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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 7116. Отображено 100.
05-04-2012 дата публикации

Reduced gulp fluid reservoir

Номер: US20120080272A1
Автор: Larry W. Spires, Paul A. Dickie
Принадлежит: United Technologies Corp

An assembly includes a reservoir for holding a fluid, and a scavenge passage connected to the reservoir at a reservoir inlet. The scavenge passage returns the fluid from a delivery location to the reservoir. A bleed passage is connected in fluid communication between the reservoir and the scavenge passage.

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Номер записи: 1
19-04-2012 дата публикации

Clustered inlet particle separator

Номер: US20120090468A1
Автор: Philip Harold Snyder
Принадлежит: Individual

A particle separator for a gas turbine engine is disclosed. The particle separator includes flow dividers operable to divide flow in a gas turbine engine particle separator and flow scavengers operable to scavenge flow in a gas turbine engine particle separator.

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Номер записи: 2
28-06-2012 дата публикации

Gas turbine engine heat exchanger

Номер: US20120159961A1
Автор: Carlos Soto-Gonzalez, Michael Stephen Krautheim
Принадлежит: Rolls Royce North American Technologies Inc

A gas turbine engine having a heat exchanger is disclosed. In one form the gas turbine engine includes a particle separator that can be used to separate particles or foreign objects and create a dirty flow and a clean flow. A blower can be used to discharge the particles or foreign objects from the separator. The heat exchanger includes a relatively warm flow path from a downstream region of a compressor and a relatively cool flow path from an upstream region of the compressor. The relatively cool flow path is merged with the dirty flow. In another embodiment, the gas turbine engine is a turbofan and the relatively cool flow path is merged with a bypass flow. In one embodiment of the engine the relatively warm flow path, after having exchanged heat with the relatively cool flow path is delivered to a working component without passing through a turbomachinery component.

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Номер записи: 3
05-07-2012 дата публикации

Gas turbine system and process

Номер: US20120167577A1
Автор: Anil Kumar Sharma, Bhaskar Pemmi, Indrajit Mazumder, Rajarshi Saha
Принадлежит: General Electric Co

A gas turbine system and process include a compressor component configured to compress fluid to form a compressed fluid stream, a combustor configured to receive at least a first portion of the compressed fluid stream and at least partially combust a syngas to form a combustor discharge stream, and a turbine component positioned to receive the combustor discharge stream and to form a turbine component stream. In the system and process, a cool stream directed from a second system cools the turbine component stream.

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Номер записи: 4
04-10-2012 дата публикации

Gearbox and oil spreader thereof

Номер: US20120247250A1
Автор: Apostolos Pavlos Karafillis, Brian Devendorf, Justin Paul Pare, Niranjan Patel
Принадлежит: General Electric Co

An oil spreader for a gearbox includes: an annular body with a central axis, opposed upper and lower ends, an upper portion adjacent the upper end, and a lower portion adjacent the lower end, the lower portion comprising at least two vanes extending between the upper portion and an annular ring disposed at the lower end, the vanes defining slots therebetween.

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Номер записи: 5
20-12-2012 дата публикации

Deaerator and conduit assembly

Номер: US20120318912A1
Автор: Christine Ingrid Schade, Melissa A. Bell
Принадлежит: Individual

An example deaerator assembly includes a housing having a housing inlet and a housing outlet. A conduit configured to communicate a deaerated coolant is located within the housing. A mixture of coolant and air is deaerated as the mixture is communicated from the housing inlet to the housing outlet within the housing and outside the conduit.

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Номер записи: 6
10-01-2013 дата публикации

Conversion of hydrocarbons to carbon dioxide and electrical power

Номер: US20130008175A1
Автор: Mark Mckenna
Принадлежит: JOHNSON MATTHEY PLC

A process for reducing CO 2 emissions from combined cycle power generation processes utilizing a gaseous hydrocarbon feed, which includes splitting the hydrocarbon feed into two portions; a first portion≦45% by volume of the feed and a larger portion≧55% by volume of the feed, feeding the first portion to an autothermal reforming process to generate a hydrogen-containing gas and a carbon dioxide stream, combining the hydrogen-containing stream with the second portion, combusting the resulting hydrogen-containing fuel stream with oxygen containing gas in a gas turbine to generate electrical power and passing the exhaust gas mixture from the gas turbine to a heat recovery steam generation system that feeds one or more steam turbines to generate additional electrical power. The captured carbon dioxide stream may be fed to storage or enhanced oil recovery processes. The process may be retrofitted into existing combined cycle processes.

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Номер записи: 7
28-02-2013 дата публикации

Valve for controlling flow of a turbomachine fluid

Номер: US20130048091A1
Автор: Enzo Dibenedetto, Francis Parnin, Robert E. Peters
Принадлежит: Individual

An exemplary valve device for controlling flow of a turbomachine fluid includes a housing and a flow control assembly within the housing. The housing has a first inlet, a second inlet, and an outlet. Movement of the housing to a first orientation causes the flow control assembly to move to a first position to restrict flow of a turbomachine fluid into the housing through the second inlet. Movement of the housing to a second orientation causes the flow control assembly to move to a second position to restrict flow of the turbomachine fluid into the housing through the first inlet.

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Номер записи: 8
09-05-2013 дата публикации

Gearbox deoiler with pre-pressuring component

Номер: US20130112029A1
Автор: Adrian L. Stoicescu, Mattew Slayter, Michael R. Blewett
Принадлежит: Hamilton Sundstrand Corp

A gearbox includes an inlet configured to receive a mixture of air and oil from an external source and a deoiler. The deoiler includes a shaft including an inlet passage and an outlet passage, both formed on an inner portion of the shaft and separated from one another, a separator unit coupled to and surrounding a portion of the shaft and including an inlet and an outlet and a pre-pressuring component coupled to the shaft that increases the pressure of the mixture of oil and air to form a pressurized mixture and provides the pressurized mixture to the inlet of the separator unit.

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Номер записи: 9
16-05-2013 дата публикации

Jet engine with carbon capture

Номер: US20130119667A1
Автор: Hermann De Meyer, Knut Borseth, Stellan Hamrin, Tor Christensen
Принадлежит: SARGAS AS

A method for producing electrical power and capture CO 2 , where gaseous fuel and an oxygen containing gas are introduced into a gas turbine to produce electrical power and an exhaust gas, where the exhaust gas withdrawn from the gas turbine is cooled by production of steam in a boiler ( 20 ), and where cooled exhaust gas is introduced into a CO 2 capture plant for capturing CO 2 from the cooled exhaust gas leaving the boiler ( 20 ) by an absorption/desorption process, before the treated CO 2 lean exhaust gas is released into the surroundings and the captured CO 2 is exported from the plant, where the exhaust gas leaving the gas turbine has a pressure of 3 to 15 bara, and the exhaust gas is expanded to atmospheric pressure after leaving the CO 2 capture plant. A plant for carrying out the method is also described.

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Номер записи: 10
23-05-2013 дата публикации

Method and apparatus for optimizing the operation of a turbine system under flexible loads

Номер: US20130125557A1
Автор: Alston I. Scipio, Douglas Corbin Warwick, Joseph Klosinski, Michael Anthony Cocca, Mike Yarnold, Ryan Eric Obenhoff, Sanji Ekanayake, Thomas John Freeman
Принадлежит: Individual

A gas turbine system includes a compressor protection subsystem; a hibernation mode subsystem; and a control subsystem that controls the compressor subsystem and the hibernation subsystem. At partial loads on the turbine system, the compressor protection subsystem maintains an air flow through a compressor at an airflow coefficient for the partial load above a minimum flow rate coefficient where aeromechanical stresses occur in the compressor. The air fuel ratio in a combustor is maintained where exhaust gas emission components from the turbine are maintained below a predetermined component emission level while operating at partial loads.

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Номер записи: 11
11-07-2013 дата публикации

Flushing the exhaust gas recirculation lines of a gas turbine

Номер: US20130174535A1
Автор: Floris Van Straaten, Juergen Hoffmann
Принадлежит: Alstom Technology AG

A method and gas turbine are provided for the reliable purging of an exhaust gas recirculation line of the gas turbine with exhaust gas recirculation without the use of additional blow-off fans. A blow-off flow of the compressor is used for the purging of the exhaust gas recirculation line. The gas turbine can include at least one purging line which connects a compressor blow-off point to the exhaust gas recirculation line.

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Номер записи: 12
01-08-2013 дата публикации

Buffer system that communicates buffer supply air to one or more portions of a gas turbine engine

Номер: US20130192251A1
Автор: Peter M. Munsell, Philip S. Stripinis
Принадлежит: United Technologies Corp

A gas turbine engine includes a buffer system that can communicate a buffer supply air to a portion of the gas turbine engine. The buffer system includes a first bleed air supply having a first pressure, a second bleed air supply having a second pressure that is greater than the first pressure, and an ejector that selectively augments the first bleed air supply to prepare the buffer supply air for communication to the portion of the gas turbine engine.

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Номер записи: 13
08-08-2013 дата публикации

Wastegate valve

Номер: US20130199175A1
Автор: Isao Tomita, Noriyuki Hayashi, Takao Yokoyama, Toru Hoshi
Принадлежит: Mitsubishi Heavy Industries Ltd

In a wastegate valve which is provided in the bypass path bypassing the turbine of the turbocharger in the exhaust gas path and which opens and closes the bypass path, the wastegate valve is provided with a valve seat which is formed in a plane perpendicular to or tilted with an inclination angle with respect to an axial direction of the bypass path, and a valving element which is pivotable around a pivot point which has a relationship of 0°<β<90° with respect to the plane including the valve seat where β is an inclination angle, the valving element being moved away from or closer to the valve seat by pivotation of the valving element to open or close the valve.

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Номер записи: 14
15-08-2013 дата публикации

Lubricating device having a bypass valve

Номер: US20130205745A1
Автор: Olivier Pierre Descubes, Sébastien Detry, Yannick Cazaux
Принадлежит: Turbomeca SA

A lubrication device including a bypass valve with an inlet connected to a feed circuit, a first outlet to be connected to elements to be lubricated, and a second outlet connected to a bypass circuit. The valve includes a valve member slidable between first and second positions, and separating a cavity into first and second chambers. The first chamber is connected to the inlet. In the first position, a fluid flow passage from the first chamber to the second chamber is open, and from the first chamber to the first outlet is closed. In the second position, a fluid flow passage from the first chamber to the first outlet is open, and from the first chamber to the second outlet is closed. At least in the second position, the valve member separates the chambers in substantially leaktight manner, while the second chamber remains in fluid flow communication with the second outlet.

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Номер записи: 15
26-12-2013 дата публикации

Spherical-link end damper system with near constant engagement

Номер: US20130343876A1
Автор: Kevin J. Cummings, Ryan Edward LeBlanc
Принадлежит: United Technologies Corp

A link includes a link body with two ends, a ring bore with a ring bore axis and a bearing, a mount bore with a mount bore axis and a bearing. The link also has an end curvature at the end having the ring bore wherein the curvature axis is substantially perpendicular to the ring bore axis.

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Номер записи: 16
06-02-2014 дата публикации

Sealing structure in steam turbine

Номер: US20140037431A1
Автор: Itaru Murakami, Kenichi Okuno, Shinichiro Ohashi, Toshio Hirano, Yoriharu Murata, Yoshifumi Iwasaki
Принадлежит: Toshiba Corp

According to an embodiment, a rotor blade cover section is integrated with the rotor blades at leading ends thereof. A plurality of sealing fins is disposed at the rotor blade cover section, the sealing fins forming a predetermined clearance relative to an inner peripheral portion of the nozzle outer ring. An annular solid particle trapping space is disposed at the inner peripheral portion of the nozzle outer ring, the solid particle trapping space communicating with an inlet of a steam leak and trapping solid particles that flow in with steam. In the sealing structure, the nozzle outer ring has a through hole through which the solid particles are to be discharged from the solid particle trapping space toward a downstream stage of the steam turbine.

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Номер записи: 17
06-01-2022 дата публикации

Turbine and turbocharger

Номер: US20220003151A1
Автор: Shun Okamoto, Yoshiaki Hirai
Принадлежит: IHI Corp

A turbine includes: a turbine impeller accommodated in an accommodation space; two turbine scroll flow paths connected to the accommodation space; a first wastegate flow path (wastegate flow path) opened to one of the turbine scroll flow paths (second turbine scroll flow path) and separated from the other turbine scroll flow path (first turbine scroll flow path), and a valve for opening and closing the first wastegate flow path.

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Номер записи: 18
03-01-2019 дата публикации

Mixing bleed and ram air using an air cycle machine with two turbines

Номер: US20190002110A1
Автор: Harold W. Hipsky, Louis J. Bruno
Принадлежит: Hamilton Sundstrand Corp

An air cycle machine for an environmental control system for an aircraft is provided. The air cycle machine includes a compressor configured to compress a first medium, a turbine configured to receive second medium, a mixing point downstream of the compressor and downstream of the turbine; and a shaft mechanically coupling the compressor and the turbine.

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Номер записи: 19
03-01-2019 дата публикации

MIXING BLEED AND RAM AIR USING AN AIR CYCLE MACHINE WITH TWO TURBINES

Номер: US20190002111A1
Автор: Bruno Louis J., Hipsky Harold W.
Принадлежит:

An air cycle machine for an environmental control system for an aircraft is provided. The air cycle machine includes a compressor configured to compress a first medium, a turbine configured to receive second medium, a mixing point downstream of the compressor and downstream of the turbine; and a shaft mechanically coupling the compressor and the turbine. 1. An air cycle machine for an environmental control system for an aircraft , the air cycle machine comprising:a compressor configured to compress a first medium;a turbine configured to receive second medium;a mixing point downstream of the compressor and downstream of the turbine;a shaft mechanically coupling the compressor and the turbine;a second turbine mounted on the shaft and configured to expand the first medium; anda fan driven by a motor.2. The air cycle machine of claim 1 , further comprising the fan on a second shaft.3. The air cycle machine of claim 2 , wherein the fan is located at a first end of the second shaft.4. The air cycle machine of claim 3 , wherein a third turbine is located at a first end of the shaft.5. The air cycle machine of claim 4 , further comprising the fan located at a second end of the shaft.6. The air cycle machine of claim 3 , wherein the second turbine is configured to receive a third medium claim 3 , andwherein the third medium is cabin discharge air.7. The air cycle machine of claim 1 , wherein the first medium comprises fresh air claim 1 , andwherein the second medium comprises bleed air.8. An air conditioning system for an aircraft comprising:a compressor configured to compress a first medium;a turbine configured to receive a second medium;a mixing point downstream of the compressor and downstream of the turbine; anda shaft mechanically coupling the compressor and the turbine;a second turbine mounted on the shaft and configured to expand the first medium; anda fan driven by a motor.9. The air conditioning system of claim 8 , further comprising the fan on a second shaft.10. ...

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Номер записи: 20
05-01-2017 дата публикации

Activation Control Apparatus

Номер: US20170002690A1
Автор: IYANAGA Norihiro, SUZUKI Fumiyuki, Yamanaka Kazunori, YASHIKI Tatsuro, Yoshida Takuya, Yoshida Yasuhiro
Принадлежит:

An object of the invention is to provide an activation control apparatus by which a steam turbine can be activated safely at a high speed in response to a state of a power generation plant. In an activation control apparatus for a power generation plant including a heat source apparatus that heats low-temperature fluid by a heat source medium to generate high-temperature fluid; steam generation equipment that generates steam by thermal exchange with the high-temperature fluid; a steam turbine that is driven by the steam; and an adjustment apparatus that adjusts a plant operation amount, the activation control apparatus comprises: a thermal effect amount prediction calculation device that calculates at least a prediction value for a thermal effect amount for use for activation control of the steam turbine; a changeover device that decides, based on a state value of the power generation plant, the sensitivity of the thermal effect amount to a variation of the plant operation amount and outputs a changeover signal for a control mode for the thermal effect amount in accordance with the sensitivity; and an adjustment device that calculates, based on the changeover signal, the plant operation amount so as not to exceed a predetermined limit value. 1. An activation control apparatus for a power generation plant including:a heat source apparatus configured to heat low-temperature fluid by a heat source medium to generate high-temperature fluid;steam generation equipment configured to generate steam by thermal exchange with the high-temperature fluid;a steam turbine configured to be driven by the steam; andan adjustment apparatus configured to adjust a plant operation amount; the activation control apparatus comprising:a thermal effect amount prediction calculation device configured to calculate a prediction value for at least one thermal effect amount to be used for activation control of the steam turbine;a changeover device configured to decide, based on a state value of ...

