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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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Форма поиска

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 20656. Отображено 100.
17-10-2017 дата публикации

Маслостанция стационарной газотурбинной установки

Номер: RU0000174501U1

Маслостанция предназначена для снабжения маслом стационарной газотурбинной установки.Маслостанция выполнена на общей раме и/или каркасе с поддоном, содержит маслобак с электронагревателями, датчиками уровня и температуры, с трубопроводами слива, перелива и трубопроводом заправки маслобака, снабженным фильтром, маслобак имеет также трубопровод, связывающий маслостанцию с выходом воздушного маслоохладителя; трубопровод суфлирования, соединенный через статичный воздухоотделитель циклонного типа с маслобаком и с атмосферой; электрический масляный насос перемешивания масла в маслобаке; электрический масляный насос предварительной прокачки масла, обеспечивающий подачу масла смазки в подшипниковые узлы газотурбинной установки во время подготовки к запуску, запуска и выхода на режим газотурбинной установки; блок клапанов; блок выносных масляных фильтров, содержащий две параллельные взаимно резервирующие нитки фильтрации подаваемого в газотурбинный двигатель масла, каждая из которых имеет два взаимно резервирующих фильтра, содержащий также датчик разности давления; взаимно резервирующие друг друга фильтры тонкой очистки поступающего в маслобак из подшипниковых опор газотурбинного двигателя масла, снабженные датчиками перепада давления; трубопроводную обвязку с трубопроводной арматурой, обратными клапанами и приборами контроля и измерения. Маслостанция содержит средство межблочного соединения и позиционирования группы трубопроводов для внешнего подключения маслостанции, выполненное в виде пластины, предпочтительно металлической, жестко соединенной с рамой маслостанции, в которой жестко закреплены трубопроводы, снабженные разъемным соединением. Маслостанция выполнена таким образом, что все приборы контроля и измерения, трубопроводная арматура, обратные клапаны, блоки фильтров, требующие настройки, регулирования и обслуживания расположены с одной стороны маслостанции. В средстве удержания и позиционирования группы трубопроводов могут быть закреплены трубопроводы слива, перелива ...

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13-03-2018 дата публикации

Реактивный двигатель

Номер: RU0000177796U1

Реактивный двигатель содержит обтекаемый корпус, камеры сгорания, закрепленные за корпус, размещенную в корпусе электромагнитную подушку, состоящая из пустотелых цилиндров с электромагнитами статора, обратимую электромашину, состоящую из пустотелых цилиндров с электромагнитами статора и роторов. Полезная модель позволяет расширить возможности бортового или навесного электрооборудования, позволяющим применить для создания дополнительной тяги движители с электроприводами на реактивном двигателе или как бортовые движители с электроприводом на летательных аппаратах. 2 ил. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 177 796 U1 (51) МПК F02K 3/00 (2006.01) F01D 15/10 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ПОЛЕЗНОЙ МОДЕЛИ К ПАТЕНТУ (52) СПК F02K 3/00 (2018.01); F01D 15/10 (2018.01) (21)(22) Заявка: 2017121758, 20.06.2017 (24) Дата начала отсчета срока действия патента: (73) Патентообладатель(и): Шахов Борис Андреевич (RU) Дата регистрации: 13.03.2018 (56) Список документов, цитированных в отчете о поиске: RU 2014482 C2, 15.06.1994. US 2743375 A, 24.04.1956. EP 0305763 A1, 08.03.1989. GB 2288642 A, 25.10.1995. US 4253031A, 24.02.1981. US 5376827 A, 27.12.1994. (45) Опубликовано: 13.03.2018 Бюл. № 8 R U (54) РЕАКТИВНЫЙ ДВИГАТЕЛЬ (57) Реферат: Реактивный двигатель содержит обтекаемый корпус, камеры сгорания, закрепленные за корпус, размещенную в корпусе электромагнитную подушку, состоящая из пустотелых цилиндров с электромагнитами статора, обратимую электромашину, состоящую из пустотелых цилиндров с электромагнитами Стр.: 1 статора и роторов. Полезная модель позволяет расширить возможности бортового или навесного электрооборудования, позволяющим применить для создания дополнительной тяги движители с электроприводами на реактивном двигателе или как бортовые движители с электроприводом на летательных аппаратах. 2 ил. U 1 U 1 Адрес для переписки: 644023, г. Омск, ул. 25 Рабочая, 125, кв. 75, Шахову Б.А. 1 7 7 7 9 6 Приоритет(ы): (22) Дата подачи ...

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11-01-2019 дата публикации

Стенд для испытания асинхронных машин

Номер: RU0000186188U1

Полезная модель относится к области электротехники и может быть применена в качестве стенда для испытания асинхронных машин. Заявленный стенд отличается от известных тем, что дополнен задатчиком параметров, контактором, вычислителем частоты питающего напряжения, системой управления, датчиком тока, датчиком частоты вращения; выходы системы управления соединены с управляющими входами управляемых выпрямитель-инверторов и управляющим входом контактора, входы системы управления соединены с выходом задатчика параметров, выходом вычислителя частоты питающего напряжения, вход которого соединен с выходом управляемого инвертора; выходом датчика тока, вход которого соединен с выходом управляемого выпрямитель-инвертора; выходом датчика частоты вращения, соединенного с валами асинхронных машин; обмотка статора второй асинхронной машины подключается к сети через контактор. Техническим результатом при реализации заявленного решения является повышение надежности стенда за счет исключения возможности перегрузки испытуемой и нагрузочной машины в процессе их нагружения. 1 ил. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 186 188 U1 (51) МПК G01R 31/34 (2006.01) H02K 15/02 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ПОЛЕЗНОЙ МОДЕЛИ К ПАТЕНТУ (52) СПК G01R 31/34 (2018.08); H02K 15/02 (2018.08); F01D 15/10 (2018.08) (21)(22) Заявка: 2018133027, 17.09.2018 (24) Дата начала отсчета срока действия патента: (73) Патентообладатель(и): Федеральное государственное бюджетное образовательное учреждение высшего образования "Омский государственный университет путей сообщения" (RU) Дата регистрации: 11.01.2019 (56) Список документов, цитированных в отчете о поиске: RU 178539 U1, 06.04.2018. RU (45) Опубликовано: 11.01.2019 Бюл. № 2 1 8 6 1 8 8 R U (54) Стенд для испытания асинхронных машин (57) Реферат: Полезная модель относится к области электротехники и может быть применена в качестве стенда для испытания асинхронных машин. Заявленный стенд отличается от известных тем, ...

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02-10-2020 дата публикации

Задняя коробка привода агрегатов

Номер: RU0000200042U1
Принадлежит: ПАО "ОДК-Сатурн"

Полезная модель относится к области авиадвигателестроения и энергетического машиностроения, преимущественно к системам приводов вспомогательных агрегатов, обеспечивающих работу газотурбинного двигателя, и может быть использована для привода вспомогательных агрегатов газотурбинных двигателей с размещением приводных агрегатов с внешней стороны корпуса газотурбинного двигателя, имеющих частоты вращения, отличные от ротора турбокомпрессора.Техническим результатом, на достижение которого направлено данное техническое решение, является повышение надежности передачи крутящего момента, упрощение конструкции корпуса, а также снижения массы и габаритов коробки привода агрегатов за счет оптимизация схемы передачи крутящего момента, в результате сокращения количества валов, уменьшения количества зубчатых колес и подшипников, снижения тепловыделений в зубчатых зацеплениях и подшипниках.Технический результат достигается тем, что в задней коробке привода агрегатов, содержащей разъемный корпус, внутри которого размещены и связаны между собой зубчатые колеса приводов к агрегатам и датчикам, смонтированных снаружи корпуса, в число которых входят привод гидронасоса реверсивного устройства, привод насоса самолетного, привод датчика тахометра, привод топливного насоса, привод маслонасоса, привод центробежного суфлера, привод насоса регулятора и датчика приведенных оборотов, запасной привод, при этом передача вращения от центрального привода, размещенного в разделительном корпусе, к агрегатам и датчикам задней коробки осуществляется через переднюю коробку приводов посредством шлицевого валика, который вращает ведущее цилиндрическое зубчатое колесо, в отличие от известной, передача крутящего момента от ведущего цилиндрического зубчатого колеса осуществляется через промежуточное зубчатое колесо на центральную шестерню, которая обеспечивает его дальнейшую раздачу на ведущие зубчатые колеса привода топливного насоса, привода маслонасоса, привода датчика тахометра, от которого далее ...

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12-01-2012 дата публикации

Split flow valve arrangement

Номер: US20120006433A1
Автор: Antony Morgan
Принадлежит: Rolls Royce PLC

A split flow valve arrangement comprising a first valve portion having an inlet, a first outlet and a second outlet; and a second valve portion having a first inlet coupled to the first outlet, a second inlet coupled to the second outlet, a main outlet and a secondary outlet. The inlet is selectively coupled to none, one or both of the first and second outlets; the first inlet is selectively coupled to the main outlet and the second inlet is selectively coupled to the secondary outlet. The first and second valve portions are constrained to move in synchronicity to therefore selectively direct fluid to flow from the inlet to none, one or both of the main and secondary outlets.

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26-10-2021 дата публикации

Свеча зажигания газотурбинных промышленных установок

Номер: RU0000207379U1

Свеча зажигания для газотурбинного двигателя, содержащая основной трубчатый корпус с установленным в нем искрообразующим изолятором с полупроводниковым покрытием и внутренним каналом, в котором расположен центральный электрод, металлическую втулку, закрепленную в основном корпусе свечи и поджимающую искрообразующий изолятор к внутреннему торцу основного корпуса, образующего боковой электрод свечи, герметизирующий изолятор с ножками и внутренним каналом с закрепленным в нем в стеклогерметике токоведущим стержнем, установленный с упором в бурт дополнительного корпуса и закрепленный в нем медной клиновой втулкой, обращенной своим большим сечением в сторону искрообразующего изолятора, и стеклогерметизирующей уплотнительной втулкой, выполненной из нетокопроводящего стеклогерметика, охватывающей герметизирующий изолятор, экранную трубку, цангу, соединяющую токоведущий стержень с центральным электродом, при этом свеча дополнительно содержит промежуточный корпус и монтажный корпус, при этом в монтажном корпусе частично расположен дополнительный корпус и соединен с ним сваркой, а промежуточный корпус расположен между основным и монтажным корпусами, при этом контакт между монтажным, промежуточным и основным корпусами отсутствует, в основном корпусе дополнительно расположена керамическая трубка, в промежуточном корпусе размещен промежуточный изолятор, а в монтажном корпусе установлен дополнительный изолятор, помимо внутреннего канала основного изолятора центральный электрод расположен во внутренних каналах керамической трубки, промежуточного изолятора и дополнительного изолятора, центральный электрод состоит из трех частей, соединенных сваркой в местах между корпусами, при этом промежуточный изолятор установлен с упором в бурт промежуточного корпуса и закреплен в нем металлической втулкой, зафиксированной в промежуточном корпусе сваркой, при этом с упором в торцы промежуточного изолятора на центральном электроде закреплены сваркой два металлических кольца, керамическая трубка ...

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12-01-2012 дата публикации

Compressible supports for turbine engines

Номер: US20120009058A1
Принадлежит: General Electric Co

A system is provided that includes a first turbine alignment component for a turbine engine; and a shim comprises a metal foam. The shim mounts between a first surface of the first turbine alignment component and a second surface of a second turbine alignment component.

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26-01-2012 дата публикации

Systems and methods for controlling the startup of a gas turbine

Номер: US20120017602A1
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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02-02-2012 дата публикации

Auxiliary power unit fire enclosure drain seal

Номер: US20120023897A1
Принадлежит: Hamilton Sundstrand Corp

A drain assembly for an auxiliary power unit having a hot zone formed by a combustor case comprises a fire enclosure, a drain fitting, a discharge port and a piston seal. The fire enclosure encapsulates the hot zone of the combustor case. The drain fitting connects to the fire enclosure. The discharge port extends from the combustor case into the drain fitting. The piston seal is positioned between the drain fitting and the discharge port.

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02-02-2012 дата публикации

Methods for controlling fuel splits to a gas turbine combustor

Номер: US20120023953A1
Принадлежит: General Electric Co

Methods for controlling fuel splits to a combustor of a gas turbine are disclosed. The methods may include determining a combustion reference temperature of the gas turbine, measuring a biasing parameter of the gas turbine, determining at least one fuel split biasing value based on the combustion reference temperature and the biasing parameter and adjusting a nominal fuel split schedule based on the at least one fuel split biasing value.

