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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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05-01-2012 дата публикации

Turbine nozzles and methods of manufacturing the same

Номер: US20120003086A1

Автор: Daniel Ryan, Donald G. Godfrey, Jason Smoke, Mark C. Morris

Принадлежит: Honeywell International Inc

A turbine nozzle is provided and includes a first ring having a first microstructure, a vane extending from the first ring, a first porous zone between the first ring and the vane that is more porous than the first microstructure to attenuate thermo-mechanical fatigue cracking between the vane and the first ring. Methods of manufacturing the turbine nozzle are also provided.

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Номер записи: 1

20-11-2011 дата публикации

Модуль для паровой турбины

Номер: RU0000110410U1

Автор: Жак МИЗЕРА, Жюльен РОЖЕ

Принадлежит: АЛЬСТОН ТЕКНОЛОДЖИ ЛТД

1. Модуль (1) для паровой турбины, содержащий внутренний кожух (5) турбины с, по меньшей мере, одним комплектом неподвижных лопаток, ротор (6), оснащенный, по меньшей мере, одним комплектом лопаток, и плиту (16), при этом внутренний кожух (5) турбины опирается на плиту (16) посредством, по меньшей мере, двух поперечин (20), закрепленных на упомянутом внутреннем кожухе (5) турбины, а соединение между упомянутыми поперечинами (20) и плитой (16) выполнено в виде нескольких механических средств соединения (23), каждое из которых обеспечивает предотвращение подъема внутреннего кожуха (5) турбины относительно плиты (16), а также обеспечивает скольжение упомянутого внутреннего кожуха (5) турбины по подобной плите (16). ! 2. Модуль по п.1, отличающийся тем, что место (22) сопряжения между поперечиной (20) и плитой (16) является, по существу, горизонтальным, при этом каждое средство (23) соединения содержит вертикальную штангу (24), неподвижно закрепленную в плите (16), и оснащено шайбой (30), каждая поперечина (20) опирается на плиту (16) посредством упомянутых штанг (24), проходящих через нее с зазором вдоль места (22) сопряжения, а шайбы (30) расположены над каждой поперечиной (20). ! 3. Модуль по п.2, отличающийся тем, что каждое средство (23) соединения содержит управляющие устройства (27), закрепленные на плите (16) и обеспечивающие локальное регулирование по высоте внутреннего кожуха (5) турбины, при этом каждая поперечина (20) опирается на управляющее устройство (27). ! 4. Модуль по п.3, отличающийся тем, что управляющее устройство является вращательным приводом (27), приводимым в действие в месте (22) сопряжения, после того как поперечина (20) установлена на упомянутое управляющее ус� РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 110 410 (13) U1 (51) МПК F01D 25/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ, ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ (12) ТИТУЛЬНЫЙ ЛИСТ ОПИСАНИЯ ПОЛЕЗНОЙ МОДЕЛИ К ПАТЕНТУ (21)(22) Заявка: 2011114266/28, 12.04.2011 (24) Дата начала отсчета ...

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Номер записи: 2

26-01-2012 дата публикации

Systems and methods for controlling the startup of a gas turbine

Номер: US20120017602A1

Автор: Brian Patrick Hansen, Christopher Edward LaMaster, David August Snider, Timothy Edward DeJoris

Принадлежит: General Electric Co

Systems and methods for controlling the startup of a gas turbine are described. A gas discharge component may be configured to discharge gas from a compressor component associated with the gas turbine. A fuel control component may be configured to control a fuel flow provided to a combustor component associated with the gas turbine. A drive component may be configured to supply a rotational force to a shaft associated with the gas turbine. At least one control device may be configured to (i) direct the gas discharge component to discharge gas from the compressor component, (ii) direct the fuel control component to adjust the fuel flow, and (iii) direct the drive component to rotate the shaft.

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Номер записи: 3

26-01-2012 дата публикации

Fluid Machine

Номер: US20120019010A1

Автор: Hirofumi Wada, Shinji Nakamura

Принадлежит: Sanden Corp

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

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Номер записи: 4

02-02-2012 дата публикации

Systems, methods, and apparatus for monitoring corrosion or corrosive contaminants associated with liquid fuel

Номер: US20120023894A1

Автор: Paul Joseph Martin

Принадлежит: General Electric Co

Certain embodiments of the invention may include systems, methods, and apparatus for monitoring corrosion or corrosive contaminants associated with liquid fuel. According to an example embodiment of the invention, a method is provided for monitoring and predicting corrosion. The method can include monitoring corrosion or corrosive contaminants associated with liquid fuel in a fuel supply system of a gas turbine, predicting, based at least in part on the monitoring, a cumulative level of corrosion of one or more components associated with a gas turbine, and outputting information associated with the monitoring.

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Номер записи: 5

02-02-2012 дата публикации

Exhaust manifold flange connection

Номер: US20120023968A1

Автор: Brian H. Terpos, Brian Micklos, Christopher Scogin, David Wiebe, James Marshall, Jonathan Leagon, Robert T. Brooks, Robert W. Spitzer, Scott Smith, Yevgeniy Shteyman

Принадлежит: Siemens Energy Inc

A flange connection for an exhaust section of a gas turbine engine. The flange connection includes a stub flange attached to an exhaust manifold. The stub flange has a first axial face for engagement with the axial face of a cylinder flange extending radially from an exhaust cylinder. A plate structure attached to the cylinder flange is configured to provide axial retention of the stub flange to the axial face of the cylinder flange. The plate structure includes a resilient beam portion extending radially inwardly and engaging a second axial face of the stub flange. The stub flange is retained between the cylinder flange and the beam portion of the plate structure in an interference fit to provide three degrees of freedom of the stub flange relative to the exhaust cylinder.

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Номер записи: 6

09-02-2012 дата публикации

Ventilation inlet

Номер: US20120034068A1

Автор: Zahid M. Hussain

Принадлежит: Rolls Royce PLC

A ventilation inlet comprising a ventilation pipe to receive flow from a first flow zone and to deliver the flow to a second flow zone; a divider arranged to divide a portion of the ventilation pipe into a static pressure zone and a total pressure zone; and a deflector arranged to direct flow from the total pressure zone at least partially across the static pressure zone to restrict delivery of the flow from the static pressure zone to the second flow zone dependent on the pressure of the flow in the first flow zone.

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Номер записи: 7

16-02-2012 дата публикации

Method for compensating for combustion efficiency in fuel control system

Номер: US20120036861A1

Автор: Michael John Hughes, William Forrester Seely

Принадлежит: General Electric Co

Compensation is provided for a fuel demand signal of a gas turbine controller during transition between operating modes. The compensation adjusts fuel demand to account for combustion efficiency differences between the starting and ending operating mode that otherwise can lead to severe swings in combustion reference temperature and lean blowout.

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Номер записи: 8

16-02-2012 дата публикации

Methods and systems for adaptively cooling combustion chambers in engines

Номер: US20120037100A1

Автор: Melvin J. Larsen, Roy E. McAlister, Roy Edward McAlister

Принадлежит: McAlister Technologies LLC

The present disclosure is directed to various embodiments of systems and methods for cooling a combustion chamber of an engine. One method includes introducing fuel into the combustion chamber of an engine having an energy transfer device that moves through an intake stroke, a compression stroke, a power stroke, and an exhaust stroke. The method further includes monitoring a temperature of the combustion chamber. When the temperature reaches a predetermined value, the method also includes introducing coolant into the combustion chamber only during at least one of the power stroke and the exhaust stroke of the energy transfer device.

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Номер записи: 9

01-03-2012 дата публикации

Retaining ring arrangement for a rotary assembly

Номер: US20120051918A1

Автор: Bruno Chatelois, David F. GLASSPOOLE

Принадлежит: Pratt and Whitney Canada Corp

A retaining ring arrangement is provided for axially holding a component on a rotating component of a gas turbine engine. The retaining ring arrangement comprises a split retaining ring mounted in a circumferential groove defined in a radially outer surface of the rotating component. The inner diameter of the retaining ring is biased inwardly in radial contact with a radially outer facing seat provided on one of the two components to be assembled. An anti-rotation feature is provided at the inner diameter of the retaining ring for restraining the ring against rotation. A sleeve surrounds the retaining ring to limit radial expansion thereof when subject to centrifugal forces during engine operation.

