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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 3579. Отображено 100.
26-01-2012 дата публикации

Fluid Machine

Номер: US20120019010A1
Автор: Hirofumi Wada, Shinji Nakamura
Принадлежит: Sanden Corp

Purpose: To provide a fluid machine, the production efficiency and maintenance characteristics of which can be improved while performance is ensured. Means to attain the purpose: A fluid machine ( 14, 102, 108 ) has a plurality of fluid units ( 16, 20 ) that include rotating bodies ( 40, 66 ) and suck/discharge a working fluid along with the rotation of the rotating bodies, and a drive shaft ( 72 ) connected with the rotating bodies of the fluid units; and an Oldham's coupling ( 85 ) is mounted on a shaft portion between each two adjacent rotating bodies of the drive shaft.

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Номер записи: 1
31-05-2012 дата публикации

Compressed Air Engine And Motor Vehicle

Номер: US20120132477A1
Автор: Yang Cong
Принадлежит: Individual

A compressed air engine comprises a housing and an impeller body fixed on a primary power output shaft and located within the housing. An ejecting inlet ejects air to the impeller body in the housing. Working chambers are provided on the impeller body. The inner surface of the housing closes the working chambers so that the compressed air ejected to the working chambers pushes the impeller body to rotate and is temporarily stored in the working chamber, and an ejecting outlet is provided on the housing so that the compressed air temporarily stored in the working chamber expands outwards when the compressed air is rotated to the gas ejecting outlet and do work to further push the impeller body to rotate.

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Номер записи: 2
06-09-2012 дата публикации

Turbine drive-train apparatus

Номер: US20120225750A1
Автор: Brian Allen Rittenhouse, Daniel Richard Waugh, Jason Dean Fuller, Justin Aaron Allen, Karl Dean Minto
Принадлежит: General Electric Co

An apparatus configured to increase the operational range of a turbine is disclosed. In one embodiment, an apparatus includes: a turbine coupled to a driveshaft; a drive-train coupled to the driveshaft; a first torque convertor coupled to the drive-train, the first torque convertor being configured to deliver an operational torque to the drive-train; a second torque convertor coupled to the first torque convertor, the second torque convertor being configured to deliver a torque to the first torque convertor; a first motor coupled to the second torque convertor, the first motor being configured to deliver a power input to the second torque convertor; and a control system operably connected to at least one of the first torque convertor and the second torque convertor, the control system configured to monitor and adjust a speed of the drive-train by controlling at least one of the operational torque provided by the first torque converter and the torque provided by the second torque converter.

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Номер записи: 3
20-12-2012 дата публикации

Airflow based microturbine power supply

Номер: US20120319408A1
Автор: Vadim Plotsker
Принадлежит: BAE Systems Information and Electronic Systems Integration Inc

An airflow based microturbine power supply is disclosed. In one embodiment, the airflow based microturbine power supply includes at least one microturbine configured to circulate upon receiving airflow and to convert to mechanical energy. Further, the airflow based microturbine power supply includes a generator coupled to the at least one microturbine to convert the mechanical energy of the microturbine into electrical energy via electromagnetic induction.

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Номер записи: 4
21-03-2013 дата публикации

Device for Driving an Auxiliary Unit

Номер: US20130071233A1
Автор: FREHLAND Peter
Принадлежит:

A device for driving an auxiliary unit, in particular a high-pressure pump, includes a rotatably supported drive shaft of an internal combustion engine, wherein the drive shaft and a unit shaft of the auxiliary unit are operatively connected to each other by a coupling. The unit shaft has a first bearing on the side facing away from the coupling, and the coupling is a second bearing for the unit shaft. The device provides a low-cost, acoustically inconspicuous, tolerance-insensitive coupling solution for connecting, for example, a high-pressure pump camshaft to an available intake or exhaust camshaft. 1. A device for driving an auxiliary unit by a rotatably disposed driveshaft of an internal-combustion engine , the device comprising:a unit shaft of the auxiliary unit;a coupling by which the driveshaft and the unit shaft are coupled in a mutually operative position;a first bearing arranged on a side of the unit shaft facing away from the coupling; anda second bearing of the unit shaft being provided by the coupling.2. The device according to claim 1 , wherein the auxiliary unit is a high-pressure fuel pump.3. The device according to claim 1 , wherein the coupling comprises a shaft end having an interior profile and a complementary shaft end having an exterior profile.4. The device according to claim 3 , wherein the complementary interior and exterior profiles are polygonal profiles.5. The device according to claim 4 , wherein at least one of the drive shaft and the unit shaft has a cam that generates an alternating torque during operation of the device claim 4 , said polygonal profiles corresponding to the alternating torque.6. The device according to claim 3 , wherein the shaft end with the exterior profile has a circumferential radius in an axial direction.7. The device according to claim 4 , wherein the shaft end with the exterior profile has a circumferential radius in an axial direction.8. The device according to claim 5 , wherein the shaft end with the exterior ...

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Номер записи: 5
28-03-2013 дата публикации

Method of operating a gas turbine and gas turbine

Номер: US20130074511A1
Автор: Edwin Snoeks, Irina Tanaeva
Принадлежит: Individual

A gas turbine system comprises a gas turbine having a low pressure compression stage and a high pressure compression stage, a combustion chamber, and an expansion stage connected to the combustion chamber. The low pressure compression stage and the high pressure compression stage are connected with each other via an intercooling stage, wherein the low pressure compressed air stream from the low pressure compression stage is chilled to an intercooling temperature that is lower than the ambient temperature of the air source from which the air stream was supplied to the low pressure compression stage of the gas turbine.

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Номер записи: 6
02-05-2013 дата публикации

Gearbox in a turbine engine

Номер: US20130104681A1
Автор: Jean-Pierre Elie Galivel
Принадлежит: SNECMA SAS

A gearbox in a turbine engine for imparting rotary drive to at least one piece of rotary equipment, the gearbox including a transmission shaft guided in rotation in bearings and carrying a toothed wheel meshing with at least one rotary drive gearwheel. One of the bearings is a rolling bearing mounted inside the toothed wheel in a radial plane containing the toothed wheel and the drive gearwheel, and another of the bearings is a smooth bearing for taking up forces tending to tilt the transmission shaft.

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Номер записи: 7
04-07-2013 дата публикации

WINDTRACKER TWIN-TURBINE SYSTEM

Номер: US20130170986A1
Автор: Steel Dennis Patrick
Принадлежит:

The turbine system for wind and/or water power, wherein the radial turbines have a rotor which can rotate about an axis and comprises one or more turbine blades, wherein the turbine blades are aligned parallel to the rotor, wherein the turbine blades are arranged within a cylindrical shell, which is arranged concentrically around the axis and has an outer radius R and an inner radius R, is characterized in that the turbine blades have a specific geometry and in that two radial turbines () which are aligned alongside one another and parallel are arranged, which radial turbines () are connected to one another and can pivot about a pivoting axis () parallel to the turbine axes (), wherein the pivoting axis and the guide surfaces () are not located on the connecting line between the turbine axes, and are both located on the same side of the connecting line. It is proposed that the abstract be published without any drawing. 2. The turbine system according to claim 1 , wherein a deflector surface orientated parallel to the rotor is arranged outside the cylindrical shell claim 1 , and is of a width{'br': None, 'i': B', 'f', 'R, '3=9×1'}{'b': '9', 'claim-text': {'b': '2', 'claim-text': {'br': None, 'i': A', 'f', 'R, '2=6×1'}, 'the edge of the deflector surface facing the turbine shaft being at a distance A'}, 'where f=0.7 to 2.5,'}{'b': '6', 'where f=0.25 to 0.55 from a first longitudinal section plane through the turbine shaft,'}{'b': '1', 'claim-text': {'br': None, 'i': A', 'f', 'R, '1=5×1'}, 'and at a distance A'}{'b': '5', 'claim-text': {'br': None, 'α=40° to 60°'}, 'where f=1.00 to 1.10 from a second longitudinal section plane through the turbine shaft, the second longitudinal section plane being perpendicular to the first longitudinal section plane, and in that the deflector surface has an angle of incidence'}with respect to the first longitudinal section plane.31. The turbine system according to claim 1 , wherein the total width B of the turbine blade is{'br': None, ...

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Номер записи: 8
10-04-2014 дата публикации

Super Efficient Regulator

Номер: US20140096513A1
Автор: Eric Trevor Ensley, Frank Benjamin Springett, Walter Warren Weaver
Принадлежит: National Oilwell Varco LP

A system for producing mechanical energy. In some embodiments, the system includes a first source providing a first fluid, a fluid pressurization device, a second source supplying a second fluid, a first motor, and a second motor. The fluid pressurization device draws in the first fluid from the first source and increases the pressure of the first fluid. The first motor is driven by the second fluid, the second fluid decreasing in pressure and the first motor powering the fluid pressurization device as the second fluid passes through the first motor. The second motor receives a mixture of the first fluid from the first motor and the second fluid from the fluid pressurization device, whereby the second motor produces the mechanical energy.

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Номер записи: 9
01-01-2015 дата публикации

Energy Recovery Apparatus for a Refrigeration System

Номер: US20150001849A1
Автор: Garrison Bobby D., Post Steven W.
Принадлежит:

An energy recovery apparatus for use in a refrigeration system, comprises an intake port, a nozzle, a turbine and a discharge port. The intake port is adapted to be in fluid communication with a refrigerant cooler of a refrigeration system. The nozzle comprises a fluid passageway. The nozzle is configured to reduce temperature and pressure of refrigerant discharged from the refrigerant cooler and increase velocity of the refrigerant as it passes through the fluid passageway. The turbine is positioned relative to the nozzle and configured to be driven by refrigerant discharged from the fluid passageway. The discharge port is downstream of the turbine and is configured to be in fluid communication with an evaporator of the refrigeration system. 1. An energy recovery apparatus for use in a refrigeration system , the refrigeration system comprising an evaporator , a compressor and a refrigerant cooler , the refrigeration system being configured to circulate refrigerant along a flow path such that the refrigerant flows from the evaporator to the compressor , and from the compressor to the refrigerant cooler , and from the refrigerant cooler to the evaporator , the energy recovery apparatus being adapted and configured to be in the flow path operatively between the refrigerant cooler and the evaporator , the energy recovery apparatus comprising:an intake port adapted to permit refrigerant to flow into the energy recovery apparatus;a discharge port adapted to permit refrigerant to flow out of the energy recovery apparatus;{'sup': '1/2', 'a nozzle comprising a conduit region downstream of the intake port, the conduit region defining a passageway, the passageway being adapted to constitute a portion of the flow path, the passageway having an upstream cross-section, a downstream cross-section, a passageway length extending from the upstream cross-section to the downstream cross-section, and a discharge end, the downstream cross-section of the passageway being closer to the ...

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Номер записи: 10
05-01-2017 дата публикации

FAN-DRIVE GEAR SYSTEM WITH SEPARATE SCAVENGE PUMP

Номер: US20170002687A1
Автор: Dolman Paul H.
Принадлежит: UNITED TECHNOLOGIES CORPORATION

A lubrication circulation system may comprise a first oil pump configured to retrieve oil from a bearing compartment, and a second oil pump located separately from the first oil pump and configured to retrieve the oil from a fan-drive gear system compartment. The first oil pump may be configured to provide the oil to the bearing compartment and the fan-drive gear system compartment. 1. A lubrication circulation system , comprising:a first oil pump configured to retrieve oil from a bearing compartment; anda second oil pump located separate from the first oil pump and configured to retrieve the oil from a fan-drive gear system compartment, wherein the first oil pump is configured to provide the oil to the bearing compartment and the fan-drive gear system compartment.2. The lubrication circulation system of claim 1 , further comprising an epicyclic gear system in the fan-drive gear system compartment claim 1 , wherein the second oil pump is configured to retrieve the oil from the epicyclic gear system.3. The lubrication circulation system of claim 1 , wherein the second oil pump is located in the fan-drive gear system compartment.4. The lubrication circulation system of claim 1 , further comprising a scavenge line fluidly coupled to the fan-drive gear system compartment and the second oil pump.5. The lubrication circulation system of claim 4 , wherein the scavenge line comprises a diameter less than 2 inches.6. The lubrication circulation system of claim 1 , further comprising an oil tank claim 1 , wherein the second oil pump and the first oil pump urge the oil to the oil tank.7. The lubrication circulation system of claim 6 , wherein the first oil pump is configured to pump the oil from the oil tank into the bearing compartment and the fan-drive gear system compartment.8. The lubrication circulation system of claim 1 , wherein the second oil pump is located closer to the fan-drive gear system compartment than the first oil pump.9. A gas turbine engine claim 1 , ...

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Номер записи: 11
07-01-2016 дата публикации

HYDRODYNAMIC ENERGY GENERATION SYSTEM WITH NEUTRALIZED PRESSURE PUMP

Номер: US20160003089A1
Автор: Hanna Ibrahim
Принадлежит:

A hydrodynamic energy generation system comprises a pump and three vertically aligned compartments and a fourth compartment proximate to the lower ends of the vertically aligned compartments. Each of the three vertically aligned compartments has an opening on an upper end and a lower end. The first compartment has a first turbine mechanically coupled to a first generator producing electrical power when the first turbine is moved by water that falls into the first compartment. The first compartment has a controlled water level under the first turbine. A second turbine proximate to the opening at the second compartment's lower end is mechanically coupled to a pump through gear box and/or second generator producing electrical or rotational power when the second turbine is moved by water flowing out of the second compartment's lower end opening. A pump for moving water from the first and second compartments through the fourth compartment and into the third compartment is at least partially powered by the second generator, mechanically by second turbine and by an external power source according to the following formula (pumping energy=*disk ratio*flow+external energy), where is the pressure change regardless of pumping height and disk ratio is the (gear box modified) ratio between the driving turbine disk under second compartment and the driving disk of the pump. 1. A hydrodynamic energy generation system , comprising:a housing comprising a hollow interior;a pump located at a bottom of the system, the pump equipped with a first fluid inlet providing fluid at a low head pressure and a second fluid inlet at a high head pressure;a first vertically aligned compartment within the housing, wherein the first vertically aligned compartment has a first opening on an upper end and a second opening on a lower end, which interfaces with the first fluid inlet;a first water wheel located below the opening on the upper end and within the first compartment, wherein the first water wheel ...

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Номер записи: 12
07-01-2016 дата публикации

NACELLE INTERNAL AND EXTERNAL FLOW CONTROL

Номер: US20160003091A1
Автор: Malecki Robert E.
Принадлежит:

A nacelle () for a gas turbine engine () that extends along an engine centerline (CO includes an inner portion (), an outer portion (), and a nacelle flow control system (). The outer portion () surrounds the inner portion () and connects to the inner portion () at a leading edge (). The nacelle flow control system () includes an internal flow control () for the inner portion () and an external flow control () for the outer portion (). 1. A nacelle for a gas turbine engine , the nacelle including an inner portion , a surrounding outer portion , and a leading edge connecting therebetween; the nacelle comprising: an internal flow control for the inner portion for modifying a first airflow, the internal flow control including a first passage for flowing air; and', 'an external flow control for the outer portion for modifying a second airflow, the external flow control including a second passage for flowing air., 'a nacelle flow control system that includes2. The nacelle of claim 1 , wherein the nacelle flow control system further comprises:a pump that provides airflow through at least one of the first and second passages of the nacelle flow control system; anda control valve connected to at least one of the first and second passages and configured to direct flow through the nacelle flow control system.3. The nacelle of claim 2 , wherein the flow control valve is connected to the first and second passages and directs flow through the internal flow control or the external flow control or to neither the internal nor the external flow controls.4. The nacelle of claim 2 , wherein the nacelle flow control system further comprises:a manifold fluidly connected to the pump and to the control valve, wherein the control valve is fluidly connected to the internal flow control; anda second control valve fluidly connected to the manifold, wherein the second control valve is fluidly connected to the external flow control.5. The nacelle of claim 2 , wherein the internal flow control ...

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Номер записи: 13
04-01-2018 дата публикации

SYSTEM AND METHOD FOR A MULTIPHASE HYDROCARBON PUMP HAVING AN AUGER COUPLING

Номер: US20180003022A1
Автор: Draper David R, Grande, III Salvatore F, Suheil Sami
Принадлежит:

A bladeless conical radial rotary machine method and system are disclosed. Turbo-machinery and methods are disclosed for a bladeless conical radial rotary machine wherein fluid is directed axially within the pump body to produce an axial output. The rotor comprises a plurality of spaced apart conical elements. The fluid is smoothly directed to any number of subsequent boundary layer pumping stages which are axially positioned with respect to each other. The fluid is smoothly directed to any number of subsequent boundary layer pumping stages which are axially positioned with respect to each other. A coupling between pumping stages is disclosed. 1. An apparatus comprising:a first rotary machine operable for transformation of energy between rotary mechanical energy and fluid kinetic energy, the rotary machine comprising:a drive shaft;a tubular housing defining a fluid input and a fluid output and a rotor operating region;a rotor mounted within the rotor operating region for rotation about a rotor axis of rotation through the drive shaft, the rotor comprising a first rotor end and a second rotor end, the axis of rotation extending between the first rotor end and the second rotor end, the rotor operating region being positioned between the fluid input and the fluid output; and a plurality of rotor elements for the rotor, the plurality of rotor elements being axially spaced from each other along the rotor, the plurality of rotor elements comprising a plurality of surfaces oriented on the rotor so as to be concentric to the rotor axis of rotation, the plurality of rotor elements axially spaced a distance RD between the rotor elements, defining therebetween a plurality of radial flow paths each having a path width PW defined by the distance RD between the rotor elements, the plurality of rotor elements defining a plurality of centrally positioned apertures that collectively define an unrestricted interior opening that surrounds the drive shaft and connects to the plurality ...