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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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23-02-2012 дата публикации

method and device for feeding a turbomachine combustion chamber with a regulated flow of fuel

Номер: US20120042657A1
Принадлежит: SNECMA SAS

High-pressure fuel is supplied at a controlled rate to a combustion chamber via a position-controlled valve and a variable-restriction stop-and-pressurizing cut-off valve. A value representative of the real mass flow rate of fuel as delivered is calculated by a calculation unit on the basis of information representative of the pressure difference between the inlet and the outlet of the cut-off valve and of the flow section through the cut-off valve, e.g. as represented by the position X of the slide of the cut-off valve. The position-controlled valve has a variable position that is controlled by the calculation unit as a function of the difference between the calculated value representative of the real mass flow rate and a value representative of a desired mass flow rate.

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23-02-2012 дата публикации

Air turbine starter inlet housing assembly airflow path

Номер: US20120042659A1
Принадлежит: Hamilton Sundstrand Corp

An inlet housing assembly for an Air Turbine Starter includes an outer flowpath curve of an inlet flowpath defined by a multiple of arcuate surfaces in cross-section.

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23-02-2012 дата публикации

Air turbine starter turbine blade airfoil

Номер: US20120045342A1
Принадлежит: Hamilton Sundstrand Corp

A blade profile section for an Air Turbine Starter includes an airfoil which defines an airfoil profile section through a leading edge and a trailing edge. The airfoil profile section is defined by a set of X-coordinates and Y-coordinates defined in any of Table I, Table II, Table III or Table IV scaled by a desired factor. The X-coordinate is the tangential direction, the Y-coordinate is the axial direction, and the Z-coordinate is a radial direction between an airfoil root and an airfoil tip.

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22-03-2012 дата публикации

Exhaust washed structure and associated composite structure and method of fabrication

Номер: US20120066882A1
Принадлежит: Boeing Co

A composite structure and an associated exhaust washed structure are provided which may be formed of ceramic matrix composite (CMC) materials. A method of fabricating a composite structure which may include the CMC material is also provided. A composite structure may include a corrugated septum extending in a lengthwise direction. The composite structure may also include a flute within which the corrugated septum is disposed to form, for example, a partitioned flute assembly.

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05-04-2012 дата публикации

Method, apparatus and system for igniting wide range of turbine fuels

Номер: US20120079831A1
Принадлежит: General Electric Co

In operating a gas turbine, there can be a difference between the desired heating value of the fuel and the actual needs of the fuel for the supplied fuel to be ignited. In one aspect, fuel parameters related to the molecular weight of the fuel such as specific gravity and pressure drop are determined. Ignitability of the fuel is calculated based on the fuel parameters and adjusted as necessary to bring the fuel's ignitability to designed values. The fuel's ignitability can be calculated without actually igniting the fuel and also without direct knowledge of the fuel's calorific value or its composition.

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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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05-04-2012 дата публикации

Method for installing heat shielding on a fixed internal structure of a jet engine nacelle

Номер: US20120082808A1
Принадлежит: Aircelle SA

The invention relates to a method for installing heat shielding ( 31 ), including a heat cushion ( 33 ) covered with a ply ( 35 a ) made from a structural material, on a fixed internal structure ( 29 ) of a jet engine nacelle, including the following consecutive steps: spreading an adhesive ( 43 ) that guarantees good mechanical strength at high temperatures on at least one of the elements selected from said ply ( 35 a ) and an internal skin ( 39 ) of the fixed internal structure; applying said ply ( 35 a ) to said internal skin ( 39 ); and, if necessary, setting said adhesive ( 43 ).

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19-04-2012 дата публикации

Systems and methods for providing ac power from multiple turbine engine spools

Номер: US20120091716A1
Принадлежит: Boeing Co

Systems and methods for providing AC power from multiple turbine engine spools are disclosed. An aircraft system in a particular embodiment includes an engine having a first shaft connected and a second shaft. The aircraft system can further include a bus system and a first energy converter including a starter/generator, coupled between the first shaft and the bus system to convert a first variable frequency energy transmitted by the first shaft to a first generally constant frequency energy. A second energy converter can be coupled between the second shaft and the bus system, with the second energy converter including a generator to convert a second variable frequency energy transmitted by the second shaft to a second generally constant frequency energy.

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26-04-2012 дата публикации

Catcher pin assembly

Номер: US20120096951A1
Автор: Lawrence D. Foster
Принадлежит: Rolls Royce PLC

A catcher pin assembly for attachment to a catcher link of an aircraft frame, the catcher pin assembly having an engine mounting element, a catcher pin, a compressible element, and a nut, which is lockable to the catcher pin, the compressible element being compressed between the pin and the mounting element and/or between the mounting element and the nut, in the assembled condition of the assembly, such that the compressible element applies a predetermined resistance to rotation of the catcher pin relative to the mounting element. The invention also relates to a method of testing a catcher pin assembly to determine if the catcher pin is carrying load from the catcher link, the method including applying a predetermined torque to the catcher pin sufficient to overcome the resistance to rotation of the catcher pin when it is unloaded, and determining whether the catcher pin rotates relative to the mounting element.

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10-05-2012 дата публикации

Igniter with integral pressure sensing line

Номер: US20120110975A1
Автор: Hannes A. Alholm
Принадлежит: United Technologies Corp

An igniter device for a combustor system includes an igniter housing and a pressure sense passage. The igniter housing surrounds an electrode and an insulating body. The igniter has a tip to be positioned within a chamber for combustion. The pressure sense passage is attached to an exterior surface of the igniter housing. The pressure sense passage is configured to direct fluid to a pressure sensor.

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31-05-2012 дата публикации

Advanced Optics and Optical Access for Laser Ignition for Gas Turbines Including Aircraft Engines

Номер: US20120131927A1
Принадлежит: General Electric Co

A laser ignition system for an internal combustion engine, and more specifically a gas turbine engine, is provided. The system including a laser light source configured to generate a laser beam, an ignition port configured to provide optimized optical access of the laser beam to a combustion chamber and an optical beam guidance component disposed between the laser light source and the ignition port. The optical beam guidance component is configured to include optimized optic components to transmit the laser beam to irradiate on a fuel mixture supplied into the combustion chamber to generate a combustor flame in a flame region. A method for igniting a fuel mixture in an internal combustion engine is also presented.

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21-06-2012 дата публикации

Pegless secondary fuel nozzle

Номер: US20120151927A1
Принадлежит: General Electric Co

A unitary fuel injection manifold for a secondary fuel nozzle improves fuel-air mixing and offers flexibility to alter the mixing profile through adaptability to a variety of number, types, and orientation of discharge outlets to the combustion air mixing space around the secondary fuel nozzle. An aerodynamic surface with reduced extension into the mixing space reduces pressures drop and interference with design airflow. Manifold integrity is enhanced by elimination of fillet welds to mount external pegs.

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28-06-2012 дата публикации

Accessory gearbox with a starter/generator

Номер: US20120159964A1
Автор: Hao Huang, Jan Zywot
Принадлежит: General Electric Co

An assembly for a gas turbine engine comprising an accessory gearbox comprising a drive gear and pinion gear and a starter/generator mechanically mounted to the accessory gearbox. The starter/generator comprising a housing and a portion of a rotatable shaft with a safety disconnect where the safety disconnect is located within the housing of the starter/generator.

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28-06-2012 дата публикации

Gearbox assembly

Номер: US20120159966A1
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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28-06-2012 дата публикации

Structure for gas turbine casing

Номер: US20120163963A1
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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05-07-2012 дата публикации

Fuel anti-icing and apu compartment drain combination

Номер: US20120167579A1
Принадлежит: Hamilton Sundstrand Corp

A heat exchanger has a first passage to be connected to a source of fuel. The heat exchanger has an outlet to communicate the fuel downstream. A second passage connects to a source of air. The air passes adjacent to the first passage to heat fuel in the first passage. A jet pump is positioned downstream of the second passage to receive air from the second passage. The jet pump includes a tap connected to a housing compartment to drain fluid from the compartment. A method is also disclosed.

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05-07-2012 дата публикации

Method to maximize lng plant capacity in all seasons

Номер: US20120167619A1
Принадлежит: Chevron USA Inc

As described herein, a method and system for operating a liquefied natural gas (LNG) plant are provided. The method and system also provide for domestic natural gas production. In the present methods and systems, substantially all of the natural gas produced from a well or formation is processed to form LNG; a portion of the LNG produced is regasified; and the regasification is utilized to cool the inlet air to the gas turbines in the LNG plant, either directly or indirectly.

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05-07-2012 дата публикации

Anti-rotation for thrust washers in planetary gear system

Номер: US20120171017A1
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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30-08-2012 дата публикации

Assembly for holding the interface of stationary outer structure of a nacelle and housing of a jet engine

Номер: US20120217372A1
Принадлежит: Aircelle SA

The invention relates to an assembly for holding the interface of a stationary outer structure ( 15 ) of a nacelle ( 3 ) and housing ( 27 ) of a jet engine ( 5 ), said assembly including: a first raised element belonging to the upstream end of the stationary outer structure ( 15 ); a second raised element belonging to the downstream end of the housing ( 27 ), said first and second raised elements being formed so as to be placed in contact with each other; two half-rings ( 109 ) formed by a wall defining a recess that is formed so as to receive the first and second raised elements when the housing ( 27 ) and the stationary outer structure ( 15 ) are mounted edge to edge; and an abutment means formed so as to keep the first and second raised elements in the recess.

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06-09-2012 дата публикации

Mounting an agb on an intermediate casing for a turbojet fan compartment

Номер: US20120224950A1
Автор: Jeremy Edmond Fert
Принадлежит: SNECMA SAS

An intermediate casing for a turbojet fan compartment, including: a shroud centered along a longitudinal axis of the turbine engine; an annular cheek plate centered along the longitudinal axis of the turbine engine and mounted against a downstream face of the shroud; a suspension beam fastened to the cheek plate and extending downstream parallel to the longitudinal axis of the turbine engine; and an AGB suspended from the beam and including an upstream side face spaced apart axially from the cheek plate, a downstream side face opposite the upstream side face, and a plurality of accessories mounted against its downstream side face and distributed about the longitudinal axis of the turbine engine.

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06-09-2012 дата публикации

Turbine drive-train apparatus

Номер: US20120225750A1
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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13-09-2012 дата публикации

Combustion chamber having a ventilated spark plug

Номер: US20120227373A1
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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13-09-2012 дата публикации

Exhaust gas turbocharger, motor vehicle and method for assembling an exhaust gas turbocharger

Номер: US20120227398A1
Автор: Christian Uhlig
Принадлежит: Continental Automotive GmbH

An exhaust gas turbocharger, in particular for an internal combustion engine of a motor vehicle, has a bearing housing for supporting an impeller shaft and a compressor housing receiving a compressor disc. A clamping device with a first arm section and an engagement section, wherein the first arm section contacts a surface of the bearing housing at least in sections, and a counter-clamping device with a head segment and a counter-engagement section. The head section contacts a first surface of the compressor housing at least in sections, and the counter-engagement section can be brought into form-fit contact with the engagement section, such that the bearing housing and the compressor housing; are connected to each other by way of a force fit. The invention also includes a motor vehicle and a method for assembling such an exhaust gas turbocharger.

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13-09-2012 дата публикации

Methods of removing a torque converter and a starting motor from an auxiliary compartment of a gas turbine

Номер: US20120228255A1
Принадлежит: General Electric Co

Methods for moving a starting motor or a torque converter within an auxiliary compartment of a gas turbine are provided. A removal apparatus, which includes a lifting fixture attached to a beam pivotally mounted on a mast, is secured within the auxiliary compartment. To move the starting motor, a plurality of lifting hooks on the lifting fixture are attached to the starting motor, and the lifting fixture and the starting motor are hoisted. To move the torque converter, a pair of lifting lugs on the lifting fixture is attached to the torque converter, and the lifting fixture and the torque converter are hoisted. Methods are also generally provided for securing a removal apparatus within an auxiliary compartment of a gas turbine.

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20-09-2012 дата публикации

Combustor Liner and Flow Sleeve Tool

Номер: US20120233845A1
Автор: Mustafa Gerengi
Принадлежит: General Electric Co

A tool includes an annular frame portion including a mount portion extending radially from the frame portion, a hook portion arranged on the mount portion, the hook portion sized and shaped to engage a member of a tubular component of a turbine combustor, and a force exertion portion arranged on the mount portion, the force exertion portion operative to engage a portion of the turbine combustor.

