim 3 , wherein the airflow regulator is configured downstream of the cold turbine rotor.5. The gas turbine engine of claim 3 , wherein the airflow regulator comprises a door.6. The gas turbine engine of claim 1 , further comprising:a second spool comprising a compressor rotor and a hot turbine rotor; anda combustor fluidly between the compressor rotor and the hot turbine rotor.7. The gas turbine engine of claim 6 , further comprising:a first flowpath extending through the cold turbine rotor;a second flowpath extending through the combustor and the hot turbine rotor; anda manifold configured to receive a compressed airflow from the compressor rotor, to direct a portion of the compressed airflow into the first flowpath as the airflow, and to direct another portion of the compressed airflow into the second flowpath as a second ...

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Номер записи: 24
17-03-2022 дата публикации

VACUUM PUMP

Номер: US20220082103A1
Автор: Kabasawa Takashi
Принадлежит:

Decane (C10H22) is sprayed as a mist from spray nozzles toward a rotor blade via a supply pipe and communication passages. Since decane has a boiling point of 174° C. at atmospheric pressure, the decane is a liquid at normal temperature and normal pressure. On the other hand, the pressure inside a turbomolecular pump is in a substantially vacuum state of about 100 Pa, and the boiling point of decane at this pressure is 14° C. Thus, although the pressure is high and the decane is in a liquid state until the decane is sprayed, when the decane adheres to surfaces of the rotor blades and the temperature of the decane rises, the decane vaporizes. At this moment, since the amount of heat of the rotor blades is consumed as heat of vaporization, the rotor blades can be cooled. 1. A vacuum pump , comprising:an outer cylinder;a rotor blade contained in the outer cylinder;a rotor shaft attached to the rotor blade;a magnetic bearing supporting the rotor shaft in a levitated manner in the air;a rotary drive means for driving the rotor shaft to rotate;a stator disposed between the rotor blade and the rotor shaft; andan injection port disposed on the stator so as to face at least either the rotor blade or the rotor shaft,wherein liquid is ejected from the injection port to cool at least either the rotor blade or the rotor shaft with the liquid.2. The vacuum pump according to claim 1 , further comprising:a supply port to which the liquid is supplied from the outside of the pump; anda communication passage connecting the supply port and the injection port.3. The vacuum pump according to claim 1 , wherein the liquid has vapor pressure characteristics in which the liquid is in the form of liquid when ejected from the injection port and becomes a gas on a surface of at least either the rotor blade or the rotor shaft.4. The vacuum pump according to claim 1 , further comprising:a temperature detecting means for detecting a temperature of at least either the rotor blade or the rotor shaft ...

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Номер записи: 25
27-02-2020 дата публикации

Turbomachinery

Номер: US20200063566A1
Автор: Ian M. BUNCE, Martin N. Goodhand
Принадлежит: Rolls Royce PLC

A turbomachine (105) configured to compress supercritical carbon dioxide is shown. The turbomachine comprises, in fluid flow series, an inlet (201), an inducerless radial impeller (202) having a plurality of blades, and a fully vaneless diffuser (203). The radius of the inlet (r0) is from 25 to 50 percent of the radius of the impeller (r2).

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Номер записи: 26
27-02-2020 дата публикации

TURBOMACHINERY

Номер: US20200063567A1
Автор: BUNCE Ian M., GOODHAND Martin N.
Принадлежит: ROLLS-ROYCE PLC

A turbomachine () configured to compress supercritical carbon dioxide is shown. The turbomachine comprises, in fluid flow series, an inlet (), an inducerless radial impeller () having a plurality of blades, and a fully vaneless diffuser (). The inlet is radially flared to induce a radial component in flow prior to an entry to the impeller. 1. A turbomachine configured to compress supercritical carbon dioxide , the turbomachine comprising , in fluid flow series:an inlet;an inducerless radial impeller having a plurality of blades; anda fully vaneless diffuser;wherein the inlet is radially flared to induce a radial component in flow prior to an entry to the impeller.2. The turbomachine of claim 1 , in which a hub hade angle of the impeller at the entry thereto (γ) is from 50 to 70 degrees.3. The turbomachine of claim 2 , in which said hade angle (γ) is 60 degrees.4. The turbomachine of claim 1 , in which each of the plurality of blades is a backswept blade.5. The turbomachine of claim 4 , in which each of the plurality of blades have a blade exit angle (χ) of from −50 to −70 degrees.6. The turbomachine of claim 5 , in which each of the plurality of blades have a blade exit angle (χ) of −60 degrees.7. The turbomachine of claim 1 , in which the plurality of blades comprises:a set of main blades; anda set of splitter blades.8. The turbomachine of claim 1 , in which a meridional chord length of the splitter blades (c) is 70 percent of a meridional chord length of the main blades (c).9. The turbomachine of claim 7 , in which the impeller comprises one splitter blade for each main blade.10. The turbomachine of claim 1 , in which the radius of the inlet (r) is from 25 to 50 percent of the radius of the impeller (r).11. The turbomachine of claim 10 , in which the radius of the inlet (r) is from 30 to 50 percent of the radius of the impeller (r).12. The turbomachine of claim 1 , in which the diffuser has an annulus height ratio (b/b) of 1.13. The turbomachine of claim 1 , in ...

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Номер записи: 27
27-02-2020 дата публикации

TURBOMACHINERY

Номер: US20200063568A1
Автор: BUNCE Ian M., GOODHAND Martin N.
Принадлежит: ROLLS-ROYCE PLC

A turbomachine () configured to compress supercritical carbon dioxide is shown. The turbomachine comprises, in fluid flow series, an inlet (), an inducerless radial impeller () having a plurality of backswept blades () each of which have a blade exit angle (χ) of from −50 to −70 degrees, and a fully vaneless diffuser (). 1. A turbomachine configured to compress supercritical carbon dioxide , the turbomachine comprising , in fluid flow series:an inlet;{'sub': '2', 'an inducerless radial impeller having a plurality of backswept blades each of which have a blade exit angle (χ) of from −50 to −70 degrees; and'}a fully vaneless diffuser.2. The turbomachine of claim 1 , in which the backswept blades have a blade exit angle (χ) of −60 degrees.3. The turbomachine of claim 1 , in which the inlet is radially flared to induce a radial component in flow prior to an entry to the impeller.4. The turbomachine of claim 3 , in which a hub hade angle of the impeller at the entry thereto (γ) is from 50 to 70 degrees.5. The turbomachine of claim 4 , in which said hade angle (γ) is 60 degrees.6. The turbomachine of claim 1 , in which each of the plurality of blades is a backswept blade.7. The turbomachine of claim 1 , in which the plurality of blades comprises:a set of main blades; anda set of splitter blades.8. The turbomachine of claim 7 , in which a meridional chord length of the splitter blades (c) is 70 percent of a meridional chord length of the main blades (c).9. The turbomachine of claim 7 , in which the impeller comprises one splitter blade for each main blade.10. The turbomachine of claim 1 , in which the radius of the inlet (r) is from 25 to 50 percent of the radius of the impeller (r).11. The turbomachine of claim 10 , in which the radius of the inlet (r) is from 30 to 50 percent of the radius of the impeller (r).12. The turbomachine of claim 1 , in which the diffuser has an annulus height ratio (b/b) of 1.13. The turbomachine of claim 1 , in which the radius of the diffuser ...

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Номер записи: 28
27-02-2020 дата публикации

Compressed gas and recycled liquid turbine power system

Номер: US20200063595A1
Автор: Michael Newgent
Принадлежит: Individual

The Compressed Gas and Recycled Liquid Turbine Power System (CGRLTPS) generates rotational energy by converting energy stored within compressed gas into rotational energy and can convert that rotational energy into electricity.

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Номер записи: 29
11-03-2021 дата публикации

Method for assembling a water pump

Номер: US20210071685A1
Автор: Ernesto Giovanni ARNOLDI, Paolo Lincoln Maurino
Принадлежит: Hanon Systems EFP Deutschland GmbH

Method to assemble a water pump with an impeller driven by an electrical machine comprising a housing cap and a volute with an inlet and an outlet and a boot hosting a stator and a rotor of the electrical machine and an electronic board mounted at the side apart from the impeller and covered by the cap housing, the boot having a radial extending rim comprising at least slots defined by the following steps: connecting the volute to the boot by inserting axial hooks in the boot's slots, twisting the volute versus the boot to fix the axial hooks, inserting radial hooks of the cap housing in the same slots.

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Номер записи: 30
19-03-2015 дата публикации

GAS TURBINE ENGINE SYSTEM THAT USES ORGANIC MEDIUM

Номер: US20150075133A1
Автор: Bohn Dieter, Braun Rene, Kusterer Karsten, MORISHITA Hiroshi, Sugimoto Takao, Tanaka Ryozo, TANIMURA Kazuhiko
Принадлежит: KAWASAKI JUKOGYO KABUSHIKI KAISHA

A gas turbine engine system is provided which achieves high efficiency while using sunlight as a heat source. In a gas turbine engine system including: a compressor configured to compress a first working medium; a heater configured to heat the compressed first working medium by an external heat source; a turbine configured to output power from the first working medium; and an intermediate cooler provided at the compressor and configured to cool the first working medium compressed by a low-pressure compression part of the compressor and supply the first working medium to a high-pressure compression part of the compressor, an organic Rankine cycle engine using, as a second working medium, an organic substance which is a cooling medium of the intermediate cooler is provided. 1. A gas turbine engine system comprising:a compressor configured to compress a first working medium;a heater configured to heat the compressed first working medium utilizing an external heat source;a turbine configured to output power from the first working medium;an intermediate cooler provided at the compressor and configured to cool the first working medium compressed by a low-pressure compression part of the compressor and supply the first working medium to a high-pressure compression part of the compressor; andan organic Rankine cycle engine using, as a second working medium, an organic substance which serves as a cooling medium of the intermediate cooler.2. The gas turbine engine system as claimed in claim 1 , further comprising:a heat exchanger provided on a discharge path for discharging the first working medium discharged from the turbine, the heat exchanger using, as a heating medium, the first working medium discharged from the turbine; andan organic Rankine cycle engine using, as a third working medium, an organic substance which serves as a heat receiving medium of the heat exchanger.3. The gas turbine engine system as claimed in comprising claim 1 , as the heater claim 1 , a solar ...

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Номер записи: 31
17-03-2016 дата публикации

AIR INLET ARRANGEMENT AND METHOD OF MAKING THE SAME

Номер: US20160076448A1
Автор: Conners Timothy R., Henne Preston A., Howe Donald C.
Принадлежит:

An inlet arrangement is disclosed herein for use with a supersonic jet engine configured to consume air at a predetermined mass flow rate when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed. The air inlet arrangement includes, but is not limited to, a cowl having a cowl lip and a center body coaxially aligned with the cowl. A protruding portion of the center body extends upstream of the cowl lip for a length greater than a conventional spike length. The protruding portion is configured to divert air flowing over the protruding portion out of a pathway of an inlet to the supersonic jet engine such that a remaining airflow approaching and entering the inlet matches the predetermined mass flow rate. 1. An air inlet arrangement for use with a supersonic jet engine configured to consume air at a predetermined mass flow rate when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed , the air inlet arrangement comprising:a cowl having a cowl lip; anda center body coaxially aligned with the cowl, the center body having an apex, a first compression surface downstream of the apex, and a second compression surface downstream of the first compression surface, the second compression surface being spaced apart from the cowl lip such that the second compression surface and the cowl lip define an inlet,wherein a protruding portion of the center body extends upstream of the cowl lip for a length greater than a conventional spike length and wherein the protruding portion of the center body is configured to divert a portion of a flow of air located in a path of the inlet out of the path of the inlet such that a remaining flow of air approaching and entering the inlet is not greater than the predetermined mass flow rate when the supersonic jet engine is operating at the predetermined power setting and moving at the predetermined Mach speed.2. The air inlet ...

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Номер записи: 32
16-03-2017 дата публикации

NOZZLE MODULE FOR AN ENERGY CONVERTER

Номер: US20170074108A1
Автор: BOSCHER Matthias
Принадлежит:

A nozzle module for an energy converter, in particular for a power plant, including a first nozzle for the introduction of a motive fluid into a mixing chamber and an introduction opening for the introduction of a suction fluid into the mixing chamber, the mixing chamber having a geometry for merging the motive fluid and the suction fluid in the mixing chamber in a flow-intensifying manner. To specify a nozzle module which effects an increase in efficiency of the power plant, a vapor pressure of the motive fluid upstream of the first nozzle is lower than a vapor pressure of the suction fluid upstream of the introduction opening, and a gas pressure in the mixing chamber in a region downstream of the first nozzle is lower than a gas pressure in the mixing chamber in a region downstream of the introduction opening. 1123433324362374: A nozzle module () for an energy converter , comprising a first nozzle () for the introduction of a motive fluid into a mixing chamber () and comprising an introduction opening () for the introduction of a suction fluid into the mixing chamber () , the mixing chamber () having a geometry for merging the motive fluid and the suction fluid in the mixing chamber () in a flow-intensifying manner , wherein a vapor pressure of the motive fluid upstream of the first nozzle () is lower than a vapor pressure of the suction fluid upstream of the introduction opening () , and a gas pressure in the mixing chamber () in a region () downstream of the first nozzle () is lower than a gas pressure in the mixing chamber () in a region () downstream of the introduction opening ().213517: The nozzle module () as claimed in claim 1 , wherein the mixing chamber () is in the form of a receiving nozzle () for the joint discharge of the motive fluid and of the suction fluid to a turbine ().3143: The nozzle module () as claimed in claim 1 , wherein the introduction opening () is in the form of a second nozzle claim 1 , the second nozzle being designed to evaporate ...

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Номер записи: 33
14-03-2019 дата публикации

SPRAY NOZZLE

Номер: US20190078784A1
Автор: BACHAROUDIS Evangelos, HUANG Hua Wei, MULDAL Carl L, ROMAN CASADO Juan Carlos, TENTORIO Luca
Принадлежит: ROLLS-ROYCE PLC

A fuel spray nozzle, for atomising liquid fuel in gas, including: an gas passage; a liquid fuel passage; a swirler provided in the gas passage and including vanes such that, when gas passes through the gas passage, the swirler produces a jet flow of gas from between adjacent vanes and a turbulent flow of gas in the wake of each vane; a prefilming surface for receiving liquid fuel from the liquid fuel passage, and gas from the gas passage, wherein the prefilming surface includes areas that receive jet flow of gas from the gas passage, in use; wherein the fuel spray nozzle is configured to direct the liquid fuel passing through the liquid fuel passage to the areas on the prefilming surface that receive a jet flow of gas from the gas passage. 1. A fuel spray nozzle , for atomising liquid fuel in a gas , comprising:a gas passage;a liquid fuel passage;a swirler provided in the gas passage and comprising vanes such that, when gas passes through the gas passage, the swirler produces a jet flow of gas from between adjacent vanes and a turbulent flow of gas in the wake of each vane;a prefilming surface configured to receive liquid fuel from the liquid fuel passage, and to receive gas from the gas passage, wherein the prefilming surface comprises areas that, in use, receive jet flow of gas from the gas passage;wherein the fuel spray nozzle is configured to direct the bulk of the liquid fuel passing through the liquid fuel passage to the areas on the prefilming surface that receive a jet flow of gas from the gas passage.2. A fuel spray nozzle according to claim 1 , further comprising apertures for supplying liquid fuel to the liquid fuel passage.3. A fuel spray nozzle according to claim 2 , wherein the apertures are configured to direct liquid fuel through the liquid fuel passage to the areas on the prefilming surface that receive a jet flow of gas from the gas passage.4. A fuel spray nozzle according to claim 2 , wherein the number of apertures is the same as the number of ...