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Номер записи: 21
05-01-2017 дата публикации

Air supply and conditioning system for a gas turbine

Номер: US20170002739A1
Автор: Humberto Sanchez Moreno, Ismael Orozco Arciga, Juan Leonardo Soria Ramirez, Luis Alberto Aguado Mandujano
Принадлежит: General Electric Co

An air supply and conditioning system for an inlet system of a gas turbine includes an air processing unit having an inlet configured to receive compressed air from a compressor of the gas turbine. The air processing unit includes a heat exchanger that is downstream from the inlet. A vortex cooler is disposed downstream from the inlet of the air processing unit. The vortex cooler is in fluid communication with the heat exchanger and with an outlet of the air processing unit. The system further includes a self-cleaning filter that is disposed within a duct of the inlet system. The self-cleaning filter is in fluid communication with at least one of the outlet of the air processing unit or an outlet of the vortex cooler.

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Номер записи: 22
05-01-2017 дата публикации

Vacuum pump

Номер: US20170002832A1
Автор: Manabu Nonaka, Takashi Kabasawa
Принадлежит: Edwards Japan Ltd

To provide a vacuum pump capable of heating only a flow channel extending from the vicinity of an exit of a thread groove exhaust flow channel toward an outlet port and prevents the accumulation of a product that is caused by a decrease in the temperature of process gas near the exit of the thread groove exhaust flow channel and the flow channel. A vacuum pump has a thread groove exhaust portion that has thread groove exhaust flow channels at least in respective parts of portions on inner and outer circumferential sides of a rotor (rotating body), a casing enclosing the thread groove exhaust portion, an outlet port for exhausting gas compressed by the thread groove exhaust portion to the outside of the casing, and a partition wall that covers a flow channel extending from the exits of the thread groove exhaust flow channels toward the outlet port.

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Номер записи: 23
01-01-2015 дата публикации

Steam turbine

Номер: US20150003969A1
Автор: Junichi Tominaga, Naoki Shibukawa, Shinichiro Ohashi, Tomohiko Tsukuda
Принадлежит: Toshiba Corp

A steam turbine 10 according to an embodiment includes rotor blades 22 implanted to a turbine rotor 21, stationary blades 26 making up a turbine stage together with the rotor blades 22, diaphragm outer rings 23 including an annular extending part 24 surrounding a periphery of the rotor blades 22, and supporting the stationary blades 26, and diaphragm inner rings 25 supporting the stationary blades 26. The steam turbine 10 further includes an annular slit 40 formed at an inner surface of the diaphragm outer ring 23 between the stationary blades 26 and the rotor blades 22 along a circumferential direction, and communication holes 50 provided in plural at an outer surface of the diaphragm outer ring 23 along the circumferential direction, communicated to the annular slit 40 from the outer surface side, and communicated to an exhaust chamber sucking water films via the annular slit 40.

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Номер записи: 24
04-01-2018 дата публикации

Variable geometry thruster

Номер: US20180003128A1
Автор: Andrei Evulet
Принадлежит: Jetoptera Inc

A propulsion system coupled to a vehicle. The system includes a diffusing structure and a conduit portion configured to introduce to the diffusing structure through a passage a primary fluid produced by the vehicle. The passage is defined by a wall, and the diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid. A constricting element is disposed adjacent the wall. An actuating apparatus is coupled to the constricting element and is configured to urge the constricting element toward the wall, thereby reducing the cross-sectional area of the passage.

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Номер записи: 25
07-01-2021 дата публикации

Systems and Methods for Controlling Liquid Flow to a Turbine Fogging Array

Номер: US20210003077A1
Автор: Ammons Mark, Scoggins Brian, Shepherd Donald W.
Принадлежит:

Methods and apparatus for controlling liquid flow to a turbine fogging array. Some implementations are generally directed toward adjusting the output of a variable output pump that supplies water to the turbine fogging array. In some of those implementations, the output is adjusted based on a determined target pump output value that is indicative of a pump output required to change the moisture content of intake air of a combustion turbine to meet a target humidity value. Some implementations are generally directed toward actuating at least one control valve of a plurality of control valves that control liquid throughput to one or more fogging nozzles of a fogging array. 1. A system for controlling output of a fogging array positioned upstream of a combustion turbine , the system comprising:one or more weather sensors measuring one or more conditions of intake air of the combustion turbine and providing weather sensor data responsive to the measurements, the weather sensor data enabling determination of relative humidity of the intake air;a variable output pump supplying liquid to a fogging array positioned upstream of the combustion turbine, the variable output pump operable at a plurality of speeds;memory storing instructions;a controller receiving the weather sensor data and coupled to a drive for the pump, the controller operable to execute the instructions stored in the memory; identify a target humidity value for the intake air;', 'determine, based on the weather sensor data and the target humidity value, a target pump output value indicative of a pump output required to change the moisture content of the intake air to meet the target humidity value; and', 'adjust the speed for the variable output pump based on the target pump output value., 'wherein the instructions comprise instructions to2. The system of claim 1 , further comprising:a temperature sensor measuring temperature of the liquid and generating temperature sensor data, the temperature sensor ...

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Номер записи: 26
07-01-2021 дата публикации

TURBOJET ENGINE NACELLE INCLUDING A SINGLE MOVABLE FRAME OF A CASCADE THRUST REVERSER AND PASSAGES OF ANCILLARIES

Номер: US20210003096A1
Автор: Caruel Pierre, GUILLEMANT Sébastien Michel Thierry, HEAU Olivier, HELLEGOUARCH Antoine Elie, KERBLER Olivier, LEROUVREUR Mathieu
Принадлежит:

A turbojet engine nacelle having a cascade-type thrust reverser includes a movable frame surrounding a cold air flow path, guided axially by longitudinal rails fixed to an intermediate casing surrounding the cold air flow path and supporting cascades of thrust-reversal guide vanes and mobile rear cowls. The nacelle has a passage of ancillaries opening radially towards the outside of the movable frame, in a zone with no bearing structure passing radially across the cold air flow path. The movable frame is cut in an axial plane at the passage for the passage of ancillaries, and each edge of the cut of the movable frame is connected to the intermediate casing by a slide rail fitted on a longitudinal rail arranged each on one side of this passage. 1. A nacelle for a turbojet engine including a cascade thrust reverser , the nacelle comprising:a movable frame surrounding a cold air flow path, guided axially by longitudinal rails fastened on an intermediate casing surrounding the cold air flow path, the movable frame supporting thrust reverser cascades and rear cowls; anda passage of ancillaries opening radially outwardly of the movable frame in an area including no support structure passing radially through the cold air flow path,wherein the movable frame is cut in an axial plane at the passage of ancillaries, and each edge of a section of the movable frame is connected to the intermediate casing by a slide rail adjusted on the longitudinal rails, each slide rail disposed on a side of the passage of ancillaries.2. The nacelle according to further comprising a shutter plate closing a space between the longitudinal rails receiving the slide rails.3. The nacelle according to claim 2 , wherein the shutter plate includes a bore receiving the passage of ancillaries.4. The nacelle according to claim 3 , wherein the shutter plate extends relative to a rear of the thrust reverser cascades by a distance equal to a stroke of the movable frame.5. The nacelle according to claim 4 , ...

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Номер записи: 27
03-01-2019 дата публикации

EXHAUST PORTING APPARATUS

Номер: US20190003378A1
Автор: Warner Mark Mcgregor
Принадлежит:

Provided is an exhaust porting apparatus () for a turbocharged internal combustion engine () which includes a turbocharger () that is conventionally arranged in fluid communication with the exhaust (), the turbo in turn facilitating forced air induction back into the engine via air intake (). The apparatus () comprises a housing () that defines an inlet port () and an outlet port (). The apparatus () also includes a valve member which is arranged within the housing (). The valve member () is generally displaceable between a high-velocity gas inlet position, wherein the valve member () allows unobstructed fluid flow between the inlet and outlet ports () and (), and a low-velocity gas inlet position, wherein the valve member () obstructs fluid flow through the outlet port whilst allowing unobstructed fluid flow into the inlet port (). The apparatus () further includes an actuator () which is generally configured for dynamically actuating the valve member () between the low- and high-velocity gas inlet positions. In this manner, when the inlet and outlet ports () and () operatively arranges the housing () in fluid communication with the engine's exhaust (), dynamic actuation of the valve member () enables an increase in exhaust gas velocity via the outlet port into the turbocharger () by means of the Venturi effect. 1. An exhaust porting apparatus for a turbocharged internal combustion engine , said apparatus comprising:a housing comprising a tube defining an inlet port and an outlet port at opposite ends thereof;a valve member arranged within the tube between said ports, said valve member displaceable between a high-velocity gas inlet position (wherein the valve member allows unobstructed fluid flow between the inlet and outlet ports) and a low-velocity gas inlet position (wherein the valve member obstructs fluid flow through the outlet port whilst allowing unobstructed fluid flow into the inlet port), the valve member comprising a solid tubular member defining a ...

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Номер записи: 28
03-01-2019 дата публикации

Systems and methods for particle separator in a gas turbine engine

Номер: US20190003388A1
Автор: Byron Andrew Pritchard, Jr., Corey Bourassa, Erich Alois Krammer, Satoshi Atsuchi
Принадлежит: General Electric Co

A particle separator system for use with a turbomachine is provided. The particle separator system includes a first end, a second end opposite the first end, a main separator body extending between the first and second ends, the main separator body including at least one step configured to cause a fluid flow to turn up to 180 degrees, and at least one transversely oriented cyclone separator disposed within the main separator body and defining at least one of a swirling cylinder, a bent cylinder, and a conical volume.

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Номер записи: 29
03-01-2019 дата публикации

Gas turbine engine

Номер: US20190003487A1
Автор: Daisuke Uemura, Hiroshi Kubo, Koji Terauchi, Naoto Sakai, Toshimasa Miura, Yuki Ishitobi
Принадлежит: Kawasaki Jukogyo KK

A gas turbine engine, in which a compressed gas from a compressor is burned in a combustor and obtained combustion gas drives a turbine, includes: a compressed gas supply portion configured to supply the compressed gas obtained from the compressor to the combustor; an annular dividing guide body disposed in a diffuser that forms an upstream-side portion of the compressed gas supply portion, the dividing guide body being configured to divide the compressed gas in a radial direction; and a guide support body that supports the dividing guide body on an inner diameter side wall of the compressed gas supply portion.

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Номер записи: 30
20-01-2022 дата публикации

Turbine casing cooling device for a turbomachine

Номер: US20220018264A1
Автор: Julian Nicolas Girardeau, Maxime Aurelien Rotenberg
Принадлежит: Safran Aircraft Engines SAS

The invention relates to a device (9) for cooling a turbine casing (7) for a turbomachine, such as for example an aircraft turbojet engine, extending around an axis (X) and comprising air-distribution means configured to take in air and convey it to the casing, characterized in that the air-distribution means comprising at least a first ramp (20a, 20b) and a second ramp (20a, 20b) extending circumferentially about the axis (X) respectively on a first circumferential portion and on a second circumferential portion which are different from each other, each ramp (20a, 20b) comprising air ejection orifices intended to be directed towards the casing in order to cool it, characterized in that it comprises adjustment means (23) capable of adjusting the flow rate of air ejected at the level of the first ramp (20a, 20b) with respect to the flow rate of air ejected at the level of the second ramp (20a, 20b).

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Номер записи: 31
20-01-2022 дата публикации

Steam Turbine Hollow Blade

Номер: US20220018265A1
Автор: SASAO Yasuhiro, TABATA Soichiro, TAKATA Ryo, TANIGUCHI Nao
Принадлежит:

A steam turbine hollow stationary blade is able to reduce the amount of water droplets captured on a blade surface. The steam turbine hollow stationary blade, which has a cavity therein, includes a partition wall dividing the cavity into a pressure chamber on a leading edge side and an exhaust chamber on a trailing edge side, at least one steam inlet hole connecting the pressure chamber and an outside of the stationary blade to each other, and at least one pressure conditioning hole connecting the pressure chamber and the exhaust chamber. Total opening area of the pressure conditioning hole is smaller than total opening area of the steam inlet hole. 1. A steam turbine hollow stationary blade , that has a cavity therein , comprising:a partition wall dividing the cavity into a pressure chamber on a leading edge side and an exhaust chamber on a trailing edge side;at least one steam inlet hole connecting the pressure chamber and an outside of the stationary blade to each other; andat least one pressure conditioning hole connecting the pressure chamber and the exhaust chamber, whereintotal opening area of the pressure conditioning hole is smaller than total opening area of the steam inlet hole.2. The steam turbine hollow stationary blade according to claim 1 , Whereinthe steam inlet hole is positioned on a leading edge of the stationary blade.3. The steam turbine hollow stationary blade according to claim 1 , whereinthe pressure conditioning hole is provided to the partition wall at both inner and outer circumferential sides of the partition wall.4. The steam turbine hollow stationary blade according to claim 1 , further comprising:a slit connecting the exhaust chamber to the outside of the stationary blade.5. The steam turbine hollow stationary blade according to claim 1 , further comprising:an exhaust hole connecting the exhaust chamber to a steam condenser. The present invention relates to a steam turbine hollow stationary blade.In steam turbines, during the process ...

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Номер записи: 32
20-01-2022 дата публикации

DEVICES AND METHODS FOR GUIDING BLEED AIR IN A TURBOFAN ENGINE

Номер: US20220018292A1
Автор: ANAND Karan, CAPRON Alexandre, YAM Tammy
Принадлежит:

Device and methods for guiding bleed air in a turbofan gas turbine engine are disclosed. The devices provided include louvers and baffles that guide bleed air toward a bypass duct of the turbofan engine. The louvers and baffles have a geometric configuration that promotes desirable flow conditions and reduced energy loss. 1. A device for guiding bleed air into a bypass duct of a turbofan engine having a central axis , the device comprising:a body defining a flow-guiding surface having opposite first and second ends defining a span of the flow-guiding surface around the central axis, the flow-guiding surface extending between a radially-inner edge of the body and a radially-outer edge of the body relative to the central axis; anda side wall adjacent the first end of the flow-guiding surface of the body, the side wall extending at least partially axially relative to the central axis, the side wall extending from a first position radially inwardly of the radially-inner edge of the body to a second position radially outwardly of the radially-inner edge of the body relative to the central axis.2. The device as defined in claim 1 , wherein the second position is adjacent the radially-outer edge of the body.3. The device as defined in claim 1 , wherein the side wall is substantially planar.4. The device as defined in claim 3 , wherein the side wall is non-parallel to a radial direction relative to the central axis.5. The device as defined in claim 1 , wherein the side wall is curved.6. The device as defined in claim 1 , wherein the side wall has a Bellmouth profile when viewed along the central axis.7. The device as defined in claim 1 , wherein the side wall has a unitary construction with the body.8. The device as defined in claim 1 , comprising a baffle disposed axially of the body to define a bleed air passage between the baffle and the flow-guiding surface of the body claim 1 , wherein a gap is defined between the side wall and the baffle.9. The device as defined in ...

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Номер записи: 33
20-01-2022 дата публикации

IN-SPACE PROPULSION SYSTEM

Номер: US20220018313A1
Автор: Do Hieu
Принадлежит:

Apparatus and associated methods relate to an in-space propulsion system configured to generate propulsion from a recirculated working fluid. In an illustrative example, the propulsion system may include a boiler configured to generate high pressure gas from the working fluid. The gas may, for example, be ejected from a nozzle into a distributor tube. A radiator coupled to the distributor tube may, for example, facilitate phase transition of the gas back into the working fluid. The fluid may be collected via one or more collection ducts coupled to the radiator. One or more pumps may recirculate the working fluid from the one or more collection ducts back into the boiler. Various embodiments may advantageously recirculate the working fluid such that propulsion is generated in response to an external power source while substantially an entire mass of the working fluid is preserved in the propulsion system. 1. An in-space propulsion system comprising:a power source and a boiler configured to generate from a working fluid a gas at high pressure;a nozzle to deliver the gas into a distributor tube, the distributor tube allowing expansion of the gas such that the pressure of the gas drops after being ejected from the nozzle;a radiator coupled to the distributor tube, the radiator configured to facilitate the cooling of the gas back into the working fluid;one or more collection ducts coupled to the radiator and configured to receive the working fluid produced from the gas;one or more pumps to move the working fluid from the one or more collection ducts back into the boiler; andwherein the working fluid and the gas are substantively recirculated in the propulsion system such that substantively no mass from the fluid and gas is ejected into space.2. The propulsion system of claim 1 , further comprising one or more storage tanks for receiving the working fluid from the collections ducts claim 1 , and wherein the storage tanks are coupled to pumps.3. The propulsion system of ...