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27-09-2012 дата публикации

Turbine shell with pin support

Номер: US20120243976A1
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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06-12-2012 дата публикации

Integrated fuel nozzle and ignition assembly for gas turbine engines

Номер: US20120304651A1
Принадлежит: Pratt and Whitney Canada Corp

There is provided an integrated fuel nozzle and ignition assembly for a gas turbine engine comprising a body having a fuel nozzle portion and an igniter portion. The fuel nozzle portion defines a fuel passage extending therethrough between a fuel inlet and a fuel outlet for directing a fuel flow into a combustion chamber. The igniter portion projects laterally from the fuel nozzle portion on a side thereof and comprises an igniter receiving cavity positioned adjacently and laterally on a side of the fuel passage. The assembly further comprises an igniter secured in the igniter receiving cavity for igniting the fuel flow discharged by the fuel passage.

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20-12-2012 дата публикации

Flow Machine

Номер: US20120321450A1
Принадлежит: MAN Diesel and Turbo SE

A flow machine includes two structural component parts that cooperate with one another by a bellows seal so that the bellows seal forms a medium barrier between two spaces of the flow machine which directly adjoin the two structural component parts. The flow machine is constructed as a gas turbine, and one space of the two spaces is a hot-gas space of a high-pressure stage of the gas turbine.

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20-12-2012 дата публикации

Support structure forming method

Номер: US20120321459A1
Автор: Michael L. Carlisle
Принадлежит: Rolls Royce PLC

A method of forming an annular support structure for fastening a component of a gas turbine engine to a static part of the engine is provided. The support structure has a substantially frustoconical skin portion which, in use, extends inwardly from the static part. The support structure further has a flange portion which extends inwardly from an inner edge of the skin portion. In use, a mating flange extending outwardly from the component is attached to the flange portion. The flange portion has an engagement face against which a corresponding face of the mating flange is secured. The flange portion further has an inwardly-facing land at an outer edge of the engagement face which restrains the component against radial movement.

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03-01-2013 дата публикации

Impingement cooled nozzle liner

Номер: US20130001319A1
Принадлежит: Individual

A nozzle liner for a rotatable nozzle includes a seal land and a rotatable seal for moving with the nozzle. The seal has a first diffusion hole for distributing cooling air if the rotatable seal is in a first position and a second diffusion hole for distributing cooling air if the rotatable seal is in a first position and if in a second position.

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10-01-2013 дата публикации

Apparatus and systems relating to fuel injectors and fuel passages in gas turbine engines

Номер: US20130008169A1
Принадлежит: General Electric Co

A combustor casing fuel injector in a combustor of a combustion turbine engine, the combustor including a combustor casing that encloses internal structure of the combustor, wherein the combustor casing fuel injector includes a fuel manifold adjacent to an outer surface of the combustor casing. In certain embodiments, the combustor casing fuel injector includes a fuel injector; wherein the fuel injector extends through the combustor casing from a position within the fuel manifold to a predetermined fuel injection location; and wherein the fuel injector includes a protruding injector inlet within the fuel manifold.

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31-01-2013 дата публикации

Gear train lubricating device

Номер: US20130025405A1
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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31-01-2013 дата публикации

Strut, a gas turbine engine frame comprising the strut and a gas turbine engine comprising the frame

Номер: US20130028718A1
Принадлежит: Volvo Aero Corp

A strut is provided for being arranged between an annular inner structural casing and an annular outer structural casing in a gas turbine engine frame for carrying loads between the inner and outer structural casing during operation. The strut includes a first tube, which is configured to house a service line or pipe between the inner and outer structural casing. The strut includes a second tube, which is configured to house a fastening element for rigidly connecting the inner and outer structural casing. The first and second tube are arranged in a side-by-side relationship and rigidly attached to each other.

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31-01-2013 дата публикации

Power generation unit startup evaluation

Номер: US20130030582A1
Принадлежит: Southern Company Services Inc

Various methods and systems are provided for evaluation of events such as the startup of power generation units. In one embodiment, a method includes obtaining operational data associated with a power generation unit, the operational data corresponding to a predefined period of time; determining start and end times for a startup phase associated with the power generation unit based upon a set of predefined startup conditions corresponding to the startup phase; and generating a network page including the start and times. In another embodiment, a system includes a unit evaluation system executable in a computing device that includes logic that obtains operational data associated with a power generation unit, the operational data corresponding to a predefined period of time and logic that determines start and end times for an event phase associated with the power generation unit based upon a set of predefined conditions corresponding to the event phase.

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07-02-2013 дата публикации

Bipod flexure ring

Номер: US20130034378A1
Принадлежит: Boeing Co

A thermal coupling includes a first structure having a first coefficient of thermal expansion; a second structure having a second coefficient of thermal expansion lower than the first coefficient of thermal expansion; a plurality of thermal expansion fingers provided in the first structure; a plurality of thermal expansion flanges extending from the plurality of thermal expansion fingers, respectively; and a flange extending from the second structure and attached to the plurality of thermal expansion flanges.

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28-02-2013 дата публикации

Method and Apparatus to Provide Sealing Contact Between First and Second Fueldraulic Components

Номер: US20130049301A1
Автор: Kevin M. Ryan
Принадлежит: Hamilton Sundstrand Corp

According to one aspect, an apparatus to provide sealing contact between first and second fueldraulic components includes a metallic member, wherein the metallic member comprises a layer of metal that is formed into a spring energized seal member. The apparatus also includes a layer disposed on an outer portion of the metallic member to provide sealing contact between the first and second fueldraulic components.

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28-02-2013 дата публикации

Nacelle assembly having integrated afterbody mount case

Номер: US20130052005A1
Автор: Thomas G. Cloft
Принадлежит: Individual

A nacelle assembly for a gas turbine engine includes an integrated afterbody mount case. The integrated afterbody mount case includes an outer ring and a plurality of spokes that extend radially inwardly from the outer ring. The outer ring includes a radially outer surface and a radially inner surface. The plurality of spokes are circumferentially disposed about the radially inner surface and extend radially inwardly from the radially inner surface.

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28-02-2013 дата публикации

Light jewels

Номер: US20130052596A1
Автор: Jeffrey T. Holman
Принадлежит: Individual

A wickless candle system includes a housing, a wax reservoir, a light, and an ornament, with at least one hole through a panel of the housing. The light provides a source of heat to melt wax within the wax reservoir, and the ornament is mounted in a position of alignment with the hole through the panel of the housing. The ornament is offset from the panel of the housing to maintain a substantially unobstructed airflow path between the ornament and the panel of the housing.

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07-03-2013 дата публикации

Turbine casing assembly mounting pin

Номер: US20130058780A1
Принадлежит: General Electric Co

In certain embodiments of the present disclosure, a turbine casing assembly is described. The turbine casing assembly includes an inner casing and an outer casing surrounding the inner casing. The outer casing has a first outer casing section and a second outer casing section that join together along a flange. A bolt extends through the flange and joins together the first outer casing section and the second outer casing section. The turbine casing assembly further includes a pin. The pin has a segment defining an opening therethrough. The pin extends through the inner casing and the outer casing and supports the inner casing relative to the outer casing. The bolt passes through the opening defined by the pin.

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14-03-2013 дата публикации

Fuel manifold cooling flow recirculation

Номер: US20130061599A1
Принадлежит: General Electric Co

Cooling flow recirculation in fuel manifolds, such as fuel manifolds associated with gas turbine engines is disclosed. An example system for jet pump driven recirculation of manifold cooling flow according to at least some aspects of the present disclosure may include a flow split valve having a spool valve disposed therein, the flow split valve having a pilot manifold and a main manifold attached thereto; a jet pump fluidically coupled to the pilot manifold, the jet pump being arranged to drive recirculation of a cooling flow through the main manifold via a cooling flow circuit in a pilot only mode of operation; and/or a fuel nozzle in fluid communication with the pilot manifold and the main manifold.

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14-03-2013 дата публикации

Aerofoil assembly

Номер: US20130064661A1
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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21-03-2013 дата публикации

FUEL SUPPLY DEVICE OF GAS TURBINE ENGINE

Номер: US20130067919A1
Автор: OGATA Hideki
Принадлежит: KAWASAKI JUKOGYO KABUSHIKI KAISHA

A fuel divider included in a fuel supply device of a gas turbine engine includes a movable member which is movable according to a fuel pressure at a fuel entrance, opens only a pilot port when the fuel pressure at the fuel entrance is lower than a first pressure, and opens both of the pilot port and the main port when the fuel pressure at the fuel entrance is higher than the first pressure. In addition, the fuel divider includes an adjusting means which adjusts a value of the first pressure in such a manner that it applies to the movable member a counter force in a direction opposite to a direction in which the movable member moves according to the fuel pressure at the fuel entrance, and adjusts the counter force. 1. A fuel supply device of a gas turbine engine , which supplies a fuel to a combustor including a pilot burner and a main burner; the fuel supply device comprising:a pilot fuel passage through which the fuel is supplied to the pilot burner;a main fuel passage through which the fuel is supplied to the main burner;a collecting fuel passage through which the fuel is supplied to the pilot fuel passage and to the main fuel passage; anda fuel divider which divides the fuel supplied from the collecting fuel passage to feed the fuel to the pilot fuel passage and to the main fuel passage;wherein the fuel divider includes:a fuel entrance into which the fuel supplied from the collecting fuel passage is introduced;a pilot port connected to the pilot fuel passage;a main port connected to the main fuel passage;a movable member which is movable according to a fuel pressure at the fuel entrance, the movable member being configured to open only the pilot port when the fuel pressure at the fuel entrance is lower than a first pressure, and to open both of the pilot port and the main port when the fuel pressure at the fuel entrance is higher than the first pressure; andan adjusting means for adjusting a value of the first pressure in such a manner that the adjusting means ...

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21-03-2013 дата публикации

FUEL INJECTOR AND SWIRLER ASSEMBLY WITH LOBED MIXER

Номер: US20130067920A1
Принадлежит:

Disclosed is a gas turbine fuel injector and swirler assembly, including: a delivery tube structure arranged on a central axis of the fuel injector and swirler assembly, a first fuel supply channel arranged in the delivery tube structure, a shroud surrounding the delivery tube structure, swirl vanes arranged between the delivery tube structure and the shroud, a radial passage in each swirl vane, communicating with the first fuel supply channel, a set of apertures open between the radial passage and the exterior surface of said each swirl vane, wherein a second fuel supply channel is arranged in the delivery tube structure extending to a downstream end of the delivery tube structure and a mixer with lobes for fuel injection is arranged at the downstream end. Further disclosed is an assembly method for assembling a fuel injector and swirler assembly. 115-. (canceled)16. A gas turbine fuel injector and swirler assembly , comprising:a delivery tube structure arranged on a central axis of the fuel injector and swirler assembly;a first fuel supply channel arranged in the delivery tube structure;a shroud surrounding the delivery tube structure;a plurality of swirl vanes arranged between the delivery tube structure and the shroud;a radial passage in each swirl vane, communicating with the first fuel supply channel;a set of apertures open between the radial passage and the exterior surface of each swirl vane; anda second fuel supply channel arranged in the delivery tube structure extending to a downstream end of the delivery tube structure,wherein a mixer with a plurality of lobes for fuel injection is arranged at the downstream end.17. The fuel injector and swirler assembly as claimed in claim 16 , wherein the delivery tube structure comprises coaxial cylindrical inner and outer tubes claim 16 , providing the first fuel supply channel in the inner tube and forming the annular second fuel supply channel between the inner and outer tubes.18. The fuel injector and swirler ...

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21-03-2013 дата публикации

Multiple Tube Premixing Device

Номер: US20130067926A1
Принадлежит: GENERAL ELECTRIC COMPANY

The present application provides a premixer for a combustor. The premixer may include a fuel plenum with a number of fuel tubes and a burner tube with a number of air tubes. The fuel tubes extend about the air tubes. 1. A premixer for a combustor , comprising: a plurality of fuel tubes comprising a first plurality of fuel tubes and a second plurality of fuel tubes:', 'a first chamber in communication with the first plurality of fuel tubes; and', 'a second chamber in communication with the second plurality of fuel tubes; and, 'a fuel plenum comprisinga burner tube comprising a plurality of air tubes,wherein the plurality of fuel tubes extend about the plurality of air tubes.2. The premixer of claim 1 , wherein the burner tube comprises a bell mouth at a first end and a burner tube nozzle at a second end.3. The premixer of claim 2 , wherein the plurality of air tubes extends from the bell mouth to the burner tube nozzle.4. The premixer of claim 1 , further comprising a plurality of spacers positioned between the fuel plenum and the burner tube.5. The premixer of claim 1 , wherein the fuel plenum comprises a chamber in communication with the plurality of fuel tubes.68-. (canceled)9. The premixer of claim 1 , wherein the first plurality of fuel tubes surrounds the second plurality of fuel tubes.10. The premixer of claim 1 , wherein the plurality of air tubes comprises a first diameter claim 1 , wherein the plurality of fuel tubes comprises a second diameter claim 1 , and wherein the first diameter is larger than the second diameter.11. A method of mixing a first flow and a second flow claim 1 , comprising:dividing the first flow into a plurality first flow tubes;dividing the second flow into a plurality of second flow tubes;placing the plurality of first flow tubes about the plurality of second flow tubes; andmixing the first flow and the second flow within the plurality of second flow tubes.12. The method of claim 11 , further comprising dividing a third flow into a ...