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Номер записи: 10

08-03-2012 дата публикации

Fan array fan section in air-handling systems

Номер: US20120057962A1

Автор: Lawrence G. Hopkins

Принадлежит: Huntair Inc

A fan array fan section in an air handling system includes a plurality of fan units arranged in a fan array and positioned within an air handling compartment. One preferred embodiment may include an array controller program to operate the plurality of the fan units at peak efficiency. The plurality of fan units may be arranged in a true array configuration, a space pattern array configuration, a checker board array configuration, rows slightly offset configuration, columns slightly offset configuration, or a staggered array configuration.

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Номер записи: 11

15-03-2012 дата публикации

Air-oil heat exchanger

Номер: US20120060466A1

Автор: Frederick L. Elsaesser, Frederick M. Schwarz

Принадлежит: United Technologies Corp

A heat exchange system for use in fluid operated equipment to provide air and working fluid heat exchanges to cool the working fluid in airstreams on a stream side of a wall. An actuator is mounted to be substantially located on a side of the wall opposite the stream side thereof having a positionable motion effector. A heat exchanger core having a plurality of passageway structures therein to enable providing the working fluid to, and removal therefrom. The heat exchanger core is mounted on the motion effector so as to be extendable and retractable thereby through the opening for selected distances into that region to be occupied by the airstreams.

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Номер записи: 12

15-03-2012 дата публикации

Apparatus and method for cooling a combustor cap

Номер: US20120060511A1

Автор: Baifang Zuo, Chunyang Wu, Roy Marshall Washam

Принадлежит: General Electric Co

A combustor includes an end cap having a perforated downstream plate and a combustion chamber downstream of the downstream plate. A plenum is in fluid communication with the downstream plate and supplies a cooling medium to the combustion chamber through the perforations in the downstream plate. A method for cooling a combustor includes flowing a cooling medium into a combustor end cap and impinging the cooling medium on a downstream plate in the combustor end cap. The method further includes flowing the cooling medium into a combustion chamber through perforations in the downstream plate.

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Номер записи: 13

22-03-2012 дата публикации

Wireless sensor for an aircraft propulsion system

Номер: US20120068003A1

Автор: Nicholas Charles Soldner, Peter G. Smith, Sanjay Bajekal, Vijaya Ramaraju Lakamraju

Принадлежит: United Technologies Corp

A method is provided for wirelessly monitoring an aircraft propulsion system having a plurality of rotor blades, at least some of which rotor blades have an internal compartment. The method includes: providing a primary transducer having a primary coil, and one or more secondary transducers, each secondary transducer having a secondary coil connected to a sensor, wherein the secondary transducers are respectively disposed within the internal compartments; wirelessly powering the secondary transducers using a magnetic field generated by the primary transducer; monitoring at least one operational parameter from within each internal compartment using a respective sensor; and transmitting output signals from the secondary transducers to the primary transducer through the magnetic field, wherein the output signals are indicative of the monitored parameters.

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Номер записи: 14

29-03-2012 дата публикации

Cooled turbine blades for a gas-turbine engine

Номер: US20120076665A1

Автор: Erik Janke, Heinz-Peter SCHIFFER, Jens Taege, Knut Lehmann, Nils WINTER, Sebastian Meier, Thomas SCHIESSL

Принадлежит: Rolls Royce Deutschland Ltd and Co KG

The present invention relates to a cooled turbine blade for a gas-turbine engine having at least one cooling duct ( 14 ) extending radially, relative to a rotary axis of the gas-turbine engine, inside the airfoil and air-supply ducts ( 12 ) issuing into said cooling duct, characterized in that the cooling duct ( 14 ) extends into the blade root ( 6 ) in order to generate close to the wall a cooling airflow moved at high circumferential velocity and radially in helical form and that in the area of the blade root ( 6 ) at least one nozzle-shaped air-supply duct ( 12 ) issues into the cooling duct ( 14 ) tangentially or with a tangential velocity component.

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Номер записи: 15

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: 16

05-04-2012 дата публикации

Steam turbine rotor, method of manufacturing the same, and steam turbine

Номер: US20120082542A1

Автор: Masato Misawa

Принадлежит: Individual

In one embodiment, a steam turbine rotor has a first and a second rotor, a first and a second flange, a bolt, and a cap nut. The first flange is connected to an end portion of a first shaft of the first rotor and has a first through hole. The second flange is connected to an end portion of a second shaft of the second rotor and has a second through hole. The bolt is inserted through the first and second through holes and has a shaft part, a male screw part disposed on one end of the shaft part, and a projection part disposed on an end portion of the male screw part. The cap nut has a female screw part engaged with the male screw part and a projection through hole which the projection part penetrates.

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Номер записи: 17

05-04-2012 дата публикации

Cooed IBR for a micro-turbine

Номер: US20120082563A1

Автор: Jack W. Wilson, Jr., James P. Downs, John E. Ryznic

Принадлежит: Florida Turbine Technologies Inc

A micro gas turbine engine in which the turbine rotor blades are formed as an integral bladed rotor with cooling air passages formed within the blades and the rotor disk by an EDM process. an adjacent stator vane includes an air riding seal with an air cushion supplied through the vanes to provide cooling, and where the air cushion is then passed into the turbine blades and rotor disk to provide cooling for the turbine blades. With cooling of the turbine blades, higher turbine inlet temperatures for micro gas turbine engines can be produced.

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Номер записи: 18

12-04-2012 дата публикации

Rotor For Turbomachines With Shrouded Blades

Номер: US20120087794A1

Автор: Paolo Calza, Rosario Grillo, Sergio Salvano

Принадлежит: Avio SpA

A rotor for turbomachines with shrouded blades comprising a row of a plurality of blades covered by an external ring, coaxial to said row of blades; the external ring being composed of a plurality of sectors, commonly referred to as shrouds, which are adjacent to one another and transversely and circumferentially attached to the end of respective blades; a damping member being arranged so as to straddle a respective pair of adjacent sectors and being pushed, in use, against radially internal surfaces of the sectors of the pair of adjacent sectors.

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Номер записи: 19

12-04-2012 дата публикации

Planetary gear system arrangement with auxiliary oil system

Номер: US20120088624A1

Автор: William G. Sheridan

Принадлежит: Individual

A lubricating system for lubricating components across a rotation gap has an input that provides lubricant to a stationary first bearing. The first bearing has an inner first race in which lubricant flows. A second bearing rotates within the first bearing and has a first opening in registration with the inner first race such that lubricant may flow from the inner first race through the first opening into a first conduit.

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Номер записи: 20

19-04-2012 дата публикации

Combustion chamber comprising a condensation-proof barrier on a regenerative circuit

Номер: US20120090292A1

Автор: Daniel Cornu

Принадлежит: SNECMA SAS

The invention concerns a combustion chamber ( 10 ) comprising a neck ( 15 ) downstream of the injection ( 11 ) of gases, and downstream of this neck a divergent section ( 20 ) whereof the outer face of the wall ( 30 ), when in operation, is cooled by a cooling system using a cryogenic product and surrounding this outer face. This divergent section ( 20 ), on the inner face ( 32 ) of its wall ( 30 ), comprises a coating ( 40 ) acting as temperature compensator so that the temperature of the inner face ( 42 ) of the coating ( 40 ) is higher than the condensation temperature of the combustion gases on this inner face ( 42 ) under operating conditions, such that no condensation is formed on this inner face ( 42 ).

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Номер записи: 21

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: 22

19-04-2012 дата публикации

Thermally insulating turbine coupling

Номер: US20120093661A1

Автор: Keith R. Pullen, Michael J. Vick

Принадлежит: IMPERIAL INNOVATIONS LTD

A rotor assembly, including at least one driven member, e.g., a compressor rotor, and at least one driving member, e.g., a turbine. At least one rotating thermal insulator rigidly attached to either the driven member or the driving member. A coupling feature that includes mating geometric surfaces on the driven member and the driving member, wherein the geometric surfaces are configured to allow radial sliding, relative centering, torque transmission, and axial constraint between the driven member and the driving member.