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Номер записи: 34
24-03-2016 дата публикации

TURBINE ENGINE DIFFUSER ASSEMBLY WITH AIRFLOW MIXER

Номер: US20160084502A1
Автор: Cunha Frank J., Kostka Stanislav
Принадлежит:

A diffuser assembly is provided for a turbine engine. This diffuser assembly includes a. diffuser module with a combustor plenum and a mixing chamber. The diffuser module is configured to receive first and second airflows into the mixing chamber and direct a mixed airflow out of the mixing chamber. The diffuser module includes a mixer configured to mix the first and the second airflows together within the mixing chamber to provide the mixed airflow. 1. A diffuser assembly for a turbine engine , the assembly comprising:a diffuser module with a combustor plenum and a mixing chamber;the diffuser module configured to receive first and second airflows into the mixing chamber and direct a mixed airflow out of the mixing chamber; andthe diffuser module including a mixer configured to mix the first and the second airflows together within the mixing chamber to provide the mixed airflow.2. The assembly of claim 1 , further comprising a hollow strut extending across an inlet passage of the diffuser module which inlet passage leads to the combustor plenum claim 1 , wherein the hollow strut is configured to receive at least a portion of the mixed airflow from the mixing chamber.3. The assembly of claim 2 , further comprising an inlet through which at least a portion of the first airflow is directed into the mixing chamber claim 2 , wherein the mixer is configured to obstruct a direct path between the inlet and the hollow strut.4. The assembly of claim 2 , further comprising an inlet through which at least a portion of the first airflow is directed into the mixing chamber claim 2 , wherein the inlet is substantially circumferentially aligned with the hollow strut.5. The assembly of claim 1 , wherein the mixer is configured to diffuse the first airflow into the mixing chamber.6. The assembly of claim 1 , further comprising an inlet through which at least a portion of the first airflow is directed into the mixing chamber claim 1 , wherein the mixer comprises a mixing device located ...

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Номер записи: 35
23-03-2017 дата публикации

TURBO PUMP

Номер: US20170081971A1
Автор: KAKUTA Tomoya, MIHARA Rei
Принадлежит: IHI CORPORATION

A turbo pump includes: an impeller which pressurizes liquid, a turbine disk at which a blade cascade is provided; a shaft which connects the impeller and the turbine disk; a bearing which rotatably supports the shaft, and a housing which accommodates the impeller, the turbine disk, the shaft, and the bearing; a seal part which is provided between the bearing and the turbine disk; a slinger which is disposed between the bearing and the seal part and has a disk which is fixed to the shaft, and a plurality of wing parts which are provided on the seal part side of the disk; and a partition wall which partitions the inside of the housing into a pressure reduction chamber in which the wing parts of the slinger are disposed, and a bearing accommodation chamber in which the bearing is accommodated, the pressure reduction chamber and the bearing accommodation chamber being connected to each other through a clearance flow path. 1. A turbo pump comprising:an impeller which pressurizes liquid;a turbine disk at which a blade cascade is provided;a shaft which connects the impeller and the turbine disk;a bearing which rotatably supports the shaft;a housing which accommodates the impeller, the turbine disk, the shaft, and the bearing;a seal part which is provided between the bearing and the turbine disk;a slinger which is disposed between the bearing and the seal part and has a disk which is fixed to the shaft, and a plurality of wing parts which are provided on the seal part side of the disk; anda partition wall which partitions the inside of the housing into a pressure reduction chamber in which the wing parts of the slinger are disposed, and a bearing accommodation chamber in which the bearing is accommodated, the pressure reduction chamber and the bearing accommodation chamber being connected to each other through a clearance flow path.2. The turbo pump according to claim 1 , wherein the pressure reduction chamber is provided to extend further to the outside in a radial ...

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Номер записи: 36
23-03-2017 дата публикации

Engine, Biomass Powder Energy Conversion and/or Generation System, Hybrid Engines Including the Same, and Methods of Making and Using the Same

Номер: US20170082022A1
Автор: LEE Brent
Принадлежит:

An engine, a biomass powder energy conversion and/or generation system, hybrid turbine engines, and methods of manufacturing and using the same are disclosed. The engine includes a housing having an inner wall and an outer wall, a central rotary shaft extending from the housing, at least one fuel and air supply channel having a first portion extending radially from the rotary shaft and a second portion in fluidic communication with first portion of the fuel and air supply channel, at least two propulsion vessels, each propulsion vessel connected to the at least one of the fuel and air supply channel and configured to burn or detonate the fuel and rotate around the central rotary shaft; and at least one exhaust duct extending from the housing. 1. An engine , comprising:a) a housing having an inner wall and an outer wall;b) a central rotary shaft extending from said housing;c) at least one fuel and air supply channel having a first portion extending radially from said rotary shaft and a second portion in fluidic communication with first portion of said fuel and air supply channel;d) at least two propulsion vessels, each propulsion vessel connected to said at least one of said fuel and air supply channel and configured to burn or detonate said fuel and rotate around said central rotary shaft; ande) at least one exhaust duct extending from said housing.2. The engine of claim 1 , wherein said housing further comprises an insulation layer on said outer wall.3. The engine of claim 1 , wherein said engine further comprises a generator configured to receive rotational force or mechanical energy from said central rotary shaft.4. The engine of claim 1 , wherein said fuel and air supply channel comprises at least two conduits or paths claim 1 , said at least two conduits or paths having a first conduit or path for said fuel supply and a second conduit or path for said air supply.5. The engine of claim 1 , wherein each of said propulsion vessels further comprise an igniter claim ...

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Номер записи: 37
31-03-2016 дата публикации

DIFFUSER CASE STRUT FOR A TURBINE ENGINE

Номер: US20160090914A1
Автор: Lyons Christopher B.
Принадлежит:

An inner diffuser case for a turbine engine includes a fore gas path edge and an aft gas path edge defining a strut, wherein each of the fore gas path edge and the aft gas path edge include a gas path opening, a support cone structure extending radially outward from the strut, wherein the support cone structure is operable to structurally connect the strut to a turbine engine case, a diffuser case skirt structure extending radially inward from the strut, wherein the diffuser case skirt structure is operable to structurally connect the diffuser case strut to an inner support structure of the turbine engine, and at least one direct feed air passage passing radially through the strut including a radially outward upper mixing chamber opening and a radially inward direct air feed opening, the direct air feed opening is connected to a direct air feed. 1. A turbine engine comprising:a compressor section having a first compressor portion and a second compressor portion, wherein the second compressor portion is a high pressure compressor relative to the first compressor portion;a combustor in fluid communication with the compressor section;a turbine section in fluid communication with the combustor;a gas path passing through each of said compressor section, said combustor, and said turbine section;the second compressor portion further including an exit guide vane at an aftmost edge, relative to gas flow through the gas path, of the second compressor portion; andan inner diffuser case including a diffuser case strut positioned in said gas path aft of said exit guide vane, wherein said diffuser case strut includes at least a first direct feed passage connected on a first end to a cooled air system and on a second end to a direct air feed, wherein said direct air feed delivers air to at least one of a compressor rim and an aftmost compressor stage of said second compressor portion.2. The turbine engine of claim 1 , wherein said diffuser case strut further comprises a second ...

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Номер записи: 38
21-03-2019 дата публикации

FUEL CELL SYSTEM AND METHOD FOR CONTROLLING FUEL CELL SYSTEM

Номер: US20190088962A1
Автор: Chikugo Hayato, Tomita Yousuke
Принадлежит: NISSAN MOTOR CO., LTD.

A fuel cell system includes a fuel cell configured to be supplied with an anode gas and a cathode gas and generate electric power, a compressor configured to supply the cathode gas to the fuel cell, a turbine configured to be supplied with a cathode discharged gas discharged from the fuel cell and generate power, an electric motor connected to the compressor and the turbine and configured to perform power running and regeneration, a combustor disposed between the fuel cell and the turbine and configured to mix and combust the cathode gas and the anode gas, a cooler configured to cool the cathode gas that is supplied from the compressor to the fuel cell, a bypass passage configured to supply the cathode gas from an upstream side of the cooler to the combustor by bypassing the cooler and the fuel cell, and a bypass valve disposed in the bypass passage. 18.-. (canceled)9. A fuel cell system comprising:a fuel cell configured to be supplied with an anode gas and a cathode gas and generate electric power;a compressor configured to supply the cathode gas to the fuel cell;a turbine configured to be supplied with a cathode discharged gas discharged from the fuel cell and generate power;an electric motor connected to the compressor and the turbine and configured to perform power running and regeneration;a combustor disposed between the fuel cell and the turbine and configured to mix and combust the cathode gas and the anode gas;a cooler configured to cool the cathode gas that is supplied from the compressor to the fuel cell;a bypass passage configured to supply the cathode gas from an upstream side of the cooler to the combustor by bypassing the cooler and the fuel cell;a bypass valve disposed in the bypass passage; anda control unit configured to control the bypass valve based on a system required output,wherein the control unit is configured to, when the system required output is equal to or greater than a predetermined output, increase an opening degree of the bypass valve ...

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Номер записи: 39
01-04-2021 дата публикации

COMBINED CYCLE PLANT AND METHOD FOR OPERATING SAME

Номер: US20210095572A1
Автор: FUJIMURA Daiki
Принадлежит:

In a combined cycle plant and a method for operating the same, the combined cycle plant is provided with a gas turbine, a waste heat recovery boiler, and a steam turbine, and is also provided with a low-pressure gland steam line for supplying steam to a low-pressure gland portion of a low-pressure turbine, and a first heat exchanging unit which performs heat exchange between gland steam flowing through the low-pressure gland steam line, and fuel gas to be supplied to a combustor. 1. A combined cycle plant comprising:a gas turbine including a compressor, a combustor, and a turbine;a heat recovery steam generator that uses waste heat of flue gas from the gas turbine to generate steam;a steam turbine including a high-pressure turbine and a low-pressure turbine that are driven by the steam generated by the heat recovery steam generator;a low-pressure gland steam line that supplies the steam to a low-pressure gland portion of the low-pressure turbine; anda first heat exchange part that performs heat exchange between the steam flowing through the low-pressure gland steam line and fuel gas to be supplied to the combustor.2. The combined cycle plant according to claim 1 ,wherein a second heat exchange part that performs heat exchange between water heated by the heat recovery steam generator and the fuel gas is provided, and the first heat exchange part performs heat exchange between the fuel gas having exchanged heat with the water in the second heat exchange part and the steam flowing through the low-pressure gland steam line.3. The combined cycle plant according to claim 2 ,wherein a third heat exchange part that performs heat exchange between the water subjected to heat exchange in the second heat exchange part and the steam flowing through the low-pressure gland steam line is provided.4. The combined cycle plant according to claim 1 ,wherein a third heat exchange part that performs heat exchange between water heated by the heat recovery steam generator and the steam ...

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Номер записи: 40
12-05-2022 дата публикации

Air circulator

Номер: US20220146143A1
Автор: Hideki Yamamoto, Hiroshi Ishikawa, Kazuhito Fukumasu
Принадлежит: Iris Ohyama Inc

An air circulator includes a blower unit that is provided with an airflow opening on a front side of the blower unit. A grill is provided in the airflow opening, and is provided with airflow guide blades in a spiral manner Each of the airflow guide blades is convex toward an airflow direction between its inner end portion and its outer end portion to form the grill three-dimensionally. The grill further includes a circular ring that intersects with the airflow guide blades.

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Номер записи: 41
06-04-2017 дата публикации

LIQUID CRYOGEN VAPORIZER METHOD AND SYSTEM

Номер: US20170098977A1
Автор: CARISTAN Charles L.
Принадлежит: AIR LIQUIDE INDUSTRIAL U.S. LLP

Liquid cryogen from a tank having a head space pressure P1 is vaporized with a pressure building vaporizer to gaseous cryogen and the pressure of the gaseous cryogen is built to a pressure P2. The pressurized gaseous cryogen at pressure P2 is expanded across an expander to decrease its pressure and fed to a point of use at an installation including the vaporizer at a pressure P3. P2≧2×P3. Energy from the expanded gas may be recovered in the form of mechanical energy, electrical energy. 1. A method for vaporizing liquid cryogen to supply a flow of gaseous cryogen , said method comprising the steps of:feeding a liquid cryogen from a storage tank to at least one pressure building vaporizer located at an installation, the storage tank having a headspace pressure P1;exchanging heat between the fed liquid cryogen and a relatively warmer fluid across said at least one vaporizer to produce pressurized gaseous cryogen at pressure P2 exceeding P1;feeding the pressurized gaseous cryogen from said at least one vaporizer to an expander located at the installation to expand the gaseous cryogen to a pressure P3;feeding the expanded gaseous cryogen into a supply conduit;feeding the expanded gaseous cryogen from the supply conduit to a point of use located at the installation, wherein P2≧2×P3.2. The method of claim 1 , wherein the fluid is ambient air.3. The method of claim 1 , wherein the fluid is water.4. The method of claim 1 , wherein P2≧2×P1.5. The method of claim 1 , further comprising the steps of powering a gas turbine with the expander and converting the gas turbine power to electricity using an alternator.6. The method of claim 1 , wherein:said at least one pressure building vaporizer comprises n pressure building vaporizers operated in an alternating sequence where n is an integer greater than 1;as the liquid cryogen is being fed to a first of the n vaporizers, no liquid cryogen is being fed to a second of the n vaporizerssimultaneous with feeding the liquid cryogen to ...

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Номер записи: 42
23-04-2015 дата публикации

Coupling of a Turbopump For Molten Salts

Номер: US20150107245A1
Автор: Dethier Alfred
Принадлежит:

The invention relates to a device comprising at least one vertical pump () and at least one associated turbine () for transporting, over a level difference, a heat-transfer fluid brought to a high temperature, wherein the device further comprises a device for mechanically coupling the turbine () with the pump (), comprising a gearbox () with a gimbal coupling () located on the turbine () side, allowing the mechanical energy produced by the turbine () to be reused to actuate the pump (). 13431724175432141443. A device comprising at least one vertical pump () and at least one associated turbine () for transporting , over a level difference , a heat-transfer fluid brought to a high temperature , the pump () ensuring an upward movement of said fluid in a first section of a pipe () from a first so-called cold reservoir () and the turbine () being actuated by said fluid during the downward return movement of said fluid in a second section of the pipe () toward a second so-called hot reservoir () , wherein the device further comprises a mechanical device for coupling the turbine () with the pump () , said mechanical coupling device comprising a gearbox () with a gimbal coupling () located on the turbine () side , allowing the mechanical energy produced by the turbine () to be reused to actuate the pump ().243. The device according to claim 1 , wherein the turbine () is of the same type as the pump () claim 1 , but is used in the opposite direction.334. The device according to claim 2 , wherein the pump () or the turbine () is of the type with a vertical axis claim 2 , and is mono- or multi-staged claim 2 , (multi)cellular and has wheels with closed or semi-open radial vanes.434. The device according to claim 3 , wherein the pump () or the turbine () is situated above the reservoir or has an immersed body.534. The device according to claim 1 , wherein the pump () and the turbine () are designed to operate with a mixture of molten salts selected from the group consisting of ...