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21-03-2013 дата публикации

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

Номер: US20130071231A1
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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28-03-2013 дата публикации

Rotor centralization for turbine engine assembly

Номер: US20130074334A1
Принадлежит: Pratt and Whitney Canada Corp

One or more support elements radially extend through one or more openings defined in a turbine engine casing and are configured to centralize and at least partially support a rotor assembly of the engine during an engine disassembly or assembly procedure. The support elements are configured to transfer any rotor assembly weight loads to an engine casing while a bearing support of the rotor assembly is absent or removed.

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28-03-2013 дата публикации

Pre-compressed seal including removable pre-compression member

Номер: US20130074338A1
Принадлежит: Eaton Corp

A seal is provided that includes a resilient, arc-shaped body having a pair of sealing portions movable between a pre-compressed state and a compressed state. A removable pre-compression member slidingly engages the seal body along at least a portion of its length to hold the sealing portions in the pre-compressed state. In an embodiment, the seal body includes a pair of first retaining features and the pre-compression member includes a retaining portion having a pair of second retaining features that engage the pair of first retaining features to hold the sealing portions in the pre-compressed state. A strap portion extends from and between each retaining portion to allow the pre-compression member to flex during assembly of the seal to accommodate the radius of the seal body.

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28-03-2013 дата публикации

Motor-generator turbomachine starter

Номер: US20130076035A1
Принадлежит: Hamilton Sundstrand Corp

An exemplary turbomachine starter assembly includes a motor-generator that selectively operates in a motor mode or a generator mode. The motor-generator provides a rotational input to a turbomachine when operating in the motor mode. The motor-generator generates a supply of electrical power when operating in the generator mode. The supply of electrical power is used to power accessories of the turbomachine.

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04-04-2013 дата публикации

GUIDE AND SEALING DEVICE FOR A TURBINE ENGINE, THE DEVICE HAVING A CARBON GASKET AND AN INTEGRATED SMOOTH BEARING

Номер: US20130081405A1
Принадлежит: SNECMA

A guide and sealing device a shaft in an orifice in a casing in a turbine engine, the device including a carbon gasket mounted around the shaft including a ring secured to the shaft and having an annular friction face rubbing against a carbon annulus mounted in a support bushing fastened to the casing, the ring presenting a cylindrical wall that is centered and guided in rotation in a cylindrical wall of the support bushing so as to form a smooth bearing for guiding the shaft. 110-. (canceled)11. A guide and sealing device for mounting in an orifice in a casing through which a shaft passes in a turbine engine , the device comprising:a carbon gasket mounted around the shaft in the orifice of the casing and comprising a ring that is carried by the shaft and that has an annular friction face for rubbing against a carbon annulus that is mounted in a support bushing fastened to the casing and that is urged axially towards the ring;wherein the ring includes a cylindrical wall that is centered and guided in rotation in a cylindrical wall of the support bushing so as to form a smooth bearing for guiding the shaft.12. A device according to claim 11 , wherein the cylindrical wall of the ring is formed as a single piece with the ring or is a fitting that is fastened to the ring.13. A device according to claim 11 , wherein the cylindrical wall of the ring presents an outer cylindrical surface that is coated in a thin layer or that is surrounded by a hoop claim 11 , the thin layer or the hoop being made of a material that is hard and has a low coefficient of friction.14. A device according to claim 11 , wherein the inner cylindrical surface of the cylindrical wall of the ring defines an annular groove opening out axially away from the carbon annulus and into which cooling oil is to be injected.15. A device according to claim 11 , wherein the cylindrical wall of the support bushing is made as a single piece with the support bushing or is a fitting that is fastened to the bushing. ...

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11-04-2013 дата публикации

Low Emission Power Generation Systems and Methods

Номер: US20130086916A1
Принадлежит:

Methods and systems for C0separation for low emission power generation in combined-cycle power plants are provided. One system includes a gas turbine system that stoichiometrically combusts a fuel and an oxidant in the presence of a compressed recycle stream to provide mechanical power and a gaseous exhaust. The compressed recycle stream acts as a diluent to moderate the temperature of the combustion process. A boost compressor can boost the pressure of the gaseous exhaust before being compressed into the compressed recycle stream. A purge stream is tapped off from the compressed recycle stream and directed to a C0separator configured to absorb C0from the purge stream using a potassium carbonate solvent. 1. An integrated COseparation system , comprising:a gas turbine system having a combustion chamber configured to stoichiometrically combust a compressed oxidant and a fuel in the presence of a compressed recycle stream in order generate a discharge stream, which is expanded in an expander, thereby generating a gaseous exhaust stream and at least partially driving a main compressor, wherein the compressed recycle stream acts as a diluent configured to moderate the temperature of the discharge stream;an exhaust gas recirculation system having at least one of a boost compressor and one or more cooling units configured to increase the mass flow rate of the gaseous exhaust stream to provide a cooled recycle gas to the main compressor, wherein the main compressor compresses the cooled recycle gas and generates the compressed recycle stream, a portion of which is directed to the combustion chamber and a portion of which provides a purge stream; and{'sub': 2', '2, 'claim-text': [{'sub': '2', 'an absorber column configured to receive the purge stream and circulate a potassium carbonate solvent therein to absorb COin the purge stream, wherein the absorber column discharges a nitrogen-rich residual stream and a bicarbonate solvent solution;'}, 'a first valve fluidly coupled to ...

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11-04-2013 дата публикации

EXTERNALLY THREADED JOURNAL HOUSING

Номер: US20130089407A1
Автор: Ranz Andrew J.
Принадлежит: DRESSER-RAND COMPANY

A journal housing including a series of housing threads defined on an outer radial surface. The series of housing threads may be adapted to threadably engage a series of casing threads defined on an inner radial surface of a casing. A shoulder may extend radially-outward from the outer radial surface, and the shoulder may be disposable axially-adjacent the casing and adapted to receive at least one first mechanical fastener. 1. A journal housing , comprising:a series of housing threads defined on an outer radial surface, the series of housing threads being adapted to threadably engage a series of casing threads defined on an inner radial surface of a casing; anda shoulder extending radially-outward from the outer radial surface, the shoulder being disposable axially-adjacent the casing and adapted to receive at least one first mechanical fastener.2. The journal housing of claim 1 , wherein the series of housing threads comprises buttress threads.3. The journal housing of claim 2 , wherein the buttress threads comprise square buttress threads.4. The journal housing of claim 1 , wherein the series of housing threads comprises external threads and the series of casing threads comprises internal threads.5. The journal housing of claim 1 , wherein the at least one first mechanical fastener prevents the journal housing from threadably disengaging with the casing.6. The journal housing of claim 1 , wherein the casing comprises a compressor head.7. The journal housing of claim 1 , further comprising:an inner journal housing; andan outer journal housing disposed radially-outward from and concentric with the inner journal housing, wherein the outer journal housing defines the series of housing threads.8. The journal housing of claim 7 , wherein the inner journal housing comprises first and second outer surfaces that are radially offset from one another.9. The journal housing of claim 7 , wherein the inner journal housing comprises:a first inner journal housing section; anda ...

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18-04-2013 дата публикации

GAS TURBINE AND GAS-TURBINE PLANT HAVING THE SAME

Номер: US20130091824A1
Принадлежит: MITSUBISHI HEAVY INDUSTRIES, LTD.

The invention provides a gas-turbine fuel nozzle () that includes a plurality of fuel supply channels () to which fuel is supplied, a plurality of fuel/scavenging-fluid supply channels () to which fuel or a scavenging fluid for scavenging the fuel is supplied, and a plurality of injection holes () that are provided at downstream ends of the fuel supply channels () or the fuel/scavenging-fluid supply channels () and that inject the fuel guided from the fuel supply channels () or the fuel/scavenging-fluid supply channels (); a scavenging-fluid supply channel () that is connected to the fuel/scavenging-fluid supply channels () to guide the scavenging fluid; and scavenging-fluid cooling means () for cooling the scavenging fluid to a temperature lower than a self-ignition temperature of the fuel. 1. A gas turbine comprising:a gas-turbine fuel nozzle that includes a plurality of fuel supply channels to which fuel is supplied, a plurality of fuel/scavenging-fluid supply channels to which fuel or a scavenging fluid for scavenging the fuel is supplied, and a plurality of injection holes that are provided at downstream ends of the fuel supply channels or the fuel/scavenging-fluid supply channels and that inject the fuel or the scavenging fluid guided from the fuel supply channels or the fuel/scavenging-fluid supply channels;a scavenging-fluid supply channel that is connected to the fuel/scavenging-fluid supply channels and guides the scavenging fluid; andscavenging-fluid cooling means for cooling the scavenging fluid to a temperature lower than a self-ignition temperature of the fuel.2. A gas turbine according to claim 1 ,wherein the scavenging-fluid supply channel is connected to the fuel/scavenging-fluid supply channels and to a casing of the gas turbine and guides, as the scavenging fluid, a fluid extracted from the casing; andthe scavenging-fluid cooling means is a plurality of projections that are provided around the scavenging-fluid supply channel.3. A gas turbine ...

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18-04-2013 дата публикации

Method and a device for producing a setpoint signal

Номер: US20130091851A1
Принадлежит: SNECMA SAS

A method and device producing a setpoint signal representing a flow rate of fuel that a metering unit having a slide valve is to supply to a fuel injection system of a combustion chamber in a turbine engine, the position of the valve depending on the setpoint signal. The method: obtains a first signal representing a measurement as delivered by a flow meter of a flow rate of fuel injected into the chamber; evaluates a second signal representing the flow rate of fuel injected into the chamber based on a measurement of the position of the valve; estimates a third signal representative of the measurement delivered by the flow meter by applying a digital model of the flow meter to the second signal; and produces the setpoint signal by adding a compensation signal to the first signal, the compensation signal obtained by subtracting the third signal from the second signal.

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25-04-2013 дата публикации

Hydrajetting Nozzle and Method

Номер: US20130098043A1
Автор: Surjaatmadja Jim B.
Принадлежит: Halliburton Energy Services, Inc.

A jetting device comprises a body, and an interior flow path within the body. The interior flow path comprises a flow section, an expansion section, and a shoulder formed at the intersection of the flow section and the expansion section. The length and diameter of the expansion section are configured to allow a portion of the pressure of the fluid downstream of the expansion section to provide power to a fluid flowing through the nozzle when the fluid is flowing through the nozzle. 1. A jetting device comprising:a body; and a flow section;', 'an expansion section; and', 'a shoulder formed at the intersection of the flow section and the expansion section, wherein the length and diameter of the expansion section are configured to allow a portion of the pressure of the fluid downstream of the expansion section to provide power to a fluid flowing through the jetting device when the fluid is flowing through the jetting device., 'an interior flow path within the body, wherein the interior flow path comprises2. The jetting device of claim 1 , wherein a length and a diameter of an expansion section of the jetting device are configured such that a fluid stream diameter of a fluid stream discharged from the jetting device is less than the diameter of the expansion section at an outer end of the jetting device.3. The jetting device of claim 1 , wherein the portion of the pressure of the fluid downstream of the expansion section is at least about 10% of the pressure of the fluid downstream of the expansion section.4. The jetting device of claim 1 , wherein the portion of the pressure of the fluid downstream of the expansion section is less than about 80% of the pressure of the fluid downstream of the expansion section.5. A flow device comprising:a body; and a flow section;', 'an expansion section; and', 'a shoulder formed at the intersection of the flow section and the expansion section, wherein the length and diameter of the expansion section are configured to control the ...

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25-04-2013 дата публикации

Method for Operating a Gas Turbine

Номер: US20130098054A1
Принадлежит: ALSTOM TECHNOLOGY LTD.