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Номер записи: 23

26-04-2012 дата публикации

Seal apparatus

Номер: US20120098211A1

Автор: Bhaskar Mani, DONKADA Santhosh, Upendra Prabhu Nath Vemula Gopinath, Vishwas Kumar Pandey

Принадлежит: General Electric Co

A seal apparatus including at least first and second adjacent seal segments, each including an elongate body with ends defined at opposing elongate body ends, to be arranged such that an end of the first seal segment joins with a complementary end of the second seal segment, the end of the first seal segment including a first male component protruding from a plane of a first seal surface to define a first female mating section about the first male component, the end of the second seal segment including a second male component protruding from a plane of a second seal surface to define a second female mating section about the second male component, the first and second male components being receivable in the second and first female mating sections, respectively, to form first and second male component overlaps in at least two dimensions.

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Номер записи: 24

26-04-2012 дата публикации

Rotary machine having non-uniform blade and vane spacing

Номер: US20120099961A1

Автор: Brian Denver Potter, John McConnell Delvaux

Принадлежит: General Electric Co

A system, including a rotary machine including: a stator, a rotor configured to rotate relative to the stator, wherein the rotor comprises a plurality of blades having a non-uniform spacing about a circumference of the rotor.

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Номер записи: 25

26-04-2012 дата публикации

Drive mechanism for a pair of contra-rotating propellers through an epicyclic gear train

Номер: US20120099988A1

Автор: Francois Gallet, Gilles Alain Charier

Принадлежит: SNECMA SAS

A turbine driving a planet gear and an epicyclic gear train and including a planet pinion cage and a ring driving two propellers in rotation, is connected to the planet gear through a flexible sleeve surrounding a turbine support shaft rather than through a support shaft itself to achieve a flexible assembly with a limit stop position in contact with the shaft to limit parasite internal forces applied to the epicyclic gear train without tolerating a loose assembly or breakage of the sleeve due to a condition of the limit stop after a clearance has been eliminated.

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Номер записи: 26

26-04-2012 дата публикации

Annular flow channel section for a turbomachine

Номер: US20120100008A1

Автор: Fathi Ahmad

Принадлежит: SIEMENS AG

An annular flow channel section for a turbomachine is provided. The annular flow channel includes a guide vane ring having a number of guide vanes which are arranged next to each other in the circumferential direction, each guide vane including a vane base, a platform and an airfoil that projects into the flow channel in a radiating pattern. The flow channel is delimited on the platform side by shielding elements, each of which being disposed between two immediately adjacent airfoils, wherein the shielding elements are arranged on the platforms for creating a particularly space-saving flow channel section while creating a gap, and impingement-cooling openings are provided in the platform.

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Номер записи: 27

03-05-2012 дата публикации

Systems, methods, and apparatus for compensating fuel composition variations in a gas turbine

Номер: US20120102914A1

Автор: Denis Michel Martin, Joseph Kirzhner, Matthieu Paul Frederic Vierling, Nicolas Pourron, Predrag Popovic

Принадлежит: General Electric Co

Certain embodiments of the invention may include systems and methods for compensating fuel composition variations in a gas turbine. According to an example embodiment of the invention, a method is provided for compensating for fuel composition variations in a turbine. The method can include: monitoring at least one fuel parameter associated with a turbine combustor; monitoring one or more combustion dynamics characteristics associated with the turbine combustor; monitoring one or more performance and emissions characteristics associated with the turbine; estimating fuel composition based at least in part on the at least one fuel parameter, the one or more combustion dynamics characteristics, and the one or more performance and emissions characteristics, and adjusting at least one fuel parameter based at least in part on the estimated fuel composition.

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Номер записи: 28

03-05-2012 дата публикации

Partial coarse pitch start ram air turbine with enhanced spring support

Номер: US20120107119A1

Автор: David G. Bannon

Принадлежит: Hamilton Sundstrand Corp

A Ram Air Turbine (RAT) is provided and includes a turbine hub having an end plate and a nose cone attached thereto at trailing and leading ends, respectively, a governor shaft, to which turbine blades are connected, which is coupled to the end plate and supported within the nose cone to be rotatable with the turbine blades about a central axis thereof and axially movable from a first position relative to the turbine hub to a second position relative to the turbine hub and a hub assembly operably coupled to the turbine hub, the governor shaft and the turbine blades whereby the hub assembly biases the governor shaft toward the first position at low rotational speeds such that the turbine blades assume a partial coarse pitch angle, and the second position at high rotational speeds such that the turbine blades assume a fine pitch angle.

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Номер записи: 29

10-05-2012 дата публикации

Control method for cooling a turbine stage in a gas turbine

Номер: US20120111020A1

Автор: Federico Bonzani, Luca Bozzi, Marco Mantero

Принадлежит: Ansaldo Energia SpA

A control method for cooling a turbine stage of a gas turbine, whereby cooling air is bled from combustion air flowing in a compressor of the gas turbine, and is fed to a cooling circuit staring from a stator of the turbine stage; and cooling airflow is adjusted as a function of the pressure at the inlet of the cooling circuit, and as a function of the combustion air pressure at the exhaust of the compressor; more specifically, there is a feedback control setting a setpoint, which is predetermined as a function of the power output of the turbine to reduce contaminating emissions.

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Номер записи: 30

10-05-2012 дата публикации

Turbine assembly and method for securing a closure bucket

Номер: US20120114490A1

Автор: Manish Joshi, Vivekanandhan Thiruvettipuram Madhivanan

Принадлежит: General Electric Co

According to one aspect of the invention, a turbine assembly is provided, wherein the turbine assembly includes a drum rotor comprising a slot and a closure bucket configured to be placed in the slot, the closure bucket including a lock pin disposed in a base member of the closure bucket. In addition, a portion of the lock pin is configured to rotatably extend into a cavity in the slot thereby securing the closure bucket within the slot.

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Номер записи: 31

17-05-2012 дата публикации

Gas turbine engine with pylon mounted accessory drive

Номер: US20120117940A1

Автор: Michael Winter

Принадлежит: United Technologies Corp

A gas turbine engine includes an accessory gearbox within an engine pylon. The accessory components may be mounted within the engine pylon to save weight and space within the core nacelle as well as provide a relatively lower temperature operating environment.

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Номер записи: 32

24-05-2012 дата публикации

Bladed disk assembly

Номер: US20120128498A1

Автор: Matthew Peter Basiletti, Michelle Lynn Tucker, Richard Christopher Uskert

Принадлежит: Rolls Royce Corp

A bladed disk assembly is disclosed herein. The bladed disk assembly includes a disk centered on an axis. The disk has at least one groove extending along the axis. The bladed disk assembly also includes a blade received in the groove. The bladed disk assembly also includes a retaining clip contacting the blade and limiting movement of the blade along the axis. The retaining clip is engaged with the disk through a snap-fit.

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Номер записи: 33

31-05-2012 дата публикации

Gas turbine of the axial flow type

Номер: US20120134779A1

Автор: Alexander Anatolievich Khanin, Valery Kostege

Принадлежит: Individual

In an axial flow gas turbine ( 30 ), a reduction in cooling air mass flow and leakage in combination with an improved cooling and effective thermal protection of critical parts within the turbine stages of the turbine is achieved by providing, within a turbine stage (TS), devices ( 43 - 48 ) to direct cooling air that has already been used to cool, especially the airfoils of the vanes ( 31 ) of the turbine stage (TS), into a first cavity ( 41 ) located between the outer blade platforms ( 34 ) and the opposed stator heat shields ( 36 ) for protecting the stator heat shields ( 36 ) against the hot gas and for cooling the outer blade platforms ( 34 ).