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Номер записи: 34
12-01-2017 дата публикации

Turbo-machine having a thermal transfer line

Номер: US20170009597A1
Автор: Alexander Rambach, Bernhard Fischer, Changsheng Xu, Dennis Bensing, José Ángel Carvajal Soto, Michael Opheys, Pascal Hoffmann
Принадлежит: SIEMENS AG

A turbo-machine having a plurality of component slots accessible from the outside, wherein a thermal transfer line is supplied to at least one section of a component slot such that, upon escape of leakage gas out of the section of the component slot, the leakage gas thermally interacts with the thermal transfer line, wherein the thermal transfer line has a plurality of temperature sensors at different locations on the thermal transfer line and the temperature sensors are designed to detect temperature values on the thermal transfer line at the different locations.

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Номер записи: 35
27-01-2022 дата публикации

DOUBLE JOURNAL BEARING IMPELLER FOR ACTIVE DE-AERATOR

Номер: US20220026021A1
Автор: Martin Bruno
Принадлежит:

An active de-aerator for an aircraft engine is provided, with a housing having an air-oil inlet, an oil outlet and an air outlet. An impeller is received within and rotatable relative to the housing about a central axis. The active de-aerator has a first journal bearing on a first side of the impeller for rotatably supporting the impeller relative to the housing and a second journal bearing on a second side of the impeller for rotatably supporting the impeller relative to the housing, the second side being opposite the first side. 1. An active de-aerator for an aircraft engine , comprising:a housing having an air-oil inlet, an oil outlet and an air outlet;an impeller received within and rotatable relative to the housing about a central axis;a first journal bearing on a first side of the impeller for rotatably supporting the impeller relative to the housing; anda second journal bearing on a second side of the impeller for rotatably supporting the impeller relative to the housing, the second side being opposite the first side.2. The active de-aerator as defined in claim 1 , wherein the active de-aerator is adapted to be driven by an oil pump claim 1 , the impeller defining a shaft connecting portion for connecting the impeller to an end of a pump shaft.3. The active de-aerator as defined in claim 1 , wherein the impeller defines a shaft connecting portion for connecting the impeller to an end of a pump shaft claim 1 , the first journal bearing defined by a portion of the housing and the shaft connecting portion of the impeller.4. The active de-aerator as defined in claim 1 , wherein the impeller defines a flange claim 1 , the second journal bearing defined by a portion of the housing and the flange of the impeller.5. The active de-aerator as defined in claim 1 , wherein the impeller has blades circumferentially distributed about the central axis claim 1 , the first and second sides of the impeller being on opposite sides of the blades along the central axis claim 1 , ...

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Номер записи: 36
14-01-2016 дата публикации

INTERMEDIATE CASING FOR A TURBOFAN ENGINE

Номер: US20160010501A1
Автор: Behaghel Laurent Donatien, Cameau Jerome Etienne Robert, Contal Kévin Michel Robert, Juigne Sébastien Nicolas
Принадлежит: SNECMA

An intermediate casing comprising an inner annular hub, an outer annular barrel and an annular part for separating flows situated between the hub and the outer barrel. A primary stream is delimited between the hub and the separation part. A secondary stream is delimited between the separation part and the outer barrel. At least one hollow arm extends radially from the hub to the outer barrel, passing through the primary and secondary streams. A transmission shaft extends radially in the hollow arm. The hollow arm comprises a hydraulic-fluid outlet situated downstream of the transmission shaft. The arm further comprises a bypass channel or pocket able to bypass the transmission shaft. 1. An intermediate casing for a turbofan comprising a radially internal annular hub , a radially external annular barrel and an annular flow-separation part situated radially between the hub and the outer barrel , a primary stream for flow of a primary flow being delimited between the hub and the separation part , a secondary stream allowing flow of a secondary flow being delimited between the separation part and the outer barrel , at least one hollow arm extending radially from the hub to the outer barrel passing through the primary and secondary streams , a transmission shaft extending radially in said hollow arm , wherein the hollow arm comprises a hydraulic-fluid outlet situated downstream of the transmission shaft with respect to the direction of circulation of the primary flow or secondary flow , said arm further comprising a bypass channel or pocket able to bypass the transmission shaft and extending from upstream to downstream of said transmission shaft.2. An intermediate casing according to claim 1 , wherein the arm comprises first and second walls externally delimiting the arm claim 1 , extending radially and joining at an upstream edge claim 1 , said bypass channel or pocket being formed by a hollow region produced in the first wall and/or the second wall of the arm and ...

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Номер записи: 37
14-01-2016 дата публикации

BLEED VALVE ASSEMBLY

Номер: US20160010564A1
Автор: LIOR Raphael, PAVLIK Mark G.
Принадлежит:

A bleed valve assembly according to an exemplary aspect of the present disclosure includes, among other things, a bleed adaptor having an inlet portion, a fitting opposite the inlet portion, an adaptor body that extends between the inlet portion and the fitting, and a bleed opening disposed on the adaptor body that is selectively exposed to direct fluid into the bleed adaptor. 1. A bleed valve assembly , comprising: an inlet portion;', 'a fitting opposite said inlet portion;', 'an adaptor body that extends between said inlet portion and said fitting; and', 'a bleed opening disposed on said adaptor body that is selectively exposed to direct fluid into said bleed adaptor., 'a bleed adaptor having2. The bleed valve assembly as recited in claim 1 , wherein said fluid includes at least one of air claim 1 , mist and fuel.3. The bleed valve assembly as recited in claim 1 , comprising a hose connected to said fitting.4. The bleed valve assembly as recited in claim 1 , comprising a nut and a threaded portion between said inlet portion and said fitting.5. The bleed valve assembly as recited in claim 4 , comprising a seal between said nut and said threaded portion.6. The bleed valve assembly as recited in claim 1 , wherein an inlet portion of said bleed adaptor is received against a seat of a tube boss to prevent said fluid from entering said bleed adaptor.7. The bleed valve assembly as recited in claim 6 , wherein said bleed opening is disposed on said inlet portion.8. The bleed valve assembly as recited in claim 6 , wherein said inlet portion of said bleed adaptor is selectively spaced from said seat to direct said fluid into said bleed opening.9. The bleed valve assembly as recited in claim 1 , wherein an inlet portion of said bleed adaptor is moveable away from a seat of a tube boss to expose said bleed opening.10. The bleed valve assembly as recited in claim 1 , wherein said bleed adaptor is threadably received by a tube boss.11. A gas turbine engine claim 1 , comprising: ...

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Номер записи: 38
11-01-2018 дата публикации

COOLING SYSTEM FOR GAS TURBINE, GAS TURBINE EQUIPMENT PROVIDED WITH SAME, AND PARTS COOLING METHOD FOR GAS TURBINE

Номер: US20180010520A1
Автор: AI Toshishige, FUKUNAGA Yuya, Iwasaki Tatsuya, Iwasaki Yoshifumi
Принадлежит:

A cooling system includes: a high pressure bleed line configured to bleed high pressure compressed air from a first bleed position of a compressor and to send the air to a first hot part; a low pressure bleed line configured to bleed low pressure compressed air from a second bleed position of the compressor and to send the air to a second hot part; an orifice provided in the low pressure bleed line; a connecting line configured to connect the high pressure bleed line and the low pressure bleed line; a first valve provided in the connecting line; a bypass line configured to connect the connecting line and the low pressure bleed line; and a second valve provided in the bypass line. 120-. (canceled)21. A cooling system for a gas turbine which includes a compressor configured to compress air , a combustor configured to burn a fuel in the air compressed by the compressor to generate a combustion gas , and a turbine driven using the combustion gas , the cooling system for a gas turbine comprising:a high pressure bleed line configured to bleed air from a first bleed position of the compressor and to send the air bled from the first bleed position to a first hot part coming into contact with the combustion gas among parts constituting the gas turbine;a cooler configured to cool air passing through the high pressure bleed line;a low pressure bleed line configured to bleed air at a pressure lower than that of the air which is bled from the first bleed position from a second bleed position of the compressor, to send the air bled from the second bleed position to a second hot part coming into contact with the combustion gas and disposed under a lower pressure environment than the first hot part among the parts constituting the gas turbine, and is not provided with a cooler;a minimum flow rate securing device configured to secure a minimum flow rate of air flowing through the low pressure bleed line while limiting a flow rate of the air flowing through the low pressure bleed ...

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Номер записи: 39
14-01-2021 дата публикации

FEEDFORWARD CONTROL OF A FUEL SUPPLY CIRCUIT OF A TURBOMACHINE

Номер: US20210010430A1
Автор: De Wergifosse Huguette, Pora Loïc Michel Pierre
Принадлежит: SAFRAN AIRCRAFT ENGINES

A fuel supply system for a turbomachine, comprising a fuel circuit comprising pressurizer at the output of the circuit, a pump arranged to send into the circuit a fuel flow rate which is an increasing function of the rotational speed of a shaft of the pump, and a control circuit arranged to control the device to comply with a flow rate setpoint at the output of the fuel circuit. The system further comprises a feedforward corrector circuit configured to calculate an increment of the flow rate setpoint as a function of the engine speed of the turbomachine and of a variation in the engine speed of the turbomachine, and to add this increment to the flow rate setpoint. A method of regulating the pump is also described.

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Номер записи: 40
10-01-2019 дата публикации

LOW FAN NOISE TURBOJET

Номер: US20190010896A1
Автор: CHANEZ Philippe Gerard, SENSIAU Claude
Принадлежит: SAFRAN AIRCRAFT ENGINES

A double flow turbojet includes a fan including a disk centered on an axis of the fan which is provided with fan blades on its periphery, the blades having a leading edge, and an air inlet sleeve extending upstream of the fan and configured to delimit a gas flow designed to enter into the fan the air inlet sleeve having a collecting surface, the turbojet having an aspect ratio 2. The turbojet according to claim 1 , wherein the form factor is comprised between 0.1 and 0.45.3. The turbojet according to claim 1 , wherein the turbojet has a bypass ratio greater than or equal to 10.4. The turbojet according to claim 1 , wherein the diameter of the fan is comprised between 203.2 centimeters and 279.4 centimeters.530. The turbojet according to claim 1 , wherein an upstream portion of the air inlet sleeve is not symmetrical.6. The turbojet according to claim 5 , wherein a downstream portion of the air inlet sleeve is axisymmetric claim 5 , a connection between the non-symmetrical upstream portion of the air inlet sleeve and its downstream axisymmetric portion extending at a distance comprised between one and five centimeters from a plane situated at the intersection between a radially internal wall of the air inlet sleeve and a most upstream point of the leading edge of the fan blades.7. The turbojet according to claim 1 , further comprising:a primary flow space and a concentric secondary flow space,a turbine, housed in the primary flow space and in fluid communication with the fan, anda reduction mechanism, coupling the turbine and the fan, said reduction mechanism comprising a star or planetary gear reduction mechanism having a reduction ratio comprised between 2.5 and 5.8. An aircraft comprising the turbojet according to .10. The method of dimensioning according to claim 9 , further comprising a step during which the form factor is defined so that said ratio is comprised between 0.1 and 0.45.11. The turbojet according to claim 2 , wherein the form factor is comprised ...

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Номер записи: 41
09-01-2020 дата публикации

POWER PLANT METHODS AND APPARATUS

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

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

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Номер записи: 42
09-01-2020 дата публикации

CENTRIFUGAL DEAERATOR FOR A TURBOMACHINE

Номер: US20200011246A1
Автор: CAZAUX Yannick, FULLERINGER Benjamin, PAJARD Jean-Pierre
Принадлежит:

The invention relates to a centrifugal deaerator for an air/oil mixture of a turbomachine, comprising: an annular housing () for the centrifugal separation of said mixture, arranged around a hollow shaft (); axial inlets () for the flow of said air/oil mixture into said housing (); a pinion () for rotating said housing (); and radial oil outlets () and oil-free air outlets (), characterised in that it comprises a metal foam () housed in said housing () by partially extending along the axial direction (XX′) so as to define two successive spaces, a foam-free space () and a foam-lined space (), said foam-free space opening up towards said axial inlets. A device can be advantageously added to the hollow shaft in order to reduce the free-vortex phenomenon and to thereby significantly reduce the load losses of the deaerator. 1. Centrifugal deaerator for an air/oil mixture of a turbomachine comprising:an annular housing for the centrifugal separation of said mixture arranged around a hollow shaft extending along a direction, so-called axial direction, and delimited by an outer annular wall and an inner annular wall,at least one axial inlet of said air/oil mixture in said housing,a pinion for rotating said housing comprising a web securely connected to said inner and outer annular walls such that a rotation of said pinion drives said housing in rotation,at least one radial oil outlet arranged in said outer wall and configured to be able to evacuate the oil separated from said mixture towards the outside of the deaerator,at least one de-oiled air outlet arranged in said inner wall and configured to be able to evacuate the de-oiled air towards said hollow shaft,characterised in that it comprises a metal foam housed in said housing by extending partially along said axial direction so as to delimit two successive spaces along the axial direction (X′X), a foam-free space and a foam-lined space, said foam-free space opening onto said axial inlet(s).2. Deaerator according to claim ...

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Номер записи: 43
09-01-2020 дата публикации

Aircraft engine fan

Номер: US20200011273A1
Автор: Benedict R. PHELPS, Mark J. Wilson, Stephane M. M. BARALON
Принадлежит: Rolls Royce PLC

A gas turbine engine system has an engine core and a bypass duct. A fan drives the flow through the bypass duct. A bypass efficiency is defined as the efficiency of the fan compression of the bypass flow. The bypass efficiency is a function of the bypass flow rate at a given set of conditions. The fan bypass inlet mass flow rate at the reference operating point is appreciably higher than the mass flow rate through the bypass duct at the peak bypass efficiency at a given fan reference rotational speed and cruise conditions. This results in increased design flexibility and improved overall engine performance.

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Номер записи: 44
09-01-2020 дата публикации

HIGH EFFICIENCY GAS TURBINE ENGINE

Номер: US20200011274A1
Автор: BARALON Stephane M. M., BEMMENT Craig W., BENSON Christopher, HALES Michael O., PHELPS Benedict R., SELLERS Benjamin J., Wilson Mark J.
Принадлежит: ROLLS-ROYCE PLC

A gas turbine engine has a quasi-non-dimensional mass flow rate in a defined range and a specific thrust in a defined range to achieve improved over all performance, taking into account fan operability and/or bird strike requirements as well as engine efficiency. The defined ranges of quasi-non-dimensional mass flow rate and specific thrust may be particularly beneficial for gas turbine engines in which the fan is driven by a turbine through a gearbox. 2. A gas turbine engine according to claim 1 , wherein at cruise conditions claim 1 , 0.03 KgsNK≤Q≤0.035 KgsNK.3. A gas turbine engine according to claim 1 , wherein at cruise conditions claim 1 , 031 KgsNK≤Q≤0.034 KgsNK.4. A gas turbine engine according to claim 1 , wherein at cruise conditions claim 1 , the specific thrust is less than 100 Nkgs.5. A gas turbine engine according to claim 1 , wherein a fan tip loading is defined as dH/Utip claim 1 , where dH is the enthalpy rise across the fan and Utip is the translational velocity of the fan blades at the tip of the leading edge claim 1 , and at cruise conditions claim 1 , 0.28 JkgK/(ms) Подробнее

Номер записи: 45
19-01-2017 дата публикации

METHANOL PRODUCTION FROM METHANE AND CARBON DIOXIDE

Номер: US20170015611A1
Автор: STAUFFER John E.
Принадлежит:

Carbon dioxide is reacted with methane in a free radical reaction to produce methanol and carbon monoxide. A system for producing carbon dioxide as a feed ingredient for the process through electric power generator is disclosed. 1. A process for the production of methanol and carbon monoxide from methane and carbon dioxide in a single step comprising a free radical reaction conducted at about one atmosphere pressure and at a temperature in the range of 600° C. to 10000° C.2. A process for the production of methanol comprising the steps of:a. mixing carbon dioxide with methane at a temperature of between about 600° C. and 1000° C. in a free radical reaction to produce methanol and carbon monoxide; andb. separating the carbon monoxide from the methanol.3. The process of wherein the reactants carbon dioxide and methane are quenched after high temperature mixing.4. A process for the production of electric powers comprising the steps of:a. driving a turbine by combustion gas to produce flue gases;b. recovering carbon dioxide from flue gases produced in step (a); and{'claim-ref': {'@idref': 'CLM-00003', 'claim 3'}, 'c. using the carbon dioxide in the process of to produce methanol.'} Existing technology relates to a process for the production of methanol wherein carbon dioxide is reacted with methane.Existing technology is capable of producing methanol from methane and carbon dioxide, however it is a long, tedious and expensive undertaking. Multiple reactions are required for which dedicated equipment is needed. Like many organic preparations, conversions are low and repeated separations are involved. At the heart of the process is the generation of synthesis gas with all that such chemistry implies: high pressure, elevated temperatures and finicky catalysts.To illustrate the known procedures for producing methanol, the following equations are helpful.CO+3 H→CHOH+HO   1.CH+HO→CO+3 H  2.Equation no. 1 represents the classical reaction for producing methanol from synthesis ...