In a method for operating a gas turbine (), a CO2-containing gas is compressed in a compressor (), the compressed gas is used to burn a fuel in at least one subsequent combustion chamber (), and the hot combustion gases are used to drive at least one turbine (). Improved control and performance can be achieved by measuring the species concentration of the gas mixture flowing through the gas turbine () at several points within the gas turbine () by a distributed plurality of species concentration sensors (-), and utilizing the measured concentration values to control the gas turbine () and/or optimize the combustion performance of the gas turbine (). 1. A method for operating a gas turbine , in which turbine a CO-containing gas is compressed in a compressor , the compressed gas is used to burn a fuel in at least one subsequent combustion chamber to form hot combustion gases , and the hot combustion gases are used to drive at least one turbine , the method comprising:measuring the species concentration of the gas mixture flowing through the gas turbine at several points within the gas turbine with a distributed plurality of species concentration sensors; andcontrolling the gas turbine, optimizing the combustion performance of said gas turbine, or both, based on the measured species concentration values.2. A method according to claim 1 , wherein measuring comprises:{'sub': '2', 'measuring at least the Oconcentration with said plurality of species concentration sensors.'}3. A method according to claim 1 , wherein said species concentration sensors comprise ZrOsensors.4. A method according to claim 1 , wherein said species concentration sensors consist of ZrOsensors.5. A method according to claim 1 , in which the gas turbine is a sequential-combustion turbine with two combustors claim 1 , two turbines claim 1 , and flue gas recirculation claim 1 , and in which at least part of the flue gas at an exit of the gas turbine is recirculated and enters the compressor after ...

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25-04-2013 дата публикации

Fuel Management of a Melting Fuel

Номер: US20130101946A1
Принадлежит:

A fuel management system provides a burning system to melt solid fuel and supply the fuel to a wick for producing a larger flame. 1. A torch for burning fuel comprising:a wick for lighting to produce a flame,a proximal fuel reservoir surrounding the wick,a remote fuel reservoir surrounding the proximal fuel reservoir,a liquid fuel reservoir located beneath the proximal fuel reservoir and remote fuel reservoir and in connection with the wick,wherein a solid fuel may be added to the proximal fuel reservoir and remote fuel reservoir to fuel the flame.2. The torch for burning fuel according to claim 1 , wherein the fuel is a paraffin wax.3. A method of burning solid fuel comprising:adding solid fuel to a proximal fuel reservoir surrounding a wick, and a remote fuel reservoir surrounding the proximal fuel reservoir,providing a source of ignition to the wick, producing heat to convert the solid fuel in the proximal fuel reservoir into a liquid state,allowing the liquid state fuel to collect in a liquid fuel reservoir to provide fuel to the wick for burning.3. The method according to claim 3 , wherein the solid fuel is paraffin wax.4. The method of burning solid fuel according to claim 3 , wherein the heat from the flame melts the solid fuel in the remote fuel reservoir and the fuel is carried by gravity flow to the liquid fuel reservoir. This application claims the priority of Provisional Application 61/061,378 filed on Jun. 13, 2008, which is hereby incorporated by reference in its entirety.Existing liquid fuel burning apparatuses like lanterns, lamps, and torches are plagued with fuel handling issues, including spills of flammable material, subsequent wicking and transfer to clothing and hands, and other types of difficulties, messes, and hazards. Typical liquid fuel burning systems, because of the flammable nature of the fuel, cannot be refueled without first extinguishing the flame. The U.S. Consumer Product Safety Commission tracks incidents associated with the use ...

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02-05-2013 дата публикации

Turbomachine including an inner-to-outer turbine casing seal assembly and method

Номер: US20130104565A1
Принадлежит: General Electric Co

A turbomachine includes an inner casing component having a first end that extends to a second end and a seal member. An outer casing component is coupled to the inner casing component. The annular outer casing component includes a first end portion that extends to a second end portion and a seal element that aligns with the seal member of the annular inner casing component to form a seal passage. A seal is arranged in the seal passage. The seal includes a first end section that extends to a second end section through an intermediate zone. The first end section includes a recessed portion and the second end section includes a connecting portion. The connecting portion is configured and disposed to nest within the recessed portion to form a substantially continuous seal.

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02-05-2013 дата публикации

TURBINE HOUSING AND EXHAUST GAS TURBINE SUPERCHARGER

Номер: US20130108414A1
Автор: Maeda Osamu, Nagai Kouji
Принадлежит: TOYOTA JIDOSHA KABUSHIKI KAISHA

A turbine housing includes a first shell member and a third shell member, which are formed from metal sheets and forming a housing body, and a tongue member, which is fixed to inner circumferential surfaces of the shell members and and discrete from the shell members and. The tongue member defines an inlet port and a scroll compartment in the housing body. 1. A turbine housing that surrounds a turbine wheel , the turbine housing comprising:a housing body formed from a metal sheet; anda tongue member fixed to an inner circumferential surface of the housing body and discrete from the housing body, wherein the tongue member defines an inlet port and a scroll compartment in the housing body.2. The turbine housing according to claim 1 , wherein the housing body includes two shell members sandwiching the tongue member in an axial direction of the turbine wheel claim 1 , and the two shell members are joined with each other in a lap joint.3. The turbine housing according to claim 2 , wherein the tongue member includes a protruding portion having a shape that is in conformance with a stepped void formed by joining the two shell members in a lap joint claim 2 , and the protruding portion being located in the stepped void.4. The turbine housing according to claim 1 , wherein the tongue member is formed by a metal piece having a predetermined thickness in an axial direction of the turbine wheel.5. The turbine housing according to claim 2 , wherein the tongue member is formed by a metal piece having a thickness that is greater than the sum of plate thicknesses of the two shell members in the axial direction of the turbine wheel.6. The turbine housing according to claim 4 , wherein a cooling passage that circulates a cooling medium is formed in the tongue member.7. The turbine housing according to claim 4 , wherein a bypass passage that bypasses the turbine wheel is formed in the tongue member.8. The turbine housing according to claim 1 , wherein the tongue member is covered by a ...

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02-05-2013 дата публикации

CENTERLINE SUSPENSION FOR TURBINE INTERNAL COMPONENT

Номер: US20130108437A1
Принадлежит:

A centerline suspension arrangement () for a turbine (). A turbine inner casing () is supported within an outer casing () via a support member () that includes an inner portion () contacting the inner casing and an outer portion () extending into a slot () formed in the outer casing. The support member is slid into an axially oriented slot () formed in the inner casing and is body bound therein with respect to radial movements, with the support member and the inner casing slot including opposed vertical support surfaces () and a pair of oppositely facing opposed horizontal support surfaces ( and ). Thus, dead weight and operating loads from the inner casing are reacted through the support member and into the outer casing without the necessity for any bolting or other fastener attachment in the design load path between the support member and the inner casing. 1. A centerline suspension arrangement for a turbine comprising:an outer casing;an inner casing;a support member comprising an inner portion disposed within an axially oriented slot in the inner casing, the support member inner portion and inner casing slot cooperatively shaped for insertion of the support member inner portion into the slot in the axial direction and for a body bound fit lacking freedom of movement in radial directions between the support member inner portion and the inner casing; andan outer portion of the support member extending beyond the inner casing slot and being vertically supported within a slot formed in the outer casing;wherein the body bound fit between the inner casing and the support member is effective to establish a design load path for a transfer of dead weight and operating loads from the inner casing to the support member and to the outer casing without a necessity for a fixed connection between the support member and the inner casing.2. The arrangement of claim 1 , further comprising an outer casing lower half shim member disposed within the outer casing slot between the ...

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09-05-2013 дата публикации

Aircraft ignition system and method of operating the same

Номер: US20130111914A1
Автор: Steve J. Kempinski
Принадлежит: CHAMPION AEROSPACE LLC

An aircraft ignition system having a power circuit, a control circuit, and a discharge circuit and coupled to the spark plugs of an aircraft engine. The power circuit may include two independent power sources; e.g., alternator power (such as a permanent magnet alternator) and power from aircraft or DC power bus. The control circuit may control one or more aspects of the discharge circuit, e.g., the ignition timing. And the discharge circuit may trigger a capacitive discharge ignition event to the spark plugs.

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09-05-2013 дата публикации

ASSEMBLY COMPRISING A SHAFT SEAL

Номер: US20130115049A1
Автор: Grieshaber Dirk
Принадлежит:

A shaft seal includes more than one sealing module, at least one fluid supply and a fluid discharge, and a main seal which is subject to a greatest partial pressure difference. A second main seal is a radial double seal, which includes two gas seals, each gas seal having a rotating sealing surface and a stationary sealing surface, wherein the two sealing surface pairs are located opposite each other in a sealing plan, and wherein the two sealing planes have substantially radial extension to the shaft. 114.-. (canceled)15. A shaft seal for sealing a gap of a penetration of a shaft through a casing ,wherein the shaft seal comprises a plurality of sealing modules,wherein in the interior of the casing there is a process fluid having a sealing pressure, and outside the casing there is an ambient fluid having an ambient pressure,wherein the ambient pressure differs from the sealing pressure by a pressure differential, which pressure differential, divided into proportions, is applied to individual sealing modules of the plurality of sealing modules as partial pressure differentials,wherein the plurality of sealing modules comprises a first main seal, wherein a greatest partial pressure differential is applied to the first main seal,wherein, between the plurality of sealing modules, a fluid drain is provided for discharging a first drain fluid,wherein the first main seal is a simple gas seal and is designed such that, during normal trouble-free operation and during starting and shutting down, the greatest partial pressure differential is applied to the first main seal, starting from the highest pressure level from the inside outwards,wherein the plurality of sealing modules comprises s second main seal which is designed such that, in an event of a malfunction of the first main seal, the greatest partial pressure differential is applied to the second main seal, starting from the highest pressure level from the inside outwards,wherein the second main seal is a radial double ...

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09-05-2013 дата публикации

Wax Burning Method and Apparatus

Номер: US20130115565A1
Принадлежит:

A wax burning system provides a melting plate and burning assembly for maintaining a burning flame to consume substantially all of the provided wax in the system. 1. A wax burning system comprising:a melting grate within a bowl housing,a hollow-core wick extending above the melting grate,wherein a solid fuel may be placed on the melting grate for supply of fuel to a flame on the hollow-core wick.2. The wax burning system according to claim 1 , further comprising a secondary starter wick located in proximity to the hollow-core wick claim 1 , such that ignition of the starter wick will cause ignition of the hollow-core wick.3. The wax burning system according to claim 1 , wherein the hollow-core wick is surrounded by a heat-conductive wick sheath.4. The wax burning system according to claim 1 , wherein the hollow-core wick has an upper end adjacent to a flame and a lower end for receiving liquid fuel5. The wax burning system according to claim 4 , wherein the hollow-core wick includes notched sections at the upper end.6. A method of fueling a flame comprising:adding solid fuel into a basin having a melting plate for heating the solid fuel to a liquid state,providing a source of ignition to a wick adjacent to the melting plate.7. The method of fueling a flame according to claim 6 , wherein the solid fuel may be added while the flame is burning.8. The method of fueling a flame according to claim 6 , wherein the source of ignition is provided to a starter wick claim 6 , which is in close proximity to the wick to then provide ignition to the wick. This application claims the priority of Provisional Application 61/061,207 filed on Jun. 13, 2008, which is hereby incorporated by reference in its entirety.Flaming entities like candles or torches are limited in their ability to produce a larger flame without creating a plume or a periodic wisp of soot. Similarly, larger flames tend to be excessively high for safe indoor use, resulting in fire hazard concerns. Smaller flames ...