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Номер записи: 34

31-05-2012 дата публикации

Fluid Turbine Having Optimized Blade Pitch Profiles

Номер: US20120134820A1

Автор: Jason Daniel Cormey, Robert Clifton Vance

Принадлежит: Broadstar Investment Co LLC, Broadstar Wind Systems Group LLC

A fluid turbine comprising a rotor, having an axis of rotation, comprising at least two rotor blades disposed at a radius from the axis of rotation, each rotor blade having a pitch axis and a variable pitch angle. The fluid turbine comprises a mechanism operable to control the pitch angle of at least one rotor blade about its pitch axis and to vary the pitch angle of the rotor blade between various pitch angles as the blade moves radially about the axis of rotation of the rotor.

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Номер записи: 35

31-05-2012 дата публикации

method of manufacturing a component

Номер: US20120135198A1

Автор: Oliver M. Strother

Принадлежит: Rolls Royce PLC

A method of manufacturing a component having first and second layers, the first and/or second layers including one or more depressions provided on a surface of the respective layer. The method including: arranging the first and second layers so that they face one another and with the depressions on inner facing surfaces of the layers; diffusion bonding the first and second layers together about their edges; applying a first differential pressure across each of the first and second layers to evacuate an inner space defined by the layers, thereby forming one or more depressions on an outer facing surface of the first or second layer; and applying a second differential pressure across each of the first and second layers to expand the inner space defined by the layers.

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Номер записи: 36

07-06-2012 дата публикации

Fluid impingement arrangement

Номер: US20120137650A1

Автор: Andrew J. Mullender, Brian A. Handley, Christopher T.J. SHEAF, David Macmanus, Zahid M. Hussain

Принадлежит: Rolls Royce PLC

A fluid impingement arrangement comprising a supply manifold and at least one nozzle exit coupled to the supply manifold. The nozzle exit is arranged as a Coanda surface having a restriction and has at least one static pressure tapping that cross-connects two regions of the restriction to induce passive oscillation in a fluid jet passing through the nozzle exit.

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Номер записи: 37

14-06-2012 дата публикации

Passive air-fuel mixing prechamber

Номер: US20120144832A1

Автор: Fengfeng Tao, Giridhar Jothiprasad, Grover Andrew Bennett, John Thomas Herbon, Matthew Patrick Boespflug

Принадлежит: General Electric Co

A gas turbine combustion system passive air-fuel mixing prechamber includes one or more fuel passages. Each fuel passage includes at least one downstream fuel injection orifice. One or more fluid conduits connect an upstream portion of at least one fuel passage with one or more air passages such that pressure drops across each fuel injection orifice substantially self-equalize in a passive manner with corresponding air passage pressure drops over a broad range of fuel lower heating value (LHV) from about 150 Btu/scf to about 900 Btu/scf of fuel passing through the fuel passage while mixing with air passing through one or more connected fluid conduits. The effective area of each fluid conduit relative to the corresponding fuel and air passages is dependent upon the desired fuel LHV operating range.

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Номер записи: 38

14-06-2012 дата публикации

Gas turbine engine and cooling system

Номер: US20120144843A1

Автор: Eric Sean Donovan, Steven Wesley Tomlinson, William Daniel Feltz

Принадлежит: Rolls Royce North American Technologies Inc

One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique cooling system for a gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for cooling one or more objects of cooling. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

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Номер записи: 39

14-06-2012 дата публикации

Gas turbine engine control using acoustic pyrometry

Номер: US20120150413A1

Автор: Richard H. Bunce, Upul P. Desilva

Принадлежит: Individual

A method and apparatus for operating a gas turbine engine including determining a temperature of a working gas at a predetermined axial location within the engine. Acoustic signals are transmitted from a plurality of acoustic transmitters and are received at a plurality of acoustic receivers. Each acoustic signal defines a distinct line-of-sound path from one of the acoustic transmitters to an acoustic receiver corresponding to the line-of-sound path. A time-of-flight is determined for each of the signals traveling along the line-of-sound paths, and the time-of-flight for each of the signals is processed to determine a temperature in a region of the predetermined axial location.

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Номер записи: 40

21-06-2012 дата публикации

Hot gas path component cooling for hybrid pulse detonation combustion systems

Номер: US20120151896A1

Автор: Adam Rasheed, Brian Gene Brzek, Douglas Carl Hofer, Fuhua Ma, Narendra Digamber Joshi, Thomas Michael Lavertu, Venkat Eswarlu Tangirala

Принадлежит: General Electric Co

The flow through the core of a hybrid pulse detonation combustion system is passed through a compressor and then separated into a primary flow, that passes directly to the combustor, and a bypass flow, which is routed to a portion of the system to be used to cool components of the system. The bypass flow is routed to a nozzle of the pulse detonation combustor. The flow is then passed back into the primary flow through the core downstream of where it was extracted.

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Номер записи: 41

21-06-2012 дата публикации

Thermal Inspection and Machining Systems and Methods of Use

Номер: US20120154570A1

Автор: Jared Crosby, Jason Randolph Allen, Ronald Scott Bunker

Принадлежит: General Electric Co

The present application provides a thermal imaging and machining system for a machine component. The thermal imaging and machining system may include a machining subsystem with a machining device for drilling one or more holes in the machine component and a thermal inspection subsystem positioned about the machining subsystem. The thermal inspection subsystem may include an imager and one or more fluid supply lines such that a thermal response of the holes in the machine component may be determined.

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Номер записи: 42

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: 43

28-06-2012 дата публикации

Gearbox assembly

Номер: US20120159966A1

Автор: Brian D. Merry, Christopher M. Dye, Gabriel L. Suciu

Принадлежит: United Technologies Corp

An assembly for a gas turbine engine includes an intermediate case and a gearbox. The intermediate case defines an annular transition duct. The gearbox comprises a plurality of lobes and is integrally formed with the annular transition duct.

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Номер записи: 44

28-06-2012 дата публикации

Structure for gas turbine casing

Номер: US20120163963A1

Автор: Shinya Hashimoto, Yukihiro Hashimoto

Принадлежит: Mitsubishi Heavy Industries Ltd

A structure for a gas turbine casing, capable of preventing gas from leaking when the structure is subjected to pressure. A structure for a gas turbine casing, divided by a horizontal plane at flange sections into two halves comprising an upper-half casing ( 10 ) and a lower-half casing ( 11 ). The structure is provided with bolts ( 12 ) which are disposed in the inner surfaces of the upper-half casing ( 10 ) and the lower-half casing ( 11 ) so as to bridge therebetween, upper nuts ( 13 ) which are disposed in the inner surface of the upper-half casing ( 10 ) and attached to the bolts ( 12 ), and lower nuts ( 14 ) which are disposed in the inner surface of the lower-half casing ( 11 ) and attached to the bolts ( 12 ).

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Номер записи: 45

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: 46

05-07-2012 дата публикации

Noise attenuation panel and a gas turbine component comprising a noise attenuation panel

Номер: US20120168248A1

Автор: Lars-Erik Eriksson, Markus Olander Burak

Принадлежит: Volvo Aero Corp

A noise attenuation panel includes a first wall, a second wall and partition walls connected to the first and second walls and defining cells between the first and second walls. The first wall is provided with a plurality of through holes. At least two of the cells are interconnected via a communication hole. One of the through holes leads to a first of the at least two interconnected cells and a second of the interconnected cells is configured to prevent any gas flow through the second cell.

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Номер записи: 47

05-07-2012 дата публикации

Anti-rotation for thrust washers in planetary gear system

Номер: US20120171017A1

Автор: Bradley A. Delmore, Dean A. Norem, Jeff A. Brown, Tye L. Klipp, William C. Trommer

Принадлежит: Hamilton Sundstrand Corp

A bushing for use in a planetary gear system has a cylindrical body portion defining a bore extending along a central axis to be received on a planetary gear shaft. A tab extends axially beyond a nominal body portion of the bushing and is received in a notch in a thrust washer adjacent to the bushing to prevent rotation of the thrust washer. A gear cage and an air turbine starter incorporating the bushing, along with a method of installing the bushing are also disclosed.