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Номер записи: 46
21-01-2016 дата публикации

Gas turbine engine exhaust drain

Номер: US20160017748A1
Автор: Daniel T. Rog
Принадлежит: United Technologies Corp

An exhaust system of a gas turbine engine includes an exhaust duct, and a venturi drainage device that drains fluid collected in the exhaust duct. The venturi drainage device includes an inlet in fluid communication with the exhaust duct. The venturi drainage device operates in an entrain mode when a flight condition occurs during operating of the gas turbine engine and operates in a drain mode when the gas turbine engine is not operating to drain the fluid from the exhaust duct.

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Номер записи: 47
21-01-2016 дата публикации

EXPANDING SHELL FLOW CONTROL DEVICE

Номер: US20160017815A1
Автор: Izquierdo Felix, McAlice Timothy J.
Принадлежит:

A gas turbine engine includes a bypass flowpath between an outer engine case structure and a core engine. The bypass flow exits the engine through a nozzle. A flow control device that can expand or contract is arranged around the nozzle to control the bypass flow and includes a plurality of overlapping arcuate segments. A method of controlling a bypass flow includes providing a flow control device with overlapping segments that defines a bypass flow path, and actuating the segments to change the amount of overlap between segments and therefore the size of the bypass flow path.

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Номер записи: 48
17-01-2019 дата публикации

Steam Turbine Drain Structure and Method of Modifying the Same

Номер: US20190017416A1
Автор: KUBO Naoto, SHIGA Takumi
Принадлежит:

A steam turbine drain structure includes a drain pocket for collecting drain water generated in a steam turbine, and a drain hole communicating with the lower side of the drain pocket. The steam turbine drain structure further includes a drain pan arranged below the exit of the drain hole and configured to collect drain water discharged from the drain hole, and a connection pipe one end of which is connected to the bottom portion of the drain pan and the other end of which is connectable to piping laid outside the steam turbine. 1. A steam turbine drain structure comprising:a drain pocket defined by part of a stationary assembly accommodating a rotary assembly, the drain pocket extending in a circumferential direction;at least one drain hole provided in a lower side portion of the stationary assembly so as to communicate with a lower side of the drain pocket;a drain pan arranged below an exit of the at least one drain hole, the drain pan being configured to collect drain water discharged from the at least one drain hole; anda connection pipe one end of which is connected to a bottom portion of the drain pan and other end of which is connectable to piping laid outside a steam turbine.2. The steam turbine drain structure according to claim 1 , whereinthe at least one drain hole comprises a plurality of drain holes, the plurality of drain holes being provided along a circumferential direction of the stationary assembly, andthe drain pan is a member extending from a drain hole at one end in the circumferential direction of the plurality of drain holes to a drain hole at other end.3. The steam turbine drain structure according to claim 1 , whereinthe stationary assembly includes a turbine casing accommodating the rotary assembly, a plurality of nozzles arranged on an inner circumferential side of the turbine casing, and an annular outer ring fixed to the turbine casing and supporting the plurality of nozzles,the drain pocket is a hollow portion formed inside the outer ...

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Номер записи: 49
16-01-2020 дата публикации

Turbine vane with dust tolerant cooling system

Номер: US20200018182A1
Автор: Ardeshir Riahi, Daniel C. Crites, Mark C. Morris, Steven Whitaker
Принадлежит: Honeywell International Inc

A turbine vane includes an airfoil that extends from an inner diameter to an outer diameter, and from a leading edge to a trailing edge. The turbine vane includes an inner platform coupled to the airfoil at the inner diameter. The turbine vane includes a cooling system defined in the airfoil including a first conduit in proximity to the leading edge to cool the leading edge and a second conduit to cool the trailing edge. The first conduit has an inlet at the outer diameter to receive a cooling fluid and an outlet portion that is defined at least partially through the inner platform. The first conduit includes a plurality of cooling features that extend between a first surface and a second surface of the first conduit, and the first surface of the first conduit is opposite the leading edge.

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Номер записи: 50
10-02-2022 дата публикации

TWO-PART VALVUE MEMBER ASSEMBLY

Номер: US20220040804A1
Автор: PURDEY Matthew J.
Принадлежит:

A two-part wastegate valve member assembly comprises a support member and a valve member. The support member defines an aperture. The valve member comprises a central portion extending through the aperture and two opposed end portions disposed on opposite sides of the aperture. Each of the two end portions has dimensions such that the valve member is held captive by the support member. The central portion and two opposed end portions of the valve member are integrally formed. A method for forming the two-part wastegate valve member assembly comprises casting a single manufacturing intermediate and subsequently processing the manufacturing intermediate so as to form the two-part assembly. 1. A method for forming a two-part wastegate valve member assembly , the method comprising:casting a single manufacturing intermediate;processing the manufacturing intermediate so as to form a two-part assembly, the two-part assembly comprising a support member and a valve member, wherein the support member defines an aperture and wherein the valve member comprises a central portion extending through the aperture and two opposed end portions disposed on opposite sides of the aperture each of the two end portions having dimensions such that the valve member is held captive by the support member.2. The method of wherein the casting of the single manufacturing intermediate is achieved using investment casting.3. The method of wherein casting the single manufacturing intermediate includes:forming first and second temporary patterns, each of the first and second temporary patterns corresponding to a different portion of the manufacturing intermediate, wherein the first temporary pattern comprises a portion that corresponds to a portion of the manufacturing intermediate from which part of the valve member will be formed and the second temporary pattern comprises a portion that corresponds to a portion of the manufacturing intermediate from which a second part of the valve member will be ...

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Номер записи: 51
28-01-2016 дата публикации

METHOD OF SUPPLYING FUEL TO AN INTERNAL FUEL MANIFOLD

Номер: US20160025009A1
Автор: Morenko Oleg, Olver Bryan
Принадлежит:

The described method of supplying fuel to an internal fuel manifold of a bypass gas turbine engine includes directing a fuel flow through a fuel fairing having an outer surface exposed to a cool bypass airflow, directing the fuel flow in the fuel fairing through a heat exchanging structure on the outer surface of the fuel fairing to cool the fuel flow being below a coking temperature of the fuel, and then feeding the cooled fuel flow from the fuel fairing to the internal fuel manifold. 1. A method of supplying fuel to an internal fuel manifold of a bypass gas turbine engine , the method comprising:directing a fuel flow through a fuel fairing having an outer surface exposed to a cool bypass airflow;directing the fuel flow in the fuel fairing through a heat exchanging structure on the outer surface of the fuel fairing to cool the fuel flow below a coking temperature of the fuel; and subsequentlyfeeding the cooled fuel flow from the fuel fairing to the internal fuel manifold.2. The method of claim 1 , wherein directing fuel through the fuel fairing includes directing fuel through a fuel channel extending through the fuel fairing between a fuel inlet and the fuel outlet claim 1 , the fuel channel having a portion disposed in a body of the fuel fairing directly behind the plurality of heat exchanging structures so as to be in direct conductive heat transfer communication therewith.3. The method of claim 2 , wherein directing fuel through the fuel channel includes directing fuel through a first portion of the fuel channel claim 2 , directing fuel through a U-turn connected to the first portion claim 2 , and directing fuel through a second portion of the fuel channel claim 2 , the first portion being the portion directly behind the plurality of heat exchanging structures.4. The method of claim 1 , wherein cooling the fuel in the fuel fairing below the predetermined temperature comprises using a plurality of heat exchanging fins disposed on the outer surface of the fuel ...

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Номер записи: 52
26-01-2017 дата публикации

TURBINE VENTILATION STRUCTURE

Номер: US20170022843A1
Автор: OBAYASHI Katsuyoshi, TAKASHIMA Kei, TAKI Hiroshi, TANIMURA Kazuhiko
Принадлежит: KAWASAKI JUKOGYO KABUSHIKI KAISHA

A turbine ventilation structure includes: an exhaust diffuser including inner and outer tubes to form an exhaust passage for exhaust gas; a strut extending across the exhaust diffuser from a housing to support a bearing inside the inner tube; a strut cover in the exhaust passage that covers the strut; and a connecting member disposed downstream of the strut cover and including a hollow portion to connect the housing and the inner tube. The housing includes a first intake port to introduce an air from outside. The strut cover has a discharge hole at a rear edge portion thereof. The turbine ventilation structure includes a first ventilation passage extending from the first intake port through the hollow portion, then extending from an inner end portion of the strut through between the strut and the strut cover, and the discharge hole, into the exhaust passage. 1. A turbine ventilation structure in a gas turbine engine , comprising:an exhaust diffuser including an inner tube and an outer tube to form therebetween an annular exhaust passage through which an exhaust gas from a turbine passes;a strut extending across the exhaust diffuser from a housing disposed radially outward of the outer tube and configured to support a bearing inside the inner tube;a strut cover, disposed in the exhaust passage, configured to cover an outer circumference of the strut; anda connecting member connecting the housing and the inner tube, the connecting member being disposed downstream of the strut cover in the exhaust passage and including therein a hollow portion in which an accessory is inserted, the connecting member,wherein the housing includes a first intake port to introduce an air from outside,the strut cover has a discharge hole at a rear edge portion thereof, the turbine ventilation structure further comprisinga first ventilation passage extending from the first intake port through the hollow portion of the connecting member, then extending from an inner end portion of the strut ...

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Номер записи: 53
26-01-2017 дата публикации

Combined Cycle Power Plant and Start-Up Method of the Same

Номер: US20170022847A1
Автор: Eunkyeong Kim, Fumiyuki Suzuki, Kazunori Yamanaka, Miyuki Kawata, Norihiro Iyanaga, Takuya Yoshida, Tatsuro Yashiki, Yasuhiro Yoshida
Принадлежит: Mitsubishi Hitachi Power Systems Ltd

There is provided a combined cycle power plant in which a high-pressure steam turbine and an intermediate-pressure steam turbine can operate in a state where amounts of thermal effect thereof are close to a limit value, and capable of reducing start-up time. A combined cycle power plant includes: an exhaust heat recovery boiler that includes a high-pressure superheater which superheats steam for a high-pressure steam turbine, and a reheater which reheats steam for an intermediate-pressure steam turbine; bypass pipes through which steam bypasses the high-pressure superheater and the reheater; bypass valves that regulate flow rates of steam which flows through the bypass pipes; and a bypass controller that controls the bypass valves such that a difference between thermal effect-amount margins of the turbines is decreased.

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Номер записи: 54
28-01-2016 дата публикации

Vacuum Pump

Номер: US20160025096A1
Автор: Manabu Nonaka, Tsutomu Takaada, Yasushi Maejima, Yongwei Shi, Yoshinobu Ohtachi
Принадлежит: Edwards Japan Ltd

An object is to reduce an adhesion amount of a product in a vacuum pump as a whole and effectively prevent occurrence of a trouble in a vacuum pump electric system due to a magnetic flux leak. A vacuum pump includes a rotor enclosed in a pump case, a rotating shaft fixed to the rotor, a supporting means that rotatably supports the rotating shaft, a driving means that rotates the rotating shaft, and thread-groove-exhaust-portion stators that form thread grove exhaust passages between the thread-groove-exhaust-portion stator and an outer circumferential side of or an inner circumferential side of the rotor. A heating portion is provided below the thread-groove-exhaust-portion stators. The heating portion includes a yoke, a coil, and a heating plate. The heating portion heats the yoke and the heating plate with electromagnetic induction heating by feeding an alternating current to the coil.

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Номер записи: 55
26-01-2017 дата публикации

DOOR-TYPE THRUST REVERSER DEVICE FOR AIRCRAFT TURBOJET ENGINE NACELLE

Номер: US20170022934A1
Автор: Caruel Pierre, LE DOCTE Thiery
Принадлежит: AIRCELLE

A door-type thrust reverser device for a turbojet engine nacelle is provided that includes a fixed structure, a mobile structure mobile with respect to said fixed structure, and at least one door mounted with the ability to pivot via pivots between a retracted position corresponding to the nacelle operating in direct-jet mode, and a deployed position corresponding to the nacelle operating in reverser-jet mode. The thrust reverser device includes a device for bleeding off some of a secondary or bypass airflow, which device is able to bleed off part of the secondary airflow from a duct through which the secondary airflow circulates and for conveying said bled-off airflow toward at least one pivot of the door, so as to cool areas on and/or around the door pivots. 1. A door-type thrust reverser device for a nacelle of an aircraft turbojet engine comprising:a fixed structure;a structure movable relative to said fixed structure comprising at least one door pivotally mounted by pivots between a retracted position corresponding to an operation of the nacelle in direct jet, and a deployed position corresponding to an operation of the nacelle in reverse jet; anda device for collecting a portion of a secondary air flow and to convey said portion of the secondary air flow towards at least one pivot of the door, so as to cool adjacent areas of the pivots of the door.2. The door-type thrust reverser device according to claim 1 , wherein the fixed structure comprises an outer wall and an inner wall in contact with a flow path of the secondary air flow claim 1 , wherein said inner wall comprises at least one ventilation aperture providing communication between the flow path of the secondary air flow and a space for conveying the collected secondary air flow claim 1 , defined between said inner and outer walls.3. The door-type thrust reverser device according to claim 2 , wherein the device for collecting a portion of the secondary air flow comprises at least one ventilation valve ...

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Номер записи: 56
24-01-2019 дата публикации

A METHOD OF FORMING DUST-REMOVAL HOLES FOR A TURBINE BLADE, AND AN ASSOCIATED CERAMIC CORE

Номер: US20190022743A1
Автор: Bechelany Mirna, ROLLINGER Adrien Bernard Vincent
Принадлежит:

A ceramic core used for fabricating a hollow turbine blade for a turbine engine using the lost wax casting technique, the blade including calibrated dust-removal holes emanating from a top of at least one cavity and opening out into a bathtub of the blade, wherein each of the calibrated dust-removal holes is formed in a core portion of height that is determined to be sufficient to guarantee mechanical strength, the core portion including a through orifice of axis perpendicular to a longitudinal axis of the calibrated dust-removal hole and defining on either side of the through orifice firstly a core cylinder having a determined diameter corresponding to the dust-removal hole that is to be formed, and secondly a remaining core volume that is to be plugged after casting, such that the calibrated dust-removal hole is obtained without drilling and without using connection rods. 1. A ceramic core used for fabricating a hollow turbine blade for a turbine engine using the lost wax casting technique , said blade including calibrated dust-removal holes emanating from a top of at least one cavity and opening out into a bathtub of said blade , wherein each of said calibrated dust-removal holes is formed in a core portion of height that is determined to be sufficient to guarantee mechanical strength , said core portion including a through orifice of axis perpendicular to a longitudinal axis of said calibrated dust-removal hole and defining on either side of said through orifice firstly a core cylinder having a determined diameter corresponding to said dust-removal hole that is to be formed , and secondly a remaining core volume that is to be plugged after casting , such that said calibrated dust-removal hole is obtained without drilling and without using connection rods.2. The ceramic core according to claim 1 , wherein said core portion forms a portion of a side column that is to create a side cavity of said blade.3. The ceramic core according to claim 1 , wherein said core ...

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Номер записи: 57
25-01-2018 дата публикации

Internal manifold with fuel inlet

Номер: US20180023477A1
Автор: Oleg Morenko
Принадлежит: Pratt and Whitney Canada Corp

A combustor assembly in a gas turbine engine includes a gas generator casing, an annular combustor supported within the casing, and a fuel injection system that includes an internal fuel manifold assembly having a fuel manifold ring with at least one fuel conveying passage in fluid flow communication with fuel injection nozzles. An inlet member is connected to the manifold ring and includes a drainage passage for collecting possible leaked fuel that is defined between the inlet member and a heat shield surrounding the inlet member. Any leaked fuel is discharged out of the inlet member at an exit of the fuel passage on an end surface of the inlet member proximate the second end thereof.