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Номер записи: 14
04-01-2018 дата публикации

GAS TURBINE ENGINE

Номер: US20180003079A1
Автор: MADGE Jason J
Принадлежит: ROLLS-ROYCE PLC

A gas turbine engine comprises a gearbox comprising a sun gear, an annulus gear, a plurality of planet gears and a planet gear carrier. The sun gear meshes with the planet gears and the planet gears mesh with the annulus gear. Each planet gear is rotatably mounted in the planet gear carrier. The planet gear carrier comprises a plurality of axles arranged parallel to the axis of the gearbox. The axially spaced ends of each axle are secured to the planet gear carrier. Each planet gear is rotatably mounted on a corresponding one of the axles by a bearing arrangement. Each bearing arrangement comprises a journal bearing and a rolling element bearing and each planet gear is rotatably mounted on a journal bearing and each journal bearing is rotatably mounted on an axle by at least one rolling element bearing. 1. A gas turbine engine comprising a bearing arrangement for first and second relatively rotatable members , the bearing arrangement comprising a journal bearing and a rolling element bearing , the second member being arranged coaxially around the first member , the second member having a cylindrical inner surface , the rolling element bearing and the journal bearing being arranged radially between the first member and the second member , the rolling element bearing being positioned radially between the first member and the journal bearing and the journal bearing being positioned radially between the rolling element bearing and the second member , the journal bearing comprising a tubular member , the tubular member having a cylindrical outer surface arranged to cooperate with the cylindrical inner surface of the second member , the tubular member and the second member being relatively rotatable , the bearing arrangement comprising a lubricant supply to supply lubricant to the rolling element bearing and the journal bearing having at least one passage extending radially there-through to supply lubricant from the rolling element bearing to the journal bearing.2. A gas ...

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Номер записи: 15
04-01-2018 дата публикации

INTERNAL GEAR PUMP

Номер: US20180003173A1
Автор: CHENOUX MATHIEU, Cornet Albert
Принадлежит: SAFRAN AERO BOOSTERS S.A.

An internal gear pump includes a pinion, a ring arranged around the pinion, and a cylindrical wall arranged around the ring. A support element, on which the pinion and the ring are supported, carries high-pressure liquid towards a recess located at the junction between the ring and the cylindrical wall, and also carries low-pressure liquid towards another recess located at another point of the junction between the ring and the cylindrical wall. The recess allows the load of the ring on the cylindrical wall to be reduced. 1. An internal gear pump comprising:a pinion capable of rotating about a first axis of rotation;a ring arranged around the pinion, having a cylindrical periphery and being configured to rotate about a second axis of rotation that is different to the first axis of rotation and parallel thereto, the pinion and the ring being arranged to delimit a work space comprising a high-pressure space and a low-pressure space;a first support element arranged on a first side of the ring to limit the movement thereof in a first sense along a first orientation that is substantially parallel to the first and second axes of rotation;a second support element arranged on a second side of the ring to limit the movement thereof in a second sense that is opposite the first sense and in the first orientation;a cylindrical wall arranged around the ring to limit the movement thereof in a plane that is substantially perpendicular to the second axis of rotation;a first high-pressure recess in an arc of a circle and in fluid contact with a first portion of the cylindrical periphery of the ring;a first low-pressure recess in an arc of a circle and in fluid contact with a second portion of the cylindrical periphery of the ring, the first high-pressure recess and the first low-pressure recess being separated;a first high-pressure conveying means forming a fluid connection between the high-pressure space and the first high-pressure recess; anda first low-pressure conveying means ...

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Номер записи: 16
03-01-2019 дата публикации

COMPRESSED AIR ENERGY STORAGE AND RECOVERY

Номер: US20190003384A1
Автор: Bannari Abdelfettah
Принадлежит:

A compressed air system energy storage and recovery system has a compressed air tank structured to store compressed air above 200 bars, a heat storage unit containing a heat transfer fluid and having a latent heat storage material, and a heat exchanger. The heat exchanger extracts heat from compressed ambient air above 200 bars for storage and to heat compressed air from the tank above 200 bars prior to expansion and use to recover energy in the air motor. Efficiency of energy storage and heat exchange is improved using pressures above 200 bars. 1. A compressed air system energy storage and recovery system comprising:a compressed air tank structured to store compressed air above 225 bars;a heat storage unit containing a heat transfer fluid and having a latent heat storage material;a heat exchanger connected on one side to the compressed air tank and connectable to an air compressor and an air motor, and on another side receiving said heat transfer fluid to a cold conduit of the heat storage unit and to a hot conduit of the heat storage unit, the heat exchanger configured to extract heat from compressed ambient air above 200 bars for storage and to heat compressed air from said tank above 200 bars prior to expansion and use to recover energy in the air motor.2. The system as defined in claim 1 , wherein said compressed air tank is structured to store compressed air above 275 bars.3. The system as defined in claim 1 , wherein said heat transfer fluid contains a mixture comprising a liquid and particles of said latent heat storage material.4. The system as defined in claim 3 , wherein said mixture comprises oil and salt particles.5. The system as defined in claim 4 , wherein said mixture further comprises metal particles.6. The system as defined in claim 1 , wherein said heat storage unit comprises a first reservoir of cool heat transfer fluid claim 1 , a second reservoir of hot heat transfer fluid claim 1 , and at least one circulation pump.7. The system as defined in ...

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Номер записи: 17
14-01-2016 дата публикации

TURBINE DRIVEN POWER UNIT FOR A CUTTING TOOL

Номер: US20160008937A1
Автор: SANDERS Gerald Jay
Принадлежит:

A turbine power unit for a power tool having a turbine housing with an interior space configured to receive therein a fluid powered turbine supported for rotation on a bearing within the turbine housing. A service opening through the turbine housing into the interior space thereof, the service opening configured to permit installation and removal of a bearing into and out of the interior space of the turbine housing. A removable cover releasably securable to the turbine housing over the service opening and transitionable between an open configuration in which a bearing can be installed into and removed from the interior space of the turbine housing through the service opening and a closed configuration in which an installed bearing within the interior space is secured for operation in the turbine housing. 1. A turbine power unit for a cutting tool , the power unit comprising:a turbine housing having an interior space configured to receive therein a fluid powered turbine supported for rotation on a bearing within the turbine housing;a service opening through the turbine housing into the interior space thereof, the service opening configured to permit installation and removal of the bearings into and out of the interior space of the turbine housing; anda removable cover releasably securable to the turbine housing over the service opening and transitionable between an open configuration in which a bearing can be installed into and removed from the interior space of the turbine housing through the service opening and a closed configuration in which an installed bearing within the interior space is secured for operation in the turbine housing.2. The power unit as recited in claim 1 , further comprising a tool shank claim 1 , wherein the turbine is coupled to the tool shank and the bearing supports the tool shank.3. The power unit as recited in claim 1 , wherein the turbine is supported on the bearing and an additional bearing within the turbine housing claim 1 , at least ...

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Номер записи: 18
11-01-2018 дата публикации

TURBOJET AUTOMOBILE

Номер: US20180009304A1
Автор: CHEN Xiaohui
Принадлежит:

The present invention discloses a turbojet automobile, comprising an air storage bottle in a superhigh-pressure air producing and sealing device, wheels, a chassis, a lever braking device, a spray pipe, a turbine wheel and a turbine shaft. The superhigh-pressure air producing and sealing device comprises a frame, an air compressor arranged at an upper part of the frame, and the air storage bottle arranged at a lower part of the frame; a left part of the spray pipe is fixedly connected with a right part of the chassis; a bottle body is placed on the chassis; the turbine wheel and the turbine shaft are arranged in the spray pipe; the turbine shaft can drive the wheels to rotate together when rotating; and an air outlet pipe of the bottle body is connected with the spray pipe. 11514161718. A turbojet automobile , comprising an air storage bottle in a superhigh-pressure air producing and sealing device , wheels () , a chassis () , a lever braking device , a spray pipe () , a turbine wheel () and a turbine shaft () , wherein{'b': 1', '2', '3', '29', '3', '2', '29', '3', '29', '3', '3', '2', '29', '2', '7', '1', '1', '4', '30', '3', '4', '29', '30', '5', '1', '1', '2', '1, 'the superhigh-pressure air producing and sealing device comprises a frame, an air compressor arranged at an upper part of the frame and the air storage bottle arranged at a lower part of the frame; the air compressor comprises an inner shell and an outer shell (); the inner shell comprises an upper pressing plate () and a double-layer cylindrical plate; the double-layer cylindrical plate comprises a first-layer cylindrical plate () and a second-layer cylindrical plate (); the first-layer cylindrical plate () is cylindrical and has a caliber less than a width of the upper pressing plate (); the second-layer cylindrical plate () is also cylindrical and has a caliber less than a caliber of the first-layer cylindrical plate (); the second-layer cylindrical plate () is sleeved in the first-layer cylindrical ...

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Номер записи: 19
18-01-2018 дата публикации

GEARED GAS TURBINE ENGINE AND A GEARBOX

Номер: US20180016938A1
Автор: DOORBAR Phillip J., MADGE Jason J.
Принадлежит: ROLLS-ROYCE PLC

A gas turbine engine comprises a gearbox comprises a sun gear, an annulus gear, a plurality of planet gears and a carrier. The sun gear meshes with the planet gears and the planet gears mesh with the annulus gear. The planet gear carrier comprising a first ring, a second ring spaced axially from the first ring and a plurality of circumferentially spaced axles extending axially between the first ring and the second ring. Each planet gear is rotatably mounted on a respective one of the axles and the axles are arranged at a first radius. At least one of the first ring and the second ring comprises a metal matrix composite material ring and the metal matrix composite ring comprises a ring of reinforcing fibres and the ring of reinforcing fibres having a second radius greater than the first radius. 1. A gas turbine engine comprising a gearbox , the gearbox comprising a sun gear , an annulus gear , a plurality of planet gears and a carrier , the sun gear meshing with the planet gears and the planet gears meshing with the annulus gear , the carrier comprising a first ring , a second ring spaced axially from the first ring and a plurality of circumferentially spaced axles extending axially between the first ring and the second ring , each planet gear being rotatably mounted on a respective one of the axles , the axles being arranged at a first radius , at least one of the first ring and the second ring comprising a metal matrix composite material , the metal matrix composite material comprising a ring of reinforcing fibres and the ring of reinforcing fibres having a second radius greater than the first radius.2. A gas turbine engine as claimed in wherein the first ring comprises a first metal matrix composite material and the second ring comprises a second metal matrix composite material claim 1 , the first metal matrix composite material comprises a first ring of reinforcing fibres claim 1 , the first ring of reinforcing fibres having a second radius greater than the first ...

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Номер записи: 20
17-04-2014 дата публикации

Multi-Propulsion, Multi-Fuel Marine Power System

Номер: US20140102104A1
Автор: Read Brian L.
Принадлежит:

A marine propulsion and power supply for maritime vessels that includes an arrangement of modules that can be internal combustion engines, regenerative electric motors, engine generators, turbine generators and/or battery banks. These components can be arranged in such a way as to work together to increase efficiency and to utilize various fuel combinations to achieve the lowest overall operating cost or other goals whilst minimizing harmful emissions. Sensors can be used monitor various power parameters and can be coupled to a closed-loop in a control system to achieve vessel operating goals. 1. A high efficiency propulsion system for a marine vessel comprising:a plurality of rotating power sources of different types coupled to at least one propeller;wherein, at least one of these power sources is a regenerative electric motor and at least one is an internal combustion engine;a battery electrically connectable to said at least one regenerative electric motor;a turbine powered generator electrically connectable to propulsion systems;an engine generator electrically connectable to said battery;a control system programmed to select combinations of power sources from said plurality of rotating power sources;whereby, said control system optimizes vessel performance based on a predetermined efficiency goal.2. The high efficiency propulsion system of wherein said control system further controls one of said turbine powered generator or said engine generator.3. The high efficiency propulsion system of wherein said control system contains a processor.4. The high efficiency propulsion system of wherein said predetermined efficiency goal is selected from the group consisting of lowest cost claim 1 , fastest trip claim 1 , minimum emissions and lowest fuel usage.5. The high efficiency propulsion system of further comprising a plurality of sensors coupled to said control system.6. The high efficiency propulsion system of wherein said sensors are selected from the group ...

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Номер записи: 21
17-04-2014 дата публикации

CONTINUOUS ELECTRICAL GENERATING WATER FLOW SYSTEM /OR C.E.G.F.S.

Номер: US20140103659A1
Автор: PRIOVOLOS ERNEST
Принадлежит:

An improved self-contained electrical unit it has three separate components that produces electricity. This by using reducing theory PVC tubing in which increases pressure on the exiting two feet tubes, that spin standard water wheel systems 1. Its another new form , or land Hydroelectric power generation. It has a self-contained water reflow system. The gravity flow and the use of sloping in conjunction with the three components.2. The component are attached to PVC tubing , and to a V shaped water container at no more than a twenty four degree slope which is at a depth of no more than forty five feet.3. The standard waterwheel or turbine system has a hollow bottom to retrieve excess water and is connected to PVC exit tubes that follow to the refill container.4. The exit refill container has a center point in which water overflows into a rectangular container that has a depth of no more than twenty five feet.5. It has three drain hole connected to ten foot PVC exits drain tubes that are connected to component in which the exit water travels downward into one spiral and further downward until it reaches component one at forty five feet. Then which is a water trap system.6. The water trap system or the container of component one is blocked or trap by one third of container one.7. The center tube of component one see figure two Is the water retrieving system from the existing water trap noted above. Not ApplicableNot ApplicableNot ApplicableThe present invention relates to a pulley system which is based on gravity water flow. That refills itself if in the form of land apparatus that self-contained and has three separate components as noted herein.The applicant explains the aforementioned patents cited. (TESLA) These are unique and produce DC and AC current which are much like a modern coil, or transformer motor system whether, AC or Dc. However, it is not a complete system and is not attached to any completed form of electrical generation. As noted in this present ...

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Номер записи: 22
24-01-2019 дата публикации

COMPRESSOR TRAIN START-UP USING VARIABLE INLET GUIDE VANES

Номер: US20190024528A1
Автор: BALDANZINI Fabio, BALDASSARRE Leonardo, MARCUCCI Nicola, PELAGOTTI Antonio, PELELLA Marco
Принадлежит: Nuovo Pignone Tecnologie Srl

A method for operating start-up of a compressor train is disclosed. The train includes a driver machine and at least a centrifugal compressor drivingly coupled to the driver machine. The centrifugal compressor in turn includes a plurality of compressor stages and at least a first set of variable inlet guide vanes at an inlet of one of the compressor stages. The method includes at least partly closing the first set of variable inlet guide vanes; when the first set of variable inlet guide vanes is at least partly closed, starting rotation of the centrifugal compressor and accelerating the centrifugal compressor up to a minimum operating speed; opening the at least one set of variable inlet guide vanes to increase the gas flow through the centrifugal compressor once the minimum operating speed has been achieved. 1. A method for operating start-up of a compressor train comprising a driver machine and at least a centrifugal compressor drivingly coupled to the driver machine , the centrifugal compressor comprising a plurality of compressor stages and at least a first set of variable inlet guide vanes at an inlet of one of said compressor stages; the method comprising:at least partly closing the first set of variable inlet guide vanes;starting rotation of the centrifugal compressor and accelerating the centrifugal compressor up to a minimum operating speed, while the first set of variable inlet guide vanes is at least partly closed;opening the first set of variable inlet guide vanes to increase the gas flow through the centrifugal compressor once the minimum operating speed has been achieved.2. The method of claim 1 , wherein the first set of variable inlet guide vanes is arranged at the inlet of a most upstream compressor stage of the centrifugal compressor.3. The method of claim 1 , wherein the driver machine comprises a single-shaft gas turbine engine and a starter; and wherein during starting rotation of the centrifugal compressor and accelerating the centrifugal ...

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Номер записи: 23
02-02-2017 дата публикации

Electric powered pump down

Номер: US20170030178A1
Автор: Brandon N. Hinderliter, Jared Oehring
Принадлежит: US Well Services LLC

A method of operations in a subterranean formation, including driving a pump with an electrically powered motor to pressurize fluid, inserting a tool into a wellbore that intersects the formation, and directing the pressurized fluid into the wellbore above the tool to push the tool into the wellbore.

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Номер записи: 24
01-02-2018 дата публикации

Carbon Dioxide Capture from Flu Gas

Номер: US20180031315A1
Автор: Baxter Larry
Принадлежит:

A method for capturing carbon dioxide from a flue gas includes (i) removing moisture from a flue gas to yield a dried flue gas; (ii) compressing the dried flue gas to yield a compressed gas stream; (iii) reducing the temperature of the compressed gas stream to a temperature Tusing a first heat exchanger; (iv) reducing the temperature of the compressed gas stream to a second temperarature Tusing a second heat exchanger stream, where T Подробнее

Номер записи: 25
05-02-2015 дата публикации

SYSTEM AND METHOD FOR A GAS TURBINE ENGINE SENSOR

Номер: US20150033757A1
Автор: Beadie Douglas Frank, Floyd, II Donald Earl, Krull Anthony Wayne, White Eugene Delano
Принадлежит:

A system includes a gas turbine engine that includes a combustor section having a turbine combustor that generates combustion products, a turbine section having one or more turbine stages driven by the combustion products, an exhaust section disposed downstream of the turbine section, an oxygen sensor adaptor housing disposed in at least one of the combustor section, the turbine section, or the exhaust section, or any combination thereof, and an oxygen sensor disposed in the oxygen sensor adaptor housing. The oxygen sensor adaptor housing is configured to maintain a temperature of a portion of the oxygen sensor below an upper threshold. 1. A system , comprising: a combustor section having a turbine combustor that generates combustion products;', 'a turbine section having one or more turbine stages driven by the combustion products;', 'an exhaust section disposed downstream of the turbine section;', 'an oxygen sensor adaptor housing disposed in at least one of the combustor section, the turbine section, or the exhaust section, or any combination thereof; and', 'an oxygen sensor disposed in the oxygen sensor adaptor housing, wherein the oxygen sensor adaptor housing is configured to maintain a temperature of a portion of the oxygen sensor below an upper threshold., 'a gas turbine engine, comprising2. The system of claim 1 , wherein the oxygen sensor comprises at least one of a wideband oxygen sensor claim 1 , a lambda sensor claim 1 , an air/fuel meter claim 1 , or a universal exhaust gas oxygen (UEGO) sensor claim 1 , or any combination thereof.3. The system of claim 1 , wherein the portion of the oxygen sensor comprises at least one of a hex section claim 1 , a gland packing claim 1 , wiring claim 1 , or a connector shell claim 1 , or any combination thereof.4. The system of claim 1 , wherein the oxygen sensor comprises a heater configured to maintain a tip temperature of a tip portion of the oxygen sensor within a temperature range.5. The system of claim 1 , ...