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16-05-2013 дата публикации

FUEL INJECTION SYSTEM FOR TURBOJET ENGINE AND METHOD OF ASSEMBLING SUCH AN INJECTION SYSTEM

Номер: US20130118177A1
Принадлежит: SNECMA

A fuel injection system for a turbojet engine including a fixed part and a sliding lead-through, the fixed part and the sliding lead-through extending along a reference axis, the fixed part including a cavity that has a bottom and a closure cup, the sliding lead-through being provided with a sole plate contained inside the cavity. The injection system has increased resistance to wearing of the injector on which it is mounted. To achieve this it further includes a spring arranged in such a way as to apply to the sole plate a force capable of preventing the vibration-induced micro-movements of the sliding lead-through with respect to the fixed part in the absence of thermal expansion. 1. A fuel injection system for a turbojet engine , comprising:a fixed portion and a sliding cross-member, the fixed portion and the sliding cross-member extending along a reference axis, the fixed portion comprising a cavity defined axially by a base and a closing cup, the sliding cross-member being provided with a flange contained in the cavity; anda spring disposed in the cavity so as to exert an axial force on the flange.2. The injection system as claimed in claim 1 , wherein the spring comprise comprises a corrugated plate.3. The injection system as claimed in claim 2 , wherein the corrugated plate is circular.4. The injection system as claimed in claim 1 , wherein the spring is axially constrained in the cavity.5. The injection system as claimed in claim 1 , comprising a washer disposed between the spring and the flange.6. The injection system as claimed in claim 1 , wherein the spring is configured to exert a force in the range 10 Newtons to 30 Newtons on the flange.7. A combustion chamber comprising at least one injection system as claimed in claim 1 , the sliding cross-member further comprising a centring cone in which a fuel injector is inserted.8. An aircraft engine comprising a combustion chamber as claimed in .9. A method for assembling an injection system comprising a fixed ...

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16-05-2013 дата публикации

PROCEDURE FOR IGNITING A TURBINE ENGINE COMBUSTION CHAMBER

Номер: US20130118181A1
Принадлежит: SNECMA

A procedure for igniting a combustion chamber of a turbine engine, the chamber being fed with fuel by injectors and including an igniter mechanism igniting the fuel injected into the chamber. The procedure includes an initial stage during which fuel is injected into the chamber at a constant rate while simultaneously exciting the igniter mechanism, and in event of non-ignition of the chamber at an end of the initial stage, a second stage during which a rate at which fuel is injected is increased rapidly by 20% to 30%. 17-. (canceled)8. A method for igniting a combustion chamber of a turbine engine , the chamber being fed with fuel by injectors and including igniter means for igniting the fuel injected into the chamber , the method comprising:an initial stage during which fuel is injected into the chamber at a constant rate while simultaneously exciting the igniter means; andin event of non-ignition of the chamber at an end of the initial stage, comprising a second stage during which a rate at which fuel is injected is increased rapidly by 20% to 30%;the second stage being followed by a stage of progressively increasing the fuel flow rate by an amount that is smaller and slower than in the second stage.9. A procedure according to claim 8 , wherein the initial stage has a duration of about 5 to 8 seconds claim 8 , and in the second stage the rapid increase in the fuel flow rate takes place over a time of about 1 to 2 seconds.10. A procedure according to claim 8 , wherein the progressive increase in the fuel flow rate lasts for about 10 to 15 seconds.11. A procedure according to claim 10 , wherein the fuel flow rate from the injectors at an end of the progressive increase is greater than about 50% to 80% of the constant flow rate during the initial stage.12. A procedure according to claim 8 , wherein a speed of rotation of the engine increases progressively during the first and second stages.13. A procedure according to claim 8 , wherein all of the injectors are ...

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16-05-2013 дата публикации

LEAF SEAL

Номер: US20130119612A1
Принадлежит: ROLLS-ROYCE PLC

A leaf seal is provided for effecting a seal between two coaxial, relatively rotating components. The leaf seal has a pair of annular packs of stacked leaves. Each pack is mountable to one of the components with its leaves extending towards the other component such that the leaf edges of at least one of the packs are presented for wiping contact with the other component. The packs are axially spaced from each other by a controlled axial clearance. Within each pack the leaves are stacked face-to-face such that neighbouring leaves are separated from each other by interleaf gaps which allow an axial leakage flow through the seal. Further, within each pack the packs are positioned such that, when viewed in the axial direction, the leaves of each pack of the pair substantially obscure the interleaf gaps of the other pack of the pair. The controlled axial clearance is the dominant flow restriction in the seal determining the amount of leakage flow through the seal. 1. A leaf seal for effecting a seal between two coaxial , relatively rotating components , the leaf seal having a pair of annular packs of stacked leaves , each pack being mountable to one of the components with its leaves extending towards the other component such that the leaf edges of at least one of the packs are presented for wiping contact with the other component , and the packs being axially spaced from each other by a controlled axial clearance;wherein within each pack the leaves are stacked face-to-face such that neighbouring leaves are separated from each other by interleaf gaps which allow an axial leakage flow through the seal, and the packs are positioned such that, when viewed in the axial direction, the leaves of each pack of the pair substantially obscure the interleaf gaps of the other pack of the pair; andwherein the controlled axial clearance is the dominant flow restriction in the seal determining the amount of leakage flow through the seal.2. A leaf seal according to claim 1 , wherein each ...

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16-05-2013 дата публикации

LEAF SEAL

Номер: US20130119613A1
Принадлежит: ROLLS-ROYCE PLC

A leaf seal is provided for effecting a seal between two coaxial, relatively rotating components. The leaf seal has an annular pack of leaves which are stacked face-to-face within the pack, and which are mountable to one of the components at respective root portions of the leaves such that the leaves extend towards the other component and respective edges of the leaves are presented for wiping contact with the other component. The pack includes a plurality of spacers, each spacer separating the root portions of neighbouring leaves to form therebetween interleaf gaps which allow an axial leakage flow through the pack. The spacers are distributed around the pack such that the leaves are divided into blocks of two or more leaves sandwiched at their root portions between nearest-neighbour spacers. 1. A leaf seal for effecting a seal between two coaxial , relatively rotating components , the leaf seal having an annular pack of leaves which are stacked face-to-face within the pack , and which are mountable to one of the components at respective root portions of the leaves such that the leaves extend towards the other component and respective edges of the leaves are presented for wiping contact with the other component;wherein the pack includes a plurality of spacers, each spacer separating the root portions of neighbouring leaves to form therebetween interleaf gaps which allow an axial leakage flow through the pack; andwherein the spacers are distributed around the pack such that the leaves are divided into blocks of two or more leaves sandwiched at their root portions between nearest-neighbour spacers.2. A leaf seal according to claim 1 , wherein within each block the leaves make face-to-face contact with their nearest-neighbour leaves in the block over substantially their entire lengths from their respective root portions to their respective wiping contact edges.3. A leaf seal according to claim 1 , wherein the spacers are distributed such that the number of leaves in ...

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16-05-2013 дата публикации

ELECTRIC POWER SUPPLY CIRCUIT FOR A TURBOJET ENGINE NACELLE

Номер: US20130119664A1
Принадлежит: AIRCELLE

The present invention relates to an electric power supply circuit () for a turbojet engine nacelle including at least one electric generator () mechanically connected to the shaft of a turbojet engine, said generator being capable of directly supplying electric power to a first electric power device other than a simple monitoring or supervising unit, characterized in that said generator is capable of directly supplying electric power to at least one second electric power device other than a monitoring or supervising unit, as well as to a nacelle including such an electric circuit. 1. An electric power supply circuit for a turbojet engine nacelle , comprising:at least one electric generator mechanically connected to a shaft of the turbojet engine, said generator being capable of directly supplying electric power to a first electric power device other than a simple monitoring or supervising unit;wherein said generator is capable of directly supplying electric power to at least one second electric power device other than a monitoring or supervising unit.2. The power supply circuit according to claim 1 , wherein one of the electric power supply devices is an electric deicing device.3. The electric power supply circuit according to claim 1 , wherein one of the electric power supply devices is a thrust reverser device.4. The electric power supply circuit according to claim 3 , wherein the thrust reverser device comprises an electrodynamic braking output line able to at least partially power another electric device.5. The electric power supply circuit according to claim 1 , wherein one of the electric power devices is a variable nozzle device.6. The power supply circuit according to claim 1 , wherein the electric generator is of a generator/starter type.7. The power supply circuit according to claim 6 , wherein the electric generator in a starter mode can be powered by a return line of one of the electric devices.8. The electric power supply circuit according to claim 1 , ...

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16-05-2013 дата публикации

METHOD OF PRODUCING POWER

Номер: US20130119677A1
Принадлежит: SHELL OIL COMPANY

A process for producing power from a fuel stream containing at least 30 mol % hydrogen sulfide is provided. The fuel stream is combusted with an oxidant stream containing molecular oxygen to generate a combusted gas stream containing thermal power, where the molar ratio of molecular oxygen to hydrogen sulfide is at least 1:1. Electrical power is generated from the thermal power of the combusted gas stream. 1. A method of producing power comprising combusting an oxidant stream and at least a portion of a fuel stream comprising one or more feed streams to generate a combusted gas stream containing thermal power , wherein the fuel stream has a hydrogen sulfide content of at least 30 mol % , at least 90 mass % of the components of the fuel stream are gaseous , the oxidant stream contains molecular oxygen , and the molar ratio of molecular oxygen to hydrogen sulfide is at least 1:1; andgenerating electrical power from the thermal power of the combusted gas stream.2. The method of wherein the molar ratio of molecular oxygen to hydrogen sulfide is from 1.3:1 to 1.7:1.3. The method of wherein electrical power is generated from the thermal power of the combusted gas stream by exchanging sufficient heat between the combusted gas stream and a liquid aqueous stream to convert the liquid aqueous stream to steam and to cool the combusted gas stream claim 1 , where the cooled combusted gas stream is a flue gas stream comprising sulfur dioxide; expanding the steam through an expander to generate mechanical power and an expanded steam stream; and claim 1 , converting the mechanical power to electrical power.4. The method of claim 3 , further comprising the steps of exchanging heat between the expanded steam stream and a fluid having a boiling point at least 50° C. lower than the liquid of the liquid aqueous stream at 0.101 MPa and having a latent heat of vaporization of at least 350 kJ/kg to condense water from the expanded steam stream and to form a heat transfer gas from the fluid ...

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16-05-2013 дата публикации

Flexible seal system for a gas turbine engine

Номер: US20130121813A1
Принадлежит: United Technologies Corp

A flexible seal system for a gas turbine engine includes an annular mounting bracket, an annular support bracket, an annular flexible seal and a plurality of mounting spacers. The flexible seal extends axially between a first mounting segment and a second mounting segment. The first mounting segment is connected axially between the mounting bracket and the support bracket, and includes a plurality of mounting apertures that extend axially through the first mounting segment. Each of the mounting spacers is arranged within a respective one of the mounting apertures, and extends axially between the mounting bracket and the support bracket.

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16-05-2013 дата публикации

TURBOJET ENGINE NACELLE

Номер: US20130121814A1
Принадлежит:

A nacelle for a turbojet engine is provided that includes an air intake upstream from the turbojet engine, a middle section intended to surround a fan of the turbojet engine and its case, and a downstream section. The middle section is made from at least one aerostructure capable of ensuring external aerodynamic continuity of the nacelle, and the aerostructure is rigidly bound, so as to be able to be taken apart, to at least one surrounding fixed structure. 1. A nacelle for a turbojet engine , comprising:an air intake upstream from the turbojet engine;a middle section intended to surround a fan of the turbojet engine and its case; anda downstream section,the middle section being made from at least one aerostructure capable of ensuring external aerodynamic continuity of the nacelle, characterized in that said aerostructure is rigidly bound, so as to be able to be taken apart, to at least one surrounding fixed structure.2. The nacelle according to claim 1 , characterized in that the aerostructure comprises at least one hatch allowing access to the inside of the nacelle located in proximity to at least one of an upper twelve o'clock claim 1 , a lower so-six o'clock claim 1 , and a middle area.3. The nacelle according to claim 1 , characterized in that it comprises two aerostructures claim 1 , notably substantially hemicylindrical claim 1 , positioned on either side of a substantially longitudinal axis of the nacelle.4. The nacelle according to any of claim 1 , characterized in that the aerostructure is rigidly connected claim 1 , so as to be able to be taken apart claim 1 , to a pylon or an interface for connecting the nacelle to a pylon.5. The nacelle according to claim 1 , characterized in that the aerostructure is rigidly bound claim 1 , so as to be able to be taken apart claim 1 , to a lower longitudinal beam.6. The nacelle according to claim 1 , characterized in that the aerostructure is bound to another aerostructure claim 1 , notably in the lower portion.7. The ...

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16-05-2013 дата публикации

TURBINE HOUSING FOR A TURBOCHARGER OF TWIN SCROLL TYPE

Номер: US20130121820A1
Принадлежит: MITSUBISHI HEAVY INDUSTRIES, LTD.