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Номер записи: 43
23-04-2015 дата публикации

HYDRAULIC BLOCKER DOOR DEPLOYMENT SYSTEMS

Номер: US20150108249A1
Автор: James Norman John
Принадлежит: Rohr, Inc.

A hydraulic circuit for a jet engine thrust reverser is disclosed. The hydraulic circuit may comprise a primary hydraulic actuator cylinder assembly and a secondary hydraulic actuator cylinder assembly. The primary hydraulic actuator cylinder assembly may be hydraulically coupled to the secondary hydraulic actuator cylinder assembly, in a master-slave relationship, and the secondary hydraulic actuator cylinder assembly may drive a thrust reverser blocker door. The primary hydraulic actuator cylinder assembly may comprise a rod, and the rod may comprise a channel through which hydraulic fluid is capable of flowing. The hydraulic circuit may further comprise a group of secondary hydraulic actuator cylinder assemblies, wherein the group of secondary hydraulic actuator cylinder assemblies may be coupled to the primary hydraulic actuator cylinder assembly. 1. A hydraulic circuit for a jet engine thrust reverser comprising:a primary hydraulic actuator cylinder assembly; and wherein the primary hydraulic actuator cylinder assembly is hydraulically coupled to actuate the secondary hydraulic actuator cylinder assembly, and', 'wherein the secondary hydraulic actuator cylinder assembly drives a thrust reverser blocker door., 'a secondary hydraulic actuator cylinder assembly,'}2. The hydraulic circuit of claim 1 , wherein the primary hydraulic actuator cylinder assembly comprises a piston and a rod claim 1 , and wherein the piston and the rod help define a channel through which hydraulic fluid is capable of flowing from the rod-end surface of the piston claim 1 , through the piston claim 1 , and through the rod to exit the primary hydraulic actuator cylinder assembly and actuate the secondary hydraulic actuator cylinder assembly.3. The hydraulic circuit of claim 1 , further comprising a group of secondary hydraulic actuator cylinder assemblies claim 1 , wherein the group of secondary hydraulic actuator cylinder assemblies are coupled to the primary hydraulic actuator cylinder ...

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Номер записи: 44
13-04-2017 дата публикации

GROUND-PROJECTILE SYSTEM

Номер: US20170101884A1
Автор: Harris Gordon L., Harris Stephen L.
Принадлежит:

A Projectile Continuous Power Module (PCMP) is configured to take incoming or oncoming airflow of an inflight projectile and direct the airflow to a turbine for converting the airflow into electrical power. The PCMP is mounted within or otherwise coupled to an airframe of the projectile. The PCMP is coupled to the projectile in a manner such that an air inlet of the projectile is positioned to capture incoming or oncoming boundary layer airflow as the projectile travels. 1. A power system for a ground-launched projectile , comprising:a ground-launch projectile, the projectile having an outer housing that defines an outer surface, wherein the projectile lacks a battery;a rotatable turbine that rotates about an axis, the turbine having a plurality of blades that radiate outward from a central hub;a power generator inside the turbine, wherein the turbine is attached to the power generator such that the power generator generates power upon rotation of the turbine;an annular bearing that surrounds the power generator, the annular bearing being aligned about the axis;an air inlet in the outer surface of the outer housing, wherein the air inlet directs airflow toward the turbine when the projectile is in flight and wherein the airflow causes the turbine to rotate about the axis; andan air outlet in the outer surface of the outer housing, wherein the air outlet directs exhaust airflow from the turbine out of the outer housing along a direction that is 90 degrees relative to a direction of flight of the projectile.2. The power system of claim 1 , further comprising a turbine housing that contains the turbine claim 1 , the power generator and the annular bearing.3. The power system of claim 1 , wherein the air inlet is flush with the outer housing.4. The power system of claim 1 , wherein the turbine is attached to a drive shaft of the generator and wherein the turbine rotates the drive shaft upon rotation of the turbine.5. The power system of claim 2 , wherein the turbine ...

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Номер записи: 45
08-04-2021 дата публикации

CHILLED INTAKE AIR FOR INCREASED POWER GENERATION

Номер: US20210102531A1
Автор: Bodishbaugh Adrian Benjamin, Murtland Carrie
Принадлежит: Typhon Technology Solutions, LLC

A mobile source of electricity is converted from a transportation mode to an operational mode. A turbine disposed on the mobile source of electricity is operated to generate electricity in the operational mode. A first control valve is operated to feed a cooling agent from a cooling agent source into a heat transfer apparatus disposed in an air intake flow path of the turbine to cool intake air. A second control valve is operated to vent from the heat transfer apparatus, the cooling agent that is heated by absorbing heat from the intake air flowing through the air intake flow path. A controller controls the first and second control valves to maintain the cooling agent having predetermined properties in the heat transfer apparatus. 1. A method comprising:converting a mobile source of electricity to an operational mode;generating electricity in the operational mode by operating a turbine disposed on the mobile source of electricity; andcooling intake air to the turbine by feeding a cooling agent into a heat transfer apparatus disposed in an air intake flow path of the intake air to the turbine.2. The method according to claim 1 , wherein feeding the cooling agent into the heat transfer apparatus comprises:feeding the cooling agent from a cooling agent source into the heat transfer apparatus by operating a first control valve;venting the cooling agent, heated by absorbing heat from the intake air flowing through the air intake flow path, from the heat transfer apparatus by operating a second control valve; andmaintaining predetermined properties of the cooling agent in the heat transfer apparatus by controlling the first and second control valves.3. The method according to claim 2 , further comprising:receiving sensor data from a plurality of sensors indicating one or more of: (i) an ambient air temperature at an upstream end of the air intake flow path, (ii) an elevation of the mobile source of electricity, (iii) a pressure level of the cooling agent that is in the ...

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Номер записи: 46
02-06-2022 дата публикации

Linear compressor

Номер: US20220170450A1
Автор: Kiwon NOH, Sungchul Gong
Принадлежит: LG ELECTRONICS INC

A linear compressor includes a frame, a cylinder disposed in the frame, a piston disposed in the cylinder and configured to reciprocate relative to the cylinder along an axis of the cylinder, a discharge valve disposed forward relative to the piston, and a discharge cover assembly coupled to the frame and disposed forward relative to the piston. The discharge cover assembly includes a discharge cover forming an inner space, a first discharge plenum disposed in the discharge cover and configured to partition the inner space into a plurality of discharge spaces, and a second discharge plenum disposed forward relative to the first discharge plenum and being in close contact with an inner surface of the discharge cover.

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Номер записи: 47
21-04-2016 дата публикации

DUAL MODE CHEMICAL ROCKET ENGINE, AND DUAL MODE PROPULSION SYSTEM COMPRISING THE ROCKET ENGINE

Номер: US20160108855A1
Автор: Anflo Kjell, Bergman Göran
Принадлежит:

The invention relates generally to dual mode bipropellant chemical rocket propulsion systems to be used in aerospace applications for 1) orbit raising, orbit manoeuvres and maintenance, attitude control and deorbiting of spacecraft, and/or 2) propellant settling, attitude and roll control of missiles, launchers and space planes. The present invention also relates to a dual mode chemical rocket engine for use in such systems. The engine uses low-hazardous storable liquid propellants and can be operated either in monopropellant mode or in bipropellant mode. The monopropellants used are a low-hazard liquid fuel-rich monopropellant, and hydrogen peroxide, respectively. 1100140150125. A dual mode chemical rocket engine () having a primary reaction chamber () for hydrogen peroxide comprising a catalyst bed for hydrogen peroxide , which primary reaction chamber is connected to a secondary reaction chamber () having means for injection () therein of a fuel-rich monopropellant , characterized in that the fuel-rich monopropellant is a liquid ADN based , or HAN based monopropellant.2125121150. The dual mode chemical rocket engine of claim 1 , wherein the means for injection () is configured to enable injection of the fuel-rich monopropellant from a propellant feed line () from outside into the secondary reaction chamber ().31150135. The dual mode chemical rocket engine of claim 1 , additionally comprising in the secondary reaction chamber () a high temperature resistant catalytic device ().4150. The dual mode chemical rocket engine of claim 1 , wherein the secondary reaction chamber () is fabricated from rhenium.5100. A dual mode propulsion system comprising the dual mode chemical rocket engine () of .6. The dual mode propulsion system of claim 5 , comprising a liquid storable low-hazard fuel-rich monopropellant based on ADN or HAN claim 5 , and hydrogen peroxide.740. The dual mode propulsion system of claim 5 , comprising monopropellant rocket engines () and a liquid storable ...

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Номер записи: 48
21-04-2016 дата публикации

TWO-PHASE EXPANSION DEVICE CAPABLE OF MAXIMIZING THE AMOUNT OF MOVEMENT PRODUCED BY A TWO-PHASE FLOW

Номер: US20160108899A1
Автор: Favy Claude
Принадлежит:

A two-phase expansion device () capable of maximizing the amount of movement produced by a two-phase flow. The two-phase expansion device () includes at least: one dispenser () for dispensing the fluid to a plurality of two-phase expansion nozzles (); a plurality of adjacent two-phase expansion nozzles () with substantially parallel axes, each two-phase expansion nozzle () including sequentially at least one diffuser (), one neck (), and one tube (), the two-phase expansion nozzles () being arranged to each receive a portion of the flow from the hot source; and elements for supporting the plurality of two-phase expansion nozzles () and including elements for sealably separating the two-phase expansion nozzles (). 118-. (canceled)19. A device for two-phase expansion capable of maximizing the momentum produced by a two-phase flow originating from the expansion of a significant saturation flow rate of a fluid originating from a so-called hot source , the device for two-phase expansion comprising at least:one distributor making it possible to distribute said fluid originating from said hot source to a plurality of nozzles for two-phase expansion;said plurality of adjacent nozzles for two-phase expansion with substantially parallel axes, each nozzle for two-phase expansion comprising successively at least one converging portion, one neck and one tube and said nozzles for two-phase expansion being arranged so that each receives a portion of said flow originating from said hot source;means making it possible to hold said plurality of nozzles for two-phase expansion in place and comprising impervious separating means between said nozzles for two-phase expansion.20. The device according to claim 19 , wherein said neck of said at least one nozzle for two-phase expansion is designed to produce a liquid jet.21. The device according to claim 20 , wherein said neck is of circular or square shape.22. The device according to claim 19 , wherein said neck of said at least one nozzle ...

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Номер записи: 49
20-04-2017 дата публикации

BYPASS VALVE ASSEMBLY FOR TURBINE GENERATORS

Номер: US20170107844A1
Автор: JR. Mark Jeffrey, Koonce Andrew, Monty Matthew, Passino, Satzman Roy, Werther Dominick
Принадлежит: Turbo Parts, LLC

A bypass valve assembly for use in turbine generators includes a valve body defining a central bore and a plurality of passageways. Each passageway has a smaller area at an inlet portion and a larger area at an outlet portion to define a flared passageway. A plurality of bypass valves is disposed within the plurality of passageways within the valve body. Each bypass valve includes a base portion and a nose portion, with each nose portion defining a predefined contoured surface area. At least a portion of the contoured surface area includes a wear coating disposed thereon. Optionally, the wear coating includes a plasma enhanced magnetron sputtering nanocoating. 1. A bypass valve assembly for use in turbine generators comprising:a valve body defining a central bore and a plurality of passageways, each passageway having a smaller area at an inlet portion and a larger area at an outlet portion to define a flared passageway;a plurality of bypass seats disposed within each of the inlet portions of the passageways, the bypass seats being formed of a material having higher wear resistance than the valve body;a valve stem disposed within the central bore of the valve body;a valve cap secured to a distal end portion of the valve body;a bypass valve disc secured to a distal end portion of the valve stem;a plurality of bypass valves disposed within the plurality of passageways within the valve body, each bypass valve having a base portion and a nose portion, each nose portion defining a predefined contoured surface area, and at least a portion of the contoured surface area having a wear coating disposed thereon; anda pressure seal head disposed around a distal end portion of the valve stem, the pressure seal head defining proximal facing steps having a wear coating disposed thereon.2. The bypass valve assembly according to further comprising:at least one socket bolt securing the valve cap to the valve body; anda cap pin disposed under a head of the socket bolt and extending ...

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Номер записи: 50
29-04-2021 дата публикации

THERMAL BARRIER COATING FILM AND TURBINE MEMBER

Номер: US20210123124A1
Автор: Horie Shigenari, KUDO Daisuke, Mega Masahiko, Okajima Yoshifumi, TANIGAWA Shuji, Torigoe Taiji
Принадлежит:

The task is to provide a thermal barrier coating film () which exhibits high durability even in a gas turbine that is used under a molten salt environment, such as a heavy oil fired gas turbine, and which can be efficiently formed at low cost without requiring complicated processes, and a thermal barrier coating film () configures a turbine member includes a ceramic material thermally sprayed and formed on a base material () made of a heat resistant alloy, in which ytterbia partially stabilized zirconia is used as the ceramic material of the film (), and the porosity of the film () is 5% or more and less than 8%. 1. A thermal barrier coating film including a ceramic material thermally sprayed and formed on a base material made of a heat resistant alloy constituting a turbine member in a heavy oil fired gas turbine engine using low-quality fuel ,wherein ytterbia partially stabilized zirconia is used as the ceramic material of the film, and a porosity of the thermal barrier coating film is 5% or more and less than 8%.2. The thermal barrier coating film according to claim 1 , wherein the porosity is in a range of 5% to 6%.3. The thermal barrier coating film according to claim 1 , wherein the thermal barrier coating film in which thermal spray powder which has a particle size distribution in which a 10% particle diameter in a cumulative particle size distribution is 30 μm or more and 100 μm or less claim 1 , is used as ceramic spray powder for film formation claim 1 ,the thermal spray powder has a maximum particle diameter of 150 μm or less, andthe thermal spray powder contains particles having a particle diameter of 30 μm at a ratio of 3% or less and particles having a particle diameter of 40 μm at a ratio of 8% or less.4. A turbine member comprising:{'claim-ref': {'@idref': 'CLM-00001', 'claim 1'}, 'the thermal barrier coating film according to formed on a base material.'}5. The turbine member according to claim 4 , wherein the thermal barrier coating film is formed ...

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Номер записи: 51
02-04-2020 дата публикации

Centrifugal compressor

Номер: US20200102964A1
Автор: Kaho TAKEUCHI, Ryo Umeyama, Ryosuke FUKUYAMA, Satoru Mitsuda, Takahito Kunieda, Yoshiyuki Nakane
Принадлежит: Toyota Industries Corp

A centrifugal compressor includes a low-speed shaft, an impeller, a speed increaser, a housing, a separation wall, a shaft insertion hole, a seal member, an oil pan, an oil supply passage, an oil return passage, and a pressure reduction passage. The impeller is integrally rotated with a high-speed shaft. The housing has therein an impeller chamber accommodating the impeller and a speed increaser chamber accommodating the speed increaser. The centrifugal compressor includes a bypass passage having a first end communicating with the speed increaser chamber and a second end communicating with the oil pan.