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Номер записи: 26
30-01-2020 дата публикации

Fuel delivery system

Номер: US20200030720A1
Автор: Erick Ramos, Morgan O'Rorke
Принадлежит: Hamilton Sundstrand Corp

A fuel delivery system includes a turbine, a pump, and an oxygen removal unit. The turbine is adapted to receive and expel fuel at different pressures. The pump is in fluid communication with, and mechanically coupled to, the turbine, and is configured to expel and receive the fuel at about the respective different pressures. The turbine is configured to convert pressure energy of the fuel to kinetic energy to drive the pump. The oxygen removal unit is in fluid communication with at least one of the turbine and the pump, and is configured to remove oxygen from the fuel.

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Номер записи: 27
08-02-2018 дата публикации

GAS TURBINE STARTING DEVICE AND GAS TURBINE SYSTEM

Номер: US20180038283A1
Автор: Kobayashi Masahiro, Mori Yasushi
Принадлежит: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION

Provided is a gas turbine starting device which has a sun gear, a planetary carrier, an internal gear, and a planetary gear, the sun gear, the planetary carrier and the internal gear serving as rotating bodies rotating about an axis; and a variable speed power source which has a rotor connected to one of the rotating bodies in the planetary gear mechanism. A rotating shaft of the gas turbine is connected to one of the rotating bodies other than the rotating body to which the variable speed power source is connected, and the rotating shaft of the compressor is connected to the remaining one of the rotating bodies other than the rotating bodies to which the rotor of the variable speed power source and the rotating shaft of the gas turbine are connected. 1. A gas turbine starting device comprising:a planetary gear mechanism which is provided in a gas turbine system having a gas turbine, and a fluid machine rotationally driven by a driving force of the gas turbine on the same axis as a rotation center of a rotating shaft of the gas turbine, and has a sun gear, a planetary carrier disposed on an outer circumferential side of the sun gear, an internal gear having a gear unit and disposed on an outer circumferential side of the planetary carrier, and a planetary gear which is supported by the planetary carrier to mesh with the sun gear and the internal gear, the sun gear, the planetary carrier and the internal gear serving as rotating bodies rotating about the axis; anda variable speed power source which has a driving shaft connected to rotate one of the rotating bodies, which is the sun gear, the planetary carrier, or the internal gear, in the planetary gear mechanism about the axis,wherein the rotating shaft of the gas turbine is connected to rotate one of the rotating bodies, which is the sun gear, the planetary carrier, or the internal gear, other than the rotating body, to which the variable speed power source is connected, about the axis, anda rotating shaft of the ...

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Номер записи: 28
07-02-2019 дата публикации

System for reducing vibrations in a pressure pumping fleet

Номер: US20190040727A1
Автор: Jared Oehring, Robert Kurtz
Принадлежит: US Well Services LLC

An electrically powered hydraulic fracturing system having pumps for pressurizing fracturing fluid, piping for carrying fracturing fluid, and vibration reducing equipment for use with the piping. The vibration reducing equipment includes helical coils that support the piping. The coils are made of a wire rope made of strands of steel cable twisted together. Grooved fittings are provided on some piping connections, and which allow pivoting between adjacent fluid conveyance members. Swivel joints are strategically located in the piping which allow rotational flexing between adjacent sections of the piping; thereby attenuating vibration in the piping but without stressing the piping.

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Номер записи: 29
07-02-2019 дата публикации

INTEGRATED EXPANDER-MOTOR COMPRESSOR

Номер: US20190041124A1
Автор: ALBAN Thomas, Berti Matteo, Iurisci Giuseppe, Sassanelli Giuseppe
Принадлежит:

An expander and motor-compressor unit is disclosed. The unit includes a casing and an electric motor arranged in the casing. A compressor is arranged in the casing and drivingly coupled to the electric motor through a central shaft. Furthermore, a turbo-expander is arranged for rotation in the casing and is drivingly coupled to the electric motor and to the compressor through the central shaft. 1. An expander and motor-compressor unit comprising:a casing;an electric motor arranged in the casing;a multi-stage compressor drivingly coupled to the electric motor through a central shaft and arranged in the casing;wherein a turbo-expander is arranged for rotation in the casing and is drivingly coupled to the electric motor and to the compressor through the central shaft, wherein the central shaft is supported by at least three radial bearings.2. The expander and motor-compressor unit of claim 1 , wherein the turbo-expander and the compressor are fluidly coupled such that gas expanded through the turbo-expander is delivered to the compressor and compressed thereby.3. The expander and motor-compressor unit of claim 1 , wherein a liquid removal arrangement is positioned between the turbo-expander and the compressor claim 1 , and wherein the liquid removal arrangement is fluidly coupled to a delivery side of the turbo-expander and to a suction side of the compressor claim 1 , such that expanded gas from the turbo-expander flows through the liquid removal arrangement and is subsequently delivered to the suction side of the compressor.4. The expander and motor-compressor unit of claim 1 , wherein the turbo-expander is positioned in an overhung configuration on the central shaft.5. The expander and motor-compressor unit of claim 1 , wherein the electric motor is arranged between the turbo-expander and the compressor.6. The expander and motor-compressor unit of claim 1 , wherein the turbo-expander is arranged in a first casing compartment and the electric motor is arranged in a ...

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Номер записи: 30
07-02-2019 дата публикации

FULL TURBOMACHINERY MODULE FOR LNG PLANTS OR THE LIKE

Номер: US20190041127A1
Автор: CECARINI Michele, GIANCOTTI Marco, GUIDOTTI Luciano, RIGHESCHI Andrea
Принадлежит:

A modular gas turbine system is disclosed. The system includes a base plate and a gas turbine engine mounted on the base plate. The gas turbine engine is drivingly coupled to a rotating load mounted on the base plate. A supporting frame extends above the base plate. A first bridge crane and a second bridge crane are movably supported on the supporting frame. 1. A transportable modular gas turbine system , comprising:a base plate;a gas turbine engine having a rotation axis, mounted on the base plate;at least one rotating load, mechanically coupled to the gas turbine engine and mounted on the base plate;a supporting frame extending above the base plate;a first bridge crane movably supported on the supporting frame;a second bridge crane movably supported on the supporting frame.2. The modular gas turbine system of claim 1 , wherein the first bridge crane and the second bridge crane are movable on common rails mounted on the supporting frame.3. The modular gas turbine system of claim 1 , wherein at least one of the first bridge crane and second bridge crane is movable on rails extending substantially parallel to a rotation axis of the gas turbine engine.4. The modular gas turbine system of claim 1 , wherein the first bridge crane is movable along first rails extending substantially parallel to the rotation axis of the gas turbine engine and the second bridge crane is movable along second rails extending substantially orthogonal to the rotation axis of the gas turbine engine.5. The modular gas turbine system of claim 1 , wherein at least one of said first bridge crane and second bridge crane is movable on first rails extending substantially parallel to the rotation axis of the gas turbine engine and projecting horizontally beyond the footprint of the base plate claim 1 , up to a lay down area arranged on a side of the base plate.6. The modular gas turbine system of claim 1 , wherein the first bridge crane has a lifting capacity higher than the second bridge crane.7. The ...

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Номер записи: 31
15-02-2018 дата публикации

Turbine-Driven Rotary Sinuplasty Cutter

Номер: US20180042640A1
Автор: Algawi Yehuda, Govari Assaf
Принадлежит:

A surgical apparatus includes a rotatable shaft and a turbine assembly. The rotatable shaft includes a cutter located thereon. The cutter is configured to cut an object when the shaft is rotating about a rotational axis. The turbine assembly includes a turbine and a turbine housing. The turbine housing is configured to receive a fluid that enters the housing parallel to the rotational axis, and to steer the fluid to impinge on the turbine in a direction that is not parallel to the rotational axis. The turbine is configured to rotate the shaft so as to cut the object by the cutter. 1. A surgical apparatus , comprising:a rotatable shaft, which comprises a cutter located thereon, wherein the cutter is configured to cut an object when the shaft is rotating about a rotational axis; anda turbine assembly, which comprises a turbine and a turbine housing, wherein the turbine housing is configured to receive a fluid that enters the housing parallel to the rotational axis, and to steer the fluid to impinge on the turbine in a direction that is not parallel to the rotational axis, and wherein the turbine is configured to rotate the shaft so as to cut the object by the cutter.2. The apparatus according to claim 1 , wherein the turbine housing comprises one or more fluid channels configured to receive the fluid in a first direction claim 1 , which is parallel to the rotational axis claim 1 , and to steer the received fluid to a second direction claim 1 , different from the first direction claim 1 , so that the fluid impinges on the turbine from the second direction.3. The apparatus according to claim 2 , wherein the second direction is orthogonal to the first direction.4. The apparatus according to claim 1 , wherein the fluid channels are adjacent to one another so as to form a contiguous jet of the steered fluid.5. The apparatus according to claim 1 , wherein the fluid comprises compressed air.6. The apparatus according to claim 1 , and comprising one or more fluid outlet tubes ...

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Номер записи: 32
19-02-2015 дата публикации

WASTE HEAT UTILIZATION APPARATUS

Номер: US20150047351A1
Автор: HARAGUCHI Tomonori, Ishikawa Takayuki, Iwahashi Riyako, MIZOGUCHI Shinichiro, Nagai Hiroyuki, Ogihara Satoshi
Принадлежит:

A waste heat utilization apparatus is provided with a Rankine cycle and a power transmission mechanism that transmits power regenerated by an expander to an engine. The power transmission mechanism includes an expander clutch that interrupts or permits The transmission of the power from to expander to the engine. The expander includes a rotational speed sensor that detects a rotational speed of the expander. An increase in friction of the expander is detected on the basis of an increase in the rotational speed of the expander detected by the rotational speed sensor when the expander clutch is disconnected. 1. A waste heat utilization apparatus comprising:a Rankine cycle including a heat exchanger that recovers waste heat from an engine with a refrigerant, an expander that produces power by using the refrigerant that exits the heat exchanger, a condenser that condenses the refrigerant that exits the expander, and a refrigerant pump that supplies the refrigerant that exits the condenser to the heat exchanger; anda power transmission mechanism that transmits the power regenerated by the expander to the engine, wherein:the power transmission mechanism includes a disconnection/connection means that interrupts or permits the transmission of the power from the expander to the engine; andthe expander includes a rotational speed detection means that detects a rotational speed of the expander,the waste heat utilization apparatus further comprising a friction increase detection means that detects an increase in friction of the expander on the basis of an increase in the rotational speed of the expander detected by the rotational speed defection means when the disconnection/connection means is disconnected.2. The waste heat utilization apparatus according to claim 1 , wherein the Rankine cycle includes a bypass passage that bypasses the refrigerant introduced into the expander claim 1 , and a bypass valve that interrupts or permits conduction of the refrigerant into the bypass ...

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Номер записи: 33
18-02-2016 дата публикации

RAM AIR TURBINE PUMP LEAKAGE CONTROL

Номер: US20160047267A1
Автор: Russ David Everett
Принадлежит:

An exemplary method of controlling fluid flow in a ram air turbine assembly, includes redirecting flow moving in an axial direction against the surface of a drive shaft to flow moving in a radial direction away from the drive shaft to limit flow of the fluid from a hydraulic pump to a generator. 1. A method of controlling fluid flow in a ram air turbine assembly , comprising:redirecting flow moving in an axial direction against the surface of a drive shaft to flow moving in a radial direction away from the drive shaft to limit flow of the fluid from a hydraulic pump to a generator.2. The method of claim 1 , including using a radially extending feature of the drive shaft to initiate the redirecting.3. The method of claim 1 , including driving the hydraulic pump and the generator using the drive shaft.4. The method of claim 3 , including rotating a turbine of a ram air turbine to rotate the drive shaft.5. The method of claim 1 , wherein the fluid is a hydraulic fluid.6. The method of claim 1 , further comprising moving a strut from a stowed position to a deployed position claim 1 , and redirecting after the deploying.7. The method of claim 6 , further comprising rotating the drive shaft about a drive shaft axis to directly drive the hydraulic pump and the generator when the strut is in the deployed position.8. The method of claim 7 , further comprising supporting a turbine within the strut claim 7 , the strut connected to a turbine shaft that rotates about a turbine shaft axis transverse to the drive shaft axis.9. The method of claim 7 , further comprising redirecting flow moving in the axial direction to flow moving in the radial direction into an annular cavity.10. The method of claim 9 , further comprising holding at least a portion of both the hydraulic pump and the generator within a housing assembly and providing the annular cavity within the housing assembly.11. The method of claim 9 , further comprising draining the fluid from the annular cavity using a ...

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Номер записи: 34
15-02-2018 дата публикации

NOSE CONE ASSEMBLY AND METHOD OF CIRCULATING AIR IN A GAS TURBINE ENGINE

Номер: US20180045138A1
Автор: Ackermann William K., Bifulco Anthony R., Chandler Jesse M., Rose Becky E., Snape Nathan, Suciu Gabriel L.
Принадлежит:

A nose cone assembly for a gas turbine engine and method of circulating air in a gas turbine engine are disclosed. The nose cone assembly includes a nose cone having an aperture communicating air to an interior space of the nose cone and a discharge member communicating the air out of the nose cone. 1. A nose cone assembly for a gas turbine engine comprising:a nose cone defining an interior space, the nose cone having an array of apertures in a frustoconical pattern in the nose cone and communicating air to the interior space of the nose cone, wherein the array of apertures comprises a plurality of apertures that are axially spaced from each other along the nose cone;a discharge member communicating the air out of the nose cone; anda frustoconical shaped heat exchanger within the interior space of the nose cone and disposed forward of the discharge member in the interior space.2. The assembly of claim 1 , wherein the discharge member is arranged to discharge the air at a discharge location forward of a fan of a gas turbine engine when the nose cone assembly is mounted to the gas turbine engine.3. The assembly of claim 2 , wherein the discharge location is forward of a fan inlet guide vane of the gas turbine engine when the nose cone assembly is mounted to the gas turbine engine.4. The assembly of claim 1 , wherein the heat exchanger cools fluid circulating through the discharge member.5. The assembly of claim 1 , wherein the discharge member includes a pump that draws air out of the interior space.6. The assembly of claim 5 , wherein the pump is driven by a shaft of the gas turbine engine when the nose cone assembly is mounted to the gas turbine engine.7. The assembly of claim 1 , wherein the plurality of apertures of the array of apertures are circumferentially spaced about the nose cone and communicate the air to the interior space of the nose cone.8. A gas turbine engine assembly comprising:a fan section including a fan;a nose cone defining an interior space, the ...

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Номер записи: 35
15-02-2018 дата публикации

PUMP SYSTEM FOR HIGH PRESSURE APPLICATION

Номер: US20180045202A1
Автор: Crom Elden
Принадлежит:

A pump system for high pressure, high volume applications is presented. The pump system includes a turbo-shaft engine having a drive shaft and a high pressure, high RPM centrifugal pump coupled to the drive shaft. In certain embodiments the pump system further includes a second low pressure, high RPM centrifugal pump coupled to the drive shaft. 1. A pump system , comprising:an engine including a drive shaft; andat least one pump connected to the drive shaft, the at least one pump including a primary impeller and a sacrificial impeller, the sacrificial impeller being configured, dimensioned, and positioned for increased wear relative to the primary impeller to increase usable life of the primary impeller.2. The pump system of claim 1 , further comprising:a primary housing, the primary impeller being positioned within the primary housing.3. The pump system of claim 1 , wherein the at least one pump further includes a cap covering the sacrificial impeller claim 1 , the cap being removable to facilitate repair and/or replacement of the sacrificial impeller.4. The pump system of claim 1 , wherein the at least one pump is positioned distally of the engine claim 1 , the sacrificial impeller being positioned distally of the primary impeller.5. The pump system of claim 1 , wherein the at least one pump is in direct mechanical cooperation with the engine such that there are no intervening mechanical systems between the at least one pump and the engine.6. The pump system of claim 5 , wherein the at least one pump further includes a rotor shaft claim 5 , the rotor shaft being mechanically coupled to the drive shaft of the engine such that rotational movement of the drive shaft is directly communicated to the rotor shaft.7. The pump system of claim 6 , wherein the pump system is configured and dimensioned for operation at an efficiency of about 94%.8. The pump system of claim 1 , wherein the at least one pump includes a first pump and a second pump claim 1 , the first pump being ...

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Номер записи: 36
03-03-2022 дата публикации

ENERGY RECOVERY FOR HIGH POWER PUMPING SYSTEMS AND METHODS USING EXHAUST GAS HEAT TO GENERATE THERMOELECTRIC POWER

Номер: US20220065125A1
Автор: Alberston Charles Keith, Spencer Mike, Yeung Tony
Принадлежит: BJ Energy Solutions, LLC

Embodiments of a power generation system and methods to be used in conjunction with a high-powered turbine engine are disclosed. The power generation system includes a turbine engine having an exhaust diffuser section installed on the exhaust duct of the turbine engine and a turbine engine exhaust stack assembly connected to the turbine engine exhaust diffuser section. An embodiment further includes thermo-electric generator (TEGs) sub-assemblies connected to the turbine engine exhaust stack assembly. In other embodiments electrical storage devices such as batteries are used. 1. A hydraulic fracturing power generation system positioned onboard a hydraulic fracturing trailer assembly , the system comprising: (a) a turbine engine mounted to the hydraulic fracturing trailer assembly,', '(b) a reduction gear box connected to the turbine engine and mounted to the hydraulic fracturing trailer assembly,', '(c) a drive shaft connected to the reduction gear box and mounted to the hydraulic fracturing trailer assembly, and', '(d) a turbine engine exhaust diffuser section mounted to the hydraulic fracturing trailer assembly and connected to the turbine engine;, 'a high power hydraulic fracturing generation assembly includinga reciprocating plunger pump connected to the drive shaft and mounted to the hydraulic fracturing trailer assembly; and (a) a turbine engine exhaust stack assembly mounted to the hydraulic fracturing trailer assembly and connected to the turbine engine exhaust diffuser section,', '(b) a set of thermo-electric generator (TEG) sub-assemblies connected to the turbine engine exhaust stack assembly to generate electric power responsive to the turbine engine exhaust stack assembly, and', '(c) a power storage and distribution source mounted to the hydraulic fracturing trailer assembly to store and distribute power generated from the set of TEG sub-assemblies across the hydraulic fracturing trailer assembly., 'a thermoelectric power generation assembly mounted to ...