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Номер записи: 58
10-02-2022 дата публикации

DAMPER CONTROL VALVE FOR A TURBOMACHINE

Номер: US20220042423A1
Автор: Doughty Roger Lee, Hopper Mark Leonard, Masters Justin Adam, MILLER Jacob Patrick
Принадлежит:

A gas turbine engine having a damping system that includes features for optimizing the damping response to vibrational loads on a rotary component for a wide range of operational conditions is provided. In one aspect, the damping system includes a damper control valve. The damper control valve receives working fluid from a working fluid supply and has a valve plunger movable between a first position and a second position. When the valve plunger is in the first position, the damper control valve permits working fluid to flow to a first damper associated with a first bearing coupled with the rotary component and to a second damper associated with a second bearing coupled with the rotary component. When the valve plunger is in the second position, the damper control valve permits working fluid to flow to the first damper but not the second damper. 1. A turbomachine , comprising:a rotary component rotatable about an axis of rotation;a bearing assembly having one or more bearings each operatively coupled with the rotary component, each of the one or more bearings having a damper associated therewith, each of the dampers defining one or more chambers;a damper control valve having a valve casing defining a valve chamber, the valve chamber being in fluid communication with a working fluid supply and the one or more chambers, the damper control valve operable to receive working fluid from the working fluid supply, andwherein the damper control valve has a valve plunger movable within the valve chamber between a first position in which working fluid flows to at least two chambers of the one or more chambers and a second position in which working fluid flows to at least one less chamber than the at least two chambers to which working fluid flows when the valve plunger is in the first position.2. The turbomachine of claim 1 , wherein the damper control valve has a biasing member operable to bias the valve plunger in the first position.3. The turbomachine of claim 2 , wherein ...

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Номер записи: 59
24-01-2019 дата публикации

GAS TURBINE ENGINE WITH ROTOR TIP CLEARANCE CONTROL SYSTEM

Номер: US20190024527A1
Автор: Eifert Andrew J., Skertic Richard J.
Принадлежит:

A gas turbine engine includes a turbine and a rotor tip clearance control system. The rotor tip clearance control system is configured to actively manage a clearance formed between a rotor of the turbine and a case structure of the turbine. 1. A gas turbine engine , the engine comprisinga multi-stage axial compressor configured to compress air drawn into the engine and discharge pressurized air,a combustor configured to combust fuel in pressurized air from the compressor so as to create hot, high pressure combustion products,a turbine configured to receive the combustion products and to extract mechanical work from the combustion products as the combustion products move through the turbine, the turbine including a rotor with blades mounted for rotation about an axis and a case that extends around the rotor to block combustion products from moving though the turbine without interaction with the blades, anda rotor tip clearance control system configured to actively manage a clearance formed between the rotor and the case of the turbine, the rotor tip clearance control system including (i) a first flow modulator configured to control a cool-air flow from a first bleed location within the compressor so as to control the cool-air flow, (ii) a second flow modulator configured to control a warm-air flow from a second bleed location within the compressor, the warm-air flow being warmer than the cool-air flow and the second bleed location being downstream of the first bleed location, so as to control the warm-air flow, and (iii) an air temperature unit configured to receive the cool-air flow and the warm-air flow, the air temperature unit being configured to discharge a mixed-air flow made up of air from the cool-air flow and the warm-air flow to the case of the turbine in order to adjust a diameter of the case based on thermal expansion or contraction induced by the mixed-air flow,wherein the air temperature unit includes (a) a heat exchanger that conducts the cool-air flow ...

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Номер записи: 60
24-01-2019 дата публикации

SYSTEM AND METHOD FOR POWER PRODUCTION WITH SOLID FUEL COMBUSTION AND CARBON CAPTURE

Номер: US20190024583A1
Автор: Forrest Brock Alan, LU XIJIA, Palmer Miles R.
Принадлежит:

The present disclosure relates to systems and methods useful for power production utilizing direct combustion of a solid fuel, such as coal, biomass, or the like. The systems and methods can combine a first power producing cycle that is an open loop or semi-closed loop cycle with a second power producing cycle that is a closed loop cycle utilizing a recycled working fluid, preferably CO. At least one stream from the open loop or semi-closed loop cycle can be used in a heating member to provide heat to the working fluid in the closed loop cycle. The solid fuel can be combusted at conditions facilitating easier removal of solids before a gaseous stream is treated and, optionally, at least partially recycled to the combustor as a recycle stream, preferably include CO. 1. A power generation system comprising: [{'sub': '2', 'a combustor configured for combusting a solid fuel with an oxidant in the presence of a recycle COstream and outputting a combustor exhaust stream;'}, 'at least one power producing member configured to receive at least a portion of the combustor exhaust stream, generate power, and output a turbine exhaust stream; and', 'one or more elements configured for recycling at least a portion of the combustor exhaust stream back to the combustor; and, 'a first power producing cycle that is an open loop or semi-closed loop cycle, the first power producing cycle comprising{'sub': '2', 'claim-text': {'sub': '2', 'at least one power producing member configured to receive the COworking fluid and generate power;'}, 'a second power producing cycle that is a closed loop cycle utilizing COas a working fluid, the second power producing cycle comprising{'sub': '2', 'wherein the power generation system includes at least one heating member configured to receive the COworking fluid from the second power producing cycle and transfer heat thereto from a stream generated from the first power producing cycle.'}2. The power generation system of claim 1 , wherein the first power ...

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Номер записи: 61
24-01-2019 дата публикации

SUPPLY DUCT OF A COMPRESSOR OF A TURBINE ENGINE

Номер: US20190024586A1
Автор: JODET Norman Bruno André, Mardjono Jacky Novi
Принадлежит: SAFRAN AIRCRAFT ENGINES

A supply duct of a compressor of a turbine engine, formed from internal and external walls of revolution around an axis and opposite one another to define a circulation stream of a fluid, is provided. The stream allows the fluid to be routed from the inlet of the duct to the inlet of the compressor. The radius of the external wall at the inlet of the duct is greater than the radius of the duct at the inlet of the compressor. The duct includes a portion for which the radius of the external wall along the portion is less than the radius of the external wall at the inlet of the compressor, and the radius of the internal wall along the portion of the duct is less than the radius of the internal wall at the inlet of the compressor. 18-. (canceled)9. A supply duct of a compressor of a turbine engine , formed from an internal wall and an external wall of revolution around an axis and opposite one another so as to define a circulation stream of a fluid , said stream allowing the fluid to be routed from an inlet of the duct to an inlet of the compressor , a radius of the external wall of the duct at the inlet of the duct being greater than a radius of the duct at the inlet of the compressor ,wherein the duct comprises a portion for which the radius of the external wall of the duct along the portion is less than the radius of the external wall of the duct at the inlet of the compressor, and a radius of the internal wall of the duct along the portion of the duct is less than the radius of the internal wall of the duct at the inlet of the compressor.10. The duct according to claim 9 , wherein at least one radius of the external wall of the duct along the portion of the duct satisfies:{'br': None, 'i': R', '=α*R, 'sub': ext', 'ext,comp, ', with 0<α<0.95\u2003\u2003(3)'}{'sub': ext', 'ext,comp, 'where Ris the at least one radius of the external wall along the portion of the duct, and Ris the radius of the external wall of the duct at the inlet of the compressor.'}11. The duct ...

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Номер записи: 62
24-01-2019 дата публикации

ECOLOGY FUEL RETURN SYSTEMS

Номер: US20190024588A1
Автор: Carpenter Richard J., Flow Ethan, Gibbons Kevin, JR. Leo J., Reuter Charles E., Ribarov Lubomir A., Veilleux
Принадлежит:

A shut-off valve includes a float and a negative G control component. The float is configured to occlude a tank outlet at a first fluid level and 1 G and unocclude the tank outlet at a second fluid level and 1 G. The negative G control component is operatively connected to the float to limit fluid, e.g. liquid or gas, communication between a tank outlet and an ejector pump during negative G events. An ecology fuel return system includes a tank, an ejector pump, a float, and a negative G control component, as described above. The tank has an inlet and an outlet. The inlet is configured to be in fluid communication with components of an engine. The ejector pump is in fluid communication with the tank outlet and is configured to pump fuel from the tank to a fuel pump inlet of an engine. 1. A shut-off valve comprising:a float configured to occlude a tank outlet at a first fluid level and 1 G and unocclude the tank outlet at a second fluid level and 1 G; anda negative G control component operatively connected to the float to limit fluid communication between a tank outlet and an ejector pump during negative G events.2. A shut-off valve as recited in claim 1 , wherein the negative G control component includes a slosh plate disposed proximate to the float surrounding at least a portion of the float claim 1 , wherein the slosh plate is configured to concentrate fluid between the slosh plate and the float during a negative G event to damp a displacement of the float against a negative G event force.3. A shut-off valve as recited in claim 2 , wherein a surface area of the slosh plate between a top of the float and the slosh plate is smaller than a collection area of the slosh plate.4. An ecology fuel return system claim 2 , comprising:a tank having an inlet and an outlet, wherein the inlet is configured to be in fluid communication with components of an engine for recovery of fuel;an ejector pump in fluid communication with the outlet of the tank, wherein the ejector pump is ...

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Номер записи: 63
24-01-2019 дата публикации

Compressible Air Duct Plug Apparatus, Packaging, and Methods

Номер: US20190024936A1
Автор: James Eldred Richie
Принадлежит: Individual

A compressible air duct plug apparatus and packaging includes an open-cell compressible foam block including a top surface, a bottom surface, and an outer edge extending around the perimeter of the block between the top surface and the bottom surface. The packaging can include an outer packaging enclosing the foam block, the outer packaging forming an inner cavity, the foam block received and compressed within the inner cavity. When the open-cell foam block is removed from the outer packaging, the outer edge of the block is configured to engage the duct in a compression seal when the block is installed in the duct opening.

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Номер записи: 64
23-01-2020 дата публикации

GAS TURBINE ENGINE KEEL BEAM

Номер: US20200025035A1
Автор: INGLEY Lucian, PEACE Richard
Принадлежит: ROLLS-ROYCE PLC

A gas turbine engine for an aircraft is provided. The gas turbine engine comprises an engine core comprising a compressor, a combustor, a turbine, and a core shaft connecting the turbine to the compressor. The gas turbine engine further comprises a fan located upstream of the engine core, the fan comprising a plurality of fan blades, the fan generating a core airflow which enters the engine core and a bypass airflow which flows through a bypass duct surrounding the engine core. The gas turbine engine further comprises a circumferential row of outer guide vanes located in the bypass duct rearwards of the fan, the outer guide vanes extending radially outwardly from an inner ring which defines a radially inner surface of the bypass duct. 1. A gas turbine engine for an aircraft comprising:an engine core comprising a compressor, a combustor, a turbine, and a core shaft connecting the turbine to the compressor;a fan located upstream of the engine core, the fan comprising a plurality of fan blades, the fan generating a core airflow which enters the engine core and a bypass airflow which flows through a bypass duct surrounding the engine core;a circumferential row of outer guide vanes located in the bypass duct rearwards of the fan, the outer guide vanes extending radially outwardly from an inner ring which defines a radially inner surface of the bypass duct;an inner cowl which provides an aerodynamic fairing surrounding the engine core, the inner cowl being rearwards of the inner ring, and including two door sections located on respective and opposite sides of the engine, each door section being pivotably openable about an upper edge thereof to enable maintenance access to the engine core; anda keel beam which extends rearwardly from the inner ring at bottom dead centre thereof to provide latching formations for latching to a lower edge of each door section when it is closed.2. A gas turbine engine according to claim 1 , wherein the keel beam has seal lands which extend ...

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Номер записи: 65
23-01-2020 дата публикации

Air supply system for an aircraft

Номер: US20200025074A1
Автор: Stefan Fechner
Принадлежит: Rolls Royce Deutschland Ltd and Co KG

An air supply system for a gas turbine engine including a first duct which is connected or capable of being connected to a first compressor bleed air supply of a gas turbine engine; a second duct which downstream of the first compressor bleed air supply is connected or capable of being connected to a second compressor bleed air supply of the gas turbine engine; a nozzle by way of which air from the second duct is capable of being blown into the first duct; and an exhaust air duct having an opening which downstream of the nozzle is disposed in the first duct in such a manner that air blown by way of the nozzle into the first duct can flow out of the first duct through the opening into the exhaust air duct. A gas turbine engine and an aircraft are furthermore provided.

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Номер записи: 66
23-01-2020 дата публикации

STATOR CONFIGURATION FOR GAS TURBINE ENGINE

Номер: US20200025077A1
Автор: Amadon Colin G., Firnhaber Michael C.
Принадлежит:

A stator configuration for a gas turbine engine including a splitter segment. Also included is a first stator extending radially outwardly from the splitter segment. Further included is a second stator extending radially inwardly from the splitter segment, the splitter segment, the first stator and the second stator being a single, integrally formed structure. 1. A stator configuration for a gas turbine engine comprising:a splitter segment;a first stator extending radially outwardly from the splitter segment; anda second stator extending radially inwardly from the splitter segment, the splitter segment, the first stator and the second stator being a single, integrally formed structure.2. The stator configuration of claim 1 , wherein the splitter segment is configured to split an incoming fluid flow into a first claim 1 , radially outer stream and a second claim 1 , radially inner stream.3. The stator configuration of claim 1 , wherein the splitter segment extends from a forward end to a rearward end claim 1 , the first stator positioned closer to the forward end relative to the distance between the second stator and the forward end.4. The stator configuration of claim 1 , wherein the splitter segment claim 1 , the first stator and the second stator are formed from a single manufacturing process to form the single claim 1 , integrally formed structure.5. The stator configuration of claim 1 , wherein the splitter segment claim 1 , the first stator and the second stator are multiple components joined together to form the single claim 1 , integrally formed structure.6. The stator configuration of claim 1 , further comprising a flange extending radially inwardly from the second stator claim 1 , the flange providing a location for operative coupling of the stator configuration to a stationary structure of the gas turbine engine.7. The stator configuration of claim 6 , further comprising a protrusion extending rearward from the flange to provide a locating feature during ...

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Номер записи: 67
23-01-2020 дата публикации

DIVERSION OF FAN AIR TO PROVIDE COOLING AIR FOR GAS TURBINE ENGINE

Номер: US20200025080A1
Автор: Bifulco Anthony R., Kupratis Daniel Bernard
Принадлежит:

A gas turbine engine section includes a plurality of spaced rotor stages, with a static guide vane intermediate the spaced rotor stages. The static guide vane provides swirl into air passing toward a downstream one of the spaced rotor stages, and an outer housing surrounding the spaced rotor stages. A diverter diverts a portion of air radially outwardly through the outer housing, and across at least one heat exchanger. The diverted air passes back into a duct radially inwardly through the outer housing, and is exhausted toward the downstream one of the spaced rotor stages. 1. A gas turbine engine section comprising:a plurality of spaced rotor stages, with a static guide vane intermediate said spaced rotor stages, said static guide vane providing swirl into air passing toward a downstream one of said spaced rotor stages, and an outer housing surrounding said spaced rotor stages, a diverter diverting a portion of air radially outwardly through said outer housing, and across at least one heat exchanger, with the diverted air passing back into a duct radially inwardly through said outer housing, and being exhausted toward said downstream one of said spaced rotor stages.2. The gas turbine engine as set forth in claim 1 , wherein said exhausted air passing through an injector claim 1 , and said injector imparting swirl into the air exhausting toward the downstream one of the two spaced turbine rotors.3. The gas turbine engine as set forth in claim 2 , wherein a swirl angle imparted by said injector is greater than a swirl angle imparted by said static guide vane.4. The gas turbine engine as set forth in claim 3 , wherein a swirl angle imparted by said static guide vane is greater than 40 degrees.5. The gas turbine engine as set forth in claim 4 , wherein said swirl angle is greater than 55 degrees.6. The gas turbine engine as set forth in claim 1 , wherein said at least one heat exchanger cooling an electronic component.7. The gas turbine engine as set forth in claim 1 , ...