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Номер записи: 48

12-07-2012 дата публикации

Runner for circumferential seals

Номер: US20120177486A1

Автор: Jonathan Logan Miller, Leslie Charles Kurz, M. Rifat Ullah

Принадлежит: Individual

A runner assembly for a circumferential seal assembly includes a runner having an inwardly extending runner mounting flange, a flexible mounting structure and a retainer assembly therefore.

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Номер записи: 49

12-07-2012 дата публикации

Gas Turbine Nozzle Arrangement and Gas Turbine

Номер: US20120177489A1

Автор: Stephen Batt

Принадлежит: SIEMENS AG

A sealing element is provided for sealing a leak path between a radial outer platform of a turbine nozzle and a carrier ring for carrying said radial outer platform. The carrier ring has an axially facing carrier ring surface and the radial outer platform has an axially facing platform surface. The carrier ring surface forms a first sealing surface and the platform surface forming a second sealing surface. The first and second sealing surfaces is aligned in a plane with a radial gap between them. The sealing element includes a leaf seal adapted to cover the gap between the first and second sealing surfaces, and an impingement plate for allowing impingement cooling of a radial outer surface of the radial outer platform. The impingement plate is adapted to be fixed to the turbine nozzle. The sealing element may be part of a nozzle arrangement of a gas turbine.

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Номер записи: 50

19-07-2012 дата публикации

Cooled gas turbine engine member

Номер: US20120183386A1

Автор: Mark Owen Caswell

Принадлежит: Rolls Royce North American Technologies Inc

A gas turbine engine is disclosed having a vane disposed in a flow path of a gas turbine engine component, for example a gas turbine engine compressor. The vane is in thermal contact with a heat tube that extends through a wall of the engine component and into a space in which a thermal fluid passes. The thermal fluid can be at a different temperature than the vane such that heat is transferred between the two. In one embodiment the vane forms part of an intercooler for a compressor of the gas turbine engine. The vane can have a fin disposed at the end of the heat tube to facilitate a heat transfer.

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Номер записи: 51

02-08-2012 дата публикации

Turbine engine thermal imaging system

Номер: US20120194667A1

Автор: Anusha Rammohan, Ayan Banerjee, Rajagopalan Chandrasekharan, Sandip Maity, Sheri George

Принадлежит: General Electric Co

In one embodiment, a system includes an imaging system configured to capture a first image of a rotating component within an interior of a turbine using a first integration time, to capture a second image of the rotating component within the interior of the turbine using a second integration time, different than the first integration time, and to subtract the first image from the second image to obtain a differential image.

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Номер записи: 52

02-08-2012 дата публикации

Gas turbine engine

Номер: US20120195737A1

Автор: David Butler

Принадлежит: SIEMENS AG

A gas turbine engine including a segment of an annular guide vane assembly is provided. When the engine is used, the segment directs hot combustion gases onto rotor blades of the engine. The segment includes a platform disposed at a side of the segment radially inward/outward with respect to the axis of rotation of the engine. The platform has a trailing edge portion downstream with respect to the flow of hot combustion gases through the segment, the trailing edge portion includes a rail that extends radially inwardly/outwardly from the trailing edge portion. The engine also includes a support and cooling arrangement for supporting the segment and directing a cooling fluid to cool the segment. The arrangement is located radially inward/outward of the platform, and includes a flange part that extends radially outwardly/inwardly from the arrangement. The arrangement further includes a leaf seal and a retaining pin.

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Номер записи: 53

02-08-2012 дата публикации

compressor nozzle stage for a turbine engine

Номер: US20120195745A1

Автор: Patrick Edmond Kapala

Принадлежит: SNECMA SAS

A single-piece compressor nozzle stage for a turbine engine, the stage comprising two coaxial rings, connected together by radial vanes, the inner ring including an annular cavity for housing damper means for damping vibration by friction, which damper means are secured to an annular abradable-material support.

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Номер записи: 54

09-08-2012 дата публикации

Method and apparatus for cooling combustor liner in combustor

Номер: US20120198855A1

Автор: David William Cihlar, Patrick Benedict MELTON

Принадлежит: General Electric Co

A method and apparatus for cooling a combustor liner in a combustor are disclosed. In one embodiment, a combustor is disclosed. The combustor includes a transition piece, and an impingement sleeve at least partially surrounding the transition piece and at least partially defining a generally annular flow path therebetween. The combustor further includes an injection sleeve mounted to one of the transition piece or the impingement sleeve and positioned radially outward of the impingement sleeve, the injection sleeve at least partially defining a flow channel configured to flow working fluid to the flow path. In another embodiment, a method for cooling a combustor liner in a combustor is disclosed. The method includes flowing a working fluid through a flow channel at least partially defined by an injection sleeve, and exhausting the working fluid from the flow channel into a flow path adjacent the combustor liner.

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Номер записи: 55

09-08-2012 дата публикации

Ring element and turbomachine having such a ring element

Номер: US20120198858A1

Автор: Franz-Dieter SCHMIDT, Johannes Rabe, Wilfried Schuette

Принадлежит: MTU AERO ENGINES GMBH

A ring element for a turbomachine, in particular for an aircraft gas turbine, is disclosed. The ring element has a ring element main body that has two adjacently arranged ring ends, the ring ends being connected to one another in a form-locking manner with respect to an axial plane. Also disclosed is a turbomachine having at least one such ring element.

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Номер записи: 56

16-08-2012 дата публикации

Cooling system having reduced mass pin fins for components in a gas turbine engine

Номер: US20120207591A1

Автор: Ching-Pang Lee, John J. Marra, Nan Jiang

Принадлежит: Siemens Energy Inc

A cooling system having one or more pin fins with reduced mass for a gas turbine engine is disclosed. The cooling system may include one or more first surfaces defining at least a portion of the cooling system. The pin fin may extend from the surface defining the cooling system and may have a noncircular cross-section taken generally parallel to the surface and at least part of an outer surface of the cross-section forms at least a quartercircle. A downstream side of the pin fin may have a cavity to reduce mass, thereby creating a more efficient turbine airfoil.

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Номер записи: 57

30-08-2012 дата публикации

System for measuring parameters of fluid flow in turbomachinery

Номер: US20120216608A1

Автор: Dan M. Hudson, Kurt K. Schleif

Принадлежит: General Electric Co

A system, including, a boundary layer rake, including a rake body, a coolant path extending through the rake body, and a first probe coupled to the rake body, wherein the first probe is configured to measure a first parameter of a first boundary layer flow along a first wall.

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Номер записи: 58

30-08-2012 дата публикации

Improved bearing system

Номер: US20120219245A1

Автор: Robert D. Mckeirnan, Jr.

Принадлежит: Mckeirnan Jr Robert D

The improved bearing system includes a pair of axially split and generally cylindrical cartridges having respective bearing units configured to be mountable to a common axial shaft. An annular channel is generally formed from one of the cartridges for selectively receiving a preload ring. An annular groove is formed from a portion of the other cartridge and sized to slidably receive the preload ring. A preload element is disposed within the annular groove and axially compressed between a preload surface of the annular groove and the preload ring. The preload element maintains a simultaneous axial preload thrust on the bearing cartridges and respective bearing units in inwardly opposite axial directions.

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Номер записи: 59

30-08-2012 дата публикации

Stationary vane unit of rotary machine, method of producing the same, and method of connecting the same

Номер: US20120219412A1

Автор: Takeki NAKAYAMA, Yuki Yamamoto

Принадлежит: Individual

The stationary vane unit of a rotary machine includes: a first band member that extends in the circumferential direction and comes into contact with the outer shrouds of the plurality of stationary vane members from one side thereof in the main axial direction in which a central axis extends; a second band member that extends in the circumferential direction and comes into contact with the outer shrouds of the plurality of stationary vane members from the other side thereof in the main axial direction; and a fastening member that fastens the first band member and the second band member to each other so that the outer shrouds of the plurality of stationary vane members are connected to each other.