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Номер записи: 37
23-02-2017 дата публикации

ROTARY PERCUSSIVE DEVICE

Номер: US20170051560A1
Автор: JR. Robert H., Slaughter
Принадлежит:

Repeated percussive forces may be provided using various devices, systems, assemblies, and methods. Example rotary percussive devices may be used in a downhole environment, including within a drilling system that includes a percussive hammer drill bit. The rotary percussive device may include a rotational translator to convert drilling fluid pressure into a rotational force. An axial translator coupled to the rotational translator may convert the rotational force into an axial percussive force. This conversion may be done using magnets arranged in arrays of alternating polarities. The rotational translator may longitudinally overlap the axial translator. The rotational translator may include a rotational stator rotationally fixed within a bottomhole assembly. The rotational stator may include a shaft of a positive displacement motor. 1. A rotary percussive device , comprising:a rotational translator having a rotational rotor and a rotational stator; andan axial translator having an axial stator, the axial translator being concentric with the rotational translator.2. The device of claim 1 , wherein the rotational translator comprises a positive displacement motor claim 1 , an electric motor claim 1 , or a turbine.3. The device of claim 1 , wherein the rotational translator is concentrically within the axial translator and is shorter than the axial translator.4. The device of claim 1 , wherein the axial translator further comprises an axial rotor.5. The device of claim 4 , wherein the axial rotor and axial stator each comprise angularly and longitudinally offset magnets of alternating polarity.6. The device of claim 1 , wherein the rotational rotor is at least partially integrally formed with an axial rotor.7. The device of claim 1 , further comprising a plurality of magnets coupled to the axial translator.8. The device of claim 7 , wherein the axial translator further comprises a non-magnetic body in which the plurality of magnets are held.9. The device of claim 8 , ...

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Номер записи: 38
22-02-2018 дата публикации

HIGH LOAD CAPACITY HYBRID FOIL BEARING

Номер: US20180051745A1
Автор: Himmelmann Richard A.
Принадлежит:

A bearing includes a bearing sleeve with a first portion and a second portion adjacent to the first portion. A bump foil extends along an inner face of the first portion of the bearing sleeve and a metal mesh extends along an inner face of the second portion of the bearing sleeve. A top foil extends along an inner face of the bump foil of the first portion and the metal mesh of the second portion. 1. A bearing comprising:a bearing sleeve with a first portion and a second portion adjacent to the first portion;a bump foil extending along an inner face of the first portion of the bearing sleeve;a metal mesh extending along an inner face of the second portion of the bearing sleeve; anda top foil extending along an inner face of the bump foil of the first portion and the metal mesh of the second portion.2. The bearing of claim 1 , and further comprising:a third portion in the bearing sleeve adjacent to the second portion; anda bump foil extending along an inner face of the third portion of the bearing sleeve;wherein the top foil extends along an inner face of the bump foil of the third portion.3. The bearing of claim 2 , wherein the bearing sleeve has a first wall thickness at the first portion and the third portion that is greater than a second wall thickness at the second portion.4. The bearing of claim 1 , and further comprising:a third portion in the bearing sleeve adjacent to the first portion; anda metal mesh extending along an inner face of the third portion of the bearing sleeve;wherein the top foil extends along an inner face of the metal mesh of the third portion.5. The bearing of claim 4 , wherein the bearing sleeve has a first wall thickness at the first portion and the third portion that is lesser than a second wall thickness at the second portion.6. The bearing of claim 1 , wherein the bump foil has a first section having corrugations with a first size and a second section having corrugations with a second size claim 1 , wherein the first size is larger ...

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Номер записи: 39
15-05-2014 дата публикации

METHOD AND APPARATUS FOR ENERGY RECOVERY FROM FLUID FLOWS

Номер: US20140133965A1
Автор: Ginsburg Martin A.
Принадлежит: MARGIN CONSULTING, LLC

An energy recovery apparatus includes a fixed frame, a shaft, an impeller vane, and an energy transfer unit. A fluid stream exits the host device along a flow axis. The fixed frame defining a longitudinal axis mounts the host device. The shaft is rotatably mounted to the fixed frame parallel to the longitudinal axis. The impeller vane is connected to the shaft to cause rotation when the fluid stream of the host device strikes the impeller vane. The energy transfer unit is linked to the shaft to transfer energy from the energy recovery apparatus when the shaft rotates thereby recovering energy from the fluid stream. A geologic heat exchange system includes at least one conduit in thermal contact with the geologic environment. A coolant distribution system is in fluid communication with the conduit such that heat exchange with the geologic environment occurs. 1. An energy recovery apparatus for placement in a fluid stream of a host device , the fluid stream entering or exiting the host device along a flow axis , the energy recovery apparatus comprising:a fixed frame having a proximal end for mounting the host device and a distal end opposite the proximal end, the fixed frame defining a longitudinal axis for placement parallel to the flow axis of the host device when the proximal end of the fixed frame is mounted to the host device;a shaft rotatably mounted to the fixed frame parallel to the longitudinal axis; andat least one impeller vane connected to the shaft to cause rotation of the shaft relative to the fixed frame when the fluid stream of the host device strikes the impeller vane;an energy transfer unit linked to the shaft to transfer energy from the energy recovery apparatus when the shaft rotates thereby recovering energy from the fluid stream.2. An energy recovery apparatus according to claim 1 , wherein the energy transfer unit comprises an electrical generator that generates an electrical voltage when the shaft rotates.3. An energy recovery apparatus ...

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Номер записи: 40
21-02-2019 дата публикации

REMOTE MONITORING FOR HYDRAULIC FRACTURING EQUIPMENT

Номер: US20190055826A1
Автор: Hinderliter Brandon N., OEHRING Jared
Принадлежит: U.S. Well Services, LLC

A hydraulic fracturing system for fracturing a subterranean formation including a pump in communication via pump components with a wellbore that intersects the formation, and that pressurizes fluid in the wellbore, the fluid comprising a fracturing fluid slurry. The system further includes hydraulic fracturing system components for making the fracturing fluid slurry, and a monitoring system that selectively captures and transmits real time images of at least one of the hydraulic fracturing system components or pump components to enable remote monitoring of the at least one of the hydraulic fracturing system components or pump components. 1. A hydraulic fracturing system for fracturing a subterranean formation comprising:a pump in communication via pump components with a wellbore that intersects the formation, and that pressurizes fluid in the wellbore, the fluid comprising a fracturing fluid slurry;hydraulic fracturing system components for making the fracturing fluid slurry; anda monitoring system that selectively captures and transmits real time images of at least one of the hydraulic fracturing system components or pump components to enable remote monitoring of the at least one of the hydraulic fracturing system components or pump components;wherein the monitoring system selectively captures and transmits real time images of the hydraulic fracturing system components and/or the pump components.2. The hydraulic fracturing system of claim 1 , wherein the monitoring system comprises:a camera;a controller;a display;a human machine interface; andcommunication means between the camera, controller, human machine interface, and the display.3. The hydraulic fracturing system of claim 1 , wherein the display comprises a monitor from which the images are viewed.4. The hydraulic fracturing system of claim 3 , wherein the display is disposed within a passenger compartment mounted to a fluid blender claim 3 , so that the images can be viewed by operations personnel in the ...

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Номер записи: 41
03-03-2016 дата публикации

Gas turbine engine anti-icing system

Номер: US20160061056A1
Автор: Ajith Appukuttan, Benjamin Keeler, Paolo Vanacore
Принадлежит: Rolls Royce PLC

An anti-icing system ( 100 ) for an engine section stator ( 26 ) of a gas turbine engine ( 10 ), the system ( 100 ) comprising: an environmental control system pre-cooler heat exchange system ( 116 ) configured to exchange heat between air bled from a compressor ( 14, 16 ) of the engine ( 10 ) and bypass duct air; and a conduit ( 132 ) configured to exchange heat from the pre-cooler heat exchange system ( 116 ) to a further a heat transfer medium, the conduit ( 132 ) being configured to transfer the heat from the heat transfer medium to the engine section stator ( 26 ).

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Номер записи: 42
01-03-2018 дата публикации

Ring Turbine Arrangements for Electricity Generation and Other Applications

Номер: US20180058244A1
Автор: Goodwin Robert Lovejoy
Принадлежит:

System for electrical energy generation from steam comprising at least one stage, each stage including: a steam-driven rotating toroidal ring; a housing comprising a toroidal cavity for containing the rotating toroidal ring, the housing further comprising at least one steam inlet, the housing further comprising a plurality of steam outlets for removing pressurized steam from the channels for at least a second portion of rotation of the rotating toroidal ring within the toroidal cavity; at least one bearing arrangement comprised by or attached to the housing within the toroidal cavity; and at least one pair of electrical coils, each electrical coil located on the outer surface of the housing at locations diagonally opposite from the other coil of each pair across the axis of the minor radius of the toroidal cavity and within the specific region where a time-varying magnetic field will occur as the rotating toroidal ring rotates. 1. A system for electrical energy generation from steam , the system comprising at least one stage , each stage comprising:At least one steam-driven rotating toroidal ring, the toroidal ring comprising a major-radius and a minor-radius, the rotating toroidal ring for rotation within a plane coinciding with the major-radius of the rotating toroidal ring and comprising a least one steam channel for translating force components of steam pressure into rotational motion, the steam comprising enthalpy, the rotating toroidal ring further comprising at least one magnetic field source arranged to create a time-varying magnetic field occurring in at least one specific region adjacent to the rotating toroidal ring as the rotating toroidal ring rotates;At least one housing comprising a toroidal cavity for containing the rotating toroidal ring, the toroidal cavity comprising a major-radius and a minor-radius, the major-radius of the toroidal cavity accordingly slightly larger than the major-radius of the rotating toroidal ring and the minor-radius of the ...

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Номер записи: 43
01-03-2018 дата публикации

ROTOR ASSEMBLY AND TURBINE ENGINE WITH GAS BEARINGS INCLUDING SUCH A ROTOR ASSEMBLY

Номер: US20180062467A1
Автор: BARTHES Guillaume, CHAPILLON Laurent
Принадлежит: LIEBHERR-AEROSPACE TOULOUSE SAS

This rotor assembly for a turbine engine includes: 162122644281482248. A rotor assembly for a turbine engine with gas bearings including a permanent magnet () , a first shaft () having at least one bearing () intended for engaging with a support bearing to form a gas bearing and ensure rotational guidance of the first shaft () as well as a thrust disk , the permanent magnet () is a solid magnet which is press-fitted inside a band () made of a nonmagnetic material , the band () forms an integral assembly with the first shaft () in the extension thereof , and a second shaft () has at least one bearing () intended for engaging with a support bearing to form a gas bearing and ensure rotational guidance of the second shaft () , coaxially with the first shaft () such that the first shaft () , the band () , and the second shaft () form an integral assembly.2428. The rotor assembly according to claim 1 , wherein the band () is welded both on the first shaft () and on the second shaft ().328. The rotor assembly according to claim 1 , wherein the first shaft () and the second shaft () are made of a material different from that of the band.428. The rotor assembly according to claim 1 , wherein the first shaft () and the second shaft () are each a tubular shaft.52424. The rotor assembly according to claim 1 , wherein the first shaft () holds claim 1 , opposite the band () claim 1 , a compressor wheel ().6242. The rotor assembly according to claim 5 , wherein the compressor wheel () includes a threading engaging with a tapping made at one end of the first shaft ().72282428. The rotor assembly according to claim 5 , wherein the first shaft () has an inserted tapped part () press-fitted at one end of the shaft inside thereof claim 5 , and in that the compressor wheel () is attached on the tapped part () by screwing.82282428. The rotor assembly according to claim 5 , wherein the first shaft () has a tapped part () which is centered by light pressure at one end of the shaft and ...

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Номер записи: 44
28-02-2019 дата публикации

WELL DEBRIS HANDLING SYSTEM

Номер: US20190063190A1
Автор: Ejim Chidirim Enoch, Xiao Jinjiang
Принадлежит: Saudi Arabian Oil Company

A well tool assembly, system, and method for handling well debris is described. The assembly includes an electric submersible pump (ESP) configured to be positioned within a wellbore and a well debris cutting tool configured to be positioned downhole relative to the ESP within the wellbore. The ESP is configured to rotate in a first direction to pump well fluid in an uphole direction. The well debris cutting tool is configured to rotate in a second direction opposite the first direction and to grind debris carried by the well fluid in the uphole direction. 1. A well tool assembly comprising:an electric submersible pump (ESP) configured to be positioned within a wellbore, the ESP configured to rotate in a first direction to pump well fluid in an uphole direction; anda well debris cutting tool configured to be positioned downhole relative to the ESP within the wellbore, the well debris cutting tool configured to rotate in a second direction opposite the first direction, the well debris cutting tool configured to grind debris carried by the well fluid in the uphole direction.2. The assembly of claim 1 , wherein the well debris cutting tool comprises:a turbine configured to be positioned within the wellbore, downhole relative to the ESP, the turbine configured to rotate in response to flow of the well fluid through the turbine in the uphole direction;a first cutting blade sub-assembly connected to and rotatable by the turbine, the first cutting blade sub-assembly configured to grind the debris in response to being rotated by the turbine; anda second cutting blade sub-assembly connected to and rotatable by the ESP, the second cutting blade sub-assembly being uphole relative to the first cutting blade sub-assembly and downhole relative to the ESP, the second cutting blade sub-assembly configured to grind the debris in response to being rotated by the ESP.3. The assembly of claim 2 , wherein the first cutting blade sub-assembly is configured to counter-rotate relative to ...

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Номер записи: 45
28-02-2019 дата публикации

COMPRESSOR TURBINE BLADE AIRFOIL PROFILE

Номер: US20190063226A1
Автор: GIRGIS Sami, GREWAL Jasrobin, HUSZAR Robert, MOHAN Krishan, MORADI Niloofar, PARADIS Vincent, TSIFOURDARIS Panagiota
Принадлежит:

A compressor turbine includes a series of compressor turbine blades each having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. 1. A turbine blade of a gas turbine engine having a gaspath , the turbine blade comprising an airfoil having an intermediate portion contained within the gaspath and defined by a nominal profile substantially in accordance with Cartesian coordinate values of X , Y , and Z of Sections 2 to 9 set forth in Table 2 , wherein the point of origin of the orthogonally related axes X , Y and Z is located at an intersection of a centerline of the gas turbine engine and a stacking line of the turbine blade , the Z values are radial distances measured along the stacking line , the X and Y are coordinate values defining the profile at each distance Z.2. The turbine blade as defined in claim 1 , wherein the blade is a compressor turbine blade.3. The turbine blade as defined in claim 2 , wherein the blade is a single-stage compressor turbine blade.4. The turbine blade as defined in claim 1 , wherein the turbine blade has a manufacturing tolerance of ±0.030 inches in a direction perpendicular to the airfoil.5. The turbine blade as defined in claim 4 , wherein the nominal profile defining the intermediate portion is for a cold coated airfoil claim 4 , and wherein the coating has a thickness of 0.001 to 0.002 inches.6. A compressor turbine blade for a gas turbine engine having a gaspath claim 4 , the compressor turbine blade having a cold coated intermediate airfoil portion contained within the gaspath and defined by a nominal profile substantially in accordance with Cartesian coordinate ...

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Номер записи: 46
09-03-2017 дата публикации

PUMP GEAR

Номер: US20170067367A1
Автор: Grosskopf Andrew P., Wojcik Craig J.
Принадлежит:

An integrated drive generator includes an input shaft and an input drive gear connected to the input shaft. The integrated drive generator also includes an input driven gear meshed with the input drive gear. The integrated drive generator also includes a hydraulic speed trimming device. The hydraulic speed trimming device includes an input shaft connected to the input driven gear, an output shaft, an accessory drive gear connected to the output shaft, and an output ring gear connected to the output shaft. The input driven gear, the accessory drive gear, and the output ring gear are coaxial and disposed proximate a first end of the hydraulic speed trimming device. The integrated drive generator also includes a pump assembly with a pump drive shaft and a pump gear connected to the pump drive shaft and meshed with the accessory drive gear. 1. An integrated drive generator for a gas turbine engine , the integrated drive generator comprising:an input shaft;an input drive gear connected to the input shaft;an input driven gear meshed with the input drive gear; an input shaft connected to the input driven gear;', 'an output shaft;', 'an accessory drive gear connected to the output shaft; and', 'an output ring gear connected to the output shaft,', 'wherein the input driven gear, the accessory drive gear, and the output ring gear are coaxial and disposed proximate a first end of the hydraulic speed trimming device;, 'a hydraulic speed trimming device, the hydraulic speed trimming device comprisinga pump assembly comprising a pump drive shaft; anda pump gear connected to the pump drive shaft and meshed with the accessory drive gear.2. The integrated drive generator of claim 1 , wherein the pump gear is a spur gear.3. The integrated drive generator of claim 2 , wherein the pump gear comprises:an outside diameter; anda pitch diameter,wherein a ratio of the outside diameter and the pitch diameter is about 1.027 to about 1.029.4. The integrated drive generator of claim 2 , wherein ...

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Номер записи: 47
07-03-2019 дата публикации

INLET AIR COOLING SYSTEM AND INLET AIR COOLING METHOD FOR GAS TURBINE

Номер: US20190072036A1
Автор: KAMETA Masanori, Kikkawa Yoshitsugi, Momose Toshiya, Okano Takashi, YASUDA Satoshi
Принадлежит:

An inlet air cooling system used in a gas turbine for supplying power to a refrigerant compressor for compressing refrigerant in a natural gas liquefaction plant includes: an inlet air cooler for cooling inlet air of the gas turbine; chiller motors used for a chiller for cooling coolant supplied to the inlet air cooler; a first variable speed driver for supplying electric power to each of the one or more chiller motors; and an electric generator driven by the gas turbine, wherein the electric generator is electrically connected to the first variable speed driver, and electric power generated by the electric generator can be supplied to each of the chiller motors from the first variable speed driver without using a main power line of an electric power system, which enables efficient electric power supply to the motors via the variable speed driver. 1. An inlet air cooling system used in a gas turbine for supplying power to a refrigerant compressor for compressing refrigerant in a natural gas liquefaction plant , comprising:an inlet air cooler for cooling inlet air of the gas turbine;one or more chiller motors used for a chiller for cooling coolant supplied to the inlet air cooler;a first variable speed driver for supplying electric power to each of the one or more chiller motors; andan electric generator driven by the gas turbine,wherein the electric generator is electrically connected to the first variable speed driver, and electric power generated by the electric generator is allowed to be supplied to each of the one or more chiller motors from the first variable speed driver without using a main power line of an electric power system.2. The gas turbine inlet air cooling system according to claim 1 , wherein the electric generator functions as a starter motor for starting the gas turbine claim 1 , andwherein the gas turbine inlet air cooling system further comprises a second variable speed driver for supplying electric power from the main power line to the electric ...