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Номер записи: 68
23-01-2020 дата публикации

Intercooled cooling air with auxiliary compressor control

Номер: US20200025105A1
Автор: Brian D. Merry, Gabriel L. Suciu, Michael G. Mccaffrey
Принадлежит: United Technologies Corp

A gas turbine engine includes a main compressor section with a downstream most location. A turbine section has a high pressure turbine. A tap line is connected to tap air from a location upstream of the downstream most location in the main compressor section. The tapped air is connected to a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and is connected to deliver air into the high pressure turbine. A bypass valve is positioned downstream of the main compressor section, and upstream of the heat exchanger. The bypass valve selectively delivers air directly to the cooling compressor without passing through the heat exchanger under certain conditions.

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Номер записи: 69
23-01-2020 дата публикации

Aircraft propulsion unit and process for reducing a ventilation air flow in the aircraft propulsion unit

Номер: US20200025107A1
Автор: Abdelkader Benyahia, Eric Cerutti, Loic Jeunesse, Morgan Balland
Принадлежит: Safran Aircraft Engines SAS

An aircraft propulsion unit is described. The unit may include a gas generator with a fan surrounded by a casing. A nacelle may extend around the casing and define an annular compartment with the casing wherein some equipment may be housed. An air inlet may be configured so a ventilation air flow penetrates inside the compartment. An air outlet may be configured so a ventilation air flow is evacuated from the compartment. The propulsion unit may also include an air flow adjustment regulator. The air flow adjustment regulator may be configured to maintain a nominal value of the ventilation air flow circulating through at least one of the air inlet and of the air outlet under nominal operating conditions, and to reduce the value of this ventilation air flow when a fire is detected inside the compartment.

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Номер записи: 70
23-01-2020 дата публикации

GAS TURBINE ENGINE EJECTOR

Номер: US20200025132A1
Автор: Cunningham Mark, DI PAOLA Franco, Yan Guorong
Принадлежит:

An ejector comprises a primary nozzle having an annular wall forming part of an outer boundary of an exhaust portion of a primary flow path of a gas turbine engine. The annular wall has a downstream end defining a plurality of circumferentially distributed lobes. The ejector further comprises a secondary nozzle having an annular wall disposed about the primary nozzle, the primary nozzle and the secondary nozzle defining a secondary flow passage therebetween for channeling a secondary flow. The secondary nozzle defines a mixing zone downstream of an exit of the primary nozzle. A flow guide ring is mounted to the primary nozzle lobes. The ring has an aerodynamic surface extending from a leading edge to a trailing edge respectively disposed upstream and downstream of the exit of the primary nozzle. The aerodynamic surface of the ring is oriented to guide the high velocity primary flow into the mixing zone. 1. A gas turbine engine having an engine casing enclosing a compressor section , a combustor and a turbine section defining a main gas path serially extending therethrough along a main axis of the engine , and comprising:an ejector projecting from an aft end of the engine casing axially downstream from an engine center body forming an aft end portion of an inner boundary of the main gas path, the ejector comprising a primary nozzle having an annular wall forming an outer boundary of the main gas path for guiding a primary flow, the annular wall having a downstream end defining a plurality of circumferentially distributed lobes, and a flow guide ring mounted to the circumferentially distributed lobes in the main gas path centrally about the main axis and downstream of the engine center body; the flow guide ring having an aerodynamic surface configured to minimize diffusion of the primary flow towards the main axis of the engine.2. The gas turbine engine according to claim 1 , wherein the ejector further comprises a secondary nozzle concentrically mounted about the ...

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Номер записи: 71
23-01-2020 дата публикации

BELLMOUTH NOZZLE ASSEMBLY FOR A GAS TURBINE ENGINE

Номер: US20200025140A1
Автор: IGLEWSKI Tomasz
Принадлежит:

A gas turbine engine that includes a nozzle assembly that has features that facilitate airflow into and through a bypass passage of the gas turbine engine during a reverse thrust operation is provided. The nozzle assembly of the gas turbine engine also includes features that increase the effectiveness of the thrust reverse system of the gas turbine engine. Methods for reversing the thrust of a gas turbine engine are also provided. 1. A gas turbine engine defining an outlet and an axial direction , a radial direction , and a circumferential direction , the gas turbine engine comprising:a core turbine engine;a nacelle disposed about the core turbine engine along the circumferential direction, the nacelle extending between a first end and a second end along the axial direction; and an outer panel coupled with the nacelle, the outer panel movable along the radial direction to move the nozzle assembly between the stowed position and the deployed position; and', 'an elastic member coupled with the outer panel and with the nacelle, wherein when the nozzle assembly is in the deployed position, the elastic member is inflated with an airflow such that the elastic member forms a bellmouth at the outlet of the gas turbine engine., 'a nozzle assembly disposed at or proximate the second end of the nacelle and movable between a stowed position and a deployed position, the nozzle assembly comprising2. The gas turbine engine of claim 1 , wherein the nacelle is spaced from the core turbine engine along the radial direction so as to define a bypass passage therebetween claim 1 , and wherein the outlet is a bypass passage outlet.3. The gas turbine engine of claim 1 , further comprising:a thrust reverser system, wherein the thrust reverser system is a variable pitch fan assembly.4. The gas turbine engine of claim 1 , wherein the nacelle comprises an outer surface and wherein the nacelle defines a recess along the outer surface claim 1 , and wherein when the nozzle assembly is in the ...

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Номер записи: 72
23-01-2020 дата публикации

THRUST REVERSER FLOW LIMITING VALVE

Номер: US20200025142A1
Автор: Kopecek Joseph Thomas
Принадлежит: WOODWARD, INC.

The present subject matter can be embodied in, among other things, a two-speed thrust reverser actuation system for actuating a thrust reverser element experiencing an assisting load during movement between a stowed and deployed positions. The system includes a hydraulic actuator to move the thrust reverser element between the stowed and deployed positions, and a directional control valve with a regeneration feature including a restrictor and a velocity fuse arranged in parallel with the restrictor. The velocity fuse is configured to close when the assisting load on the thrust reverser element increases the flow rate of hydraulic fluid through the velocity fuse above threshold value. In operation, the system defines a first movement speed when the velocity fuse is open, and a second movement speed when the velocity fuse is closed, thereby decreasing an effective exit orifice size of the hydraulic actuator when the assisting load increases the deploy rate. 119-. (canceled)20. A method of operating a thrust reverser element , the method comprising:flowing hydraulic fluid to a deploy port of a hydraulic actuator to move the thrust reverser element from a stowed position to a deployed position;receiving a flow of hydraulic fluid from a stow port of the hydraulic actuator through a restrictor and a velocity fuse;automatically closing the velocity fuse when a flow rate of the flow of hydraulic fluid from the hydraulic actuator though the, velocity fuse exceeds a threshold value, the flow of hydraulic fluid from the hydraulic actuator passing though the restrictor alone; andautomatically opening the velocity fuse when the thrust reverser element reaches the deployed position and the flow of hydraulic fluid from the stow port of the hydraulic actuator is below a minimum value.21. The method of claim 20 , comprising:with the thrust reverser element in the deployed position, flowing hydraulic fluid through the restrictor and the velocity fuse to the stow port of a hydraulic ...

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Номер записи: 73
28-01-2021 дата публикации

ASSEMBLY OF A SERVO PUMP AND A HYDRAULIC MOTOR

Номер: US20210025331A1
Автор: LEIVSETH Geir, WATKINS Stephanie E., Yates Martin K.
Принадлежит: ROLLS-ROYCE PLC

An assembly of a servo pump and a hydraulic motor. The assembly has a housing which contains the pump and the motor. The motor has a rotating body which rotates under the motive power of a pressurised motor liquid flow. The motor has a high pressure region which receives the pressurised motor liquid flow, and a low pressure region through which the motor liquid flow leaves the motor. The pump also has a rotating body. The pump has a low pressure region which receives servo liquid flow to be pumped by its rotating body, and a high pressure region through which pressurised servo liquid flow leaves the pump. Each rotating body is mounted on a respective journal. 1. An assembly of a servo pump and a hydraulic motor , wherein:the assembly has a housing which contains the servo pump and the hydraulic motor;{'sub': min', 'mout, 'the hydraulic motor has a rotating body which rotates under the motive power of a pressurised motor liquid flow, whereby the hydraulic motor has a high pressure region (P) which receives the pressurised motor liquid flow, and a low pressure region (P) through which the motor liquid flow leaves the hydraulic motor;'}{'sub': pin', 'pout, 'the servo pump has a rotating body, whereby the servo pump has a low pressure region (P) which receives servo liquid flow to be pumped by its rotating body, and a high pressure region (P) through which pressurised servo liquid flow leaves the servo pump;'}each rotating body is mounted on a respective journal, each journal being supported on one side of its rotating body by a respective first bearing block and being supported on the opposite side of its rotating body by a respective second bearing block, each bearing block having a running face adjacent to its rotating body and a non-running face distal from its rotating body;the assembly has a mechanical linkage having a coupling at one end to the journal of the motor rotating body and a coupling at an opposite end to the journal of the pump rotating body such that ...

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Номер записи: 74
28-01-2021 дата публикации

COMPLIANT JUMPER TUBE FITTING

Номер: US20210025527A1
Автор: Davis Todd A., Flore Brad E.
Принадлежит: UNITED TECHNOLOGIES CORPORATION

A compliant jumper tube fitting assembly may comprise an outer housing comprising a first annular cylindrical structure including a first opening defined by a base wall, and an inner housing comprising a second annular cylindrical structure including a second opening defined by an annular wall, wherein the inner housing is configured to generate a seal between an inner diameter wall of the outer housing and an outer diameter wall of the inner housing in response to inserting the inner housing into a mouth end of the outer housing, wherein the inner housing is configured to receive an end fitting and generate a seal between an inner diameter wall of the inner housing in response to inserting the end fitting into the inner housing. 1. A compliant jumper tube fitting assembly , comprising:an outer housing comprising a first annular cylindrical structure including a first opening defined by a base wall; andan inner housing comprising a second annular cylindrical structure including a second opening defined by an annular wall;wherein the inner housing is configured to generate a seal between an inner diameter wall of the outer housing and an outer diameter wall of the inner housing in response to inserting the inner housing into a mouth end of the outer housing,wherein the inner housing is configured to receive an end fitting and generate a seal between an inner diameter wall of the inner housing in response to inserting the end fitting into the inner housing, andwherein a fluid communication between the first opening, the second opening, and the end fitting is enabled in response to inserting the end fitting into the inner housing.2. The compliant jumper tube fitting assembly of claim 1 , wherein the inner diameter wall of the outer housing defines a first bore diameter extending from the base wall toward the mouth end and includes a transition portion claim 1 , wherein the first bore diameter increases toward a second bore diameter greater than the first bore diameter ...

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Номер записи: 75
04-02-2016 дата публикации

Cartridge Style Ejector Pump

Номер: US20160032838A1
Автор: Callaghan Craig Michael
Принадлежит: UNITED TECHNOLOGIES CORPORATION

In accordance with one aspect of the disclosure, a cartridge style ejector pump for a fluid flow system is disclosed. The ejector pump may have a body defining a flow path therein. The body may be structurally independent of the fluid flow system. The body may further define a suction inlet communicating through the body to the flow path, an outlet communicating through the body from the flow path, and a motive flow inlet communicating through the body to the flow path. 1. A cartridge style ejector pump for a fluid flow system , comprising:a body defining a flow path therein, the body structurally independent of the fluid flow system;a suction inlet communicating through the body to the flow path;an outlet communicating through the body from the flow path; anda motive flow inlet communicating through the body to the flow path.2. The cartridge style ejector pump of claim 1 , wherein the cartridge style ejector pump is positioned within a receiving port of the fluid flow system.3. The cartridge style ejector pump of claim 2 , wherein the cartridge style ejector pump to be removably positioned within the receiving port.4. The cartridge style ejector pump of claim 2 , further comprising a locking mechanism claim 2 , the locking mechanism configured to secure the cartridge style ejector pump in the receiving port.5. The cartridge style ejector pump of claim 4 , where the locking mechanism is a threaded connection between the cartridge style ejector pump and the receiving port.6. The cartridge style ejector pump of claim 1 , further comprising a filter claim 1 , positioned such that a fluid flowing from the suction inlet to the outlet flows through the filter.7. A fuel recovery system of a fuel supply system claim 1 , comprising:a receiving port open at a first end and including a housing defining a supply passage and return passage; anda cartridge style ejector pump including a body defining a flow path therein, the body structurally independent from but positioned ...

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Номер записи: 76
01-02-2018 дата публикации

SHROUDED TURBINE AIRFOIL WITH LEAKAGE FLOW CONDITIONER

Номер: US20180030838A1
Автор: Lee Ching-Pang, Lohaus Andrew S., Taremi Farzad, Tham Kok-Mun, Wong Li Shing
Принадлежит:

A shrouded turbine airfoil () with a leakage flow conditioner () configured to direct leakage flow to be aligned with main hot gas flow is disclosed. The leakage flow conditioner () may be positioned on a radially outer surface () of an outer shroud base () of the outer shroud () on a tip () of an airfoil (). The leakage flow conditioner () may include a radially outer surface () that is positioned further radially inward than the radially outer surface () of the outer shroud base () creating a radially outward extending wall surface () that serves to redirect leakage flow. In at least one embodiment, the radially outward extending wall surface () may be aligned with a pressure side () of the shrouded turbine airfoil () to increase the efficiency of a turbine engine by redirecting leakage flow to be aligned with main hot gas flow to reduce aerodynamic loss upon re-introduction to the main gas flow. 1. A turbine airfoil comprising:a generally elongated airfoil having a leading edge, a trailing edge, a pressure side, a suction side on a side opposite to the pressure side, a tip at a first end, a root coupled to the airfoil at a second end generally opposite the first end for supporting the airfoil and for coupling the airfoil to a disc;at least one outer shroud coupled to the tip of the generally elongated airfoil;wherein the at least one outer shroud extends in a direction generally from the pressure side toward the suction side and extends circumferentially in a turbine engine;wherein the at least one outer shroud is formed at least in part by an outer shroud base coupled to the tip of the generally elongated airfoil and an outer shroud body extending radially outward from the outer shroud base;wherein the outer shroud base has an upstream section extending upstream of the outer shroud body and a downstream section extending downstream of the outer shroud body;a downstream leakage flow conditioner positioned in the downstream section extending downstream of the ...

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Номер записи: 77
01-02-2018 дата публикации

ASSEMBLY AND METHOD FOR INFLUENCING FLOW THROUGH A FAN OF A GAS TURBINE ENGINE

Номер: US20180030893A1
Автор: DUONG Hien
Принадлежит:

Assemblies and methods for providing injection air to influence flow in a flow passage defined by a fan of a gas turbine engine are disclosed. In one embodiment, the method comprises: receiving air into an interior of a nose cone; increasing the pressure of the air in the interior of the nose cone and directing the pressurized air; and discharging the air into the flow passage defined by the fan. 1. A fan assembly for a turbofan engine , the fan assembly comprising:a fan comprising a plurality of circumferentially distributed fan blades extending from a hub, the fan blades and the hub defining a flow passage through which ambient air is propelled;a nose cone disposed upstream of the hub and having an interior in fluid communication with the ambient air; anda pump at least partially housed in the interior of the nose cone, the pump being configured to, using the ambient air in the nose cone, drive injection air into the flow passage defined by the fan blades and the hub to influence flow in the flow passage.2. The fan assembly as defined in claim 1 , wherein the hub defines one or more injection passages for directing injection air from the pump to one or more locations in the flow passage.3. The fan assembly as defined in claim 3 , wherein the one or more injection passages comprise one or more respective openings formed in an outer surface of the hub.4. The fan assembly as defined in claim 1 , wherein the pump comprises a plurality of rotor blades secured for common rotation with the fan.5. The fan assembly as defined in claim 4 , wherein the pump comprises a circular array of the rotor blades.6. The fan assembly as defined in claim 4 , wherein the plurality of rotor blades are secured to an inner surface of the outer wall of the nose cone.7. The fan assembly as defined in claim 5 , wherein the pump comprises a first stage including a first circular array of the rotor blades and a second stage including a second circular array of the rotor blades claim 5 , the ...