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Номер записи: 52
28-04-2016 дата публикации

DUAL MODE CHEMICAL ROCKET ENGINE AND DUAL MODE PROPULSION SYSTEM COMPRISING THE ROCKET ENGINE

Номер: US20160115906A1
Автор: Anflo Kjell, Bergman Göran
Принадлежит:

The invention relates generally to dual mode bipropellant chemical rocket propulsion systems to be used in aerospace applications for 1) orbit raising, orbit manoeuvres and maintenance, attitude control and deorbiting of spacecraft, and/or 2) propellant settling, attitude and roll control of missiles, launchers and space planes. The present invention also relates to a dual mode chemical rocket engine for use in such systems. The engine uses low-hazardous storable liquid propellants and can be operated either in monopropellant mode or in bipropellant mode. The monopropellants used are a low-hazard liquid fuel-rich monopropellant, and a low-hazard liquid oxidizer-rich monopropellant, respectively. 1100200130130150125. A dual mode chemical rocket engine ( , ) having a first primary reaction chamber () for a liquid fuel-rich monopropellant comprising a catalyst bed for the fuel-rich monopropellant , which first primary reaction chamber () is connected to a secondary reaction chamber () having means for injection () therein of a liquid , second , oxidizer-rich monopropellant , characterized in that the fuel-rich monopropellant is Ammonium DiNitramide (ADN) based or Hydroxyl Ammonium Nitrate (HAN) based.2125122150. The dual mode chemical rocket engine of claim 1 , wherein the means for injection () are configured to enable injection of an oxidizer-rich monopropellant from a propellant feed line () from outside into the secondary reaction chamber ().3130140150. The dual mode chemical rocket engine of claim 1 , comprising first and second primary reaction chambers ( claim 1 , ) in parallel arrangement connected to the secondary reaction chamber ():{'b': '130', 'one or more first primary reaction chambers () for the fuel-rich monopropellant comprising a catalyst for the fuel-rich monopropellant; and,'}{'b': '140', 'one or more second primary reaction chambers () for the oxidizer-rich monopropellant comprising a catalyst for the oxidizer-rich monopropellant.'}4130140. The ...

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Номер записи: 53
28-04-2016 дата публикации

Damper-integrated blower having improved airtightness

Номер: US20160115965A1
Автор: Mun Su Park
Принадлежит: CENDORI CO Ltd

The present invention relates to a damper-integrated blower having improved airtightness, which comprises a blower casing a having a suction port and a blower casing b fastened to the casing a from the opposite side; a vane stopper protrusion is formed on bottom surface of the exhaust port, and a vane contact housing part is formed above the exhaust port; damper motor screw fixing parts integrally protrude from the outer upper surface of the vane contact housing part of the blower casing a; a damper motor shaft hole is bored in a damper motor shaft hole protrusion part which is integrally formed on the outer upper side of the vane contact housing part of the blower casing a; a vane rotation shaft protrudes from the inner surface of a damper motor shaft hole protrusion part of the blower casing b facing the damper motor shaft hole protrusion part; an eccentric damper motor shaft of a damper motor is introduced into the damper motor shaft hole so as to connect with the blower casing a; a vane as a single member is connected to the damper motor shaft and the vane rotation shaft so as to open and close the exhaust port; and a gasket is coupled to the four edges of the vane providing a vane module.

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Номер записи: 54
09-06-2022 дата публикации

INLET AIR HEATING SYSTEM FOR A GAS TURBINE SYSTEM

Номер: US20220178303A1
Автор: Feher Peter
Принадлежит:

An inlet air heating system for a gas turbine system includes an inlet heat exchanger configured to be positioned upstream of a compressor of the gas turbine system. The inlet air heating system also includes a heating loop fluidly coupled to the inlet heat exchanger. The heating loop is configured to provide heating fluid to the inlet heat exchanger, and the inlet heat exchanger is configured to facilitate transfer of heat from the heating fluid to an airflow into the compressor. Furthermore, the inlet air heating system includes a heat transfer assembly configured to receive cooling tower fluid from a fluid pathway extending between a steam condenser and a cooling tower. The heat transfer assembly is configured to facilitate transfer of heat from the cooling tower fluid to the heating fluid. 1. An inlet air heating system for a gas turbine system , comprising:an inlet heat exchanger configured to be positioned upstream of a compressor of the gas turbine system;a heating loop fluidly coupled to the inlet heat exchanger, wherein the heating loop is configured to provide heating fluid to the inlet heat exchanger, and the inlet heat exchanger is configured to facilitate transfer of heat from the heating fluid to an airflow into the compressor;a first heat transfer assembly configured to receive cooling tower fluid from a fluid pathway extending between a steam condenser and a cooling tower, wherein the first heat transfer assembly is configured to facilitate transfer of heat from the cooling tower fluid to the heating fluid; anda second heat transfer assembly configured to receive heated fluid from a steam turbine system, wherein the second heat transfer assembly is configured to facilitate transfer of heat from the heated fluid to the heating fluid.2. The inlet air heating system of claim 1 , wherein the first heat transfer assembly comprises a heating loop heat exchanger configured to facilitate transfer of the heat from the cooling tower fluid to the heating fluid. ...

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Номер записи: 55
09-06-2022 дата публикации

Electric water pump

Номер: US20220178375A1
Автор: Do Jae JOO, Hong Ki Kim, Jae Gyeong LEE, Seong Wook CHA
Принадлежит: Youngshin Precision Co Ltd

Disclosed is an electric water pump including: a main body; a motor module including a rotor and a stator to generate a rotational force with power supplied from an outside; a pump module coupled to a first side of the main body, and including an impeller spinning by the rotational force of the motor module, an inlet to introduce a fluid as the impeller spins, and an outlet; a controller housing coupled to a second side of the main body and coupling with a controller for controlling the motor module; and a rotary shaft transmitting the rotational force from the motor module to the impeller, wherein the rotor is formed by performing insert injection-molding after stacking a rotor core and coupling with a magnet, and the rotary shaft is pressed into the rotor so that the rotor and the rotary shaft can be formed as a single body.

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Номер записи: 56
13-05-2021 дата публикации

GUIDE VANE AND FLUID MACHINE

Номер: US20210140332A1
Автор: Ishikawa Yoshihiro, KAWAJIRI Hideyuki, Koyama Hajime, YADA Yukito
Принадлежит:

In a guide vane according to an embodiment of the invention, where in a section perpendicular to a guide vane rotation axis, a curvature of a contour line forming a runner side vane surface of the guide vane is referred to as a positive curvature when the contour line is formed to be convex, while the curvature of the contour line is referred to as a negative curvature when the contour line is formed to be concave, a negative curvature portion where the curvature of the contour line becomes negative is provided on the runner side vane surface. The negative curvature portion is formed from an upper end portion to a lower end portion of the runner side vane surface. 1. A guide vane provided on an outer circumferential side of a runner of a fluid machine to control a flow rate of water into the runner by rotating about a guide vane rotation axis ,wherein, where in a section perpendicular to the guide vane rotation axis, a curvature of a contour line forming a runner side vane surface of the guide vane is referred to as a positive curvature when the contour line is formed to be convex, while the curvature of the contour line forming the runner side vane surface of the guide vane is referred to as a negative curvature when the contour line is formed to be concave, a negative curvature portion where the curvature of the contour line becomes negative is provided on the runner side vane surface, andwherein the negative curvature portion is formed from an upper end portion to a lower end portion of the runner side vane surface,wherein an inlet non-negative curvature portion where the curvature of the contour line becomes positive or zero is provided at a portion lying closer to an inlet end than the negative curvature portion, andwherein an outlet non-negative curvature portion where the curvature of the contour line becomes positive is provided at a portion lying closer to an outlet end than the negative curvature portion,wherein when L0 denotes a length of the negative ...

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Номер записи: 57
13-05-2021 дата публикации

Centrifugal blower, air-sending device, air-conditioning device, and refrigeration cycle device

Номер: US20210140445A1
Автор: Hiroshi Tsutsumi, Hiroyasu Hayashi, Kazuya MICHIKAMI, Ryo Horie, Takahiro Yamatani, Takuya Teramoto
Принадлежит: Mitsubishi Electric Corp

A centrifugal blower includes a fan including a main plate having a disk-shape, and a plurality of blades, and a scroll casing configured to accommodate the fan. The scroll casing includes a discharge portion and a scroll portion including a side wall, a circumferential wall, and a tongue portion. The circumferential wall includes a curved circumferential wall and a flat circumferential wall. In comparison with a centrifugal blower including a standard circumferential wall having a logarithmic spiral shape in cross-section perpendicular to a rotational shaft of the fan, in the curved circumferential wall, at a first end being a boundary between the circumferential wall and the tongue portion and at a second end being a boundary between the circumferential wall and the discharge portion, a distance L1 between an axis of the rotational shaft and the circumferential wall is equal to a distance L2 between the axis of the rotational shaft and the standard circumferential wall.

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Номер записи: 58
05-05-2016 дата публикации

GAS TURBINE USING A CRYOGENIC FUEL AND EXTRACTING WORK THEREFROM

Номер: US20160123226A1
Автор: RAZAK Ahmed, ROLT Andrew Martin
Принадлежит:

There is disclosed a method of operating a gas turbine engine of a type having a compressor section, a combustor section, and a turbine section arranged in flow series. The method involves the steps of: providing a supply of cryogenic liquid fuel; vaporising the cryogenic liquid fuel to produce a gaseous fuel; expanding said gaseous fuel in at least one fuel turbine external to the engine's turbine section; and thereafter directing said expanded gaseous fuel into the engine's combustion section for combustion therein. A related gas turbine arrangement configured for implementation of the method is also disclosed. 1. A method of operating a gas turbine engine having a compressor section , a combustor section , and a turbine section arranged in flow series , the method comprising the steps of: providing a supply of cryogenic liquid fuel; vaporising the cryogenic liquid fuel to produce a gaseous fuel; expanding said gaseous fuel in at least one fuel turbine external to the engine's turbine section ; and thereafter directing said expanded gaseous fuel into the engine's combustion section for combustion therein.2. A method according to claim 1 , wherein the or each said fuel turbine is used to drive a load.3. A method according to claim 2 , wherein the engine's turbine section includes a turbine which is also configured to drive said load claim 2 , such that the or each said fuel turbine is operable to augment the power output of the engine in driving said load.4. A method according to claim 1 , wherein said gaseous fuel is expanded in a plurality of said fuel turbines arranged in flow series.5. A method according to claim 1 , wherein said cryogenic liquid fuel is vaporized by being passed through a heat exchanger.6. A method according to claim 5 , wherein said heat exchanger is an inlet cooler arranged to cool inlet air before the inlet air passes through the engine's compressor section.7. A method according to claim 5 , wherein said heat exchanger is an intercooler ...

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Номер записи: 59
13-05-2021 дата публикации

SUPERCRITICAL CO2 COOLED ELECTRICAL MACHINE

Номер: US20210143707A1
Автор: Lowry Christopher, May Patrick King Wah, Rico Raul Ricardo
Принадлежит:

Systems and methods are provided to cool a heat producing component in an electrical machine system. The electrical machine includes a supercritical carbon dioxide (SCO) wherein the SCOis a working medium of a heat exchanger that is arranged in the electrical machine system to cool a fluid that cools the heat producing component and/or wherein the SCOdirectly cools at the heat producing component. 1. A system comprising:a dynamoelectric machine comprising a stator, and a rotor rotatable relative to the stator, the stator and the rotor are heat generating components; and{'sub': '2', 'a supercritical carbon dioxide (SCO),'}{'sub': '2', 'wherein the dynamoelectric machine comprises a heat exchanger to cool a fluid that cools at least one of the heat generating components, the SCOis a working medium of the heat exchanger, the working medium is heated during the heat exchange to form a heated working medium.'}2. The system according to claim 1 ,{'sub': '2', 'wherein the SCOis the working medium of a heat exchanger, and'}wherein the fluid is air, water or hydrogen.3. The system according to claim 2 ,wherein a heated working medium of the heat exchanger is discharged to the atmosphere.4. The system according to claim 2 ,wherein a heated working medium of the heat exchanger is sequestered.5. The system according to claim 2 ,wherein a heated working medium of the heat exchanger is used as a working medium in a further component in the system.6. The system according to claim 5 , comprising:an egress conduit arranged between the dynamoelectric machine and the further component, the egress conduit configured to conduct the heated working medium to the further component.7. The system according to claim 6 , comprising:an ingress conduit arranged between the dynamoelectric machine and the further component, the conduit configured to conduct a discharged working fluid from the further component to the heat exchanger,wherein the ingress conduit and the egress conduit form a closed ...

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Номер записи: 60
14-05-2015 дата публикации

Advanced Humid Air Gas Turbine System

Номер: US20150128559A1
Автор: Sato Kazuhiko, TAKAHASHI Yoshitaka, TAKEDA Yasushi
Принадлежит:

One of the objects of the invention is to provide a water-saving type advanced humid air gas turbine system (AHAT) that can decrease the amount of makeup water to be supplied from the outside, by reducing the amount of water consumed when the gas turbine system is starting up, shut down, or subjected to load rejection. 1. An advanced humid air gas turbine system comprising:a gas turbine system that includesa compressor for compressing air,a compressed air header for mixing high-pressure air introduced from the compressor with steam to generate humidified combustion air,a combustor for mixing combustion air from the compressed air header with fuel for sake of combustion so as to generate combustion gas, anda turbine driven by the combustion gas that is generated by the combustor;a heat recovery steam generator for generating steam by use of exhaust gas from the turbine;a water recovery system disposed on a downstream side of the heat recovery steam generator, the water recovery system recovering moisture contained in the exhaust gas;a first steam system for supplying steam, coming from the heat recovery steam generator, to the compressed air header; anda second steam system for supplying steam, coming from the heat recovery steam generator, to the heat recovery steam generator or the water recovery system,wherein when the gas turbine system is starting up, shut down, or subjected to load rejection, steam coming from the heat recovery steam generator is recovered by blocking the first steam system and making the second steam system communicate with the heat recovery steam generator.2. The advanced humid air gas turbine system according to claim 1 ,wherein the second steam system is coupled to a steam nozzle for jetting steam into an exhaust gas passage of the heat recovery steam generator.3. The advanced humid air gas turbine system according to claim 1 ,wherein the heat recovery steam generator has a box-shaped casing, the casing having at a bottom portion thereof an ...