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Номер записи: 60

30-08-2012 дата публикации

Prediction of maintenance operations on an aircraft engine

Номер: US20120221193A1

Автор: Eric Gendronneau, Guillaume Delaye, Jean-Philippe Autier

Принадлежит: SNECMA SAS

The invention relates to a method and a system for predicting maintenance operations on a current aircraft engine, comprising: processing means to compare a set of failure models (M 1, . . . , Mn) adapted to said current engine to select a relevant failure model (Mi) with a failure age (T 0 ) defining the age of said engine at the time of the failure; processing means to associate decision rules (R) about the workscope on said current engine with said relevant failure model (Mi), as a function of a set of parameters (P 1, P 2, Pi) related to said current engine; and processing means to determine the required maintenance workscope (Wf) to be applied to said current engine, as a function of said decision rules.

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Номер записи: 61

06-09-2012 дата публикации

Turbine drive-train apparatus

Номер: US20120225750A1

Автор: Brian Allen Rittenhouse, Daniel Richard Waugh, Jason Dean Fuller, Justin Aaron Allen, Karl Dean Minto

Принадлежит: General Electric Co

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

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Номер записи: 62

13-09-2012 дата публикации

Combustion chamber having a ventilated spark plug

Номер: US20120227373A1

Автор: Guillaume Sevi, Jacques Marcel Arthur Bunel, Mario César De Sousa

Принадлежит: SNECMA SAS

A combustion chamber of a gas turbine engine including a wall, a well secured to the wall, the well forming a recess for a spark plug leading into the combustion chamber, and a spark-plug guide mounted on the well to be transversally mobile relative to the axis of the well, the spark-plug guide including a cylindrical wall portion for guiding and supporting the spark plug and a seal ring mounted such as to engage slidably with a bearing surface of the well. In the combustion chamber the spark-plug guide includes a cooling chamber having openings for supplying cooling air to the chamber.

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Номер записи: 63

27-09-2012 дата публикации

Turbine shell with pin support

Номер: US20120243976A1

Автор: Fred Thomas Willett, JR., Henry Grady Ballard, JR.

Принадлежит: General Electric Co

A turbine is provided and includes a turbine shell including shrouds at multiple stages thereof, and constraining elements, disposed at least at first through fourth substantially regularly spaced perimetrical locations around the turbine shell, which are configured to concentrically constrain the shrouds of the turbine shell.

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Номер записи: 64

04-10-2012 дата публикации

Turbine combustion system cooling scoop

Номер: US20120247112A1

Автор: Andrew R. Narcus, Matthew Gent, Neal THERRIEN

Принадлежит: Siemens Energy Inc

A scoop ( 54 ) over a coolant inlet hole ( 48 ) in an outer wall ( 40 B) of a double-walled tubular structure ( 40 A, 40 B) of a gas turbine engine component ( 26, 28 ). The scoop redirects a coolant flow ( 37 ) into the hole. The leading edge ( 56, 58 ) of the scoop has a central projection ( 56 ) or tongue that overhangs the coolant inlet hole, and a curved undercut ( 58 ) on each side of the tongue between the tongue and a generally C-shaped or generally U-shaped attachment base ( 53 ) of the scoop. A partial scoop ( 62 ) may be cooperatively positioned with the scoop ( 54 ).

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Номер записи: 65

04-10-2012 дата публикации

System and method for air extraction from gas turbine engines

Номер: US20120247113A1

Автор: Michael Joseph Alexander, Paul William Plummer, Timothy Lee Janssen, Vijay Anand Raghavendran Nenmeni

Принадлежит: General Electric Co

The disclosed embodiments relate to a system and method that allows air to be extracted from a plurality of gas turbine engines and fed to a downstream process, even in situations in which one or more of the gas turbine engines are operating in a part load condition. For example, in an embodiment, a method includes monitoring signals representative of a header pressure of a header, or a pressure of extraction air flow from one or more gas turbine engines to the header, or both, and maintaining substantially continuous flows of extraction air from the gas turbine engines to the header. The substantially continuous flows are maintained when the gas turbine engines are under symmetric and asymmetric load conditions.

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Номер записи: 66

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: 67

04-10-2012 дата публикации

Supporting structure for thrust reverser, in particular having cascades

Номер: US20120248284A1

Автор: Alexandre Bellanger, Florent Bouillon, Laurent Dubois

Принадлежит: Aircelle SA

The present invention relates to a supporting structure ( 200 ) for a nacelle of a jet engine, in particular provided with a thrust reverser device, including at least one base body ( 201 ) made of a composite material, characterised in that the base body has a transverse section which is essentially open and provided with at least one reinforcement means.

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Номер записи: 68

18-10-2012 дата публикации

Variable pitch fan having a pitch sensor

Номер: US20120263593A1

Автор: Andrew L. Norell, George Antoszko, Jonathan E. Mccallum, Mariusz Kloza

Принадлежит: Flexxaire Inc

A compact variable pitch fan has a drive fluid pitch change mechanism. A pitch change piston is constrained to follow reciprocating motion under drive fluid control within a peripheral hub from which fan blades extend outward. A pitch change sensor is mounted with the rotary union.

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Номер записи: 69

25-10-2012 дата публикации

System and method for removing heat from a turbomachine

Номер: US20120266601A1

Автор: Harold Edward Miller

Принадлежит: General Electric Co

The present invention provides systems and methods of removing heat from internal areas of a turbomachine. Embodiments of the present invention may incorporate a suction device and a control system. Operatively, these elements may collectively discharge remnants of a heated fluid and/or gas from those internal areas.

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Номер записи: 70

25-10-2012 дата публикации

Turbine wheel for a turbine engine

Номер: US20120269650A1

Автор: Emmanuel Berche, Jean-Luc Bacha, Tangi Brusq

Принадлежит: SNECMA SAS

A turbine wheel for a turbine engine, comprising a disk carrying blades, each having a platform carrying an airfoil and connected by a tang to a root, and sealing and damping sheets housed in the inter-tang spaces, the platforms including projections on their radially internal faces against which the sheets bear radially in operation, in order to define radial clearance and create at least one space between the sheets and the platforms, and the sheets including holes for feeding air to the or each space.

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Номер записи: 71

01-11-2012 дата публикации

Automated tuning of gas turbine combustion systems

Номер: US20120275899A1

Автор: Christopher Chandler

Принадлежит: Gas Turbine Efficiency Sweden AB

The present disclosure provides a tuning system for tuning the operation of a gas turbine. The system comprises operational turbine controls for controlling operational control elements of the turbine, including at least one of turbine fuel distribution or the fuel temperature. The system also has a tuning controller communicating with the turbine controls. The tuning controller is configured to tune the operation of the turbine in accordance with the following steps: receiving operational data about the turbine, providing a hierarchy of tuning issues, determining whether sensed operational data is within predetermined operational limits and producing one or more indicators. If the operational data is not within predetermined operational limits, the tuning controller will rank the one or more indicators to determine dominant tuning concern, and tune the operation of the turbine based on dominant tuning concern. Also provided herein are a method and computer readable medium for tuning.

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Номер записи: 72

01-11-2012 дата публикации

Modular fan housing with multiple modular units having sound attenuation for a fan array for an air-handling system

Номер: US20120275902A1

Автор: Lawrence G. Hopkins

Принадлежит: Huntair Inc

A modular fan housing configured to hold an array of motors and fans is provided. The modular fan housing is configured for use in an air-handling system that delivers air to a ventilation system for at least a portion of a building. The fan housing comprises a plurality of modular units configured to be stacked adjacent to one another in at least one row or column to form an array. The modular units each include an interior surface and have a front end and a back end that define a chamber. The chambers are configured to receive the motors and fans. Sound attenuation layers extend along at least a portion of the interior surface of the corresponding chambers. The sound attenuation layers are positioned between at least some of the adjacent chambers.

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Номер записи: 73

15-11-2012 дата публикации

Rotor with asymmetric blade spacing

Номер: US20120288373A1

Автор: Anthony C. Jones, Benjamin E. Fishler, Bo Zheng, GAO Yang, James C. Napier, Jay M. Francisco, Loc Quang Duong, Nagamany Thayalakhandan, Xiaolan Hu

Принадлежит: Hamilton Sundstrand Corp

A turbine apparatus comprises a rotor with a hub section defined about a rotational axis and a plurality of blades attached to the hub section. The plurality of blades comprises a first group having a first angular spacing in a first circumferential sector of the rotor, and a second group having a second angular spacing in a second circumferential sector of the rotor. The first angular spacing is different from the second angular spacing, and the rotor blades are asymmetric about the rotational axis.