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Номер записи: 78
17-02-2022 дата публикации

IMPACT-COOLING TUBULAR INSERT FOR A TURBOMACHINE DISTRIBUTOR

Номер: US20220049610A1
Автор: CARREROT Guillaume, Klein Guillaume, LARDELLIER Thomas Joseph, LAVIGNOTTE Stephane, VOLLEBREGT Matthieu Jean Luc
Принадлежит:

A tubular ventilation sleeve for a turbomachine distributor, in particular for an aircraft, the sleeve having a generally elongate shape along an axis (A-A) and including a perforated tubular wall around said axis, one of the axial ends of the sleeve being open and the other being closed by a bottom wall, wherein it further includes support beams when the sleeve is made by additive manufacturing, the beams extending inside the sleeve between the tubular wall and the bottom wall and having a longitudinal cross-section with a generally triangular shape, two sides of which are respectively connected to the tubular wall and the bottom wall and the last side of which is free and extends inside the sleeve, perforations in the tubular wall being provided between the support beams. 1. A tubular ventilation sleeve for a turbomachine distributor , in particular for an aircraft , the sleeve having a generally elongated shape along an axis and comprising a tubular wall perforated around this axis , one of the axial ends of the sleeve being open and the other being closed by a bottom wall , wherein it furthermore comprises support beams when the sleeve is made by additive manufacturing , these beams extending inside the sleeve , between the tubular wall and the bottom wall and having a longitudinal cross-section with a generally triangular shape , two sides of which are respectively connected to the tubular wall and to the bottom wall , and the last side of which is free and extends inside the sleeve , perforations in the tubular wall being provided between the support beams.2. The sleeve according to claim 1 , wherein each beam has claim 1 , at the level of its side connected to the bottom wall claim 1 , a greater thickness of material than the rest of the beam.3. The sleeve according to any claim 1 , wherein the beams cover substantially the entire internal surface of the bottom wall.4. The sleeve according to any claim 1 , wherein the beams are separated into two series which ...

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Номер записи: 79
17-02-2022 дата публикации

SYSTEMS AND METHODS FOR CONTROLLING A BLEED-OFF VALVE OF A GAS TURBINE ENGINE

Номер: US20220049660A1
Автор: ARULSUTHAN Timothy, ROY Benjamin
Принадлежит:

Methods and systems for controlling a bleed-off valve of a gas turbine engine are described. The method comprises maintaining a first bleed-off valve associated with a first compressor of the gas turbine engine at least partially open upon detection of an unintended engine disturbance causing a drop in pressure of a combustion chamber of the engine; monitoring a rotor acceleration of the first compressor; and controlling closure of the first bleed-off valve when the rotor acceleration of the first compressor reaches a first threshold for a first duration. 1. A method for controlling a bleed-off valve of a gas turbine engine , the method comprising:maintaining a first bleed-off valve associated with a first compressor of the gas turbine engine at least partially open upon detection of an unintended engine disturbance causing a drop in pressure of a combustion chamber of the engine;monitoring a rotor acceleration of the first compressor; andcontrolling closure of the first bleed-off valve when the rotor acceleration of the first compressor reaches a first threshold for a first duration.2. The method of claim 1 , wherein the first compressor is a low pressure compressor and the first bleed-off valve is a low pressure compressor bleed-off valve claim 1 , and wherein controlling closure of the first bleed-off valve comprises modulating the first bleed-off valve as a function of a speed of the low pressure compressor until closure.3. The method of claim 2 , further comprising monitoring a rotor acceleration of a high pressure compressor of the engine claim 2 , and wherein controlling closure of the first bleed-off valve comprises controlling closure when the rotor acceleration of the low pressure compressor reaches the first threshold for the first duration and the rotor acceleration of the high pressure compressor reaches a second threshold for a second duration.4. The method of claim 2 , further comprising disabling a nominal mode of control of the first bleed-off valve ...

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Номер записи: 80
17-02-2022 дата публикации

DEVICE FOR COOLING HEAT-SENSITIVE CONTROL MEMBERS OF A PNEUMATIC OR ELECTROPNEUMATIC VALVE, AND VALVE EQUIPPED WITH SUCH A COOLING DEVICE

Номер: US20220049793A1
Автор: BRISTIEL Frédéric, Fauque Stéphane
Принадлежит:

The invention relates to a device () for cooling heat-sensitive control members () of a pneumatic or electropneumatic valve (), comprising a containment casing () designed to contain said control members (): a fresh air inlet () in said containment casing (); an air outlet () of said containment casing, provided with a ventilation air tube () that comprises: an air acceleration column () which puts into fluidic communication said containment casing () and the air outlet (); a primary supply () for supplying the acceleration column () with primary air; a secondary supply () for supplying the acceleration column () with secondary air, provided in said containment casing () such that the primary air can drive and accelerate the secondary air in the direction of the air outlet so as to produce forced air ventilation in said containment casing () between the air inlet () and the air outlet (). 1. A device for cooling heat-sensitive control members of a pneumatic or electro-pneumatic valve capable of being arranged in an environment subjected to temperatures above the nominal operating temperatures of these control members , the device comprising:a containment casing adapted to contain said control members of said pneumatic valve,a fresh air inlet in said containment casing,{'claim-text': ['an air acceleration column placing said containment casing and said air outlet in fluid communication;', 'a primary supply, of primary air having a temperature and pressure greater than the temperature and pressure of the fresh air, to the acceleration column,', 'a secondary supply of secondary air, present in said containment casing, to said acceleration column,'], '#text': 'an air outlet of said containment casing, which outlet is equipped with an air mover comprising:'}such that said primary air drives and accelerates the secondary air toward said air outlet so as to produce forced ventilation of air in said containment casing between said air inlet and said air outlet.2. The ...

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Номер записи: 81
31-01-2019 дата публикации

Air turbine starter

Номер: US20190032565A1
Автор: Kenneth W. MAGEE, Luis Angel Martinez
Принадлежит: Unison Industries LLC

An air turbine starter for starting an engine, comprising a housing defining an inlet, an outlet, and a flow path extending between the inlet and the outlet for communicating a flow of gas there through. A turbine member is journaled within the housing and disposed within the flow path for rotatably extracting mechanical power from the flow of gas. A gear train is drivingly coupled with the turbine member, a drive shaft is operably coupled with the gear train, and an output shaft is selectively operably coupled to rotate with the engine. A screen is located within the interior between the at least one turbine member and the set of outlets and adapted to mitigate ejection of ignited particles from within the housing.

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Номер записи: 82
31-01-2019 дата публикации

INFLATABLE CASCADE ASSEMBLY, SYSTEM, AND METHOD FOR A CASCADE THRUST REVERSER SYSTEM

Номер: US20190032601A1
Автор: Chuck Chen, Harpal Naimishkumar B., Vandemark Zachariah B.
Принадлежит:

There is provided an inflatable cascade assembly for a cascade thrust reverser system of an engine of an air vehicle. The inflatable cascade assembly has inflatable cascade members for inflation with a pressurized fluid. The inflatable cascade members are movable between a stowed deflated state and a deployed inflated state. Each inflatable cascade member has a forward end, an aft end, and a body. The body has circumferential vanes each having a first non-inflatable rigid side attached adjacent to a second inflatable flexible side. The body further has inflatable support members that are spaced apart and longitudinally extending, and coupled in a perpendicular arrangement to the circumferential vanes. The body further has a plurality of flow openings defined between the circumferential vanes and the inflatable support members. Each inflatable cascade member further has first and second extendable side supports coupled to respective first and second side ends of the body. 1. An inflatable cascade assembly for a cascade thrust reverser system of an engine of an air vehicle , the inflatable cascade assembly comprising: a forward end;', 'an aft end;', a plurality of circumferential vanes that are spaced apart and laterally extending, each circumferential vane comprising a first non-inflatable rigid side attached adjacent to a second inflatable flexible side;', 'a plurality of inflatable support members that are spaced apart and longitudinally extending, the plurality of inflatable support members being coupled in a perpendicular arrangement to the plurality of circumferential vanes; and', 'a plurality of flow openings defined between the plurality of circumferential vanes and the plurality of inflatable support members;, 'a body formed between the forward end and the aft end, the body comprising, 'a first extendable side support coupled to first side ends of the body; and', 'a second extendable side support coupled to second side ends of the body, the first extendable ...

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Номер записи: 83
30-01-2020 дата публикации

Artificial lift

Номер: US20200032630A1
Автор: David Biddick, Herman Artinian, Kuo-Chiang Chen, Patrick Mcmullen
Принадлежит: Upwing Energy Inc

An electric submersible pump (ESP) is described. The ESP includes a stator chamber, a stator within the stator chamber, a rotor, and an electrical connection. The stator chamber is configured to reside in a wellbore. The stator chamber is configured to attach to a tubing of a well. The stator chamber defines an inner bore having an inner bore wall that, when the stator chamber is attached to the tubing, is continuous with an inner wall of the tubing. The rotor is positioned within the inner bore of the stator chamber. The rotor includes an impeller. The rotor is configured to be retrievable from the well while the stator remains in the well. The stator is configured to drive the rotor to rotate the impeller and induce well fluid flow in response to receiving power through the electrical connection.

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Номер записи: 84
30-01-2020 дата публикации

DOUBLE FLOW TURBOJET INCLUDING AN INTERMEDIATE FLOW PATH DEDICATED TO SUPPLYING WITH AIR VIA RADIAL ARMS AN EXHAUST CASING OF THIS TURBOJET

Номер: US20200032664A1
Автор: Beaujard Antoine Jean-Philippe, Boudebiza Tewfik, PIKOVSKY Catherine, VERDIER Bastien Pierre
Принадлежит:

The invention relates to a double flow turbojet including: 11. Double flow turbojet () including:{'b': '3', 'a low pressure compressor ();'}{'b': 9', '10', '3', '6', '18', '23', '6, 'a series of casings (, ) extending downstream of this low pressure compressor () to delimit a primary flow path for circulating a primary stream (), and including an upstream edge () delimiting a circumferential inlet opening () of this primary stream ();'}{'b': '24', 'a high pressure compressor () situated in the primary flow path;'}{'b': 11', '9', '10', '9', '10', '7', '19', '9', '10', '9', '10', '21', '24, 'a shroud () surrounding the series of casings (, ) to delimit with this series of casings (, ) an intermediate flow path for circulating an intermediate stream (), this shroud having an upstream edge () surrounding the series of casings (, ) to delimit with this series of casings (, ) an inlet opening () situated upstream of the high pressure compressor ();'}{'b': 12', '11', '11', '8, 'a secondary flow path casing () surrounding the intermediate shroud () to delimit with this shroud () a secondary flow path for circulating a secondary stream ();'}{'b': 38', '9', '10', '39', '38, 'an exhaust casing () including an outer shell extending into the extension of the series of casings (, ) as well as radial arms coming from this outer shell, one at least of these radial arms () collecting the air coming from the intermediate flow path to supply with pressured air a central region of this exhaust casing ().'}25324678. Turbojet according to claim 1 , in which the air sucked in is divided at the level of an intermediate casing () situated between the low pressure compressor () and the high pressure compressor () claim 1 , to form the central primary stream () claim 1 , the intermediate stream () claim 1 , and the secondary stream ().33838. Turbojet according to claim 1 , in which the air supplied in the central region of the exhaust casing () contributes to pressurising the seals of a ...

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Номер записи: 85
30-01-2020 дата публикации

LUBRICATION SCAVENGE SYSTEM FOR A TURBINE ENGINE WITH COUNTER-ROTATING SHAFTS

Номер: US20200032671A1
Автор: Burnside Phillip, Lighty Kerry J.
Принадлежит:

A lubricant scavenging system for a turbine engine having a pair of concentric, counter-rotating shafts. The system comprises a lubricant sump housing having a radially inner surface, a pair of pedestal mounts each adapted to receive a bearing assembly from a respective shaft, a lubricant collection point axially disposed between the pedestal mounts, and a pair of axial channels adapted to guide lubricant toward the lubricant collection point. 1. In a multi-shaft engine , a method of scavenging lubricant at an interface between two counter rotating shafts wherein the windage from the two counter rotating shafts drives the lubricant in a first rotational direction on one side of the interface and in a second rotational direction on another side of the interface , and a fixed sump housing surrounds the interface , the method comprising:axially locating a draining orifice in the sump housing proximate the interface where the net windage approaches a minimum.2. The method of claim 1 , further comprising collecting the lubricant with a recess in the sump housing proximate the draining orifice.3. The method of claim 2 , further comprising slowing the lubricant relative to the fixed sump housing with blunt walls formed in the recess.4. The method of claim 1 , further comprising turning the lubricant on both sides of the interface from a circumferential direction to an axial direction towards the draining orifice.5. The method of claim 1 , further comprising reducing the drive on the lubricant by extending a windage wall radially inward from the sump housing on both sides of the interface.6. The method of claim 1 , further comprising creating an axial lubricant passage through the pedestal mount by spacing apart a plurality of stand-off pedestals.716-. (canceled)17. An oil sump housing comprising:an inner surface;an outer surface;two annular mount rings extending radially inward from the inner surface;a draining orifice located axially between the two annular mount rings ...

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Номер записи: 86
30-01-2020 дата публикации

Regenerative blowers-compressors with shaft bypass fluid re-vents

Номер: US20200032812A1
Автор: Joel Jack Oakman
Принадлежит: VICTORI LLC

A regenerative blower-compressor includes an impeller mounted to a drive shaft within a housing including a channel extending from an inlet adjacent to a low fluid-pressure region of the channel to an outlet adjacent to a high fluid-pressure region of the channel, the impeller extends radially outward through an annular volume within the housing from the drive shaft to blades in the channel and is configured to rotate for rotating the blades through the channel for forcing fluid through the channel from the inlet to the outlet in response to rotation of the drive shaft, the drive shaft extends from the impeller within the annular volume to into a shaft chamber within the housing configured to receive fluid from the high fluid-pressure region of the channel, and a port configured to vent fluid directly from the shaft chamber to into the low fluid-pressure region of the channel.

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Номер записи: 87
05-02-2015 дата публикации

Moisture Separator Unit for Steam Turbine and Steam-Turbine Stationary Blade

Номер: US20150037144A1
Автор: Kenjiro Narita, Koji Ishibashi, Susumu Nakano, Takeshi Kudo
Принадлежит: Mitsubishi Hitachi Power Systems Ltd

A steam turbine stationary blade is configured to be a stationary blade structure having a hollow structure. The steam turbine stationary blade is provided with a slit disposed on a stationary blade surface. The pressure of a stationary blade hollow is reduced to suction a liquid film through the slit for removing the liquid film formed on the stationary blade surface. An opening portion of the slit is covered with a sheet in a meshed pattern formed of a fine mesh thereby reducing an accompanied steam amount so as to effectively remove the liquid film.

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Номер записи: 88
08-02-2018 дата публикации

DEVICE OF A TURBOMACHINE FOR SEPARATING OIL FROM AN AIR-OIL VOLUME FLOW

Номер: US20180036664A1
Автор: BEIER Juergen, BLUMRICH Markus
Принадлежит:

A device of a turbomachine for separating oil from an air-oil volume flow, with a first separation appliance and a second separation appliance, wherein an air-oil volume flow from an oil-loaded area of the turbomachine can be supplied to the first separation appliance, and wherein the air-oil volume flow, the oil loading of which can be reduced in the area of the first separation appliance, can be supplied to the second separation appliance downstream of the first separation appliance by means of a conduit. An appliance for cooling the air-oil volume flow conducted inside the conduit is provided, being arranged downstream of the first separation appliance and upstream of the second separation appliance. 1. A device of a turbomachine for separating oil from an air-oil volume flow , with a first separation appliance and a second separation appliance , wherein an air-oil volume flow from an oil-loaded area of the aircraft gas turbine can be supplied to the first separation appliance , and wherein the air-oil volume flow , the oil loading of which can be reduced in the area of the first separation appliance , can be supplied to the second separation appliance by means of a conduit downstream of the first separation appliance , characterized in that an appliance for cooling the air-oil volume flow conducted inside the conduit is provided , which is arranged downstream of the first separation appliance and upstream of the second separation appliance.2. The device according to claim 1 , wherein the appliance is embodied as an air cooling appliance.3. The device according to claim 1 , wherein a by-pass channel of the turbomachine represents the appliance for cooling claim 1 , wherein the conduit extends inside the by-pass channel at least in certain areas.4. The device according to claim 1 , wherein the appliance for cooling the air-oil volume flow conducted inside the conduit is embodied as an oil cooling appliance.5. The device according to claim 1 , wherein the appliance ...