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Номер записи: 61
04-05-2017 дата публикации

HYBRID ELECTRICAL RENEWABLE ENERGY SOURCE

Номер: US20170122121A1
Автор: Rejniak Brian Rosser, Rejniak John Alan
Принадлежит:

A system having a motor coupled to and powering a pump for pumping a liquid, the motor being configured to start by receiving electric power from a power source, a turbine mounted in line with the pump within a conduit where flow of the liquid causes rotation of the turbine, the turbine being associated with a generator, and, an automatic transfer switch configured to monitor a power output of the generator and, when the power output is sufficient for the motor to run, to provide the power output to the motor and to disconnect the power source from the motor. 1. A system comprising a motor coupled to and powering a pump for pumping a liquid , the motor being configured to start by receiving electric power from a power source , a turbine mounted in line with the pump within a conduit where flow of the liquid causes rotation of the turbine , the turbine being associated with a generator , and , an automatic transfer switch configured to monitor a power output of the generator and , when the power output is sufficient for the motor to run , to provide the power output to the motor and to disconnect the power source from the motor.2. The system of wherein the liquid is swimming pool water and the power source is a utility line.3. The system of wherein the automatic transfer switch comprises an electronic time delay initiated by an input indicating that the power output of the generator is sufficient claim 2 , the electronic time delay allowing the generator to stabilize.4. The system of wherein the electronic time delay is about 20-30 seconds.5. The system of further comprising a flow control manifold configured to regulate the flow of the water through the conduit and thus the speed of the turbine and of the generator.6. The system of wherein the flow control manifold comprises a bypass line and a flow control module having a bi-directional flow regulator configured to divert some of the water through the bypass line claim 5 , reducing the water flow through the ...

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Номер записи: 62
12-05-2016 дата публикации

FILTRATION SYSTEM AND METHOD FOR CLEANING THE INTAKE AIR OF A GAS TURBINE

Номер: US20160131033A1
Автор: Herrmann Torsten
Принадлежит:

In a filtration system, in particular for cleaning the intake air of a gas turbine, including a flow channel surrounded by walls with an inflow opening and an outflow opening, a partition wall with at least two openings between a dirty side and a clean side which is positioned between the inflow opening and the outflow opening and limited by the walls of the flow channel, and at least two filters for purifying a flowing fluid. At least one filter is installed at a first opening on the dirty side of the partition wall and at least one filter at a second opening on the clean side of the partition wall. 1110142146148108146148142110116122124100110100116122108100116124108. A filtration system for the cleaning intake air of a gas turbine , comprising: a flow channel () surrounded by walls () with an inflow opening () and an outflow opening () , a partition wall () positioned between the inflow opening () and the outflow opening () and limited by the walls () of the flow channel () with at least two openings () between a dirty side () and a clean side () , and at least two filters () for the cleaning a fluid that flows through the flow channel () , the at least two filters including at least one first filter () mounted at a first opening () on the dirty side () of the partition wall () and at least one second filter () at a second opening () on the clean side () of the partition wall ().2118100108. The filtration system of claim 1 , wherein frames () of the first and the second filters () overlap at least partially in one direction largely vertically to the partition wall ().3118100108108. The filtration system of claim 2 , wherein an area in which the frames () of the first and the second filters () overlap in one direction largely vertically to the partition wall () amounts to at least 5% of an overall projected area of filtration at the partition wall ().4100136108100136122124108. The filtration system of claim 1 , wherein the filters () are arranged in at least one row ...

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Номер записи: 63
25-08-2022 дата публикации

AIR ENERGY STORAGE POWERED UNINTERRUPTIBLE POWER SUPPLY

Номер: US20220272871A1
Автор: JR. John A., Koerner Matthew Douglas, McDaniel Brandon, Musilli
Принадлежит:

A system includes at least one storage tank configured to store at least one of first compressed air or liquid air. The system also includes a power supply system comprising a turbine, a generator, and a flywheel. The power supply system is configured to receive second compressed air from the at least one storage tank, wherein the second compressed air comprises either the first compressed air or the liquid air which has been heated into a gaseous state; spin the turbine and the flywheel using the second compressed air, wherein the spinning of the turbine generates electrical energy at the generator; provide the electrical energy to a data center for powering electronic devices of the data center; and provide at least a portion of the second compressed air exhausted by the turbine to the data center for cooling the electronic devices of the data center. 1. A system comprising:at least one storage tank configured to store at least one of first compressed air or liquid air; and receive second compressed air from the at least one storage tank, wherein the second compressed air comprises either the first compressed air or the liquid air which has been heated into a gaseous state;', 'spin the turbine and the flywheel using the second compressed air, wherein the spinning of the turbine generates electrical energy at the generator;', 'provide the electrical energy to a data center for powering electronic devices of the data center; and', 'provide at least a portion of the second compressed air exhausted by the turbine to the data center for cooling the electronic devices of the data center., 'a power supply system comprising a turbine, a generator, and a flywheel, the power supply system configured to2. The system of claim 1 , wherein the power supply system is further configured to:provide cold thermal content from at least a portion of the first compressed air or the liquid air directly to the data center through a heater or a heat exchanger disposed prior to the turbine ...

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Номер записи: 64
01-09-2022 дата публикации

SUPERCRITICAL FLUID SYSTEMS

Номер: US20220275752A1
Автор: Greene Christopher Britton, Holley Brian M.
Принадлежит:

Supercritical fluid systems and aircraft power systems are described. The systems include a compressor, a turbine, and a generator. A primary working fluid flow path has a primary working fluid that passes through the compressor, a separator, the turbine, and back to the compressor. A secondary working fluid flow path having a secondary working fluid that passes through the generator, the compressor, the separator, and back to the generator. The primary working fluid and the secondary working fluid are compressed and mixed within the compressor to form a mixture of the two fluids and the separator separates the mixture of the two fluids to direct the primary working fluid back to the turbine and the secondary working fluid to the generator. 1. A supercritical fluid system comprising:a compressor;a turbine operably coupled to the compressor;a generator operably coupled to the turbine and configured to generate power;a primary working fluid flow path having a primary working fluid configured to pass through the compressor, a separator, the turbine, and back to the compressor; anda secondary working fluid flow path having a secondary working fluid configured to pass through the generator, the compressor, the separator, and back to the generator,wherein the primary working fluid and the secondary working fluid are compressed and mixed within the compressor to form a mixture of the two fluids, andwherein the separator is configured to separate the primary working fluid from the secondary working fluid from the mixture of the two fluids and direct the primary working fluid back to the turbine along the primary working fluid flow path and the secondary working fluid along the secondary working fluid flow path to the generator.2. The supercritical fluid system of claim 1 , wherein the secondary working fluid is hydrogen.3. The supercritical fluid system of claim 1 , wherein the secondary working fluid is helium.4. The supercritical fluid system of claim 1 , wherein the ...

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Номер записи: 65
02-05-2019 дата публикации

Combination for sealing a gap between turbomachine blades and for reducing vibrations of the turbomachine blades

Номер: US20190128120A1
Автор: Hartung Andreas
Принадлежит:

A combination including a seal (-) for sealing a gap (s) between blade platforms () of two adjacent blades of a turbomachine and a reducer (-) for reducing vibrations of at least one of the blades, the seal including at least one rib () having a rib thickness and at least one wall () having a wall thickness that is smaller than the rib thickness and/or the reducer including a tuning-element guide housing () having at least one cavity () in which at least one tuning element () is disposed with play for impacting contact with the tuning-element guide housing. 110-. (canceled)11. A combination comprising:a seal for sealing at least one gap between blade platforms of two adjacent blades of a turbomachine and a reducer for reducing vibrations of at least one of the blades, the seal including at least one rib having a rib thickness and at least one wall having a wall thickness that is smaller than the rib thickness or the reducer including a tuning-element guide housing having at least one cavity in which at least one tuning element is disposed with play for impacting contact with the tuning-element guide housing.12. The combination as recited in wherein the seal and the reducer are interconnected.13. The combination as recited in wherein the seal and the reducer are interconnected by a web.14. The combination as recited in wherein the seal and the reducer and formed in one piece or integrally with each other.15. The combination as recited in wherein the seal and the reducer are unconnected.16. The combination as recited in wherein the seal or the reducer is at least partially produced using a generative manufacturing process or is at least partially made of a nickel alloy.17. The combination as recited in wherein the combination has the tuning-element guide and the tuning-element guide housing is at least partially produced using the generative manufacturing process or is at least partially made of the nickel alloy.18. The combination as recited in wherein the seal ...

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Номер записи: 66
02-05-2019 дата публикации

BEARING DEVICE FOR AN EXHAUST GAS TURBOCHARGER, AND EXHAUST GAS TURBOCHARGER

Номер: US20190128140A1
Автор: Gramsch Torsten, Kreschel Martin
Принадлежит:

A bearing device for an exhaust gas turbocharger, comprising a first radial bearing and a second radial bearing, the radial bearings radially support a shaft with an axis of rotation of the exhaust gas turbocharger, and wherein a first outflow gap and a second outflow gap, respectively, are formed between the first radial bearing and a radially extending first supporting wall of the turbocharger, which faces a turbine wheel of the exhaust gas turbocharger for axially supporting the first radial bearing, and the second radial bearing and a radially extending second supporting wall of the turbocharger, which faces a compressor wheel of the exhaust gas turbocharger for axially supporting the second radial bearing. The first outflow gap and/or the second outflow gap is configured inclined or curved relative to the axis of rotation for the axial and simultaneously radial support and/or for the backup of the radial support. 113141314821823131727213142226214811. A bearing device for an exhaust gas turbocharger , comprising a first radial bearing () and a second radial bearing () , wherein the radial bearings ( , ) are configured for the radial support of a shaft () of the exhaust gas turbocharger () , and wherein a first outflow gap () and a second outflow gap () , respectively , are formed between the first radial bearing () and a radially extending first supporting wall () of the exhaust gas turbocharger () , which faces a turbine wheel () of the exhaust gas turbocharger () for axially supporting the first radial bearing () , and between the second radial bearing () and a radially extending second supporting wall () of the exhaust gas turbocharger () , which faces a compressor wheel () of the exhaust gas turbocharger () for axially supporting the second radial bearing () , and wherein the shaft () comprises an axis of rotation () ,characterized in that{'b': 18', '23', '11, 'the first outflow gap () and/or the second outflow gap () is configured inclined or curved ...

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Номер записи: 67
30-04-2020 дата публикации

Turbine stator blade

Номер: US20200131923A1
Автор: Asako Inomata, Hideyuki Maeda, Iwataro Sato, Kazutaka Tsuruta, Satoru Sekine, Shinji Tanigawa
Принадлежит: Toshiba Energy Systems and Solutions Corp

A stator blade of an embodiment includes: a blade effective part having hollow portions; an outer shroud having an outer plate flange portion provided on a radial-direction outer side of the blade effective part, and a pair of outer mounting portions provided in a circumferential direction on a front edge side and a rear edge side; an inner shroud having an inner plate flange portion provided on a radial-direction inner side of the blade effective part; cooling medium introduction passages which introduce a cooling medium via opening portions formed in the outer plate flange portion and passing through the outer plate flange portion in a radial direction, to the hollow portions; and a cooling medium introduction passage formed in a direction along a surface of the outer plate flange portion in a wall thickness of the outer plate flange portion, which introduces a cooling medium to the hollow portion.

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Номер записи: 68
09-05-2019 дата публикации

GUIDE VANE AND FLUID MACHINE

Номер: US20190136703A1
Автор: Ishikawa Yoshihiro, KAWAJIRI Hideyuki, Koyama Hajime, YADA Yukito
Принадлежит:

In a guide vane according to an embodiment of the invention, where in a section perpendicular to a guide vane rotation axis, a curvature of a contour line forming a runner side vane surface of the guide vane is referred to as a positive curvature when the contour line is formed to be convex, while the curvature of the contour line is referred to as a negative curvature when the contour line is formed to be concave, a negative curvature portion where the curvature of the contour line becomes negative is provided on the runner side vane surface. The negative curvature portion is formed from an upper end portion to a lower end portion of the runner side vane surface. 1. A guide vane provided on an outer circumferential side of a runner of a fluid machine to control a flow rate of water into the runner by rotating about a guide vane rotation axis ,wherein, where in a section perpendicular to the guide vane rotation axis, a curvature of a contour line forming a runner side vane surface of the guide vane is referred to as a positive curvature when the contour line is formed to be convex, while the curvature of the contour line forming the runner side vane surface of the guide vane is referred to as a negative curvature when the contour line is formed to be concave, a negative curvature portion where the curvature of the contour line becomes negative is provided on the runner side vane surface, andwherein the negative curvature portion is formed from an upper end portion to a lower end portion of the runner side vane surface.2. The guide vane according to claim 1 ,wherein an inlet non-negative curvature portion where the curvature of the contour line becomes positive or zero is provided at a portion lying closer to an inlet end than the negative curvature portion, andwherein an outlet non-negative curvature portion where the curvature of the contour line becomes positive or zero is provided at a portion lying closer to an outlet end than the negative curvature portion.3. ...

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Номер записи: 69
26-05-2016 дата публикации

DEVICE AND METHOD FOR SEPARATING DIRT PARTICLES FROM THE WORKING MEDIUM OF A TURBINE

Номер: US20160146056A1
Автор: Eisenmenger Nadja, Magel Hans-Christoph, Rueckert Frank Ulrich, Wengert Andreas
Принадлежит:

The invention relates to a device and a method for separating dirt particles from the working medium of a turbine (). The turbine () comprises at least one rotor () which is arranged in a housing (). A swirl generator () is provided that sets the working medium and the dirt particles in a spiral-shaped rotational movement along a principal axis () by means of the geometry of the swirl generator () and thereby separates the dirt particles from the working medium. The swirl generator () is designed in such a way that the working medium experiences a reversal of the speed component parallel to the principal axis () within the swirl generator (). 11010111720222020. A device for separating dirt particles from a working medium of a turbine () , the turbine () comprising at least one rotor () which is arranged in a housing () , the device comprising a swirl generator () which sets the working medium and the dirt particles in a spiral-shaped rotational movement having a speed component parallel to a principal axis () by means of the geometry of the swirl generator () and thereby separates the dirt particles from the working medium , characterized in that the swirl generator () has at least one reflection surface by means of which the speed component of the working medium is reversed within the swirl generator.220242610. The device according to claim 1 , characterized in that the swirl generator () is a hollow body () which is approximately rotationally symmetrical and into which a pipe () protrudes claim 1 , the pipe being a connection to the turbine ().32625201710. The device according to claim 2 , characterized in that the pipe () which protrudes into the hollow body () of the swirl generator () is formed by the housing () of the turbine ().428202524. The device according to claim 2 , characterized in that the working medium passes through an inlet line () into the swirl generator () claim 2 , said device being configured such that the working medium has a further speed ...