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Номер записи: 48
16-03-2017 дата публикации

PHASE CHANGE MATERIAL COOLING SYSTEM FOR A VEHICLE

Номер: US20170074166A1
Автор: Arvin John R., Gagne Steven, Rodriguez Rigoberto, Siegel William L.
Принадлежит:

A system is disclosed one form of which is an aircraft that includes a pod capable of housing a work providing device. The pod can also include a thermal conditioning system and a power generation device that can be powered from the work providing device. The pod can provide thermal conditioning services and power services to a payload aboard the aircraft. In one non-limiting form the payload is a directed energy member that can be cooled using the thermal conditioning system and powered using the power generation device. 1. An apparatus comprising:an aircraft having one or more propulsion engines and an external pod and including a turbine apart from the one or more propulsion engines, the turbine in power communication with an electrical generator and a heat exchange system that includes a phase change heat exchanger, the aircraft further including an implement in thermal communication with the heat exchange system.2. The apparatus of claim 1 , wherein the implement is an electrically driven implement.3. The apparatus of claim 2 , wherein the implement is powered by the electrical generator and takes the form of a directed energy device.4. The apparatus of claim 1 , wherein the external pod includes an opening for receiving a gas in fluid communication with the turbine.5. The apparatus of claim 4 , wherein the turbine is located downstream of a combustor claim 4 , the heat exchange system includes a first working fluid in thermal communication with the phase change heat exchanger.6. The apparatus of claim 5 , which further includes a pump powered by the turbine claim 5 , the pump circulating a second working fluid in thermal communication with the implement and the phase change heat exchanger claim 5 , the first working fluid part of a vapor compression refrigeration system.7. The apparatus of claim 1 , wherein the external pod includes coolant supply and coolant return lines as well as an electrical conduit in communication with the implement.8. The apparatus of ...

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Номер записи: 49
14-03-2019 дата публикации

CONTROL SYSTEM FOR A COMPRESSOR WITH PRESURE-BASED SUBSYSTEM, SYNTHESIS PLANT AND CONTROL METHOD

Номер: US20190078574A1
Автор: CALOSI Mirco, MOSCATELLI Pasquale Gianluca, PASQUOTTI Maura, PELELLA Marco, RIZZELLI Marco, SIGNORINI Annamaria
Принадлежит:

Control system arranged for a rotary compressor driven by a rotary engine, and includes: a first control subsystem, a second control subsystem and a selector; the first control subsystem is arranged to provide a first control signal as a function of the performance and the speed of the compressor; the second control subsystem is arranged to provide a second control signal as a function of the performance of the compressor; the selector is arranged to select the first control signal or the second control signal as a third control signal to be provided to a power control input of the engine. 1. A control system for a rotary compressor driven by a rotary engine , comprising:a first control subsystem comprising:a performance input arranged to receive a first measure signal indicating performance of the rotary compressor,a speed input arranged to receive a second measure signal indicating rotation speed of the rotary compressor or the rotary engine, anda first control output arranged to provide a first control signal as a function of the first measure signal and the second measure signal;a second control subsystem comprising:a performance input arranged to receive a third measure signal indicating performance of the rotary compressor, anda second control output arranged to provide a second control signal as a function of the third measure signal; a first input electrically connected to the first control output,', 'a second input electrically connected to the second control output, and', 'a third control output arranged to provide a third control signal to a power control input of the rotary engine,, 'a selector comprisingwherein the selector is arranged to select the first control signal or the second control signal as the third control signal to be provided at the third control output.2. The control system of claim 1 , wherein the selector is arranged to select the second control signal based on one or more of at least the following criteria:an absolute value of a ...

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Номер записи: 50
14-03-2019 дата публикации

SEGMENTED ELECTRICAL MACHINE

Номер: US20190081532A1
Автор: CHONG Ellis FH, RAMAKRISHNA Shanmukha, VISWANATHAN Vaiyapuri, WANG Shuai
Принадлежит: ROLLS-ROYCE PLC

An electrical machine has a variable reluctance rotor, and a stator formed as an annular array of stator segments. The reluctance of the rotor-to-stator magnetic flux path varies with rotor position whereby the stator segments are magnetically energizable to rotate the rotor. The stator segments are arranged in the array such that, when energized to rotate the rotor, they produce an unbalanced force on the rotor. The machine further has a compensator including one or more balancing segments which are configured to be magnetically energizable to produce a balancing force on the rotor which balances the unbalanced force. The reluctance of the rotor-to-compensator magnetic flux path is substantially invariant with rotor position. 1. An electrical machine having:a variable reluctance rotor, anda stator formed as an annular array of stator segments, the reluctance of the rotor-to-stator magnetic flux path varying with rotor position whereby the stator segments are magnetically energizable to rotate the rotor;wherein:the stator segments are arranged in the array such that, when energized to rotate the rotor, they produce an unbalanced force on the rotor; andthe machine further has a compensator including one or more balancing segments which are configured to be magnetically energizable to produce a balancing force on the rotor which balances the unbalanced force, the reluctance of the rotor-to-compensator magnetic flux path being substantially invariant with rotor position.2. An electrical machine according to claim 1 , wherein the unbalanced force is radial or includes a radial component.3. An electrical machine according to claim 1 , wherein the unbalanced force is axial or includes an axial component.4. An electrical machine according to claim 1 , wherein the stator segments are non-axisymmetrically distributed in the annular array.5. An electrical machine according to claim 1 , wherein the claim 1 , or each claim 1 , balancing segment has a core structure and a ...

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Номер записи: 51
19-06-2014 дата публикации

System for converting gaseous fuel into liquid fuel

Номер: US20140165587A1
Автор: Aaron Foege
Принадлежит: Electro Motive Diesel Inc

A system for converting gaseous fuel into liquid fuel is provided. The system may have a combustor configured to receive a supply of gaseous fuel. The system may also have a gas compressor configured to direct gaseous fuel from the supply into the combustor. The system may also have an air compressor configured to direct compressed air into the combustor, and a turbine in fluid communication with an outlet of the combustor. The turbine may be connected to drive the gas compressor and the air compressor. The system may also have at least one heat exchanger in fluid communication with an outlet of the gas compressor and an outlet of the air compressor. The system may also have at least one expander in fluid communication with an outlet of the at least one heat exchanger. The system may also have a condenser in fluid communication with an outlet of the at least one expander.

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Номер записи: 52
25-03-2021 дата публикации

FIVE CYLINDER PLUNGER PUMP

Номер: US20210087943A1
Автор: Cui Haiping, Cui Wenping, LI Hailong, Li Peng, Wang Jixin, Wei Xiaosong
Принадлежит:

The present invention discloses a five cylinder plunger pump, including a power end assembly, a hydraulic end assembly and a reduction gearbox assembly, one end of the power end assembly is connected to the hydraulic end assembly, the other end of the power end assembly is connected to the reduction gearbox assembly; the reduction gearbox assembly includes a planetary reduction gearbox and a parallel reduction gearbox which are used in conjunction with each other, with a transmission ratio of 60:1 to 106:1. Beneficial effects: the rated input power is increased to 5000-7000 hp, the stroke can be up to 10 to 12 inches, and the maximum input speed of the reduction gearbox assembly on the plunger pump is increased from the current 2100 rpm to 16000 rpm, the reduction gearbox assembly can be directly connected to the turbine engine to solve the problem that the turbine fracturing equipment is slown down through two reduction gearboxes, thus decreasing the weight of the vehicle and reducing the overall size of the equipment. 1. A quintuplex plunger pump , comprising a power end assembly , a hydraulic end assembly and a reduction gearbox assembly , one end of the power end assembly is connected to the hydraulic end assembly , the other end of the power end assembly is connected to the reduction gearbox assembly; the reduction gearbox assembly comprises two planetary reduction gearboxes and a parallel reduction gearbox which are used in conjunction with each other; wherein the reduction gearbox assembly has a transmission ratio of 60:1 to 106:1; and the quintuplex plunger pump is directly connected with the turbine engine; andwherein the reduction assembly comprises a first planetary reduction gearbox and a second planetary reduction gearbox, one end of the first planetary reduction gearbox is connected to the power end assembly, the other end of the first planetary reduction gearbox is connected to the parallel reduction gearbox, and the other end of the parallel ...

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Номер записи: 53
29-03-2018 дата публикации

POWER AND DRAG REDUCTION SYSTEM

Номер: US20180086201A1
Автор: Antrobus Craig, DINCER Ibrahim, Zadeh Reza Mohammadali, ZAMFIRESCU Calin
Принадлежит:

Power systems, heat exchanger systems, electrical regeneration systems and air drag reduction systems for a wheeled vehicle are provided. The systems comprise a vehicle that includes a compressed air system and electrical system. The power and drag reduction system also comprises a plurality of pneumatic motors, one each connected to each wheel, the pneumatic motors using compressed air to drive each wheel and a plurality of electric motors, two each connected to each wheel, the electric motors using electric power to drive each wheel. Based on operator action, the vehicle is propelled by one of compressed air system operation and electrical system operation. Motors associated with each of the compressed air system and electrical system are attached to and drive each wheel separately. The compressed air system and electrical system operate separately and recharge battery systems. 1. A system , comprising:a power system comprising air and electric motors in communication with each wheel axle, said power system being configured as a power train, wherein each of said motors is configured to transmit power to the connected wheel;a heat exchanger to heat expanding air, said heat exchanger being configured to be operable to substantially evenly distribute said heated air to actuate components associated with at least four wheels of a vehicle;at least one air tank, said at least one air tank being substantially sufficiently covered by tank heat trace lines so as to maintain a desired level of tank heat;a regeneration brake mechanism configured to actuate at least four electric motors to convert mechanical braking energy into electricity for recharging batteries and directly transferred into said heat exchanger as needed; and,a two turbine/expansion cascaded system integrated with interstage reheaters configured to be operable to increase power to air motors and electrical regeneration.2. The system of claim 1 , in which the vehicle further includes a drag reducing ...

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Номер записи: 54
05-05-2022 дата публикации

Hybrid power generation equipment

Номер: US20220136436A1
Автор: CHA Song-Hun, KANG Sung Gju, LEE Ki Hyun
Принадлежит:

Disclosed is a hybrid power generation facility. The hybrid power generation facility includes a gas turbine including a compressor configured to compress air introduced from an outside, a combustor configured to mix the compressed air with fuel and to combust the air and fuel mixture, and a turbine configured to produce power with first combustion gas discharged from the combustor, a boiler configured to burn a mixture of the first combustion gas and air, a first water heat exchanger configured to pass second combustion gas discharged from the boiler and to heat water through heat exchange to between the water and the second combustion gas, a water supply device configured to supply water to the first water heat exchanger, a steam turbine through which steam generated in the boiler passes, and a fuel heat exchanger configured to pass fuel supplied to the combustor and to pass a portion of water that is returned to the water supply device from the first water heat exchanger and has a higher temperature than the water supplied to the first water heat exchanger.

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Номер записи: 55
07-04-2016 дата публикации

Compressor and turbocharger

Номер: US20160097297A1
Автор: Clive R. Martin, Thurstan Twist
Принадлежит: Cummins Ltd

A compressor comprising a housing having an axial intake and an annular outlet volute, an impeller mounted for rotation about a shaft axis, the impeller having a plurality of blades, an annular diffuser passage surrounding the impeller extending from a diffuser inlet to a diffuser outlet, the impeller hub being mounted in an annular impeller recess in a first wall member of the diffuser, wherein an annular diffuser recess is provided in the first wall member extending radially outwardly from a first end to a second end, the first end being located at a radially outer end of the impeller recess, the second end being located axially inboard of the first end of the diffuser recess and wherein the depth of the diffuser recess at the first end of the diffuser recess is at least 30% of the maximum depth of the impeller recess.

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Номер записи: 56
19-03-2020 дата публикации

PERMANENT MAGNET, ROTARY ELECTRIC MACHINE, AND VEHICLE

Номер: US20200090844A1
Автор: HAGIWARA Masaya, OKAMOTO Keiko, SAKURADA Shinya
Принадлежит:

A permanent magnet comprises crystal grains each including a main phase. An average size of the crystal grains is 1.0 μm or less, and a degree of orientation of easy magnetization axes of the crystal grains to an easy magnetization axis of the magnet is 15% or more and 90% or less. A recoil magnetic permeability is 1.13 or more, a residual magnetization is 0.8 T or more and less than 1.16 T, and an intrinsic coercive force is 850 kA/m or more. 1. A permanent magnet comprising crystal grains including a main phase , whereinan average size of the crystal grains is 1.0 μm or less,a degree of orientation of easy magnetization axes of the crystal grains to an easy magnetization axis of the magnet is 15% or more and 90% or less, anda recoil magnetic permeability is 1.13 or more, a residual magnetization is 0.8 T or more and less than 1.16 T, and an intrinsic coercive force is 850 kA/m or more.2. The magnet according to claim 1 ,wherein the main phase is an R-Fe-B-based magnetic phase,where R is at least one element selected from the group consisting of Nd, Pr, Dy, Tb, and Ho.3. The magnet according to claim 2 ,{'sub': 2', '14, 'wherein the R-Fe-B-based magnetic phase is an NdFeB-type crystal phase.'}4. The magnet according to claim 2 , further comprisinga grain boundary phase,wherein a concentration of the R element of the grain boundary phase is higher than a concentration of the R element of the main phase.5. The magnet according to claim 1 ,wherein the main phase is an R-Co-based magnetic phase,where R is at least one element selected from the group consisting of rare earth elements.6. The magnet according to claim 5 ,{'sub': 2', '17, 'wherein the R-Co-based magnetic phase is an SmCo-type crystal phase.'}7. The magnet according to claim 5 , further comprisinga grain boundary phase,wherein a concentration of the R element of the grain boundary phase is higher than a concentration of the R element of the main phase.8. A rotary electric machine comprising:a stator; anda ...

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Номер записи: 57
12-05-2022 дата публикации

VEHICLE HAVING A TURBINE SYSTEM

Номер: US20220145795A1
Автор: Menyhart Tivadar
Принадлежит:

1. Method, device and system for operating internal combustion engines with a considerably increased pressure ratio and vehicle with this system. 12-. (canceled)3. A method for generating energy from a liquid oxidizer and a liquid or gaseous fuel in a turbo-electric system , wherein the method comprising the steps of:providing only liquid oxidizer as an oxidizer in a turbine system for a combustion process, injected the oxidizer in liquid form directly into a combustion chamber of a turbine:pressurizing the oxidizer in liquid form in a pump instead of in a compression phase;evaporating the oxidizer only in the combustion chamber, then the oxidizer is burned together with the fuel, the oxidizer being brought to an injection pressure below its critical temperature and injected into the combustion chamber;expanding combustion gases with a total pressure ratio of 200 or more (π>>200) in the turbine;delivering mechanical shaft energy from the turbine to a generator, wherein the generator is capable of being switched to an electric motor operation to drive the turbine in a startup operation;converting electrical current from the generator as required; andpassing the electrical current on to an electric drive motor by way of an intermediate storage that receives the electrical current from the generator or to the electric drive motor directly from the generator.4. A device for performing the method according to the device comprising:a vacuum-insulated vessel for storing the oxidizer;a fuel vessel for storing the fuel;an oxidizer pump, which is arranged downstream of the vacuum-insulated vessel, with connection to the turbine, or with connection to its own electric motor;a fuel pump, which is arranged downstream of the fuel vessel, with a connection to the turbine, or with a connection to its own electric motor;the combustion chamber, with an injection plate located therein, with connection to the oxidizer pump and connection to the fuel pump;the turbine, which is arranged ...

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Номер записи: 58
06-04-2017 дата публикации

Remote monitoring for hydraulic fracturing equipment

Номер: US20170096885A1
Автор: Brandon N. Hinderliter, Jared Oehring
Принадлежит: US Well Services LLC

A hydraulic fracturing system for fracturing a subterranean formation including a pump in communication via pump components with a wellbore that intersects the formation, and that pressurizes fluid in the wellbore, the fluid comprising a fracturing fluid slurry. The system further includes hydraulic fracturing system components for making the fracturing fluid slurry, and a monitoring system that selectively captures and transmits real time images of at least one of the hydraulic fracturing system components or pump components to enable remote monitoring of the at least one of the hydraulic fracturing system components or pump components.

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Номер записи: 59
14-04-2016 дата публикации

BASEPLATE FOR MOUNTING AND SUPPORTING ROTATING MACHINERY AND SYSTEM COMPRISING SAID BASEPLATE

Номер: US20160102581A1
Автор: DEL BONO Alessandro
Принадлежит:

The baseplate comprises a central elongate torsion and bending resisting member and at least a first load bearing cross-member, which extends transversely to the elongate torsion and bending resisting member. At least one machinery support platform is rigidly connected to the elongate torsion and bending resisting member and to the first load bearing cross-member. The elongate torsion and bending resisting member comprises vertically extending longitudinal lateral walls, where along auxiliaries of the rotating machinery are supported. The machinery support platform projects sideways beyond the longitudinal lateral walls of the elongate torsion and bending resisting member. 1. A baseplate for mounting and supporting rotating machinery , comprising: a central elongate torsion and bending resisting member; at least a first load bearing cross-member extending transversely to the elongate torsion and bending resisting member; at least one machinery support platform rigidly connected to said elongate torsion and bending resisting member and to said first load bearing cross-member; wherein said elongate torsion and bending resisting member comprises vertically extending longitudinal lateral walls , where along auxiliaries of said rotating machinery are supported; and wherein the machinery support platform projects sideways beyond the longitudinal lateral walls of the elongate torsion and bending resisting member2. The baseplate according to claim 1 , wherein said lateral walls are planar.3. The baseplate of claim 1 , wherein the elongate torsion and bending resisting member has a vertical extension sufficient for an operator to access said auxiliaries maintaining an erected and ergonomic position and accessing a space underneath said machine support platform.4. The baseplate of claim 1 , wherein said at least one load bearing cross-member has vertically extending lateral walls for receiving auxiliaries of the rotating machinery.5. The baseplate of claim 1 , further ...