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Номер записи: 74

13-12-2012 дата публикации

Gas turbine systems involving rotor bayonet coverplates and tools for installing such coverplates

Номер: US20120311835A1

Автор: Daniel J. Griffin, Joseph T. Caprario

Принадлежит: United Technologies Corp

Gas turbine engine systems involving rotor bayonet coverplates and tools for installing such coverplates are provided. In this regard, a representative turbine assembly for a gas turbine engine includes: a turbine disk operative to mount a set of turbine blades; and a coverplate having an annular main body portion and a spaced annular arrangement of tabs extending radially inwardly from the main body portion with open-ended gaps being located between the tabs, the tabs being operative to secure an inner diameter of the coverplate to the turbine disk.

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Номер записи: 75

13-12-2012 дата публикации

Inspection device and method for positioning an inspection device

Номер: US20120312103A1

Автор: Harm Speicher, Kai WÖSTMANN, Kerstin Hannott, Margarete Neuhaus

Принадлежит: SIEMENS AG

An inspection device includes a distal area, a proximal area, and a flexible area disposed between the distal area and the proximal area. The flexible area includes a plurality of segments disposed displaceably to each other. At least one external guide element is disposed outside of the flexible area, between the distal area and the proximal area so that the distal area can be displaced with respect to the proximal area via the external guide element.

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Номер записи: 76

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: 77

20-12-2012 дата публикации

Plug assembly for blade outer air seal

Номер: US20120319360A1

Автор: Ken F. Blaney, Paul M. Lutjen

Принадлежит: Individual

A plug assembly includes a cup which defines a cup portion and a cup anti-liberation portion along an axis, a wedge is mountable within the cup portion to at least partially radially expand the cup anti-liberation portion.

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Номер записи: 78

27-12-2012 дата публикации

Radial staging method and configuration of a liquid injection system for power plants

Номер: US20120324904A1

Автор: Chris Pin Harry, Gabriel Taraboulsi, Walter Kasimierz Omielan

Принадлежит: Rolls Royce Power Engineering PLC

A turbine power plant employs a radial staging of a liquid injection system to provide a uniform fluid distribution, for use in wet compression. The liquid injection system can be actuated to inject liquid to various radial regions of an air intake case of the turbine power plant. During a stage one actuation, liquid is directed to a first radial region of the air intake case. During a stage two actuation, liquid is directed to the first radial region and also to a second radial region of the air intake case.

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Номер записи: 79

27-12-2012 дата публикации

Method For Balancing A Propulsive System Having Non-Hull Contra-Rotating Propellers

Номер: US20120328433A1

Автор: Esteban Quiroz-Hernandez

Принадлежит: AIRBUS OPERATIONS SAS

According to the invention, at least one of the counterweights ( 40, 40.1, 40.2, 40.3, 40.4 ) is mobile mounted on a guiding slot ( 24, 34 ) coaxial to the hub envelope ( 22, 32 ) that surrounds the hub ( 21, 31 ) of the corresponding propeller ( 2, 3 ), the movement of said mobile counterweight ( 40, 40.1, 40.2, 40., 40.4 ) along said guiding slot ( 24, 34 ) being controlled on the basis of an estimation of the possible unbalance of said propulsive system ( 1 ).

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Номер записи: 80

03-01-2013 дата публикации

Dual fan gas turbine engine and gear train

Номер: US20130004297A1

Автор: William G. Sheridan

Принадлежит: Individual

A gas turbine engine includes a first fan, a second fan spaced axially from the first fan, a turbine-driven fan shaft and an epicyclic gear train coupled to be driven by the turbine-driven fan shaft and coupled to drive the first fan and the second fan. The epicyclic gear train includes a carrier that supports star gears that mesh with a sun gear, and a ring gear that surrounds and meshes with the star gears. The star gears are supported on respective journal bearings.

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Номер записи: 81

10-01-2013 дата публикации

Efficient, low pressure ratio propulsor for gas turbine engines

Номер: US20130008144A1

Автор: Anthony R. Bifulco, Becky E. Rose, Edward J. Gallagher, Jason Elliott, Jun Jiang

Принадлежит: Individual

A gas turbine engine includes a spool, a turbine coupled to drive the spool and a propulsor that is coupled to be driven by the turbine through the spool. A gear assembly is coupled between the propulsor and the spool such that rotation of the spool drives the propulsor at a different speed than the spool. The propulsor includes a hub and a row of propulsor blades that extends from the hub. The row includes no more than 16 of the propulsor blades.

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Номер записи: 82

10-01-2013 дата публикации

Turbomachine combustion chamber having a centrifugal compressor with no deflector

Номер: US20130008166A1

Автор: Thierry Cortes

Принадлежит: SNECMA SAS

An annular combustion chamber for a turbomachine, including an external wall and an internal wall which are oriented substantially axially relative to the rotation axis of the turbomachine, the combustion chamber being closed upstream by a chamber end wall oriented substantially radially, the chamber being supplied with compressed air coming from a compressor via a nozzle, the output direction of which is offset radially relative to the mid-axis of the combustion chamber, the chamber end wall including cooling air supply holes inclined to the direction normal to the chamber end wall. The number of holes oriented radially in the direction opposite to that where the outlet of the nozzle is located is greater than the number of holes oriented radially in the direction of the outlet of the nozzle.

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Номер записи: 83

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: 84

31-01-2013 дата публикации

Three spool engine bearing configuration

Номер: US20130025257A1

Автор: Brian D. Merry, Gabriel L. Suciu

Принадлежит: Individual

A disclosed gas turbine engine includes a core section having a low spool, intermediate spool and a high spool that rotate about a common axis. The intermediate spool is supported at an aft position by an inter-shaft bearing arrangement on the low spool. The low spool is supported for rotation in an aft position by an aft roller bearing supported on a turbine exhaust case of the gas turbine engine. The high spool is supported by a high spool aft roller bearing disposed within a high spool bearing compartment. The high spool bearing compartment is positioned within a radial space between the combustor and the axis.

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Номер записи: 85

31-01-2013 дата публикации

Method and device for adjusting an end position of a turbine for a charging device having a variable turbine geometry

Номер: US20130025275A1

Автор: Markus Deissler, Michael Baeuerle, Michael Nau

Принадлежит: ROBERT BOSCH GMBH

In a method for adjusting an end position of guide vanes in a turbine of a charging device in an engine system, the guide vanes are adjusted with the aid of an actuator, the end position depending on a position at a structurally determined end stop, and corresponding to a position of the guide vanes of the turbine at a predetermined gas flow rate. The actuator is activated for adjusting the guide vanes to the end position using a predetermined position value, which holds the guide vanes in the end position.

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Номер записи: 86

31-01-2013 дата публикации

Gear train lubricating device

Номер: US20130025405A1

Автор: Hidenori Arisawa, Hideyuki Imai, Motohiko Nishimura, Tatsuhiko Goi

Принадлежит: Kawasaki Jukogyo KK

A gear train lubricating device configured to supply lubricating oil OL to a gear included in a gear train is provided. The gear train lubricating device includes: a shroud covering, among components constituting the gear, at least teeth of the gear; and a lubricating oil supply port through which the lubricating oil OL is supplied to a meshing position of the gear. The shroud has an outlet port formed therein, through which the supplied lubricating oil OL is discharged. The outlet port is formed in a portion of the shroud that is positioned radially outward from the gear, such that the outlet port is disposed at an angular position that is 90°±15° forward from the meshing position in a rotation direction R 1 of the gear.

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Номер записи: 87

31-01-2013 дата публикации

Acoustic Array of Polymer Material

Номер: US20130025967A1

Автор: David C. Seib

Принадлежит: Dresser Rand Co

The invention is an acoustic liner for attenuating noise in rotating machinery. The acoustic liner may include a plurality of cells coupled together to form an annular cell matrix, the plurality of cells being made of a non-metallic material, for example, plastics, polymers, thermoplastics, or thermosets. Each cell of the acoustic liner may be hexagonally-shaped such that the annular cell matrix forms a honeycomb structure.