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Номер записи: 70
10-06-2021 дата публикации

EXPANDABLE IMPELLER PUMP

Номер: US20210172450A1
Автор: Boger David A., Campbell Robert L., Dillon Gregory P., Hambric Stephen A., Kunz Robert F., Leschinsky Boris, Mallison Thomas M., McBride Mark W., Runt James P., Walsh Justin M.
Принадлежит:

An impeller includes a hub, and a plurality of blades supported by the hub, the blades being arranged in at least .two blade rows. The impeller has a deployed configuration in which the blades extend away from the hub, and a stored configuration in which at least one of the blades is radially compressed, for example by folding the blade towards the hub. The impeller may also have an operational configuration in which at least some of the blades are deformed from the deployed configuration upon rotation of the impeller when in the deployed configuration. The outer edge of one or more blades may have a winglet, and the base of the blades may have an associated indentation to facilitate folding of the blades. 1. An impeller pump comprising:a hub;a blade supported by the hub, the blade having a proximal end attached to the hub and a distal end;the blade having a deployed configuration, a stored configuration and an operational configuration, the blade in the deployed configuration extending away from the hub, the blade in the stored configuration being compressed so as to move the distal end of the blade towards the hub, and the blade in the operational configuration being deformed from the deployed configuration upon rotation of the impeller when in the deployed configuration; anda winglet provided on the distal end of the blade, wherein the winglet comprises a length that varies along a length of the blade.2. The impeller pump of claim 1 , wherein the winglet comprises a first end claim 1 , a second end claim 1 , and an intermediate portion positioned therebetween claim 1 , wherein a length of the intermediate portion is larger than a length of either the first end or the second end.3. The impeller pump of claim 1 , wherein the blade has a pressure face and a suction face claim 1 , the winglet extending from the pressure face of the blade.4. The impeller pump of claim 1 , wherein the blade has a pressure face and a suction face claim 1 , the winglet extending from the ...

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Номер записи: 71
10-06-2021 дата публикации

EXPANDABLE IMPELLER PUMP

Номер: US20210172451A1
Автор: Boger David A., Campbell Robert L., Dillon Gregory P., Hambric Stephen A., Kunz Robert F., Leschinsky Boris, Mallison Thomas M., McBride Mark W., Runt James P., Walsh Justin M.
Принадлежит:

An impeller includes a hub, and a plurality of blades supported by the hub, the blades being arranged in at least .two blade rows. The impeller has a deployed configuration in which the blades extend away from the hub, and a stored configuration in which at least one of the blades is radially compressed, for example by folding the blade towards the hub. The impeller may also have an operational configuration in which at least some of the blades are deformed from the deployed configuration upon rotation of the impeller when in the deployed configuration. The outer edge of one or more blades may have a winglet, and the base of the blades may have an associated indentation to facilitate folding of the blades. 1. A catheter heart pump comprising:an elongate catheter body having a proximal end, and a distal end configured to be advanced to a heart of a patient;an expandable sleeve coupled to the distal end, the expandable sleeve having a stored configuration in which the expandable sleeve is advanced to the heart, and an expanded configuration, and further comprising a distal inlet port and a proximal outlet port;an expandable impeller configured to be disposed within the expandable sleeve between the distal inlet port and the proximal outlet port when in the expanded configuration, and configured to turn on a shaft to generate a fluid flow from the distal inlet port to the proximal outlet port; anda storage sleeve configured to house both the expandable sleeve and the expandable impeller therein.2. The catheter heart pump of claim 1 , wherein the impeller and the expandable sleeve are configured to expand when urged out of the storage sleeve.3. The catheter heart pump of claim 1 , wherein the storage sleeve is configured to compress the expandable sleeve into the stored configuration for insertion into the patient and advancement to the heart.4. The catheter heart pump of claim 2 , wherein the expandable sleeve is configured for insertion into the storage sleeve.5. The ...

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Номер записи: 72
04-06-2015 дата публикации

VAPOR JETTING DEVICE AND SPACECRAFT

Номер: US20150152812A1
Автор: Hashimoto Kozue, Izumiyama Taku, Mori Hatsuo, Nagao Toru
Принадлежит:

Provided is a vapor jetting device including: a box-shaped casing; a propellant holding unit that is placed in the casing and forms a space for holding a propellant; a gas storing unit that is placed in the casing, forms a space that is divided from the propellant holding unit by a partition wall including a communication hole, and stores gas; a machine housing unit that is placed in the casing, forms a space that is divided from the propellant holding unit and the gas storing unit by partition walls, and houses machines; a nozzle that is connected to the casing and ejects the gas to an outside; a gas flow path that is formed in the casing and supplies the gas stored in the gas storing unit to the nozzle; and a heater that is placed in the casing and heats at least the gas storing unit. 1. A vapor jetting device that evaporates a propellant in the form of liquid and jets gas by means of a steam pressure to thereby obtain thrust , comprising:a box-shaped casing;a propellant holding unit that is placed in the casing and forms a space for holding the propellant;a gas storing unit that is placed in the casing, forms a space that is divided from the propellant holding unit by a partition wall including a communication hole, and stores the gas;a machine housing unit that is placed in the casing, forms a space that is divided from the propellant holding unit and the gas storing unit by partition walls, and houses machines;a nozzle that is connected to the casing and ejects the gas to an outside;a gas flow path that is formed in the casing and supplies the gas stored in the gas storing unit to the nozzle; anda heater that is placed in the casing and heats at least the gas storing unit.2. The vapor jetting device according to claim 1 , wherein the gas storing unit includes: a gas outlet for discharging the gas; and a heat spreader placed between the gas outlet and the communication hole.3. The vapor jetting device according to claim 2 , whereina gas supply tube that connects ...

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Номер записи: 73
25-05-2017 дата публикации

SYSTEM AND METHOD FOR SUPPLYING AN ENERGY GRID WITH ENERGY FROM AN INTERMITTENT RENEWABLE ENERGY SOURCE

Номер: US20170145915A1
Автор: Beasley Paul, Heid Oliver, Hughes Timothy
Принадлежит: SIEMENS AKTIENGESELLSCHAFT

A system and method for supplying an energy grid with energy from an intermittent renewable energy source having a production unit for producing Hydrogen, Nitrogen, and Oxygen. The production unit is operated by using energy provided by the renewable energy source. An Oxygen storage receives and stores Oxygen produced by the production unit, a mixing unit receives and mixes the Hydrogen and the Nitrogen produced by the production unit to form a Hydrogen-Nitrogen-mixture, an Ammonia source receives and processes the Hydrogen-Nitrogen-mixture for generating a gas mixture containing Ammonia, an Ammonia power generator generates energy for the energy grid. The Ammonia power generator is fluidly connected to the Ammonia storage vessel, is configured to combust the received Ammonia in a combustion chamber to generate the energy, and is fluidly connected to the Oxygen storage to introduce Oxygen into the combustion chamber for combustion of Ammonia. 1. A system for providing energy for an energy grid based on energy provided by a renewable energy source , comprisingan H2-N2-O2-production unit for producing Hydrogen, Nitrogen, and Oxygen, wherein the H2-N2-O2-production unit is operated by using energy provided by the renewable energy source,an Oxygen storage configured to receive and store the Oxygen produced by the H2-N2-O2-production unit,a mixing unit configured to receive and mix the Hydrogen and the Nitrogen produced by the H2-N2-O2-production unit to form a Hydrogen-Nitrogen-mixture,an NH3 source for receiving and processing the Hydrogen-Nitrogen-mixture for generating a gas mixture containing NH3, wherein the NH3 source comprises a NH3 storage vessel for storing at least a part of the NH3 of the gas mixture containing NH3,an NH3 power generator for generating energy for the energy grid, wherein the NH3 power generatoris fluidly connected to the NH3 storage vessel to receive NH3 from the NH3 storage vessel,is configured to combust the received NH3 in a combustion ...

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Номер записи: 74
25-05-2017 дата публикации

GAS TURBINE ENGINE

Номер: US20170145959A1
Автор: BARALON Stephane M M
Принадлежит: ROLLS-ROYCE PLC

A gas turbine engine comprising in flow series: a fan; a series of outlet guide vanes; and a bifurcation. The outlet guide vanes are more densely distributed in a region circumferentially aligned with the bifurcation than in a region circumferentially offset from the bifurcation. 1. A gas turbine engine comprising in flow series:a fan;a series of outlet guide vanes; anda bifurcation,wherein the outlet guide vanes are more densely distributed in a region circumferentially aligned with the bifurcation than in a region circumferentially offset from the bifurcation.2. The gas turbine engine according to claim 1 , wherein the outlet guide vanes positioned in the region circumferentially aligned with the bifurcation have a shorter chord length than the remainder of the outlet guide vanes.3. The gas turbine engine according to claim 1 , wherein one or a plurality of smaller outlet guide vanes are positioned between two larger outlet guide vanes in the region circumferentially aligned with the bifurcation claim 1 , the smaller outlet guide vanes having a shorter chord length than the larger outlet guide vanes.4. The gas turbine engine according to claim 3 , wherein the one or more smaller outlet guide vanes have a chord length equal to or between a half and a quarter of the chord length of the larger outlet guide vanes.5. The gas turbine engine according to claim 4 , wherein the one or more smaller outlet guide vanes have a chord length equal to about one third of the chord length of the larger outlet guide vanes.6. The gas turbine engine according to claim 3 , wherein the larger outlet guide vanes have a rearward camber angled to an axis parallel to the longitudinal axis of the gas turbine engine claim 3 , the angle of the rearward camber from said axis being greater than the angle claim 3 , from the axis parallel to the longitudinal axis claim 3 , of a streamline flow contouring the bifurcation.7. The gas turbine engine according to claim 6 , wherein the larger outlet ...

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Номер записи: 75
15-09-2022 дата публикации

Turbine Motor for Use with a Pneumatic Tool

Номер: US20220290578A1
Автор: Bohle, II David John, Nichols Taylor Edwin
Принадлежит:

A turbine motor configured to be connected to a tool. The turbine motor includes a receptacle that houses a turbine blade. A channel is configured to receive air to drive the turbine blade. The turbine motor is configured to provide for one or more features that provide enhanced functionality. One feature includes a modular design that can be tailored to adjust the torque of the turbine blade and thus the output of the turbine motor. Another feature includes a brake that stops rotation of the turbine blade. 1. A turbine motor comprising:a housing with a receptacle;a turbine blade rotatably positioned in the receptacle, the turbine blade comprising a central body and outwardly-extending arms;a channel that extends through the housing and into the receptacle to deliver air to rotate the turbine blade within the housing; andexhaust ports that are spaced away from the channel and that extend through the housing and into the receptacle to exhaust the air from the receptacle after the air provides a force to rotate the turbine blade.2. The turbine motor of claim 1 , wherein the housing comprises a floor that forms a side of the receptacle and a sidewall that extends around a perimeter of the floor and forms a lateral wall of the receptacle with the exhaust ports extending through the floor and the channel extending through the sidewall.3. The turbine motor of claim 2 , wherein the exhaust ports are arranged along a rotational path of the turbine blade and are spaced radially outward away from a central section of the receptacle with the exhaust ports positioned in closer proximity to the sidewall than to a center of the receptacle.4. The turbine motor of claim 1 , wherein the exhaust ports are arranged along a rotational path of the turbine blade and a first one of the exhaust ports in closest proximity to the channel is smaller than a last one of the exhaust ports.5. The turbine motor of claim 4 , wherein the exhaust ports comprise a first set in closer rotational ...

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Номер записи: 76
17-06-2021 дата публикации

Arrangement for Receiving the Axial Thrust of a Centrifugal Pump

Номер: US20210180600A1
Автор: Kai Molitor, Ralph Kraemer
Принадлежит: KSB SE and Co KGaA

An arrangement for monitoring a centrifugal pump is provided. receiving the residual axial thrust of a centrifugal pump. The arrangement includes a load-relieving device configured to receive the residual axial thrust developed during pump operation, an axial bearing, and a sensor ring is associated with the axial bearing. The ring (10) is divided into segments having sensors at the segment dividing regions.

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Номер записи: 77
11-06-2015 дата публикации

COMPRESSOR DISCHARGE CASING ASSEMBLY

Номер: US20150159873A1
Автор: DiCintio Richard Martin, MELTON Patrick Benedict
Принадлежит: GENERAL ELECTRIC COMPANY

A compressor discharge casing assembly includes a diffuser disposed proximate an aft region of a compressor section, the diffuser configured to route a compressed airflow to an interior region of the compressor discharge casing assembly. Also included is a strut disposed in the interior region of the compressor discharge casing assembly and located proximate an exit region of the diffuser. Further included is a heat shield disposed proximate an upstream portion of the strut, the heat shield configured to reduce impingement of the compressed airflow on the strut. 1. A compressor discharge casing assembly comprising:a diffuser disposed proximate an aft region of a compressor section, the diffuser configured to route a compressed airflow to an interior region of the compressor discharge casing assembly;a strut disposed in the interior region of the compressor discharge casing assembly and located proximate an exit region of the diffuser; anda heat shield disposed proximate an upstream portion of the strut, the heat shield configured to reduce impingement of the compressed airflow on the strut.2. The compressor discharge casing assembly of claim 1 , wherein the strut is operatively coupled to claim 1 , and extends between claim 1 , a compressor discharge casing bulkhead and an inner support ring.3. The compressor discharge casing assembly of claim 1 , wherein the heat shield is operatively coupled to the strut.4. The compressor discharge casing assembly of claim 2 , further comprising a nozzle disposed proximate an inlet of a turbine section claim 2 , the nozzle operatively coupled to the inner support ring and an outer support ring.5. The compressor discharge casing assembly of claim 4 , wherein the heat shield is configured to reduce a rate of thermal growth of the strut.6. The compressor discharge casing assembly of claim 4 , wherein the heat shield is configured to reduce relative motion between a transition piece and the nozzle.7. The compressor discharge casing ...

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Номер записи: 78
23-05-2019 дата публикации

Carbon dioxide capturing apparatus using cold heat of liquefied natural gas and power generation system using same

Номер: US20190151789A1
Автор: Hwachang SUNG, Songhun CHA
Принадлежит: Doosan Heavy Industries and Construction Co Ltd

A carbon dioxide capturing apparatus using cold heat of liquefied natural gas (LNG) includes a heat exchanger to cool primary coolant using heat exchange between the primary coolant and the LNG; a chiller connected to the heat exchanger and configured to discharge capturing coolant colder than the primary coolant by performing a heat exchange between the capturing coolant and a cooling material; and a capturing cooler configured to capture carbon dioxide contained in flue gas by performing a heat exchange between the capturing coolant discharged from the chiller and the flue gas. A power generation system includes an LNG storage facility; a power generation facility discharging flue gas; a unit for heat exchange between the LNG and a coolant to regasify the LNG and cool the coolant; and a unit for capturing carbon dioxide contained in the flue gas by heat exchange between the discharged flue gas and the coolant.

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Номер записи: 79
23-05-2019 дата публикации

CENTRIFUGAL COMPRESSOR AND TURBOCHARGER

Номер: US20190151885A1
Автор: Hayashi Yoshihiro, Yamada Yuki, YASHIRO Yusuke
Принадлежит: MITSUBISHI HEAVY INDUSTRIES, LTD.