In a turbine housing of a turbocharger A of a twin-scroll type, a scroll-shaped passage is separated into a front scroll passage and a rear scroll passage by a partition wall A front wall and a root part of the partition wall curve toward a front side to secure cross-sectional areas a a a and b b b The scroll passages are formed to have equal cross-sectional areas, a tip part of the partition wall is arranged perpendicular to the turbine rotor blade and the scroll passages are symmetrical near the tip part about an axis X so as to eliminate the flow rate difference. 1. A turbine housing for a turbocharger of a twin-scroll type , comprising:a turbine shaft housed in the turbine housing;a partition wall formed in the housing; andtwo scroll passages, divided by the partition wall, including a front scroll passage and a rear scroll passage formed on a front side and a rear side respectively in the turbine housing, through the scroll passages exhaust gas flowing from outside toward inside in a radial direction and then flowing in an axial direction of the turbine shaft to be discharged, wherein a front wall of the front scroll passage curves toward the front side from the inside toward the outside in the radial direction so as to secure cross-sectional areas of the front scroll passage and the rear scroll passage,wherein a root part of the partition wall curves toward the front side in correspondence with the front wall so that the cross-sectional area of the front scroll passage equals to the cross-sectional area of the rear scroll passage, andwherein the cross-sectional areas of the front scroll passage and the rear scroll passage gradually decrease from the outside toward the inside in the radial direction and a tip part of the partition wall is arranged in a direction perpendicular to a leading edge of a turbine rotor blade so that the front scroll passage and the rear scroll passage are symmetrical near the tip part with respect to an axis of the tip part.2. The ...

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16-05-2013 дата публикации

GAS TURBINE ENGINE HAVING CORE AUXILIARY DUCT PASSAGE

Номер: US20130121824A1
Автор: Kupratis Daniel B.
Принадлежит: UNITED TECHNOLOGIES CORPORATION

A gas turbine engine system according to an exemplary aspect of the present disclosure includes, among other things, a nacelle assembly defined about an axis and a core engine positioned radially inward of the nacelle assembly and having a core passage and at least one core auxiliary duct passage. The at least one core auxiliary duct passage includes an inlet for receiving a portion of a core airflow from the core engine and an outlet for discharging the portion of the core airflow. At least one of the inlet and the outlet are selectively translatable to divert the portion of the core airflow into the at least one core auxiliary duct passage and a mixer disposed between the nacelle assembly and the core engine. 1. A gas turbine engine system , comprising:a nacelle assembly defined about an axis;a core engine positioned radially inward from said nacelle assembly and having a core passage and at least one core auxiliary duct passage, wherein said at least one core auxiliary duct passage includes an inlet for receiving a portion of a core airflow from said core engine and an outlet for discharging said portion of said core airflow, and at least one of said inlet and said outlet are selectively translatable to divert said portion of said core airflow into said at least one core auxiliary duct passage; anda mixer disposed between said nacelle assembly and said core engine.2. The system as recited in claim 1 , wherein said inlet is positioned upstream from said mixer.3. The system as recited in claim 1 , wherein said outlet is positioned downstream from said mixer.4. The system as recited in claim 1 , wherein said inlet includes at least one door and a translating ring that selectively translates said at least one door.5. The system as recited in claim 1 , wherein said outlet includes at least one door pivotable about a pivot.6. The system as recited in claim 1 , comprising a fan bypass passage disposed between said nacelle assembly and said core engine.7. The system as ...

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23-05-2013 дата публикации

PREHEATING A SPARK PLUG

Номер: US20130125558A1
Принадлежит: SNECMA

A method of igniting a turbine engine using a spark plug including a first electrode, a second electrode, and a semiconductor body between the first electrode and the second electrode, the semiconductor body having an exposed surface, the ignition method including: generating a spark adjacent to the exposed surface by applying a voltage difference greater than a first predetermined threshold between the first electrode and the second electrode; and prior to generating a spark, a preheating applying a voltage difference less than a second predetermined threshold between the first electrode and the second electrode, the second predetermined threshold being less than the first predetermined threshold. 110-. (canceled)11. A method of igniting a turbine engine using a spark plug including a first electrode , a second electrode , and a semiconductor body between the first electrode and the second electrode , the semiconductor body having an exposed surface , the ignition method comprising:generating a spark adjacent to the exposed surface by applying a voltage difference greater than a first predetermined threshold between the first electrode and the second electrode; andprior to generating a spark, a preheating including applying a voltage difference less than a second predetermined threshold between the first electrode and the second electrode, the second predetermined threshold being less than the first predetermined threshold.12. An ignition method according to claim 11 , wherein the preheating has a predetermined duration greater than 5 seconds.13. An ignition method according to claim 11 , wherein the first predetermined threshold is greater than 900 V.14. An ignition method according to claim 11 , wherein the second predetermined threshold is less than 900 V.15. An ignition method according to claim 14 , wherein the second predetermined threshold is less than or equal to 100 V.16. An ignition method according to claim 11 , wherein claim 11 , during the preheating ...

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23-05-2013 дата публикации

Gas turbine engine comprising a tension stud

Номер: US20130125559A1
Автор: Andrew Shepherd
Принадлежит: SIEMENS AG

A gas turbine engine including a rotor is disclosed. The rotor includes a stud extending along an axis, rotating elements of a first section, and rotating elements of a second section. The stud includes a first and second external end, the first external end adapted to engage a first pre-load nut or a shaft and the second external end adapted to engage a second pre-load nut or a shaft such that the set of rotating elements are secured. Thus stud includes a first shank connected to the first external end and a second shank connected to the second external end. The first shank is located in the first section and has a first diameter. The second shank is located in the second section and has a second diameter which is greater than the first diameter.

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23-05-2013 дата публикации

LATERAL TURBOJET IMPROVED IN ORDER TO LIMIT THE DEFORMATION THEREOF

Номер: US20130125560A1
Принадлежит: SNECMA

A turbojet includes an intermediate casing outer shroud connected to a front suspension and a primary structure connected to a rear suspension; the shroud and the primary structure are held in a coaxial relationship by arms with at least some of the arms being shaped and/or arranged to deform in response to thrust from the turbojet by creating a deforming torque between the shroud and the primary structure in opposition to opposing stress generated by the thrust. 19-. (canceled)10. A two-stream turbojet for attaching laterally to a fuselage of an airplane via two longitudinally spaced apart suspensions including a front suspension and a rear suspension , the turbojet comprising:an intermediate casing outer shroud attached to the front suspension; anda propulsion primary structure attached to the rear suspension;the intermediate casing outer shroud and the primary structure being held in a coaxial relationship by a set of arms, each arm including a right section that is hollow and being fastened by its ends to the shroud and to the primary structure; andwherein at least some of the arms are shaped and/or arranged so as to deform in response to thrust from the turbojet by creating a deforming torque between the shroud and the primary structure, the deforming torque having a direction opposite to stress that is generated under effect of the turbojet thrust by a lever arm between the thrust axis and the front suspension.11. A turbojet according to claim 10 , wherein the at least some of the arms are configured to provide coupling between shear and twisting so that a center of torsion of a right section of the arm is situated outside a midplane of the arm claim 10 , on a side opposite from the front suspension relative to the midplane.12. A turbojet according to claim 10 , wherein at least some of the arms include a slot extending from the shroud to the primary structure.13. A turbojet according to claim 12 , wherein the slot is closed by an elastomer seal.14. A turbojet ...

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23-05-2013 дата публикации

MULTI PIECE TURPOCHARGER HOUSING

Номер: US20130129479A1
Принадлежит: SCHAEFFLER TECHNOLOGIES AG & CO. KG

A turbocharger casing including a first casing part, wherein an oil line starts at a first opening on an outer side of the first casing part, runs through the first casing part and opens out at a second opening of a substantially hollow-cylindrical bearing receptacle of the first casing part. Such turbocharger casings of the prior art are produced in a complicated manner by a sand casting process and therefore give rise to high production costs. The teaching is to arrive, without functional losses, at a simple-to-produce and cost-effective turbocharger casing by the turbocharger casing having a second casing part attached to the first casing part and by both casing parts together forming a cooling water line provided for cooling the bearing receptacle. It is thus possible to arrive at a lightweight turbocharger casing by conventional machining production methods and joining technique, and this turbocharger casing can be produced cost-effectively. 110-. (canceled)11. A turbocharger housing comprising:a first housing part, an oil duct starting at a first opening of an outer side of the first housing part, extending right through the first housing part to open at a second opening into a substantially hollow cylindrical bearing receptacle of the first housing part, anda second housing part connected to the first housing part, the first and second housing parts together forming a cooling water conduit for cooling the bearing receptacle.12. The turbocharger housing as recited in wherein the second housing part is connected to the first housing part by at least one of gluing claim 11 , welding claim 11 , crimping and soldering.13. The turbocharger housing as recited in wherein connection of the second housing part to the first housing part is formed by two connecting seams extending along the cooling water conduit.14. The turbocharger housing as recited in wherein the cooling water conduit and the oil duct of the first housing part are machine finished.15. The turbocharger ...

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23-05-2013 дата публикации

TURBOCHARGER

Номер: US20130129492A1
Принадлежит: BORGWARNER INC.

A turbocharger () having a turbine housing (), a compressor housing () which has a compressor outlet (), and a silencer () which is arranged on an end region () on the compressor outlet () and which has a silencer housing () in which an insert part () is arranged so as to form at least one buffer chamber () which is connected via at least one opening () to an air-guiding duct (). The opening () has an edge () with a radially inner corner () which is designed so as not to have a sharp edge. 11. A turbocharger () having{'b': '2', 'a turbine housing (),'}{'b': 3', '20, 'a compressor housing () which has a compressor outlet (), and'}{'b': '21', 'claim-text': [{'b': 22', '20, 'which is arranged on an end region () on the compressor outlet () and'}, {'b': 23', '25', '24', '26', '27, 'which has a silencer housing () in which an insert part () is arranged so as to form at least one buffer chamber () which is connected via at least one opening () to an air-guiding duct (),'}, {'b': 26', '28', '29, 'wherein the opening () has an edge () with a radially inner corner () which does not have a sharp edge.'}], 'a silencer ()'}22930. The turbocharger as claimed in claim 1 , wherein the corner () is provided with a rounding ().32931. The turbocharger as claimed in claim 1 , wherein the corner () is provided with a bevel ().42932. The turbocharger as claimed in claim 1 , wherein the corner () is provided with an inwardly directed bulge ().523343334. The turbocharger as claimed in claim 1 , wherein the silencer housing () has another end region () claim 1 , and a connecting piece () on its other end region ().63533. The turbocharger as claimed in claim 5 , wherein an insert part () is arranged in the connecting piece ().73536. The turbocharger as claimed in claim 6 , wherein the insert part () is provided with slots ().823. The turbocharger as claimed in claim 1 , wherein the silencer housing () is a plastic part.9211. A silencer () of a turbocharger () claim 1 ,{'b': '23', 'claim- ...

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23-05-2013 дата публикации

EXHAUST-GAS TURBOCHARGER

Номер: US20130129497A1
Автор: Keller Peter
Принадлежит: BORGWARNER INC.

The invention relates to an exhaust-gas turbocharger () having a turbine () which has the following parts: a turbine wheel (); a turbine housing () in which is arranged at least one turbine channel () which has a passage opening () arranged upstream of the turbine wheel () as viewed in the exhaust-gas flow direction; and a shut-off device (), which is arranged downstream of the turbine channel () and upstream of the turbine wheel (), for opening and closing the passage opening (), wherein the shut-off device () has a shut-off sleeve () which is guided in a translatorially movable fashion in a groove () formed directly into the turbine housing (). 112. An exhaust-gas turbocharger () having a turbine () which has the following parts:{'b': '3', 'a turbine wheel ();'}{'b': 4', '5', '5', '6', '6', '3, 'a turbine housing () in which is arranged at least one turbine channel (, ′) which has a passage opening (, ′) arranged upstream of the turbine wheel () as viewed in the exhaust-gas flow direction; and'}{'b': 7', '5', '5', '3', '6', '6, 'a shut-off device (), which is arranged downstream of the turbine channel (, ′) and upstream of the turbine wheel (), for opening and closing the passage opening (, ′),'}{'b': 7', '12', '13', '4, 'wherein the shut-off device () has a shut-off sleeve () which is guided in a translatorially movable fashion in a groove () formed directly into the turbine housing ().'}2121416. The exhaust-gas turbocharger as claimed in claim 1 , wherein the shut-off sleeve () has at least one web () whose free end () is connected to an actuating device.31214151617. The exhaust-gas turbocharger as claimed in claim 1 , wherein the shut-off sleeve () has preferably two webs ( claim 1 , ) which are arranged approximately diametrically opposite one another and whose free ends ( ) are connected to an actuating device.412181916171415. The exhaust-gas turbocharger as claimed in claim 2 , wherein the shut-off sleeve () is connected to the actuating device via a lever ...