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Номер записи: 88

31-01-2013 дата публикации

Method for injecting water into a multistage axial compressor of a gas turbine

Номер: US20130028707A1

Автор: Erik Boldt, Luis Puerta, Marco Micheli, Wolfgang Kappis

Принадлежит: Alstom Technology AG

A method is disclosed for injecting water into a multistage axial compressor of a gas turbine. With low equipment cost, a significant power enhancement can be achieved, even under changing boundary conditions, by water being injected at a plurality of points along the axial compressor, and by the injected water mass flow being controlled at the individual injection points in accordance with ambient conditions and operating parameters of the gas turbine in such a way that an evened-out loading in the individual stages of the axial compressor can be created.

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Номер записи: 89

07-02-2013 дата публикации

Segmented seal assembly

Номер: US20130034428A1

Автор: Bernard Arthur Couture, Jr., Daniel Edward Jordy, Dexter Andrew Young, William Edward Adis

Принадлежит: General Electric Co

Systems and devices for sealing portions of a rotary machine are disclosed. In one embodiment, a seal assembly element includes: a head flange; an axial neck connected to the head flange, wherein the axial neck includes a mating flange extending circumferentially from a distal end of the seal assembly element, the mating flange configured to form a multidirectional seal with a recessed portion of a complementary seal assembly element; and a set of axial seal teeth connected to the axial neck.

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Номер записи: 90

14-02-2013 дата публикации

Variable vane actuation system and method

Номер: US20130039735A1

Автор: Andy Eifert

Принадлежит: Rolls Royce Corp

A variable vane actuation system and method is disclosed herein. The variable vane actuation system includes a first ring member disposed for pivoting movement about a centerline axis. The first ring member is operably connected with at least one vane such that the at least one vane pivots in response to the pivoting movement of the first ring member. The variable vane actuation system also includes a first pin engaged with the first ring member. The variable vane actuation system also includes a ring moving device operably engaged with the first pin to move the first ring member about the centerline axis. The ring moving device includes at least one plate having a first slot and an actuator operable to move the at least one plate. The first pin is received in the first slot and is a cam follower to a cam defined at least in part by a surface of the first slot.

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Номер записи: 91

21-02-2013 дата публикации

Turbine blade cooling system with bifurcated mid-chord cooling chamber

Номер: US20130045111A1

Автор: Ching-Pang Lee

Принадлежит: Siemens Energy Inc

A cooling system for a turbine blade of a turbine engine having a bifurcated mid-chord cooling chamber for reducing the temperature of the blade. The bifurcated mid-chord cooling chamber may be formed from a pressure side serpentine cooling channel and a suction side serpentine cooling channel with cooling fluids passing through the pressure side serpentine cooling channel in a direction from the trailing edge toward the leading edge and in an opposite direction through the suction side serpentine cooling channel. The pressure side and suction side serpentine cooling channels may flow counter to each other, thereby yielding a more uniform temperature distribution than conventional serpentine cooling channels.

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Номер записи: 92

28-02-2013 дата публикации

Turbocharger

Номер: US20130047605A1

Автор: Hans H. Drangel, Lorenzo Magro, Luca Trabucchi

Принадлежит: GM GLOBAL TECHNOLOGY OPERATIONS LLC

A turbocharger for an internal combustion engine, comprising a bearing housing, a rotating shaft coupled to the bearing housing, a compressor wheel mounted at one end of the rotating shaft, a compressor housing accommodating the compressor wheel and provided with an inlet and an outlet for an air stream, a turbine wheel mounted at the opposite end of the rotating shaft, and a turbine housing accommodating the turbine wheel and provided with an inlet and an outlet for an exhaust gas stream, wherein the bearing housing comprises a fastening flange suitable to be fixed to a component of the internal combustion engine, wherein the turbine housing is provided with a connecting pipe for fluidly connecting the turbine housing inlet with an exhaust manifold of the internal combustion engine, and wherein the connecting pipe includes means for compensating axial thermal deformations thereof.

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Номер записи: 93

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: 94

28-02-2013 дата публикации

Turbine shroud segment

Номер: US20130052007A1

Автор: Eric Durocher, Guy Lefebvre

Принадлежит: Pratt and Whitney Canada Corp

A turbine shroud segment is metal injection molded (MIM) about a core to provide a composite structure. In one aspect, the core is held in position in an injection mold and then the MIM material is injected in the mold to form the body of the shroud segment about the core. Any suitable combination of materials can be used for the core and the MIM shroud body, each material selected for its own characteristics. The core may be imbedded in the shroud platform to provide a multilayered reinforced platform, which may offer resistance against crack propagation.

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Номер записи: 95

28-02-2013 дата публикации

Pin-fin array

Номер: US20130052036A1

Автор: Aaron Ezekiel Smith

Принадлежит: General Electric Co

The present application provides an airfoil with a cooling flow therein. The airfoil may include an internal cooling passage, a number of cooling holes in communication with the internal cooling passage, and a number of pin-fins positioned within the internal cooling passage. The pin-fins are arranged with one or more turning openings and one or more guiding openings so as to direct the cooling flow towards the cooling holes.

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Номер записи: 96

14-03-2013 дата публикации

Aerofoil assembly

Номер: US20130064661A1

Автор: Dale E. Evans, Ian C D Care

Принадлежит: Rolls Royce PLC

This invention relates to a stator aerofoil for a gas turbine engine, comprising: a body portion; at least one panel which forms at least part of one of either the pressure or section surface of the aerofoil; at least one internal chamber which is bounded by the body portion and panel; and, at least one elastomeric component within the at least one internal chamber, wherein the elastomeric component at least partially defines a cell within the internal chamber, wherein the cell is in fluid communication with the exterior of the aerofoil.

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Номер записи: 97

21-03-2013 дата публикации

System and method for detecting abnormal movement in a gas turbine shaft

Номер: US20130071230A1

Автор: Wojciech Konrad Kulczyk

Принадлежит: Weston Aerospace Ltd

A sensor element for use in a backing sensor to monitor a gas turbine shaft. The sensor includes an oscillator circuit 30 having an oscillator and a resonance circuit 42 , and a frequency detector 31 for monitoring the frequency of the ossilation circuit. Abnormal movement of the shaft cuts the circuit in the sensor along a cutting line ( 15 ). The cutting of the sensor changes the capacitance and/or inductance of the resonance circuit and thereby changes the frequency of oscillation.

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Номер записи: 98

21-03-2013 дата публикации

Wall structure with noise damping insulation properties and gas turbine with such a wall structure

Номер: US20130071231A1

Автор: Antun Svilicic, Eduard Bruhwiler, Marc Rauch, Mladen Matan

Принадлежит: Alstom Technology AG

A wall structure is provided with noise damping insulation properties, for an air intake manifold of a gas turbine. The wall structure includes a first structure for mechanically supporting an outer sheet, which separates the spaces on both sides of the wall in an airtight manner, and further includes a second structure for establishing noise damping insulation between the spaces on both sides of the wall. The second structure is secured to the first structure. A gas turbine including the wall structure is also provided.

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Номер записи: 99

21-03-2013 дата публикации

System and method for simulating a gas turbine compressor

Номер: US20130073170A1

Автор: John Benjamin Drohan, Randy Scott Rosson

Принадлежит: General Electric Co

A method for simulating a compressor of a gas turbine is disclosed. The method may generally include determining a predicted pressure ratio and a predicted mass flow of the compressor based on a model of the gas turbine, monitoring an actual pressure ratio and an actual mass flow of the compressor, determining difference values between at least one of the predicted pressure ratio and the actual pressure ratio and the predicted mass flow and the actual mass flow, modifying the difference values using an error correction system to generate a compressor flow modifier and using the compressor flow modifier to adjust the predicted pressure ratio and the predicted mass flow.

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Номер записи: 100