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Номер записи: 89
12-02-2015 дата публикации

Inlet particle separator system with hub and/or shroud suction

Номер: US20150040535A1
Автор: Devinder N. Katariya, Eduardo Guerra, Yogendra Yogi Sheoran, Zedic Daniel Judd
Принадлежит: Honeywell International Inc

An inlet particle separator system for a vehicle engine includes a hub section, a shroud section, a splitter, and a hub suction flow passage. The shroud section surrounds at least a portion of the hub section and is spaced apart therefrom to define a main flow passageway that has an air inlet. The splitter is disposed downstream of the air inlet and extends into the passageway to divide the main flow passageway into a scavenge flow path and an engine flow path. The hub suction flow passage has a hub suction inlet port and a hub suction outlet port. The hub suction inlet port extends through the hub section and is in fluid communication with the air inlet. The hub suction outlet port extends through the splitter and is in fluid communication with the scavenge flow path.

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Номер записи: 90
11-02-2016 дата публикации

Multi-Stage Combustor

Номер: US20160040884A1
Автор: Citeno Joseph Vincent, Johnson Thomas Edward
Принадлежит:

The present application provides a combustor for use with a gas turbine engine. The combustor may include a primary stage nozzle in communication with a linear actuator and a number of stationary secondary nozzles surrounding the primary stage nozzle in whole or in part. The linear actuator varies the position of the primary stage nozzle with respect to the stationary secondary nozzles. 1. A combustor , comprising:a primary stage nozzle;a linear actuator in communication with the primary stage nozzle; anda plurality of stationary secondary nozzles surrounding the primary stage nozzle in whole or in part;wherein the linear actuator varies the position of the primary stage nozzle with respect to the plurality of stationary secondary nozzles.2. The combustor of claim 1 , wherein the primary stage nozzle comprises a micro-mixer nozzle.3. The combustor of claim 1 , wherein the plurality of stationary secondary nozzles comprises a micro-mixer nozzle.4. The combustor of claim 1 , wherein the primary stage nozzle comprises a primary stage fuel tube.5. The combustor of claim 1 , wherein the linear actuator comprises a drive rod in communication with the primary stage nozzle.6. The combustor of claim 1 , wherein the primary stage nozzle comprises a variable air bypass.7. The combustor of claim 1 , wherein the plurality of stationary secondary nozzles comprises a secondary stage fuel tube.84. The combustor of claim 1 , wherein the plurality of stationary secondary nozzles comprises four () stationary secondary nozzles.9. The combustor of claim 1 , wherein the plurality of stationary secondary nozzles comprises an angled shape.10. The combustor of claim 1 , further comprising a combustion zone downstream of the primary stage nozzle.11. A method of operating a combustor claim 1 , comprising:positioning a maneuverable primary stage nozzle within a plurality of stationary secondary nozzles;retracting the maneuverable primary stage nozzle with respect to the plurality of stationary ...

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Номер записи: 91
07-02-2019 дата публикации

DEAERATOR SHAFT WITH ATTACHMENT SURFACES

Номер: US20190038999A1
Автор: Finke Aaron M., Grosskopf Andrew P., Ooyen Christine Lynn
Принадлежит:

A deaerator shaft may have a tubular intake segment that forms an intake end of the deaerator shaft, a tubular sleeve attachment segment that is adjacent to the intake segment, a tubular central segment that is adjacent to the sleeve attachment segment, the central segment having a third diameter that is greater than the second diameter, the central segment comprising a protruding ring that radially extends from the central segment and divides the central segment, the protruding ring having opposing flat surfaces, and a tubular discharge segment that forms a discharge end of the deaerator shaft. A gear may have a central ring positioned along an axis, opposing tabs that extend from a first axial side of the central ring, and a shouldered ring that extends from a second axial side of the central ring, the shouldered ring having a lip that extends radially inward toward the axis. 1. A method of replacing deaerator shafts , the method comprising:removing a first deaerator shaft; andplacing a second deaerator shaft in place of the first deaerator shaft, the second deaerator shaft comprising:a tubular intake segment that forms an intake end of the deaerator shaft, the tubular intake segment is configured to receive fluid, the intake segment having a first diameter;a tubular sleeve attachment segment that is adjacent to the intake segment, the tubular sleeve attachment segment having a second diameter that is greater than the first diameter;a tubular central segment that is adjacent to the sleeve attachment segment, the tubular central segment having a third diameter that is greater than the second diameter, the tubular central segment comprising a protruding ring that radially extends from the tubular central segment and divides the tubular central segment, the protruding ring having opposing flat surfaces and further comprising a plurality of vanes, wherein each of the plurality of vanes form a rounded surface with an inner radial wall of the central segment; anda ...

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Номер записи: 92
24-02-2022 дата публикации

CONNECTION STRUCTURE FOR A GENERATOR ASSEMBLY

Номер: US20220056810A1
Автор: Grunwald Maciej, Hanczewski Pawel Piotr, Janczak Lukasz Maciej, Osama Mohamed, Pazinski Adam Tomasz
Принадлежит:

A generator assembly includes a stator assembly coupled to an engine stator component of a propulsion engine, the stator assembly including: a stator support structure fixedly attached to the engine stator component; a stator disposed on a supporting surface of the stator support; a manifold coupled to the stator support, the manifold defining a connection volume and including at least one coolant opening at a connection end of the manifold; and an electrical connector extending between the stator and a connection device disposed on the connection end. The generator assembly also includes a rotor assembly comprising a rotor support structure connected to a shaft of the propulsion engine and a rotor attached to the rotor support structure, wherein the rotor rotates in conjunction with the shaft to generate a power signal that travels through the electrical connector to the connection device. 1. A generator assembly , comprising:{'claim-text': ['a stator support structure fixedly attached to the engine stator component;', 'a stator disposed on a supporting surface of the stator support;', 'a manifold coupled to the stator support, the manifold defining a connection volume and comprising at least one coolant opening at a connection end of the manifold; and', 'an electrical connector extending between the stator and a connection device disposed on the connection end; and'], '#text': 'a stator assembly coupled to an engine stator component of a propulsion engine, the stator assembly comprising:'}a rotor assembly comprising a rotor support structure connected to a shaft of the propulsion engine and a rotor attached to the rotor support structure, wherein the rotor rotates in conjunction with the shaft to generate a power signal that travels through the electrical connector to the connection device.2. The generator assembly of claim 1 , further comprising a cooling duct in fluid communication with a coolant supply and a generator coupler connecting the stator assembly to ...

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Номер записи: 93
24-02-2022 дата публикации

COMPRESSOR PARTICLE SEPARATOR FOR GAS TURBINE ENGINE

Номер: US20220056844A1
Автор: Aukland Daniel, Pearson John, Sheoran Yogendra
Принадлежит: HONEYWELL INTERNATIONAL INC.

A particle separator associated with a compressor section of a gas turbine engine includes a duct that defines a fluid flow path from a diffuser to a deswirl section. The duct includes a curved portion between an outlet of the diffuser and an inlet of the deswirl section. The curved portion is configured to have at least one low velocity region and a high velocity region. The particle separator includes at least one cluster of inlet passages defined at the at least one low velocity region. The particle separator includes a scavenge plenum coupled to the duct and in fluid communication with the at least one cluster of inlet passages. At least one outlet slot is defined through the duct downstream of the at least one cluster of inlet passages in the high velocity region and is in fluid communication with the scavenge plenum. 1. A particle separator associated with a compressor section of a gas turbine engine , comprising:a duct that defines a fluid flow path from a diffuser to a deswirl section, the duct including a curved portion between an outlet of the diffuser and an inlet of the deswirl section, the curved portion configured to have at least one low velocity region and a high velocity region;at least one cluster of inlet passages defined through the curved portion of the duct at the at least one low velocity region and configured to receive a fluid that includes a plurality of entrained particles from the outlet of the diffuser;a scavenge plenum coupled to the duct and in fluid communication with the at least one cluster of inlet passages, the scavenge plenum configured to receive the fluid that includes the plurality of entrained particles from the at least one cluster of inlet passages and to separate the plurality of entrained particles from the fluid to provide at least one outlet slot with the fluid with a reduced plurality of entrained particles; andthe at least one outlet slot defined through the duct downstream of the at least one cluster of inlet ...

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Номер записи: 94
18-02-2021 дата публикации

FILTER ELEMENT, SYSTEMS, AND METHODS

Номер: US20210046415A1
Автор: ANDERSON Brent L., CARLSON Michael R., DAHLGREN Andrew C., DEJONG Richard P., MOVIA Massimo, PROOST Gert, RONNEAU Olivier, ROSS Eli Payton, TIFFANY Jason A., VAN GELDER Wim, VERSTRAETE Mathijs
Принадлежит: Donaldson Company, Inc.

A gas turbine air intake system uses a filter element having a seal member with radial projections and radial recesses. The seal member forms a seal with components on the tube sheet of the system and at the end opposite of the tube sheet. At the end opposite of the tube sheet, there can be an assembly cover, or alternatively, an additional filter cartridge. 1. A filter element comprising:(a) a tubular section of filter media; and (i) each of the first and second end caps having a seal arrangement along an inner radial surface of each of the end caps;', '(ii) each of the seal arrangements including a seal member having an inwardly radially directed seal surface and a thickness that varies along the seal member surface., '(b) first and second opposite open end caps secured to the filter media;'}2. The filter element of wherein each the seal arrangements has a same shape as the other.3. The filter element of wherein the tubular section of media is conical claim 1 , and the seal arrangements vary in proportion to each other.4. The filter element of further including a seal support; the seal member being supported by the seal support; wherein the seal support comprises an inner liner extending between the first and second end caps.5. The filter element of wherein the thickness of the seal member surface varies in a radial direction along the seal member surface.6. The filter element of wherein a length of the seal member surface is constant in an axial direction.7. The filter element of wherein the seal member thickness varies by a minimum thickness and a maximum thickness claim 1 , wherein the maximum thickness is at least 1.1 times the minimum thickness.8. The filter element of wherein the radially directed seal surface comprises a plurality of outwardly projecting and axially extending portions and a plurality of inwardly projecting and axially extending portions.9. The filter element of wherein the plurality of outwardly projecting and axially extending portions and ...

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Номер записи: 95
06-02-2020 дата публикации

TURBOCHARGER

Номер: US20200040812A1
Автор: MORITA Isao, SATO Wataru
Принадлежит: IHI CORPORATION

A turbocharger includes a turbine impeller, a turbine housing which includes a scroll portion and a discharge port, a bypassing passage portion which guides a working fluid from the scroll portion to the discharge port, and a valve portion which controls the inflow of the working fluid to the bypassing passage portion. The hub side scroll is formed so that a cross-sectional area of a passage is larger than that of a shroud side scroll. The valve portion includes a hub side valve which controls the inflow of the working fluid from the hub side scroll to the bypassing passage portion and a shroud side valve which controls the inflow of the working fluid from the shroud side scroll to the bypassing passage portion. An operation of opening and closing the hub side valve is independent from an operation of opening and closing the shroud side valve. 1. A turbocharger comprising:a turbine impeller which rotates by using a predetermined axis as a rotation axis;a housing which includes a scroll portion formed to surround the turbine impeller and supplying a working fluid to the turbine impeller and a discharge portion discharging the working fluid passing through the turbine impeller;a bypassing passage portion of which one end is connected to the scroll portion and the other end is connected to the discharge portion and which guides the working fluid from the scroll portion to the discharge portion; anda valve portion which is provided in the bypassing passage portion and controls an inflow of the working fluid from the scroll portion to the discharge portion,wherein the scroll portion includes a first scroll and a second scroll,wherein the first scroll is formed so that a cross-sectional area of a passage is larger than that of the second scroll,wherein the valve portion includes a first valve and a second valve,wherein the first valve controls the inflow of the working fluid from the first scroll to the bypassing passage portion,wherein the second valve controls the ...

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Номер записи: 96
06-02-2020 дата публикации

TURBOMACHINERY TRANSITION DUCT FOR WIDE BYPASS RATIO RANGES

Номер: US20200040847A1
Автор: Filipenco Victor G.
Принадлежит:

A gas turbine engine includes a case assembly, a splitter, an upstream blade row, and a transition duct. The case assembly defines an outer flow path wall and an inner flow path wall. The splitter is disposed between the outer flow path wall and the inner flow path wall. The splitter has a first surface and a second surface disposed opposite the first surface. The transition duct is defined by the outer flow path and the inner flow path and extends between the upstream blade row and the leading edge of the splitter. 1. A gas turbine engine comprising:a case assembly defining an outer flow path wall and an inner flow path wall, each extending between a first case end and a second case end along a central longitudinal axis;a splitter disposed between the outer flow path wall and the inner flow path wall, the splitter having a first surface and a second surface disposed opposite the first surface, each extending from the second case end towards a leading edge;an upstream blade row is disposed proximate the first case end and extends between the outer flow path wall and the inner flow path wall; anda transition duct defined by the outer flow path and the inner flow path and extends between the upstream blade row and the leading edge, the transition duct defining an entrance section that extends from the upstream blade row towards a diverging section that extends towards the leading edge.2. The gas turbine engine of claim 1 , wherein the entrance section has an entrance annular area.3. The gas turbine engine of claim 2 , wherein the transition duct includes a first outlet having a first annular area and a second outlet having a second annular area.4. The gas turbine engine of claim 3 , wherein a combination of the first annular area and the second annular area is greater than the entrance annular area.5. The gas turbine engine of claim 1 , wherein an outer duct is defined between the outer flow path wall and the first surface and extends from the leading edge towards the ...

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Номер записи: 97
06-02-2020 дата публикации

Housing assembly for a turbocharger and method for fixing multiple connections to a housing

Номер: US20200041053A1
Автор: Dariusz MARCINIAK, Natalya Platova
Принадлежит: BorgWarner Inc

A housing assembly comprising a housing that has at least one first connection opening and one second connection opening, a first connecting piece with a first flange and a second connecting piece with a second flange. The first connecting piece is connected to the first connection opening and the second connecting piece is connected to the second connection opening. The housing additionally has a projection with an overhang. The A locking part of the first flange is arranged in locking engagement with the overhang, and the first flange and the second flange are configured in such a way and arranged with respect to one another that a turning of the first flange is prevented by the second flange. A corresponding method of fixing multiple connections to a housing is also provided.

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Номер записи: 98
19-02-2015 дата публикации

OPERATION OF GAS TURBINE POWER PLANT WITH CARBON DIOXIDE SEPARATION

Номер: US20150047366A1
Автор: Carroni Richard, HOFFMANN Jürgen
Принадлежит:

The invention relates to a method for operating a gas turbine power plant, including a gas turbine, a HRSG following the gas turbine, an exhaust gas blower, and a carbon dioxide separation plant which separates the carbon dioxide contained in the exhaust gases and discharges it to a carbon dioxide outlet, the gas turbine, HRSG, exhaust gas blower, and carbon dioxide separation plant being connected by means of exhaust gas lines. According to the method a trip of the gas turbine power plant includes the steps of: stopping the fuel supply, switching off the exhaust gas blower, and controlling the opening angle of a VIGV at a position bigger or equal to a position required to keep a pressure in the exhaust gas lines between the HRSG and the exhaust gas blower above a minimum required pressure. The invention relates, further relates to a gas turbine power plant configured to carry out such a method. 1. A method for operating a gas turbine power plant , including a gas turbine , a HRSG downstream of the gas turbine , an exhaust gas blower , and a carbon dioxide separation plant which separates the carbon dioxide contained in the exhaust gases and discharges it to a carbon dioxide outlet , the gas turbine , HRSG , exhaust gas blower , and carbon dioxide separation plant being connected by means of exhaust gas lines , a trip of the gas turbine power plant comprising:stopping the fuel supply, switching off the exhaust gas blower, and controlling the opening angle of a VIGV at a position bigger or equal to a position required to keep a pressure in the exhaust gas lines between the HRSG and the exhaust gas blower above a minimum required pressure.2. The method for operating a gas turbine power plant according to claim 1 , wherein the opening angle of the VIGV is controlled as a function of the pressure in the exhaust gas lines between the HRSG and the exhaust gas blower.3. The method for operating a gas turbine power plant according to claim 1 , wherein the opening angle of ...

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Номер записи: 99
18-02-2021 дата публикации

Removal of contaminants from air for use in aircraft engines

Номер: US20210047953A1
Автор: Christopher GOVER, Guy Lefebvre
Принадлежит: Pratt and Whitney Canada Corp

A secondary air system for an aircraft engine comprises an air flow path communicating between a source of pressurized cooling air and an air consuming component. A filter is disposed in the air flow path upstream from the air consuming component. The filter has at least one of: openings of a size selected for capturing suspended particles; and a filter surface material for binding with chemical contaminants.

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Номер записи: 100