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Номер записи: 60
14-04-2016 дата публикации

A ROTOR ASSEMBLY FOR AN OPEN CYCLE ENGINE, AND AN OPEN CYCLE ENGINE

Номер: US20160102608A1
Автор: LYNN Robert Gulliver
Принадлежит: XEICLE LIMITED

A rotor assembly for an engine, comprising: a rotor, supported on bearings for axial rotation, a rotor portion forming a compression passage extending outwards from the axis, gases entering the rotor through inlets at the axis and flowing outwards through the compression passage; a combustion chamber supported within the compression passage near the maximum radius of the rotor having a closed outer end and combustion chamber gases inlets through which gases enter the combustion chamber, each combustion chamber having a fuel inlet, and; one or more expansion passages in fluidic connection with and extending radially inwards from the combustion chamber within a compression passage and fluidically connecting at or near the rotor axis to a combustion gas outlet tube that extends along the rotor axis, combustion gases created by combustion of fuel with inlet gases within the combustion chamber expanding as they flow inwards through the expansion passage. 1208.-. (canceled)209. A rotor assembly for an engine , comprising:a rotor, supported on one or more bearings configured to allow the rotor to rotate about a rotor axis, a portion of the rotor forming at least one compression passage that extends outwards from the rotor axis, gases entering the rotor through rotor gas inlets at or near the rotor axis and flowing outwards from the rotor gases inlets through the one or more compression passages undergoing compression as the rotor rotates;one or more combustion chambers, each located and supported within a compression passage at or near the maximum radius of the rotor from the rotor axis, each combustion chamber having a closed radially outermost end and one or more combustion chamber gases inlets distributed around the combustion chamber through which gases enter the combustion chamber, each combustion chamber further having at least one fuel inlet adapted to allow fuel to enter the combustion chamber and therein mix and combust;one or more expansion passages, each in ...

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Номер записи: 61
23-04-2015 дата публикации

HYDRAULIC ENGINE INCLUDING HYDRAULIC POWER UNIT

Номер: US20150107237A1
Автор: IHSL Lucas
Принадлежит:

Provided is a hydraulic engine that generates power using oil pressure, the hydraulic engine including: a hydraulic power unit including a hydraulic tube comprising a hollow portion having an opened front end and being filled with a fluid, an amplitude amplification device that is disposed at the rear side of the hydraulic tube, an oscillator that is disposed at the rear side of the amplitude amplification device so as to be deformed and increases and decreases a pressure within the hydraulic tube, and an oscillator head that is attached to a front end of the oscillator. 1. A hydraulic engine comprising:a hydraulic power unit comprising a hydraulic tube comprising a hollow portion having an opened front end and being filled with a fluid, an amplitude amplification device that is disposed at the rear side of the hydraulic tube, an oscillator that is disposed at the rear side of the amplitude amplification device so as to be deformed and increases and decreases a pressure within the hydraulic tube, and an oscillator head that is attached to a front end of the oscillator,wherein the hydraulic tube extends in a longitudinal direction, comprises a metal tube formed on the outside thereof and an elastic tube formed on the inside thereof, and is configured in the form of a double tube having an outer hollow and an inner hollow,wherein the amplitude amplification device comprises a casing having a hollow formed therein, a swell tube that is disposed within the casing and has a cylindrical hollow therein, a plurality of vibration rods that are disposed in the hollow of the swell tube, and an elastic chip that is disposed in the hollow of the swell tube, intersects with the hollow, and is disposed between the plurality of vibration rods,wherein the oscillator moves bidirectionally and changes a pressure within the hydraulic tube by applying deformation force to the vibration rod according to its deformation so that a fluid within the hydraulic tube is extruded to the outside ...

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Номер записи: 62
13-04-2017 дата публикации

Methods and Systems For Cooling A Pressurized Fluid With A Reduced-Pressure Fluid

Номер: US20170102008A1
Автор: Di Bella Francis A., Oliphant Kerry N.
Принадлежит:

Systems and methods for reducing the pressure of a first pressurized fluid, thereby reducing the temperature of the pressurized fluid, and utilization of the reduced-pressure and temperature fluid to cool a second fluid. Such an approach can enable a reduction in the size and weight of a hydraulic system, utilize waste energy in a system, and/or minimize electrical power requirements of a system, among other benefits. 1. A pumping system , comprising:a turbine mechanically coupled to a pump, the turbine having an outlet; anda heat exchanger fluidly coupled to the turbine downstream of the outlet and fluidly coupled to the pump, the heat exchanger configured to provide heat transfer between a working fluid exhausted from the turbine outlet and a liquid being pumped by the pump to cool the liquid being pumped.2. A pumping system according to claim 1 , wherein the turbine is a non-combustion vapor expansion turbine.3. A pumping system according to claim 1 , wherein the turbine has an inlet claim 1 , the pumping system further comprising at least one valve located upstream of the turbine inlet claim 1 , the valve configured to control a power output of the turbine.4. A pumping system according to claim 1 , further comprising a hydraulic circuit including at least one load claim 1 , wherein the pump is configured to maintain a pressure of a hydraulic fluid in the hydraulic circuit.5. A pumping system according to claim 1 , wherein the turbine is a non-combustion turbine and is configured to receive a high-pressure vapor as a working fluid.6. A pumping system according to claim 1 , wherein the pump is configured to pressurize a hydraulic fluid in a hydraulic drive system.7. A mechanical system for a mobile apparatus claim 1 , comprising:a pressurized gas system;a hydraulic circuit including at least one load; and{'claim-ref': {'@idref': 'CLM-00001', 'claim 1'}, 'a pumping system according to , wherein a pressurized gas from the pressurized gas system is the turbine ...

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Номер записи: 63
23-04-2015 дата публикации

Marine current power generation device

Номер: US20150110605A1
Автор: Tatsuo Yamashita, Than Trong Long, Yasuo Kabata
Принадлежит: Toshiba Corp

In one embodiment, a marine current power generation device has rotary blades, rotating shaft, power generator, guide bearings, thrust collars and thrust bearings. The guide bearing has a second slide surface being slidable relative to the first slide surface of the rotating shaft. The thrust bearing has a fourth slide surface being slidable relative to the third slide surface of the rotary plate of the thrust collar. The materials of the first and third slide surfaces include ferrous materials, stainless materials, Ti, Ti alloy, Co, or Co alloy. The materials of the second and fourth slide surfaces include a resin material filled with a first fibrous member and a second fibrous member. The second fibrous member is smaller than the first fibrous member.

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Номер записи: 64
21-04-2016 дата публикации

TURNING DEVICE AND ROTARY MACHINE

Номер: US20160108760A1
Автор: Yamada Masataka
Принадлежит: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION

A turning device is provided with: a casing; a drive motor provided above the casing; a drive wheel rotated by the drive motor, the drive wheel being supported on one side of a reference plane located on the drive axis of the drive motor and parallel to the vertical direction, the drive wheel being rotatable about a reference line intersecting the reference plane; a driven wheel disposed within the casing, the driven wheel being supported so as to be rotatable about an axis parallel to the reference line, the driven wheel being connected to the drive wheel through an annular member; a first gear wheel coaxially connected to the driven wheel and having a first spur gear; a second gear wheel having a second spur gear meshing with a wheel gear which is provided coaxially with a rotating shaft extending parallel to the reference line, the second spur gear also meshing with the first spur gear of the first gear wheel; an arm member for rotatably supporting the second gear wheel; a movement mechanism for moving the arm member to thereby move the second gear wheel between a meshed position at which the second gear wheel is meshed with the wheel gear and a retracted position at which the second gear wheel is not meshed with the wheel gear; and a cover adapted to mountable and removable from the casing and covering the drive wheel. 1. A turning device comprising:a casing;a driving motor which is attached to be positioned higher than the casing;a driving wheel which is disposed above the casing, is supported on one side with respect to a reference plane that is parallel to a vertical direction on a driving shaft of the driving motor and, to be rotatable around a reference line that intersects the reference plane, and is rotated by the driving motor;a driven wheel which is disposed in the casing, is supported to be rotatable around an axis that is parallel to the reference line, and is connected to the driving wheel via an annular member;a first toothed wheel which is ...

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Номер записи: 65
11-04-2019 дата публикации

ENGINE RECOVERY SYSTEM FOR POWER SYSTEM

Номер: US20190106130A1
Автор: Branka Scott Michael, Gawel, Goetzke Michael B., JR. Edward J., Loya Sudarshan, Moravec Keith, Pocha Siva Sankara Reddy
Принадлежит: Progress Rail Locomotive Inc.

An energy recovery system for a power system is disclosed. The power system includes an engine, a generator driven by the engine, an electrical bus configured to receive electrical power from the generator, an exhaust conduit configured to receive exhaust gases from the engine, and a turbocharger coupled to the exhaust conduit. The energy recovery system includes a bypass conduit, a turbo-generator, and a synchronizer. The bypass conduit is coupled to the exhaust conduit, and facilitates a portion of exhaust gases from the exhaust conduit to bypass the turbocharger. The turbo-generator is coupled to the bypass conduit, and is driven by the portion of exhaust gases bypassing the turbocharger. Further, the synchronizer modulates one or more parameters of electrical power received from the turbo-generator based on one or more parameters of electrical power present on the electrical bus. The synchronizer transmits modulated electrical power to the electrical bus. 1. An energy recovery system for a power system , the power system includes an engine , a generator driven by the engine to produce electrical power , an electrical bus configured to receive electrical power from the generator , an exhaust conduit configured to receive exhaust gases discharged from the engine , and a turbocharger coupled to the exhaust conduit to receive exhaust gases from the engine and configured to provide compressed air to the engine , the energy recovery system comprising:a bypass conduit coupled to the exhaust conduit upstream of the turbocharger, the bypass conduit facilitates a portion of exhaust gases from the exhaust conduit to bypass the turbocharger;a turbo-generator coupled to the bypass conduit, the turbo-generator being driven by the portion of exhaust gases bypassing the turbocharger to generate electrical power; anda synchronizer electrically coupled to the turbo-generator and the electrical bus, the synchronizer configured to modulate one or more parameters of electrical power ...

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Номер записи: 66
26-04-2018 дата публикации

REMOTE MONITORING FOR HYDRAULIC FRACTURING EQUIPMENT

Номер: US20180112507A1
Автор: Hinderliter Brandon N., OEHRING Jared
Принадлежит: U.S. Well Services, LLC

A hydraulic fracturing system for fracturing a subterranean formation including a pump in communication via pump components with a wellbore that intersects the formation, and that pressurizes fluid in the wellbore, the fluid comprising a fracturing fluid slurry. The system further includes hydraulic fracturing system components for making the fracturing fluid slurry, and a monitoring system that selectively captures and transmits real time images of at least one of the hydraulic fracturing system components or pump components to enable remote monitoring of the at least one of the hydraulic fracturing system components or pump components. 1. A hydraulic fracturing system for fracturing a subterranean formation comprising:a pump in communication via pump components with a wellbore that intersects the formation, and that pressurizes fluid in the wellbore, the fluid comprising a fracturing fluid slurry;hydraulic fracturing system components for making the fracturing fluid slurry; anda monitoring system that selectively captures and transmits real time images of a blender unit to enable remote monitoring of the blender unit;wherein the monitoring system selectively captures and transmits real time images of a hopper of the blending unit, so that a slurry level within the hopper is discernible in the images.2. The hydraulic fracturing system of claim 1 , wherein the monitoring system comprises:a camera;a controller;a display;a human machine interface; andcommunication means between the camera, controller, human machine interface, and the display.3. The hydraulic fracturing system of claim 1 , wherein the display comprises a monitor from which the images are viewed.4. The hydraulic fracturing system of claim 3 , wherein the display is disposed within a passenger compartment mounted to the blender unit claim 3 , so that the images can be viewed by operations personnel in the passenger compartment.5. The hydraulic fracturing system of claim 1 , wherein the monitoring system ...

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Номер записи: 67
26-04-2018 дата публикации

Vaneless space guide ring spacers for turbocharger

Номер: US20180112551A1
Автор: John R. Zagone, Matthew King
Принадлежит: BorgWarner Inc

Variable geometry turbine turbochargers with rotating guide vane members and spacer members. The spacer members are positioned in the space on the guide ring members between the ring of guide vane members and the turbine wheel.

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Номер записи: 68
09-06-2022 дата публикации

Intercooled Cascade Cycle Waste Heat Recovery System

Номер: US20220178268A1
Автор: Joseph Harris, Paul Angel
Принадлежит: Industrom Power LLC

Provided herein is a power generation system and method for transforming thermal energy, such as waste heat, into mechanical energy and/or electrical energy. The system employs features designed to accelerate start times, reduce size, lower cost, and be more environmentally friendly. Tire system may include multiple compressors on separate pinion shafts with multiple expanders, a temperature valve upstream of compressors with a mass management system downstream, an intercooler between compressors, and a cascade exchanger. In one embodiment, the system is configured to drive a synchronous generator, with the separate pinion shafts rotating at two separate, but constant, speeds.

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Номер записи: 69
18-04-2019 дата публикации

SUPPLEMENTAL PACK DRIVEN BY BLEED AIR AND CABIN AIR

Номер: US20190112052A1
Автор: Bruno Louis J., Millot Christina W.
Принадлежит:

An airplane is provided. The airplane includes a pack. The pack includes a shaft, a compressor, and a turbine coupled to the compressor via the shaft. The turbine receives and expands a first medium to provide power to the compressor via the shaft. The compressor receives and compresses a second medium in accordance with the power provided by the turbine via the shaft. The turbine is fluidly coupled to a heat exchanger of an air conditioning system. 1. A pack , comprising:a shaft;a compressor; anda turbine coupled to the compressor via the shaft,wherein the turbine receives and expands a first medium to provide power to the compressor via the shaft,wherein the compressor receives and compresses a second medium in accordance with the power provided by the turbine via the shaft,wherein the turbine is fluidly coupled to a heat exchanger of an air conditioning system.2. The pack of claim 1 , wherein the pack comprises a second turbine coupled to the compressor via the shaft.3. The pack of claim 2 , wherein the second turbine receives and expands a third medium to provide power to the compressor via the shaft.4. The pack of claim 1 , wherein the pack comprises a second compressor coupled to the shaft.5. The pack of claim 4 , wherein the second compressor provides a second stage of compression of the second medium.6. The pack of claim 1 , wherein the first medium comprises bleed air claim 1 ,wherein the second medium comprises fresh air.7. The pack of claim 1 , wherein the pack is configured to operate in a first or second mode.8. The pack of claim 7 , wherein the first mode is utilized for low altitude or ground operations.9. The pack of claim 7 , wherein the second mode is utilized for high altitude operations.10. A system claim 7 , comprising:an air conditioning pack comprising a heat exchanger; anda supplemental pack comprising a shaft, a compressor, and a turbine coupled to the compressor via the shaft, and at least one heat exchanger,wherein the turbine is fluidly ...

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Номер записи: 70
09-04-2020 дата публикации

DUAL TURBINE THERMAL MANAGEMENT SYSTEM (TMS)

Номер: US20200108937A1
Автор: Behrens William W., Tucker Andrew R.
Принадлежит: The Boeing Company

A thermal management system for an aircraft engine. The thermal management system extracts interstage engine bleed air from the engine's compressor and performs three stage cooling of the interstage engine bleed air using two heat exchangers and a vapor cycle system evaporator. The cooled air is then further cooled by expansion through a set of turbines and subsequently used as a heat sink for heat loads on the aircraft. 1102. A thermal management system (TMS) () , comprising:{'b': 108', '122', '122', '112', '106', '122', '122', '110', '106, 'i': a', 'b, 'a fan () drawing a first portion () of ram air () into an engine compressor () in an aircraft engine core () and a second portion () of the ram air () into an engine duct () bypassing the aircraft engine core ();'}{'b': 112', '122', '122', '126', '112', '106', '106', '106', '106', '106', '106', '126', '106', '106', '126, 'i': a', 'a', 'b', 'c', 'a', 'b', 'c', 'c', 'a', 'a, 'the engine compressor () compressing the first portion () of the ram air () so as to form compressed air (), the engine compressor () including a first compressor stage (), a final compressor stage (), and one or more intermediate compressor stages () between the first compressor stage () and the final compressor stage (), each of the intermediate compressor stages () compressing the compressed air () outputted from a previous intermediate compressor stage () or first compressor stage () so as to form interstage compressed air ();'}{'b': 156', '126', '128', '112, 'i': 'a', 'a duct system () transporting a portion of the interstage compressed air () (engine bleed air ) from the engine compressor ();'}{'b': 134', '156', '110', '134', '1', '128', '156', '122', '122', '110', '128', '138', '156, 'i': b', 'a, 'a first heat exchanger () connected to the duct system () and the engine duct (), the first heat exchanger () transferring first heat (H) from the engine bleed air () in the duct system () to the second portion () of the ram air () in the engine ...