A centrifugal compressor according to an embodiment includes a compressor impeller, a compressor housing, a suction-surface-side member disposed on a suction surface side of the compressor impeller, and a piezoelectric vibrator disposed in at least one of the compressor housing or the suction-surface-side member. The compressor housing and the suction-surface-side member have wall surfaces defining a space surrounded by the compressor housing and the suction-surface-side member. The wall surface of the at least one of the compressor housing or the suction-surface-side member is at least partially vibratable by operation of the piezoelectric vibrator. 1. A centrifugal compressor comprising:a compressor impeller;a compressor housing;a suction-surface-side member disposed on a suction surface side of the compressor impeller; anda piezoelectric vibrator disposed in at least one of the compressor housing or the suction-surface-side member,wherein the compressor housing has a wall surface, and the suction-surface-side member has a wall surface, the wall surfaces defining a space surrounded by the compressor housing and the suction-surface-side member, andwherein the wall surface of the at least one of the compressor housing or the suction-surface-side member is at least partially vibratable by operation of the piezoelectric vibrator.2. The centrifugal compressor according to claim 1 ,wherein the piezoelectric vibrator is disposed in the at least one of the compressor housing or the suction-surface-side member so as to be opposite to the space across a vibratable region of the wall surface, the vibratable region being vibratable by the piezoelectric vibrator.3. The centrifugal compressor according to claim 1 , further comprising an electric motor for rotating the compressor impeller claim 1 ,wherein the suction-surface-side member forms a part of an electric-motor housing accommodating the electric motor.4. The centrifugal compressor according to further comprisinga ...

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Номер записи: 80
23-05-2019 дата публикации

GAS TURBINE BLOWER/PUMP

Номер: US20190153938A1
Автор: HAMMOUD OMAR
Принадлежит:

A low emission, high efficiency Gas Turbine engine operating on a combination of Natural Gas and Bio Gas as fuel, driving either a high efficiency turbo-blower or a high efficiency Turbo Pump system combined with heat recovery systems and in other embodiments is provided a generator of electricity or providing evaporate cooling from using the remaining waste heat in the exhaust gas. 1. A unit having:(a) a first inlet and first outlet;(b) a second inlet and second outlet;(c) an impeller disposed between said first inlet and said first outlet;(d) a compressor for elevating the pressure of air;(e) a recuperator for increasing the temperature of said air at said elevated pressure;(f) a gas turbine disposed between said second inlet and said second outlet;(g) a combustor for receiving a combustion mixture comprising said air at said elevated temperature and said elevated pressure, and fuel introduced into said second inlet to drive said gas turbine and exhaust through said second outlet;(h) the impeller disposed between said first inlet and said first outlet; and(i) said gas turbine and said impeller directly connected to a shaft so as to drive said impeller and move a fluid from said first inlet to said first outlet.2. A unit as claimed in wherein said fluid is air and said impeller is an air blower.3. A unit as claimed in wherein said fluid is water and said impeller is a pump.4. A unit as claimed in wherein said combustion mixture includes air and a gas selected from the group of natural gas and biogas.5. A unit as claimed in wherein said gas turbine comprises a high pressure turbine and a free powered turbine and wherein said free powered turbine and said impeller are connected to a common shaft.6. A unit as claimed in wherein said gas turbine comprises a high pressure turbine claim 1 , a low pressure turbine claim 1 , and free powered turbine and wherein said free powered turbine and said impeller are connected to a common shaft.7. A unit as claimed in including an ...

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Номер записи: 81
23-05-2019 дата публикации

ACCELERATED AND-OR REDIRECTED FLOW-INDUCING AND-OR LOW PRESSURE FIELD OR AREA-INDUCING ARRANGEMENT, THEIR USE WITH TURBINE-LIKE DEVICES AND METHOD FOR USING SAME

Номер: US20190153992A1
Автор: Schurtenberger Walter
Принадлежит:

An accelerated and/or redirected flow arrangement, optimally serving as a wildlife and/or debris excluder (WDE), is used in combination with a turbine-like device having an inlet end and an outlet end for fluid flowing therethrough, e.g., a hydro-turbine. The arrangement includes at least a forward part designed to be placed in front of a fluid inlet of a turbine-like device and configured to produce at least one of the following effects on the fluid: (a) imparting a re-direction of the fluid; and/or (b) accelerating the flow velocity of the fluid, as it flows through the forward part. Turbine-like devices having both a forward part and a rearward part of flow arrangement are disclosed, as well as a method of enhancing turbine performance. 1. An accelerated and/or redirected flow arrangement intended for use in combination with a turbine-like device having an inlet end and an outlet end for fluid flowing therethrough , the arrangement comprising a forward part designed to be placed in front of a fluid inlet of a turbine-like device and being comprised of an accelerated and/or redirected flow-inducing arrangement configured so as to produce at least one of the following effects on the fluid flowing through the turbine-like device: (a) imparting a re-direction of the fluid as it passes through the forward part; and/or (b) accelerating the flow velocity of the fluid as it flows through the forward part.2. A flow arrangement as claimed in claim 1 , wherein the forward part of the flow arrangement comprises a deflector structure comprised of an array of deflector rods that are configured to provide at least one of said effects (a) and/or (b).3. A flow arrangement as claimed in claim 2 , wherein the deflector structure comprises a conically-shaped structure comprised of a conically-shaped array of deflector rods that includes a plurality of arrays oriented to produce a re-direction of the fluid that comprises at least some rotational re-direction.4. A flow arrangement as ...

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Номер записи: 82
23-05-2019 дата публикации

Method for Optimizing Blade Axis Position of Water Pump under All Operating Conditions

Номер: US20190154040A1
Автор: Cao Jinyu, Liu Di, QIU Baoyun, WU Kaiming, XU Mengfan, XUE Chenglong, ZHANG Cai
Принадлежит:

A method for optimizing the blade axis position of a water pump under all operating conditions which includes determination of multiple calculation conditions within the range of all the operating conditions of the water pump, three-dimensional modeling and mesh generation of the calculation area of the flow field of the water pump at multiple blade angles, numerical simulation of the flow field and calculation and determination of blade hydraulic torques under multiple conditions, determination of the range of the position of the blade resultant hydraulic pressure action line and an optimal blade axis position under all the operating conditions, determination of the small region of the optimal blade axis position under all the operating conditions, determination of the optimal blade axis position, and comparison of the blade hydraulic torques before and after optimization of the blade axis position. 312. The method for optimizing the blade axis position of the water pump under all operating conditions according to claim 1 , characterized in that according to the determination of the small region of the optimal blade axis position of the water pump under all the operating conditions as described in step E claim 1 , a range width between the two blade resultant hydraulic pressure action lines farthest from each other approximately on a calculation cylindrical surface is s claim 1 , the range width s is divided into k equal parts claim 1 , starting from the action line claim 1 , closer to the current blade axis claim 1 , in the two blade resultant hydraulic pressure action lines farthest from each other claim 1 , blade axes claim 1 , claim 1 , . . . claim 1 , k−1 claim 1 , k are set at the equal parts to the other end of the range with the width s claim 1 , and distances between the k blade axes and the starting resultant action line are set as s/k claim 1 , 2 s/k claim 1 , . . . (k−1)s/k claim 1 , s respectively; a coordinate system is established claim 1 , an ...

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Номер записи: 83
08-06-2017 дата публикации

COMPRESSED GAS ENERGY STORAGE AND HARVESTING SYSTEM AND METHOD WITH STORAGE OF THE HEAT BY MEANS OF A RADIAL EXCHANGER

Номер: US20170160019A1
Автор: POURIMA Christophe
Принадлежит:

The present invention relates to an AACAES system and method in which balls make it possible to store heat. The heat exchanges are produced by means of at least one radial heat exchanger, in which the balls and a first fluid circulate, the first fluid passing radially through means for circulating the balls. 1. A compressed gas energy storage and harvesting system comprising at least one gas compression means , storage means for said compressed gas , at least one expansion means for said compressed gas , heat exchange means between said compressed gas and heat storage balls , storage means , for said heat storage balls , said heat exchange means being arranged at the output of said gas compression means and/or at the input of said gas expansion means , characterized in that said heat exchange means comprise at least one radial exchanger , in which a first fluid and said heat storage balls circulate to exchange heat , said first fluid circulating within said radial exchanger by passing radially through means for circulating said heat storage balls.2. The system as claimed in claim 1 , in which said radial exchanger comprises an annular space in which said heat storage balls circulate from top to bottom claim 1 , said first fluid circulating from outside said annular space claim 1 , through said annular space claim 1 , to the interior of said annular space.3. The system as claimed in claim 1 , in which said first fluid and said balls circulate in counterflow in said radial exchanger.4. The system as claimed in claim 1 , in which said first fluid is said compressed gas.5. The system as claimed in claim 1 , in which said first fluid is a secondary fluid exchanging heat with said compressed gas.6. The system as claimed in claim 1 , in which said system comprises at least two storage means for said heat storage balls claim 1 , said heat storage balls circulating from a first storage means to a second storage means through at least one radial exchanger.7. The system as ...

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Номер записи: 84
18-06-2015 дата публикации

Gas turbine device using supercritical fluid as cooling fluid

Номер: US20150167554A1
Автор: Beom Seok Kim, Ho Kyu Moon, Hyung Hee Cho, Jun Su Park, Kyung Min Kim, Seon Ho Kim
Принадлежит: Industry Academic Cooperation Foundation of Yonsei University

The present invention relates to a gas turbine device using a supercritical fluid as a cooling fluid, the gas turbine device having a compressor for compressing air, a combustor for burning the air emitted from the compressor and fuel, and a turbine driven by the burned gas emitted from the combustor, wherein the gas turbine device includes cooling passages formed in the combustor and the turbine, along which the supercritical fluid as a cooling fluid flows to allow the combustor and the turbine to be cooled.

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Номер записи: 85
24-06-2021 дата публикации

Method for controlling the outlet pressure of a compressor

Номер: US20210190084A1
Автор: Marina DARRY
Принадлежит: Cryostar SAS

Method for controlling a compressor comprising a last stage ( 40 ) and a compressor load controller ( 90 ), a set point outlet pressure corresponding to the consumer needed pressure, being given in the load controller ( 90 ) comprising the steps of: a—measuring the temperature at the inlet of the last stage ( 40 ), b—measuring the ratio between the outlet and inlet pressure of the last stage ( 40 ), c—computing a coefficient (Ψ) based on the value of the inlet temperature (Tin) and on the pressure ratio (Pout/Pin), d—if the coefficient (Ψ) is in a predetermined range, changing the set point outlet pressure by a new greater set point outlet pressure until the coefficient (Ψ) computed with the new set point outlet pressure goes out of the predetermined range, and e—adapting the pressure of the fluid coming out of the compressor in a pressure regulator ( 100 ) to the consumer needed pressure.

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Номер записи: 86
14-06-2018 дата публикации

System and Method for Improving Output and Heat Rate for a Liquid Natural Gas Combined Cycle Power Plant

Номер: US20180163570A1
Автор: Darmoyo Adrianto, Eng Cong Cheng, Gupta Abhijit, Smith Raub
Принадлежит:

A combined cycle power plant and heating and cooling system and method for the power plant is disclosed as having a liquid natural gas supply and a vaporizer configured to vaporize the liquid natural gas into natural gas that is supplied to a gas performance heater before entering a combustion section of a gas turbine. A closed cooling water circuit is in fluid communication with at least one power plant component such as a gas turbine inlet heating/cooling coil, a heat recovery heat exchanger, the vaporizer, and mixtures thereof. An open cooling water circuit is in fluid communication with at least one power plant component such as at least one steam turbine condenser, the heat recovery heat exchanger, and mixtures thereof. 1. A heating and cooling system for a combined cycle power plant , comprising:a liquid natural gas supply and a vaporizer configured to vaporize the liquid natural gas into natural gas that is supplied to a gas performance heater before entering a combustion section of a gas turbine; 'wherein, the vaporizer is configured so that vaporized cooling is recovered by the closed cooling water circuit and transferred to at least one cooled power plant component; and', 'a closed cooling water circuit in fluid communication with at least one power plant component comprising a gas turbine inlet heating/cooling coil, a heat recovery heat exchanger, the vaporizer, a sparging unit, and mixtures thereof;'} 'wherein, the at least one steam turbine condenser is configured so that waste heat is recovered by the open cooling water circuit and transferred to at least one heated power plant component via the heat recovery heat exchanger.', 'an open cooling water circuit in fluid communication with at least one power plant component comprising at least one steam turbine condenser, the heat recovery heat exchanger, and mixtures thereof;'}2. The heating and cooling system of claim 1 , wherein the open cooling water circuit is in fluid communication with at least one ...

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Номер записи: 87
30-05-2019 дата публикации

BOV VALVE USING DIFFERENTIAL PRESSURE OF AIR

Номер: US20190162198A1
Автор: KIM Minsoo
Принадлежит:

The present invention relates to a BOV valve using differential pressure of air and, more particularly, to a BOV valve that is operated using differential pressure of air. 1{'b': 100', '110', '130', '120, 'a BOV base () having a flange () on the top, having an internal space, having a blowing port () connected with an outlet of a turbo blower, and having a discharge port () for discharging air flowing inside through the blowing port;'}{'b': 200', '210', '230', '220, 'a diaphragm () having a side being in contact with the flange, having a slope () inside, including a spring-coupling plate () formed on a side of the slope, and having a spring-coupling portion () at the center;'}{'b': '300', 'an air hole () formed at a side of the slope of the diaphragm to function as an air channel;'}{'b': '400', 'a spring () coupled to a spring-coupling portion formed at the center of the diaphragm;'}{'b': 500', '510', '520', '530, 'a BOV bonnet () having a bonnet flange () formed on the edge to be coupled to the flange of the BOV base with the diaphragm therebetween, a bonnet protrusion () formed inside the bonnet flange and protruding upward such that the bottom is higher than the bottom of the bonnet flange, and a center hole () formed at the center of the bonnet protrusion;'}{'b': '600', 'a pipe () having a first end coupled to the center hole and a second end coupled to a solenoid valve; and'}{'b': '700', 'a solenoid valve () coupled to the pipe.'}. A BOV valve using differential pressure of air, the BOV valve comprising: The present invention relates to a BOV valve using differential pressure of air and, more particularly, to a BOV valve that is operated using differential pressure of air.A turbo blower is a machine, which suctions and blows external air by rotating an impeller at a high speed using torque of a motor, and is used for transfer of powder or aeration at a sewage plant etc.According to such a turbo blower, rotation of the motor does not reach a steady state in the ...

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Номер записи: 88
30-05-2019 дата публикации

Centrifugal pump cover

Номер: US20190162204A1
Автор: Damiano Montagner, Federico Zoppas, Maurizio Biasi, Stefano Zanella
Принадлежит: IRCA SpA Industria Resistenze Corazzate e Affini

A cover (1) for a centrifugal pump which comprises a heating element (8), which has a heating stretch (10) and two end stretches (12) connected to the heating stretch (10), wherein the heating element (8) crosses the cover (1) so that the heating stretch (10) is under the cover (1) and the two end stretches (12) are over the cover (1), wherein at least one safety device (20), sensitive to the temperature of the electric resistor (8), fixed to the outer face (6), is provided and at least one control device (22), sensitive to both the temperature of the liquid and the temperature of the electric resistor (8), fixed to the outer face (6), is provided, wherein at least one first portion (14) of the heating stretch (10) is in contact with the cover (1), so that the heating stretch (10) is adapted to be contact with the liquid.