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Номер записи: 71
13-05-2021 дата публикации

CONSTANT VOLTAGE POWER DISTRIBUTION SYSTEM FOR USE WITH AN ELECTRIC HYDRAULIC FRACTURING SYSTEM

Номер: US20210140423A1
Автор: Hinderliter Brandon N., OEHRING Jared
Принадлежит: U.S. Well Services, LLC

A hydraulic fracturing system includes a turbine generator for producing electricity at a well site, the turbine generator producing electrical energy at a voltage. The system also includes an electric pump electrically coupled to the turbine generator and receiving operative power from the turbine generator. The system further includes switch gear arranged between the electric pump and the turbine generator, the switch gear distributing electrical energy from the turbine generator to the electric pump, wherein the voltage remains substantially constant from the turbine generator to the electric pump. 1. A hydraulic fracturing system , comprising:a plurality of turbine generators for producing electricity at a well site, the plurality of turbine generators producing electrical energy at a voltage; anda plurality of electric pumps, positioned on a support structure, electrically coupled to the plurality of turbine generators, each electric pump of the plurality of electric pumps being configured to operate at the voltage.2. The hydraulic fracturing system of claim 1 , further comprising:switch gear arranged between the plurality of electric pumps and the plurality of turbine generators, the switch gear distributing electrical energy from the plurality of turbine generators to the plurality of electric pumps.3. The hydraulic fracturing system of claim 2 , wherein the switch gear and the plurality of electric pumps comprise indicators claim 2 , the indicators identifying respective outlet and inlet connectors of the switch gear and plurality of electric pumps that are coupled together via respective power cables.4. The hydraulic fracturing system of claim 1 , further comprising:a step down transformer configured to receive electric energy from the plurality of turbine generators; andauxiliary equipment, the auxiliary equipment utilizing an operating voltage that is less than the voltage, the step down transformer configured to reduce the voltage to the operating ...

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Номер записи: 72
07-05-2015 дата публикации

Coupling of shafts using variable-profile splines

Номер: US20150125269A1
Автор: Guillaume Patin, Stephane Bois
Принадлежит: SNECMA SAS

A device for coupling two shafts by a gear mechanism includes a coupling part ending one of the two shafts. The coupling part is fitted concentrically into a complementary coupling part ending the other shaft. Splines of the coupling part have a constant profile along a median zone of the coupling part and which, in a first zone in continuation of the median zone, has a smaller thickness, between flanks of a spline, than a maximum thickness of the same spline in the median zone. Splines of the coupling part continue, beyond the first zone, as far as a centering zone on the same side as the first zone. The splines and the spline bottoms have, in the coupling zone between the centering zone and the first zone, a profile that continuously couples the splines and the spline bottoms to the surface of the centering zone.

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Номер записи: 73
05-05-2016 дата публикации

MODULAR THRUST SYSTEM

Номер: US20160123182A1
Автор: Duffy Michael J., Newman Daniel I., Samaritano Anthony
Принадлежит:

Disclosed herein is one embodiment of a thrust system that includes at least one modular thrust unit and at least one control module. The at least one modular thrust unit includes a base that is made from structural members that are inter-connectable in a plurality of different structural configurations. The at least one modular thrust unit further includes at least one thrust generator coupleable to the base in a thrust configuration and at least one power source operable to deliver power to the at least one thrust generator. The at least one control module is coupleable to the at least one modular thrust unit and operable to control at least one of the at least one thrust generator and the at least one power source. 1. A thrust system , comprising: a base comprising structural members inter-connectable in a plurality of different structural configurations;', 'at least one thrust generator coupleable to the base in a thrust configuration; and', 'at least one power source operable to deliver power to the at least one thrust generator; and, 'at least one modular thrust unit, wherein the modular thrust unit comprisesat least one control module coupleable to the at least one modular thrust unit and operable to control at least one of the at least one thrust generator and the at least one power source.2. The thrust system of claim 1 , wherein the base comprises at least one coupler mechanism for coupling together at least one other modular thrust unit to form an aggregated thrust unit.3. The thrust system of claim 1 , wherein the at least one modular thrust unit comprises a plurality of modular thrust units claim 1 , wherein each modular thrust unit is independently operable to generate thrust and the plurality of modular thrust units are interdependently operable to generate thrust claim 1 , wherein the plurality of modular thrust units are inter-coupleable to form an aggregated thrust unit with an aggregated configuration.4. The thrust system of claim 1 , wherein the ...

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Номер записи: 74
05-05-2016 дата публикации

METHOD AND A CIRCUIT FOR VENTILATING EQUIPMENT OF A TURBOJET BY THERMOELECTRICITY

Номер: US20160123185A1
Автор: DOMECQ Lise Jeanine Léonie, Le Pache Gwenolé Yann
Принадлежит: SNECMA

The invention provides a method of ventilating equipment of a turbojet, the turbojet () having a cold zone (ZF) including a fan () upstream from a hot zone (ZC), the turbojet equipment () for ventilating being arranged in a ventilation space () available around the hot zone between a primary air stream passage () and a secondary air stream passage () of the turbojet, the method comprising taking ventilation air from one of the air stream passages in order to convey it to the ventilation space, and providing forced flow of the ventilation air by means of at least one electric fan () positioned inside the ventilation space and powered electrically by at least one thermoelectric generator () suitable for inducing a potential difference (ΔV) and positioned in a wall () between the ventilation space and the secondary air stream passage. 1. A method for the ventilation of equipment of a turbojet , the turbojet having a cold zone including a fan upstream from a hot zone , the turbojet equipment intended to be ventilated being arranged in a ventilation space available around the hot zone between a primary air stream passage and a secondary air stream passage of the turbojet , the method comprising taking ventilation air from one of the air stream passages in order to convey it to the ventilation space , and providing forced flow of the ventilation air by means of at least one electric fan positioned inside the ventilation space and powered electrically by at least one thermoelectric generator suitable for inducing a potential difference and positioned inside a wall separating the ventilation space from the secondary air stream passage , said electric fan being electrically powered at least after the turbojet has stopped , a first face of the thermoelectric generator being positioned beside the ventilation space so as to be cooled by the ventilation air , the operation of the fan being self-regulating , such that the fan stops operating when the cooling of the first face of ...

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Номер записи: 75
05-05-2016 дата публикации

Solar and wind powered blower utilizing a flywheel and turbine

Номер: US20160123331A1
Автор: Nix Martin Eugene
Принадлежит:

Developed is a blower to make compressed and high velocity air, using a solar powered electric blower, a wind powered blower, or a wind shroud. The compressed and high velocity air drives a turbine attached to a flywheel, thus overcoming the variability of wind and solar energy. Check valves are utilized. Thus providing compressed and high velocity air 24 hours a day, 7 days a week, year round. (68 words) 1a first blower utilizing a photovoltaic cell to make electricity for a electric motor;said first blower manufacturing said compressed and high velocity air into a casing via a air inlet;a second blower utilizing a wind turbine;said second blower manufacturing the compressed and high velocity air into said casing via said air inlet;a third blower utilizing a wind shroud;said wind shroud manufacturing the compressed and high velocity air into the casing via the air inlet;the casing containing a turbine;the casing containing a flywheel;said turbine attached and adjacent to said flywheel about a common rotating axis;the casing containing an air outlet;the casing containing a check valve;the casing containing a vacuum lock;said system means to stabilize the variability of wind and solar energy and to stabilize compressed and high velocity air for utilization 24 hours a day, 7 days a week, year round.. A system for manufacturing compressed and high velocity air; Developed is a blower powered by a photovoltaic cell, a wind turbine or a wind shroud, to drive a flywheel and turbine assembly.Nix (U.S. Pat. No. 5,488,801, issued Feb. 6, 1996) illustrates the use of a photovoltaic cell to drive a electric fan for cooling air to a greenhouse.Nix (U.S. patent application Ser. No. 11/634,312, Filing date Dec. 5, 2006. Projected publication date Jun. 5, 2008) illustrates the use of flywheels for blowing compressed and high velocity air. illustrates a electric motor driving a flywheel and a centrifuge blower. Paragraphs [0216] and [0196] describe the blower's operation.Nix (U.S. ...

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Номер записи: 76
24-07-2014 дата публикации

COMBINED PUMP AND ENERGY RECOVERY TURBINE

Номер: US20140202144A1
Автор: AL-HAWAJ OSAMA M.
Принадлежит: KUWAIT UNIVERSITY

The combined pump and energy recovery turbine includes at least one fluid flow pressurizing a sliding vane pump and a sliding vane energy recovery turbine that recovers energy from a second fluid flow, such as the brine discharge from an RO seawater desalination system. A cylindrical rotor has two sliding vanes in respective slots, the rotor being concentrically disposed within an oval-shaped enclosure defining two mirror image crescent-shaped chambers, each chamber having inlet and outlet passageways. The first chamber pressurizes the first fluid flow, and the second chamber functions as a second outflow-driven energy recovery turbine, thus enabling the single rotor device to operate as a pressurizing pump on the first fluid flow, and second outflow-driven energy recovery turbine recovering energy from the pressure drop in the second fluid flow. 1. A combined pump and energy recovery turbine , comprising:at least one cylindrical rotor having an outer axial wall defining a periphery of the cylindrical rotor;substantially radially opposed slots extending from proximate an axial center of the rotor outward through the outer wall of the rotor;a corresponding sliding vane disposed in each of the slots, the sliding vane including an outer tip, the slots constraining each of the sliding vanes to inward and outward sliding displacement guided by the slots, each of the sliding vanes being slidable outward beyond the peripheral outer wall of the rotor;a modular housing having at least one oval-shaped opening formed therethrough, the at least one rotor being rotatably disposed through the at least one oval-shaped opening in axial alignment with the modular housing;an end plate affixed to the housing in coaxial alignment with the rotor, the end plate and the rotor defining first and second crescent-shaped chambers within the at least one oval-shaped opening;a first inlet manifold passageway disposed in the modular housing, the first inlet manifold passageway opening into the ...

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Номер записи: 77
04-05-2017 дата публикации

ENERGY RECOVERY SYSTEM

Номер: US20170120194A1
Автор: Goto Akira, Takita Shigeo
Принадлежит:

An energy recovery system in a seawater desalination plant uses a reverse-osmosis membrane method for removing salinity from seawater. The system is configured to supply high-pressure water produced by pressurizing raw water with a high-pressure pump to a reverse-osmosis membrane cartridge, and to supply concentrated water discharged from the cartridge to an isobaric energy recovery device to recover pressure energy of the concentrated water whereby part of the raw water supplied to the isobaric energy recovery device is pressurized, and then to allow the pressurized raw water to merge into the high-pressure water pressurized by the high-pressure pump. The system includes a booster pump for boosting a pressure of the concentrated water discharged from the cartridge, and an energy recovery turbine for recovering energy by using the pressure head difference between the pressurized raw water from the isobaric energy recovery device and the high-pressure water discharged from the pump. 1. An energy recovery system for supplying high-pressure water discharged from a high-pressure pump configured to pressurize raw water to a reverse-osmosis membrane cartridge configured to process the high-pressure water by a reverse-osmosis membrane to produce processed water , supplying concentrated water discharged from the reverse-osmosis membrane cartridge to an isobaric energy recovery device to recover pressure energy of the concentrated water whereby part of the raw water supplied to the isobaric energy recovery device is pressurized to become pressurized raw water , and making the pressurized raw water merge into the high-pressure water pressurized by the high-pressure pump , the energy recovery system comprising:a booster pump provided between the reverse-osmosis membrane cartridge and the isobaric energy recovery device and configured to boost a pressure of the concentrated water discharged from the reverse-osmosis membrane cartridge; andan energy recovery turbine configured to ...

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Номер записи: 78
04-05-2017 дата публикации

Turbine Assembly for use in a Downhole Pulsing Apparatus

Номер: US20170122034A1
Автор: Alali Aref, Donoghue Colin, Nichols Rick
Принадлежит:

A downhole pulsing apparatus having a tubular housing, a first valve assembly positioned in the housing, first and second turbine stages each comprising a stator and a rotor positioned in the housing below the first valve assembly and a second valve assembly positioned in the housing. There is a tubular mandrel connected for rotation of the rotors of the turbine stages and to a second valve assembly. The first valve assembly includes a valve element which is movable between a first position wherein pressurized fluid flow entering the housing is directed to the first turbine assembly, and a second position wherein the fluid flow is directed primarily axially through the apparatus so as to partially bypass the first turbine stage. 1. A downhole pulsing apparatus comprising:an elongate tubular housing having a first upper end and a second lower end; a valve element reciprocally mounted in said housing, said valve element comprising an elongate stem having a first end forming a head portion, a second end, and a longitudinally extending bore, a radial bleed port formed in said body proximal said heat portion, a first radial aperture formed in said stem proximal said second end;', 'a first compression spring disposed in said housing for biasing said valve element to a first position;', 'a first chamber in surrounding relationship to said stem, said bleed port providing open communication between said chamber and said bore in said stem;, 'a first valve assembly positioned in said housing proximal said first end, said first valve assembly comprising a first stator assembly positioned in said housing below said first valve assembly, said first stator assembly comprising a first stator body having a through bore forming a first stator cavity and a plurality of radially outwardly extending angled vanes attached to said first stator body, a first stator annular flow path being formed between said first stator body and said housing;', 'a first rotor assembly positioned in said ...

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Номер записи: 79
04-05-2017 дата публикации

CENTERLINE-MOUNTED HYDRAULIC PITCH CHANGE MECHANISM ACTUATOR

Номер: US20170122119A1
Автор: Miller Brandon Wayne, Niergarth Daniel Alan, Zatorski Darek Tomasz
Принадлежит:

A method and system for controlling a pitch of blades of a fan assembly having a centerline axis of rotation is provided. The system includes a pitch change mechanism (PCM) including a hydraulic actuator positioned axisymmetric with respect to the fan assembly and configured to angularly displace the blades of the fan assembly between a first position and a second position. The PCM further includes a plurality of hydraulic fluid supply lines coupled in flow communication between the hydraulic actuator and a hydraulic fluid transfer sleeve, the hydraulic fluid transfer sleeve configured to transfer a flow of pressurized hydraulic fluid across a gap between a stationary member of the hydraulic fluid transfer sleeve and a rotatable member of the hydraulic fluid transfer sleeve. 1. A pitch control mechanism (PCM) for controlling the pitch of blades of a fan assembly having a centerline axis of rotation , the PCM comprising:a hydraulic actuator positioned axisymmetric with respect to said fan assembly and configured to angularly displace the blades of said fan assembly between a first position and a second position; anda plurality of hydraulic fluid supply lines coupled in flow communication between said hydraulic actuator and a hydraulic fluid transfer sleeve, said hydraulic fluid transfer sleeve configured to transfer a flow of pressurized hydraulic fluid across a gap between a stationary member of said hydraulic fluid transfer sleeve and a rotatable member of said hydraulic fluid transfer sleeve.2. The PCM of claim 1 , wherein said hydraulic actuator circumscribes a shaft drivingly coupled to said fan assembly.3. The PCM of claim 1 , wherein said hydraulic actuator is a rotary actuator.4. The PCM of claim 1 , wherein said hydraulic actuator is a linear actuator.5. The PCM of claim 1 , wherein said hydraulic actuator comprises a paddle-type actuator configured to vary the pitch of fan blades via a bell crank and yoke system.6. The PCM of claim 5 , wherein said paddle ...

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Номер записи: 80
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: 81
04-05-2017 дата публикации

A turbine engine comprising a drive system for a device such as an accessories case

Номер: US20170122122A1
Автор: Jean-Baptiste Etienne Bernard Lepretre
Принадлежит: Safran Aircraft Engines SAS

The present invention relates to a turbine engine ( 10 ) comprising: at least one hollow guidance arm ( 44 ) radially extending from a hub ( 38 ) to an annular housing ( 42 ), and having one radially external end which opens out in an opening ( 60 ) of said annular housing, a radial countershaft ( 48 ) located in said guidance arm ( 44 ) for rotatably driving at least one device arranged at the periphery of said annular housing ( 42 ). According to the invention, a transfer case ( 50 ) is disposed facing the opening ( 60 ) of the annular housing, and the turbine engine comprises rotational power transfer means ( 78, 52 ) between the radial countershaft ( 48 ) and the device, with the guidance arm ( 44 ) being equipped, at the external end thereof, with a widened section ( 56 ) by which it opens out in the opening ( 60 ) of the annular housing and in which part of the transfer case ( 50 ) is accommodated.

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Номер записи: 82
25-04-2019 дата публикации

CONVERTIBLE DUCTED FAN ENGINE

Номер: US20190120077A1
Автор: Kempshall Scott R.
Принадлежит:

A convertible ducted fan engine having a shroud, a drive shaft connected to a mechanical fan, and a rotational drive motor configured to rotate the mechanical fan. An embodiment includes a linear drive motor configured to translate the drive shaft and mechanical fan in a direction parallel to a longitudinal axis of the shroud. The convertible ducted fan engine includes a fluid-propulsion configuration in which the mechanical fan rotates freely with respect to the shroud to produce thrust through fluid flow, and a drive-wheel configuration in which the shroud rotates about the rotational axis. 1. A ducted fan engine , comprising:a drive shaft and a translation collar, wherein the drive shaft is configured to translate in a direction parallel to a longitudinal axis of the translation collar;a mechanical fan interconnected with the drive shaft, such that movement of the drive shaft in an axial direction causes movement of the mechanical fan in the axial direction, the mechanical fan having a plurality of blades concentrically arranged about a rotational axis, the mechanical fan configured to rotate about the rotational axis;a shroud interconnected with the translation collar;a fluid-propulsion configuration in which the mechanical fan rotates freely with respect to the shroud to produce thrust through fluid flow; anda drive-wheel configuration in which at least one of the blades in the plurality of blades is incapable of rotating with respect to the shroud, thereby causing concurrent rotation of the shroud and mechanical fan when the mechanical fan rotates about the rotational axis.2. The ducted fan engine of claim 1 , wherein drive-wheel configuration includes at least one of the blades in the plurality of blades is in contact with the shroud.3. The ducted fan engine of claim 1 , wherein the plurality of blades is concentrically arranged about the drive shaft claim 1 , such that the drive shaft is axially aligned with the rotational axis claim 1 , and the translation ...