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Номер записи: 89
01-07-2021 дата публикации

Systems and methods for operating a turbocharged gas turbine engine

Номер: US20210199025A1
Автор: Deoras PRABHUDHARWADKAR, Jalal Hunain Zia, Majed Sammak
Принадлежит: General Electric Co

A power generation system includes a combustion system, a turbocharger, and a heat recovery system. The combustion system is configured to combust a fuel with a flow of air. The combustion system is further configured to generate an exhaust stream. The turbocharger is configured to compress a flow of compressed air and to channel the flow of compressed air to the combustion system. The combustion system is configured to combust the fuel with the flow of compressed air and an additional flow of air. The heat recovery system is configured to recover heat from the exhaust stream and to drive the turbocharger. The heat recovery system uses a supercritical working fluid to absorb heat from the exhaust stream and to drive the turbocharger.

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Номер записи: 90
01-07-2021 дата публикации

Radial Turbomachine

Номер: US20210199126A1
Автор: Daniel HILPERT, Ernst Scherrer, Peter Meier, Ronny ZWAHLEN
Принадлежит: Micronel AG

A radial turbomachine has a first housing part and a second housing part, which jointly form and delimit a flow channel. The first housing part forms a motor chamber for accommodating a drive motor, and the second housing part forms a gas inlet. Furthermore, a radial impeller is provided, which can be driven about an axis of rotation by the drive motor in order to suction a gas from outside the turbomachine through the gas inlet into the flow channel and to convey said gas out of the flow channel through a gas outlet to the outside. The first housing part or the second housing part forms the gas outlet at a radial distance from the axis of rotation and peripherally delimits the gas outlet.

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Номер записи: 91
21-06-2018 дата публикации

DUAL FUEL RADIAL FLOW NOZZLES

Номер: US20180172274A1
Автор: PROCIW Lev Alexander, Ryon Jason A.
Принадлежит:

A nozzle includes a nozzle body defining a longitudinal axis. The nozzle body includes an inner air passage fed by a radial swirler and having a converging conical cross-section. A first fuel circuit is radially outboard from the air passage with respect to the longitudinal axis. A second fuel circuit is radially outboard from the first fuel circuit with respect to the longitudinal axis, wherein each of the first fuel circuit and the second fuel circuit extends from a respective fuel circuit inlet to a respective annular fuel circuit outlet. An outer air passage is defined between a fuel circuit outer wall and an outer air passage wall, wherein the outer air passage is a converging non-swirling outer air passage. 1. A nozzle comprising:a nozzle body defining a longitudinal axis and including:an inner air passage fed by a radial swirler and having a converging conical cross-section;a first fuel circuit radially outboard from the air passage with respect to the longitudinal axis;a second fuel circuit radially outboard from the first fuel circuit with respect to the longitudinal axis, wherein each of the first fuel circuit and the second fuel circuit extends from a respective fuel circuit inlet to a respective annular fuel circuit outlet; andan outer air passage defined between a fuel circuit outer wall and an outer air passage wall, wherein the outer air passage is a converging non-swirling outer air passage.2. The nozzle as recited in claim 1 , wherein at least one of the first and second fuel circuits includes a plurality of helical passages claim 1 , wherein each helical passage opens tangentially with respect to the respective fuel circuit outlet.385. The nozzle as recited in claim 2 , wherein the helical passages define a flow exit angle relative to the longitudinal axis of at least ° .4. The nozzle as recited in claim 1 , wherein the second fuel circuit is defined between a fuel circuit outer wall and an intermediate fuel circuit wall claim 1 , and wherein the ...

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Номер записи: 92
22-06-2017 дата публикации

Advanced Humid Air Gas Turbine System

Номер: US20170175623A1
Автор: Sato Kazuhiko, TAKAHASHI Yoshitaka, TAKEDA Yasushi
Принадлежит:

One of the objects of the invention is to provide a water-saving type advanced humid air gas turbine system (AHAT) that can decrease the amount of makeup water to be supplied from the outside, by reducing the amount of water consumed when the gas turbine system is starting up, shut down, or subjected to load rejection. The gas turbine system includes a compressor, the compressed air header for generating humidified combustion air, a combustor for generating combustion gas, and the turbine. When the gas turbine system is starting up, shut down or subjected to load rejection, steam coming from the heat recovery steam generator is recovered by blocking the first steam system and making the second steam system communicate with the heat recovery steam generator. 1. An advanced humid air gas turbine system comprising:a gas turbine system that includesa compressor for compressing air,a compressed air header for mixing high-pressure air introduced from the compressor with steam to generate humidified combustion air,a combustor for mixing combustion air from the compressed air header with fuel for sake of combustion so as to generate combustion gas, anda turbine driven by the combustion gas that is generated by the combustor;a heat recovery steam generator for generating steam by use of exhaust gas from the turbine;a water recovery system disposed on a downstream side of the heat recovery steam generator, the water recovery system recovering moisture contained in the exhaust gas;a first steam system for supplying steam, coming from the heat recovery steam generator, to the compressed air header;a second steam system for supplying steam, coming from the heat recovery steam generator, to the heat recovery steam generator or the water recovery system; anda steam nozzle;wherein when the gas turbine system is starting up, shut down, or subjected to load rejection, steam coming from the heat recovery steam generator is recovered by blocking the first steam system and making the ...

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Номер записи: 93
06-06-2019 дата публикации

COMBUSTION CHAMBER ARRANGEMENT

Номер: US20190170352A1
Автор: MARTIN Damian, RIMMER John E., Wilson David P.
Принадлежит: ROLLS-ROYCE PLC

A combustion chamber arrangement comprises an annular combustion chamber, a plurality of circumferentially arranged vanes and a radially inner sealing ring. The vanes are arranged at the axially downstream end of the annular combustion chamber. Each of the vanes comprises an aerofoil extending radially between a radially inner platform and a radially outer platform. The radially inner sealing ring forms a seal between a downstream end of a radially inner annular wall structure of the combustion chamber and the radially inner platforms of the vanes. A portion of the axial length of the radially inner sealing ring comprises a radially inner wall and a radially outer wall spaced radially from the radially inner wall to define a chamber. The radially inner wall has apertures to supply coolant into the chamber and the radially outer wall has effusion cooling apertures to supply coolant onto the surface of the radially outer wall. 1. A combustion chamber arrangement comprising an annular combustion chamber , a plurality of circumferentially arranged vanes , a radially inner sealing ring and a radially outer sealing ring ,the annular combustion chamber comprising a radially inner annular wall structure, a radially outer annular wall structure spaced radially outwardly from the radially inner annular wall structure and an axially upstream annular wall structure, an upstream end of the radially inner annular wall structure being secured to a radially inner end of the axially upstream annular wall structure and an upstream end of the radially outer annular wall structure being secured to a radially outer end of the axially upstream annular wall structure,the vanes being arranged at the axially downstream end of the annular combustion chamber, each of the vanes comprising a radially inner platform, a radially outer platform and an aerofoil extending radially between the radially inner platform and the radially outer platform,the radially inner sealing ring being arranged to ...

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Номер записи: 94
28-05-2020 дата публикации

Waste Heat Recovery System

Номер: US20200165974A1
Автор: Miller Brandon Wayne, Ripplinger Thomas Helmut, Smith Justin Paul
Принадлежит:

A turbine engine includes a compressor section, a combustion section, a turbine section, and an exhaust section in serial flow order and together defining a core air flowpath; a fuel delivery system for providing a flow of fuel to the combustion section; and a waste heat recovery system. The waste heat recovery system includes a heat source exchanger in thermal communication with the turbine section, the exhaust section, or both; a heat sink exchanger in thermal communication with the fuel delivery system, the core air flowpath, or both; a thermal transfer bus including a thermal transfer fluid and extending from the heat source exchanger to the heat sink exchanger; and a pump in fluid communication with the thermal transfer bus downstream of the heat source exchanger and upstream of the heat sink exchanger for increasing a temperature and a pressure of the thermal transfer fluid in the thermal transfer bus. 1. A gas turbine engine comprising:a compressor section, a combustion section, a turbine section, and an exhaust section in serial flow order and together defining a core air flowpath, the compressor section defining a downstream end;a fuel delivery system for providing a flow of fuel to the combustion section; and a heat source exchanger in thermal communication with the turbine section, the exhaust section, or both;', 'a heat sink exchanger in thermal communication with the fuel delivery system, the core air flowpath upstream of the combustion section, or both;', 'a thermal transfer bus comprising a thermal transfer fluid and extending from the heat source exchanger to the heat sink exchanger; and', 'a pump in fluid communication with the thermal transfer bus downstream of the heat source exchanger and upstream of the heat sink exchanger for increasing a temperature and a pressure of the thermal transfer fluid in the thermal transfer bus., 'a waste heat recovery system comprising'}2. The gas turbine engine of claim 1 , wherein the thermal transfer bus is a ...

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Номер записи: 95
09-07-2015 дата публикации

FILAMENTOUS TURBINE

Номер: US20150192018A1
Автор: Shi Jian
Принадлежит:

A kind of filamentous turbine comprises a shell body and a rotor, the shell body is provided with a nozzle, the nozzle is used to eject gas into the shell body, the rotor which is arranged in the shell body comprises a rotor shaft, two fixing disks and a filamentous structure, the two fixing disks are mounted to the rotor shaft, the filamentous structure is mounted between the two fixing disk. The filamentous structure for this kind of filamentous turbine replaces the thin and circular disk of the traditional Tesla turbine, and the filamentous structure provides good integral rigidity and is not easy to deform, so that the rotor can be made larger in diameter, and the filamentous structure facilitates to reduce the machine noise. 1. A filamentous turbine , characterized in that , comprising:{'b': 2', '1, 'a shell (), where a nozzle () is provided thereon and the nozzle is used to spray gas into said shell;'}{'b': 7', '3', '4, 'a rotor (, , ), said rotor being located in said shell, said rotor comprising{'b': '7', 'a rotor shaft ();'}{'b': '3', 'two fixed discs (), fixed to the rotor shaft; and'}{'b': '4', 'a filamentous structure (), fixed between the two fixed discs.'}243. The filamentous turbine as recited in claim 1 , characterized in that: the filamentous structure () is vertical to a surface of respective fixed discs () with a multilayered bird-cage-like shape.34. The filamentous turbine as recited in claim 1 , characterized in that: the filamentous structure () is arranged in a crisscross pattern and shaped a three-dimensional network.412. The filamentous turbine as recited in claim 1 , characterized in that: the nozzle () is disposed along the tangential direction of the inner wall of said shell ().5765. The filamentous turbine as recited in claim 1 , characterized in that: the rotor shaft () is hollow and the surface thereof is provided with vent holes () claim 1 , where the vent holes extend through the hollow of the rotor shaft to join the vent ().623897. ...

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Номер записи: 96
09-07-2015 дата публикации

INLINE POWER GENERATOR

Номер: US20150192030A1
Автор: Leahy Malcolm Frederick, Rubinshtein Peter, Soper Kevin James
Принадлежит:

An electrical generator, comprising a rotatable impeller locatable within a flow path of a conduit. The impeller is rotated by fluid flowing along said flow path. The impeller comprises a magnetic portion, the generator further including a stator located external of the flow path. The stator generating electrical power in response to rotation of the magnetic portion. 1. An electrical generator , comprising a rotatable impeller locatable within a flow path of a conduit , the impeller being rotated by a fluid flowing along said flow path , the impeller comprising a magnetic portion , the apparatus further including a stator for location external to said flow path , said stator generating electrical power in response to rotation of said magnetic portion.2. The electrical generator of wherein the impeller is rotatable about an axis of a shaft within said conduit the shaft being co-axial with said fluid flow.3. The electrical generator of wherein claim 1 , the impeller comprises at least a plurality of blades each blade extending from radially opposite portions of the shaft claim 1 , a free end of the blades spaced apart from an internal surface of the conduit claim 1 , the magnetic portions being carried at the free ends of the blades.4. The electrical generator of wherein the stator is held in place against the outside of the conduit.5. An electrical generator comprisinga coupling, the coupling comprising a tube for connection with a flow path of a fluid conduit,an impeller comprising blades fixed to a shaft, free ends of the blades carrying magnetic portionsthe shaft aligned with the flow path inside the tube, a first and second end of the shaft supported relative to an inside surface of the tube by respective first and second mounting means, anda stator connected to the outside of tube and so aligned with the magnetic portions, that an electrical current is induced on rotation of the impeller.6. The generator of further comprising at least one fittable support frame ...

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Номер записи: 97
13-06-2019 дата публикации

METHOD FOR STORING ENERGY AND FOR DISPENSING ENERGY INTO AN ENERGY SUPPLY GRID, PRESSURIZED GAS STORAGE POWER PLANT AND COMPUTER PROGRAM

Номер: US20190178162A1
Автор: LITTMANN Wolfgang
Принадлежит:

The invention relates to a method for storing energy and for dispensing energy into an energy supply grid by means of a pressurized gas storage power plant, which has at least one first storage chamber and at least one second storage chamber separate from the first, wherein in order to store energy pressurized gas is taken from the lower-pressure storage chamber, is compressed by means of a compression machine and the compressed pressurized gas exiting the compression machine is routed into the other storage chamber; in order to dispense energy pressurized gas is taken from the higher-pressure storage chamber, is routed through an expansion machine and the expanded pressurized gas exiting the expansion machine is transferred into the other storage chamber, wherein the expansion machine dispenses energy to the energy supply grid, wherein the pressurized gas is heated by means of a heating device prior to or upon supply to the expansion machine. The invention also relates to a corresponding pressurized gas storage power plant and to a computer program for carrying out the method. 1. A method for storing energy and for dispensing energy into an energy supply grid by a pressurized gas storage power plant , comprising:storing energy by compressing pressurized gas taken from a first storage chamber with a compression machine to produce compressed pressurized gas, and routing the compressed pressurized gas into a second storage chamber that is different from the first storage chamber; anddispensing energy by expanding the compressed pressurized gas taken from the second storage chamber by routing the compressed pressurized gas through an expansion machine to produce expanded pressurized gas wherein the expansion machine dispenses energy to the energy supply grid; andheating the compressed pressurized gas with a heating device before or during supply of the compressed pressurized gas to the expansion machine.2. The method as claimed in wherein the compressed pressurized gas ...

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Номер записи: 98
04-06-2020 дата публикации

Diffuser for a Radial Compressor

Номер: US20200173462A1
Автор: Daniel Bernhard RUSCH, Rene Hunziker
Принадлежит: ABB Schweiz AG

The invention relates to a diffuser for a radial compressor, comprising a flow channel defined by a first side wall and a second side wall, a diffuser vane ring with a plurality of diffuser vanes that are at least partially arranged in the flow channel, each of the diffuser vanes having a pressure side and a suction side, a plurality of diffuser passages, said diffuser passages being formed between every two adjacent diffuser vanes of the plurality of diffuser vanes, and circuation openings, each circulation opening connecting the flow channel to a diffuser cavity, at least two circulation openings being associated with one diffuser passage, and a circulation opening associated with a diffuser passage being fluidically connected to another circulation opening associated with the same diffuser passage or to a circulation opening associated with another diffuser passage, via the diffuser cavity.

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Номер записи: 99
04-06-2020 дата публикации

Refrigerant compressor

Номер: US20200173464A1
Автор: Justin Jongsik OH
Принадлежит: Danfoss AS

One exemplary embodiment of this disclosure relates to a refrigerant compressor. The compressor includes an axial section having a plurality of blades and vanes and a centrifugal section having an impeller. The centrifugal section is arranged downstream of the axial section.

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Номер записи: 100