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Номер записи: 83
25-08-2022 дата публикации

Shaft-less twin rotor turbomachinery and the applications

Номер: US20220268206A1
Автор: Shu Jianchao
Принадлежит:

This invention relates to shaft-less twin rotor turbomachinery and the applications the shaft-less turbomachine has a twin tubing rotator assembly with vortical effect passages forming a high power zone and lower power zone, the twin tubing rotator assembly has two rotors to rotate independently or together with multiple powers universal bearings, high speed seal assemblies, it combines the best features of high flow rate of axial turbomachine and high pressure output of centrifugal turbomachine with the most efficient blade and turbine designs, it represents a new era of this turbomachine, disrupt invention and would power millions of turbomachines like the turbo pumps for rocket engines, jet engine/ramjet, submarines/torpedo and ships with the most advanced propellers as well as compression/pumping stations, turbines for power plants at an unprecedented level of efficiency and reliability with the twin tubing full port rotor assembly. 1. A turbomachine system has at least one turbomachine , the at least one turbomachine has a body assembly , a twin tubing rotor assembly movably disposed in said body assembly by means of at least two ball bearings disposed between said twin tubing rotor assembly and said body assembly for providing dynamic supports , and by means of at least two seal assemblies disposed between said twin tubing rotor assembly and said body assembly for providing seals , said body assembly has a left body assembly having at least one fixed wheel and a body bore and a right body assembly having at least one fixed wheel and a body bore , said left body assembly has one of plurality of structures including one piece structure and two-piece structure , said right body assembly has one of plurality of structures including one piece structure and two-piece structure , said twin tubing rotor assembly has a left rotor having a tubing housing having at least one internal rotary wheel and at least one external rotary wheel and a tubing bore , a right rotor ...

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Номер записи: 84
11-05-2017 дата публикации

Heat engine system including an integrated cooling circuit

Номер: US20170130614A1
Автор: Jason D. Miller, Timothy Held
Принадлежит: Echogen Power Systems LLC

A heat engine system and a method for cooling a fluid stream in thermal communication with the heat engine system are provided. The heat engine system may include a working fluid circuit configured to flow a working fluid therethrough, and a cooling circuit in fluid communication with the working fluid circuit and configured to flow the working fluid therethrough. The cooling circuit may include an evaporator in fluid communication with the working fluid circuit and configured to be in fluid communication with the fluid stream. The evaporator may be further configured to receive a second portion of the working fluid from the working fluid circuit and to transfer thermal energy from the fluid stream to the second portion of the working fluid.

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Номер записи: 85
01-09-2022 дата публикации

SYSTEM FOR PUMPING HYDRAULIC FRACTURING FLUID USING ELECTRIC PUMPS

Номер: US20220275716A1
Автор: Broussard Joel N., Kurtz Robert, McPherson Jeff
Принадлежит: U.S. Well Services, LLC

A system for hydraulically fracturing an underground formation in an oil or gas well to extract oil or gas from the formation, the oil or gas well having a wellbore that permits passage of fluid from the wellbore into the formation. The system includes a plurality of electric pumps fluidly connected to the well, and configured to pump fluid into the wellbore at high pressure so that the fluid passes from the wellbore into the, and fractures the formation. The system can also include a plurality of natural gas powered generators electrically connected to the plurality of electric pumps to provide electrical power to the pumps. 1a pump fluidly connected to the well; andan electric motor to power the pump;the pump configured to pump fluid into the wellbore at high pressure so that the fluid passes from the wellbore into the formation, and fractures the formation.. A system for hydraulically fracturing an underground formation in an oil or gas well to extract oil or gas from the formation, the oil or gas well having a wellbore that permits passage of fluid from the wellbore into the formation, the system comprising: This application is a continuation of U.S. patent application Ser. No. 16/456,777, filed Jun. 28, 2019, titled “SYSTEM FOR PUMPING HYDRAULIC FRACTURING FLUID USING ELECTRIC PUMPS,” now U.S. Pat. No. 11,136,870, issued Oct. 5, 2021, which is a continuation of U.S. patent application Ser. No. 15/202,085, filed Jul. 5, 2016, titled “SYSTEM FOR PUMPING HYDRAULIC FRACTURING FLUID USING ELECTRIC PUMPS,” now U.S. Pat. No. 10,337,308, issued Jul. 2, 2019, which is a continuation of U.S. patent application Ser. No. 13/679,689, filed Nov. 16, 2012, titled “SYSTEM FOR PUMPING HYDRAULIC FRACTURING FLUID USING ELECTRIC PUMPS,” now U.S. Pat. No. 9,410,410, issued Aug. 9, 2016, the full disclosure of which is incorporated herein by reference in its entirety.This technology relates to hydraulic fracturing in oil and gas wells. In particular, this technology relates to ...

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Номер записи: 86
18-05-2017 дата публикации

Combined pump and turbine

Номер: US20170138213A1
Автор: Adebukola Olatunde
Принадлежит: Adebukola Olatunde

A combined pump and turbine (electromechanical converter), which may be operable as a motorized centrifugal pump for starting a siphon and as an electromechanical turbine particularly for transmission of a liquid, such as water, in a water treatment plant.

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Номер записи: 87
18-05-2017 дата публикации

GEARBOX OF AIRCRAFT TURBINE ENGINE

Номер: US20170138214A1
Автор: LEPRETRE Jean-Baptiste Etienne Bernard
Принадлежит: SAFRAN AIRCRAFT ENGINES

A gearbox for an aircraft turbine engine has a casing defining an enclosure for housing rotating elements lubricated by oil. At least one tubular sleeve is coupled to the rotating elements and configured to rotate a shaft. The sleeve includes splines configured to cooperate with complementary splines of said shaft. The gearbox further includes means for recovering lubricating oil from the rotating elements and conveying the recovered oil by streaming to the splines to lubricate the splines. 1. A gearbox for an aircraft turbine engine , comprising a casing defining an enclosure for housing rotating elements lubricated by oil , and at least one tubular sleeve coupled to the rotating elements and configured to rotate a shaft , the sleeve including splines configured to cooperate with complementary splines of said shaft , the gearbox further comprising means for recovering lubricating oil from the rotating elements and conveying recovered oil by streaming to the splines to lubricate the splines , said recovery and conveying means comprising at least one inner wall collecting oil from said casing , the gearbox being configured to cause the oil to stream over said at least one collecting inner wall during the operation of the turbine engine , wherein said recovery and conveying means comprise a channeling member that extends at least partially inside said sleeve , and at least one gutter configured to convey the oil that streams over said at least one collecting inner wall to the channeling member , in which said channeling member and said at least one gutter are supported by or formed with a flange of the casing , the flange defining said at least one collecting inner wall and supporting a rolling bearing of the sleeve , the flange including at least one radial opening allowing oil flowing on said collecting inner wall to reach said channeling member.2. The gearbox according to claim 1 , wherein the flange has a planar part and a hollow cylindrical part that extends ...

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Номер записи: 88
30-04-2020 дата публикации

Gearbox ratio change

Номер: US20200131924A1
Автор: Paul F. Fox
Принадлежит: Hamilton Sundstrand Corp

A method of modifying an existing gearbox wherein the existing gearbox has an input shaft connected to drive a first idler gear. The first idler gear engages a gear for driving a fuel pump at a first speed. There is a first distance between a center point of the first idler gear and the fuel pump gear. The step includes replacing the first idler gear with a replacement first idler gear having a distinct number of teeth, and replacing the fuel pump gear with a replacement fuel pump gear having a distinct number of teeth such that a speed output to the fuel pump is distinct from the speed at the fuel pump with the existing gearbox. A gearbox is also disclosed.

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Номер записи: 89
26-05-2016 дата публикации

Fluidfoil

Номер: US20160146015A1
Автор: Michael Georg KOZUCH, Zahid Muhammad HUSSAIN
Принадлежит: Rolls Royce PLC

There is disclosed a fluidfoil comprising a selectively fluid chargeable capillary and a flexible body adjacent the capillary, the shape of the flexible body being adjustable in use via controlling the degree to which the capillary is charged and therefore the forces that the capillary exerts on the flexible body.

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Номер записи: 90
26-05-2016 дата публикации

Hybrid ram air turbine

Номер: US20160146035A1
Автор: David Chapman, Michael Larson
Принадлежит: Hamilton Sundstrand Corp

A ram air turbine is provided that utilizes a hybrid design. The ram air turbine includes a hydraulic power conversion device directly coupled to a turbine shaft and an electric power conversion device coupled to a drive shaft. A gearbox is used to couple the turbine shaft to the drive shaft.

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Номер записи: 91
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: 92
18-05-2017 дата публикации

METHOD FOR OPERATING A DRIVE DEVICE FOR A MOTOR VEHICLE AND CORRESPONDING DRIVE DEVICE

Номер: US20170141650A1
Автор: KERSTEN ROBERT, Rosenberger Uwe, Sonner Markus
Принадлежит: Audi AG

A method for operating a drive device for a motor vehicle, said method includes: permanently supplying an entire exhaust gas of a drive aggregate of the drive device to a turbine of an exhaust gas turbocharger of the drive device via a variable turbine geometry and providing compressed air by means of a compressor coupled with the turbine for the drive aggregate; operating in at least one operating mode of the drive device in each operating point of the drive aggregate an electric machine, which is mechanically operatively connected with the turbine and the compressor, as a generator for braking the turbine; and braking the turbine by means of the electric machine the stronger the further a throttle flap arranged fluidly between the compressor and the drive aggregate is opened, while maintaining the operating point of the drive aggregate constant. 1. A method for operating a drive device for a motor vehicle , said method comprising:permanently supplying an entire exhaust gas of a drive aggregate of the drive device to a turbine of an exhaust gas turbocharger of the drive device via a variable turbine geometry and providing compressed air by means of a compressor coupled with the turbine for the drive aggregate;operating in at least one operating mode of the drive device in each operating point of the drive aggregate an electric machine, which is mechanically operatively connected with the turbine and the compressor, as a generator for braking the turbine; andbraking the turbine by means of the electric machine the stronger the further a throttle flap arranged fluidly between the compressor and the drive aggregate is opened, while maintaining the operating point of the drive aggregate constant.2. The method of claim 1 , wherein the variable turbine geometry is closed the further the further the throttle flap is opened.3. The method of claim 1 , wherein the turbine is braked by means of the electric machine the stronger the further the variable turbine geometry is ...

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Номер записи: 93
24-05-2018 дата публикации

STEAM WETNESS MEASUREMENT WITH MICROWAVE TOMOGRAPHY

Номер: US20180143146A1
Автор: Barham Scott Anthony
Принадлежит:

A system for measuring steam wetness, including: a plurality of microwave sensors for detecting microwave signals passing through a supply of steam flowing through a cavity; a calibration system for calibrating the plurality of microwave sensors; a film measurement system for measuring a characteristic of a film flowing along an inner surface of the cavity; a system for determining a characteristic of the steam flowing through the cavity based on data provided by the plurality of microwave sensors; and a system for determining a wetness of the steam flowing through the cavity based on the characteristic of the steam flowing through the cavity and the characteristic of the film flowing along the inner surface of the cavity. 1. A system for measuring steam wetness , comprising:a plurality of microwave sensors for detecting microwave signals passing through a supply of steam flowing through a cavity;a film measurement system for measuring a characteristic of a film flowing along inner surface of the cavity;a system for determining a characteristic of the steam flowing through the cavity based on data provided by the plurality of microwave sensors; anda system for determining a wetness of the steam flowing through the cavity based on the characteristic of the steam flowing through the cavity and the characteristic of the film flowing along the inner surface of the cavity.2. The system for measuring steam wetness according to claim 1 , further comprising a calibration system for calibrating the plurality of microwave sensors claim 1 , the calibration system obtaining phase shift and attenuation measurements over a range of frequencies using the plurality of microwave sensors.3. The system for measuring steam wetness according to claim 1 , wherein the cavity comprises a pipe.4. The system for measuring steam wetness according to claim 1 , wherein the plurality of microwave sensors are distributed about a circumference of the cavity.5. The system for measuring steam ...

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Номер записи: 94
25-05-2017 дата публикации

NEAR ZERO VELOCITY LUBRICATION SYSTEM FOR A TURBINE ENGINE

Номер: US20170145920A1
Автор: McCune Michael E., Schwarz Frederick M.
Принадлежит:

A system is provided for a turbine engine. This turbine engine system includes a rotating assembly, a bearing and a lubrication system. The bearing is configured with the rotating assembly. The lubrication system is configured to lubricate the bearing. The lubrication system includes a lubricant pump and a lubricant reservoir. The lubricant pump is mechanically coupled with and driven by the rotating assembly. The lubricant pump is configured with the lubricant reservoir so as to be at least partially submersed in lubricant contained within the lubricant reservoir. 1. A system for a turbine engine , comprising:a rotating assembly;a bearing configured with the rotating assembly; anda lubrication system configured to lubricate the bearing, the lubrication system comprising a lubricant pump and a lubricant reservoir;wherein the lubricant pump is mechanically coupled with and driven by the rotating assembly, and wherein the lubricant pump is configured with the lubricant reservoir so as to be at least partially submersed in lubricant contained within the lubricant reservoir.2. The system of claim 1 , wherein the rotating assembly includes a fan rotor claim 1 , a compressor rotor and a turbine rotor.3. The system of claim 2 , wherein the rotating assembly further includes a gear system mechanically coupled between the fan rotor and the turbine rotor claim 2 , and the bearing is configured with the gear system.4. The system of claim 3 , wherein the bearing comprises a journal bearing.5. The system of claim 2 , wherein the fan rotor is operable to windmill claim 2 , and the lubrication system is configured to lubricate the bearing during the windmilling.6. The system of claim 1 , wherein the lubrication system is configured to lubricate the bearing as the rotating assembly rotates in a first rotational direction and a second rotational direction.7. The system of claim 1 , wherein the lubrication system is operable to lubricate the bearing where the rotating assembly ...

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Номер записи: 95
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: 96
31-05-2018 дата публикации

Gas turbine engine wash system

Номер: US20180149038A1
Автор: Ethan Patrick O'Connor, Michael Edward Eriksen
Принадлежит: General Electric Co

A wash system for a gas turbine engine includes a core turning assembly having a motor configured to be mechanically coupled to the gas turbine engine. The rotor of the core turning assembly is further configured to rotate one or more components of a compressor section or a turbine section of the gas turbine engine at a rotational speed greater than two (2) revolutions per minute and less than five hundred (500) revolutions per minute during washing operations of the gas turbine engine.

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Номер записи: 97
07-05-2020 дата публикации

BOOSTER COMPRESSOR WITH SPEED CHANGE SYSTEM

Номер: US20200141417A1
Автор: Chandler Jesse M., Lents Charles E., Merry Brian D., Suciu Gabriel L., Taylor Stephen H.
Принадлежит:

A gas turbine engine includes a main engine compressor section. A booster compressor changing a pressure of airflow received from the main engine compressor section to a pressure desired for a pneumatic system. The booster compressor operates at airflow conditions greater than a demand by the pneumatic system. A speed change system driving the booster compressor at speeds corresponding to a demand of the pneumatic system. A bleed air system for a gas turbine engine and a method of controlling engine bleed airflow are also disclosed. 1. A gas turbine engine comprising;a main engine compressor section;a booster compressor for changing a pressure of airflow received from the main engine compressor section to a pressure desired for a pneumatic system, wherein the booster compressor operates at airflow conditions greater than a demand by the pneumatic system; anda variable speed transmission in driving engagement with the booster compressor, the variable speed transmission configured to drive the booster compressor at different speeds with a constant speed driving input.2. The gas turbine engine as recited in claim 1 , including an accessory gearbox driven by a shaft of the gas turbine engine claim 1 , the accessory gearbox coupled to drive the variable speed transmission.3. The gas turbine engine as recited in claim 2 , wherein the shaft of the gas turbine engine is coupled to one of a high spool or a low spool of the gas turbine engine.4. The gas turbine engine as recited in claim 3 , wherein the low spool of the gas turbine engine includes a low pressure compressor coupled to a low pressure turbine through an inner shaft.5. The gas turbine engine as recited in claim 4 , wherein the high spool of the gas turbine engine includes a high pressure compressor coupled to a high pressure turbine through an outer shaft.6. The gas turbine engine as recited in claim 1 , including an electric motor coupled to drive the variable transmission.7. The gas turbine engine as recited in ...

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Номер записи: 98
07-06-2018 дата публикации

CONSTANT VOLTAGE POWER DISTRIBUTION SYSTEM FOR USE WITH AN ELECTRIC HYDRAULIC FRACTURING SYSTEM

Номер: US20180156210A1
Автор: Hinderliter Brandon N., OEHRING Jared
Принадлежит: U.S. Well Services, LLC

A hydraulic fracturing system includes a turbine generator for producing electricity at a well site, the turbine generator producing electrical energy at a voltage. The system also includes an electric pump electrically coupled to the turbine generator and receiving operative power from the turbine generator. The system further includes switch gear arranged between the electric pump and the turbine generator, the switch gear distributing electrical energy from the turbine generator to the electric pump, wherein the voltage remains substantially constant from the turbine generator to the electric pump. 1. A hydraulic fracturing system for fracturing a subterranean formation comprising:a turbine generator for producing electricity at a well site, the turbine generator producing electrical energy at a voltage;an electric pump electrically coupled to the turbine generator and receiving operative power from the turbine generator; andswitch gear arranged between the electric pump and the turbine generator, the switch gear distributing electrical energy from the turbine generator to the electric pump, wherein the voltage remains substantially constant from the turbine generator to the electric pump.2. The system of claim 1 , wherein the turbine generator comprises a plurality of turbine generators and the electric pump comprises a plurality of electric pumps.3. The system of claim 1 , further comprising:a transformer having a high voltage input in electrical communication with an electrical output of the turbine generator, and a low voltage output;a step down transformer having an input that is in electrical communication with the low voltage output of the transformer; andauxiliary equipment associated with hydraulic fracturing, the auxiliary equipment utilizing an operating voltage that is less than the voltage generated by the turbine generator.4. The system of claim 1 , wherein the turbine generator is powered by natural gas.5. The system of claim 1 , wherein the switch ...

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Номер записи: 99
22-09-2022 дата публикации

Turbine generator

Номер: US20220298924A1
Автор: Gareth J ROBERTS, Matthew L Strange
Принадлежит: Rolls Royce PLC

A turbine generator comprising a turbine rotor comprising a hub and one or more blade stages. Each stage comprising a circumferential array of rotor blades in driving engagement with the hub. A turbine stator comprising a hub and one or more vane stages, each stage comprising a circumferential array of vanes. The turbine rotor and turbine stator being concentrically arranged about a common axis to define an annular flow path. The vane stages and blade stages being axially spaced along the axis and having one or more magnets arranged on the rotor. A generator stator concentrically aligned with the turbine rotor and turbine stator and one or more magnets arranged on the rotor. In use, when the turbine is driven to rotate about the axis, the or each of the magnets on the turbine rotor rotate relative to the generator stator in order to generate electric power.

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Номер записи: 100