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23-05-2013 дата публикации

ADAPTABLE EXHAUST FAN HOUSING

Номер: US20130129499A1
Принадлежит:

The present invention provides an adaptable fan housing having indentation markings to facilitate the installation of the fan housing. The present invention also provides positioning clips and securing clips allowing to further facilitate the installation of a fan housing of the present invention within a ceiling or a wall. The present invention also has cover clips which allows an easy installation of a cover to be secured to the fan housing. 1. An adaptable fan housing comprising:at least one fixture marking positioned along a housing edge of the fan housing;at least one positioning clip for operatively coupling to the housing edge at a corresponding fixture marking of the at least one fixture marking on the housing;wherein the at least one positioning clip facilitates mounting of the housing in an opening.2. An adaptable fan housing according to claim 1 , further comprising at least one securing clip for operatively coupling to the at least one positioning clip and the housing.3. An adaptable fan housing according to claim 1 , further comprising a plurality of positioning clips.4. An adaptable fan housing according to claim 1 , wherein the housing has at least one rail housing support for further facilitating the mounting of the housing in the opening.5. An adaptable fan housing according to claim 1 , further comprising a fan unit operatively coupled to the housing.6. An adaptable fan housing according to claim 1 , further comprising at least one rail for operatively coupling to a corresponding support of the at least one rail housing support in the housing.7. An adaptable fan housing according to claim 5 , further including a fan cover; wherein the fan unit further includes at least one cover clip for flexibly engaging at least one receiving aperture in the fan cover to mount the fan cover to the housing.8. A fan housing system comprising:a) a fan housing;b) a fan cover having at least one receiving aperture;c) a fan unit for operatively coupling to the fan ...

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30-05-2013 дата публикации

Starter Control Valve Prediction System to Predict and Trend Starter Control Valve Failures in Gas Turbine Engines Using a Starter Control Valve Health Prognostic, Computer Readable Medium and Related Methods

Номер: US20130133306A1
Принадлежит: LOCKHEED MARTIN CORPORATION

Starter control valve failure prediction machines, systems, computer readable media, program products, and computer implemented methods to predict and trend starter control valve failures in gas turbine engines using a starter control valve health prognostic and to make predictions of starter control valve failures, are provided. A computer implemented method according to an embodiment of the present invention can include the steps of generating a continuous starter control valve deterioration trend function responsive to a plurality of health indices derived from gas turbine engine startup data downloaded from gas turbine engine sensors for a plurality of startups and analyzing the continuous starter control valve deterioration trend function to identify potential starter control valve failure points where the points on the starter control valve deterioration trend function correlate to a starter control valve health prognostic responsive to historic gas turbine engine startup data downloaded from gas turbine engine sensors. 1. A computer implemented method to predict starter control valve failures in gas turbine engines using a starter control valve health prognostic , the method comprising the steps of:extracting one or more health index features from operational gas turbine engine startup data received for one or more gas turbine engine startups of one or more gas turbine engines of a certain gas turbine engine model;calculating a starter control valve health index for each of the one or more gas turbine engine startups responsive to the one or more health index features extracted from the operational gas turbine engine startup data to thereby define one or more health indices;comparing each of the one or more health indices to a starter control valve health prognostic for the certain gas turbine engine model; anddetermining, responsive to the step of comparing, a potential predictive starter control valve failure point, the potential predictive starter control ...

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30-05-2013 дата публикации

SEAL ARRANGEMENT AND A METHOD OF REPAIRING A SEAL ARRANGEMENT

Номер: US20130134682A1
Принадлежит: ROLLS-ROYCE PLC

The seal arrangement is arranged between the casing portions and a fluoropolymer O-ring seal is positioned between the casing portions. A first protecting member is positioned between the fluoropolymer O-ring seal and the casing portion and the first protecting member consists of a polymer and hydroxyapatite. The first protecting member consists of 50 to 80 wt % polymer and 20 to 50 wt % hydroxyapatite and incidental impurities. The first protecting member is located in an annular groove and is thus arranged between the casing portion and the fluoropolymer O-ring seal. The first protecting member is substantially U-shaped in cross-section and the fluoropolymer O-ring seal is positioned between the legs of the U-shaped cross-section first protecting member. The first protecting member prevents corrosion of the casing portion by the fluoropolymer O-ring seal. 1. A seal arrangement between a first component and a second component , a fluoropolymer seal member is positioned between the first component and the second component and a first protecting member is positioned between the fluoropolymer seal member and the first component , the first protecting member consisting of a polymer and hydroxyapatite or apatite , wherein the first component comprises a metal.2. A seal arrangement as claimed in wherein a second protecting member is positioned between the fluoropolymer seal member and the second component claim 1 , the second protecting member consisting of a polymer and hydroxyapatite or apatite claim 1 , wherein the second component comprises a metal.3. A seal arrangement as claimed in wherein the first protecting member consists of 50 to 80 wt % polymer and 20 to 50 wt % hydroxyapatite and incidental impurities.4. A seal arrangement as claimed in wherein the second protecting member consists of 50 to 80 wt % polymer and 20 to 50 wt % hydroxyapatite and incidental impurities.5. A seal arrangement as claimed in wherein the polymer consists of polyimide.6. A seal ...

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06-06-2013 дата публикации

FUEL NOZZLE AND METHOD OF REPAIR

Номер: US20130139513A1
Принадлежит: PRATT & WHITNEY CANADA CORP.

A modular fuel nozzle tip for a gas turbine engine includes a body defining one or more fuel conveying passages extending therethrough, an annular cap having a radially inner shoulder surface interfacing with the peripheral end surface of the body to define a plurality of air channels extending through the head portion of the modular fuel nozzle tip. At least two fasteners fasten the annular cap to the body. 1. A modular fuel nozzle tip for a gas turbine engine , the modular fuel nozzle tip comprising:a fuel conveying body defining one or more fuel conveying passages extending between an inlet end and an outlet end of the body, the outlet end having a head portion with a peripheral end surface, the head portion having web portions extending radially therefrom, and at least two projections extending from the end of said web portions;an annular cap circumscribing only the outlet of said fuel conveying body and having a radially inner shoulder surface interfacing with the peripheral end surface of the fuel conveying body, the peripheral end surface and the shoulder surface defining a plurality of air channels extending through the head portion of the modular fuel nozzle tip; andat least two fasteners fastening the annular cap to the fuel conveying body, said fasteners being circumferentially distributed about the annular cap, each of said fasteners extending through the annular cap and into one of the projections.2. The modular fuel nozzle tip according to claim 1 , wherein the at least two projections each contain a hole claim 1 , the annular cap contains at least two holes and the holes of the projections and the holes of the annular cap are circumferentially spaced and aligned.3. The modular fuel nozzle tip according to claim 2 , wherein each fastener extends through both the hole of one of the projections and one of the holes of the cap.4. The modular fuel nozzle tip according to claim 1 , wherein a concentric annular rim extends from the shoulder surface of the ...

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06-06-2013 дата публикации

COMBUSTOR LINER SUPPORT AND SEAL ASSEMBLY

Номер: US20130139514A1
Принадлежит:

A method is disclosed herein for reducing binding between a combustor liner of a gas turbine engine and a free-standing ring disposed about the combustor liner. The method comprises the step of disposing a rolling assembly to roll between the combustor liner and the free-standing ring during relative radial displacement. 1. A method for reducing binding between a combustor liner of a gas turbine engine and a free-standing ring disposed about the combustor liner comprising the of:disposing a rolling assembly to roll between the combustor liner and the free-standing ring during relative radial displacement while substantially preventing relative circumferential movement.2. The method of further comprising the step of:limiting the extent of relative radial displacement between the combustor liner and the free-standing ring to a predetermined design amount.3. The method of further comprising the step of:disposing a seal of variable width between the combustor liner and the free-standing ring, the variable width varying in at least one of a radial direction and a circumferential direction relative to an axis along which the gas turbine engine extends.4. The method of wherein the rolling assembly rolls radially along a length of a surface defined by one of the combustor liner and the free-standing ring during the relative radial displacement.5. The method of wherein the rolling assembly substantially prevents relative circumferential movement between the combustor liner and the free-standing ring while permitting the relative radial displacement between the combustor liner and the free-standing ring in a radial direction.6. The method of wherein the rolling assembly is rotatably engaged with both the combustor liner and the free-standing ring.7. The method of wherein the rolling assembly includes a plurality of pins engaged between the combustor liner and the free-standing ring.8. The method of wherein the plurality of pins are each received in one of a plurality of slots ...

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06-06-2013 дата публикации

Multi-spool intercooled recuperated gas turbine

Номер: US20130139519A1
Принадлежит: ICR Turbine Energy Corp USA

A method and apparatus are disclosed for a multi-spool gas turbine engine with a variable area turbine nozzle and a motor/alternator device on the highest pressure turbo-compressor spool for starting the gas turbine and power extraction during engine operation. During power down of the engine, the variable area turbine nozzle may be used in conjunction with power extraction to maintain a near constant combustor outlet temperature while controlling turbine inlet temperatures on the turbines downstream of the highest pressure turbine and controlling spool speed on the highest pressure turbine.

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06-06-2013 дата публикации

METHOD FOR MONITORING A CONTROL DEVICE OF A FUEL METERING VALVE OF A TURBOJET ENGINE

Номер: US20130139520A1
Принадлежит: SNECMA

A method for monitoring a control device of a fuel metering valve of an aircraft turbojet engine, the control device supplying a control current) to a servo valve in order to modify the position of the fuel metering valve, the method comprising: 1. Method for monitoring a control device of a fuel metering valve of an aircraft turbojet engine , the control device supplying a control current to a servo valve in order to modify the position of the fuel metering valve , the method comprising:a step for determining the position of the fuel metering valve during a flight of the aircraft;a step for determining the travelling speed of the fuel metering valve;a step for determining the control current when the travelling speed of the fuel metering valve is zero;a step for calculating a mean control current when the travelling speed of the fuel metering valve is zero, the mean control current forming an indicator of deterioration of the control device;a step for comparing the deterioration indicator with a reference base of indicators with deterioration so as to infer the type of deterioration from it;a step for calculating an abnormality score for the deterioration indicator;a step for comparing the abnormality score with a decision threshold of abnormality characteristic of the type of deterioration; anda step for releasing an alarm in case of violation of the decision threshold of abnormality.2. Method according to claim 1 , in which the deterioration indicator is normalized according to its standard deviation and average obtained over a plurality of flights during a learning phase.3. Method according to claim 2 , in which the abnormality score of the deterioration indicator is a function of the absolute value of the said normalized deterioration indicator.4. Method according to claim 1 , in which the reference base of indicators with deterioration comprises an indicator of deterioration of a positive drift and an indicator of deterioration of a negative drift.5. Method ...

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06-06-2013 дата публикации

MULTI-LAYER ACOUSTIC TREATMENT PANEL

Номер: US20130142624A1
Принадлежит:

A multilayer acoustic treatment panel including a first cellular-structure core sandwiched between a perforated skin and an intermediate skin; and a second cellular-structure core sandwiched between the intermediate skin and a continuous skin. The perforated skin includes at least one pair of high-porosity zones presenting a perforation ratio greater than a perforation ratio of a remainder of the perforated skin and including an inlet zone and an outlet zone longitudinally spaced apart from each other, the high-porosity zones of a given pair communicating through the first cellular-structure core and the intermediate skin with the two ends of a soundwave flow channel arranged in the second cellular-structure core. 113-. (canceled)14. A multilayer acoustic treatment panel comprising:a first cellular-structure core sandwiched between a perforated skin and an intermediate skin; anda second cellular-structure core sandwiched between the intermediate skin and a continuous skin;wherein the perforated skin includes at least one pair of high-porosity zones presenting a perforation ratio greater than a perforation ratio of a remainder of the perforated skin and including an inlet zone and an outlet zone that are longitudinally spaced apart from each other, the high-porosity zones of a given pair communicating through the first cellular-structure core and the intermediate skin with two ends of a soundwave flow channel arranged in the second cellular-structure core.15. A panel according to claim 14 , wherein the high-porosity zones of a given pair communicate with the soundwave flow channel via wells passing both through the first cellular-structure core and the intermediate skin.16. A panel according to claim 14 , wherein the high-porosity zones of a given pair communicate with the soundwave flow channel via wells passing through the first cellular-structure core and via a plurality of orifices formed through the intermediate skin.17. A panel according to claim 14 , wherein ...

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06-06-2013 дата публикации

AIRFOIL SEAL SYSTEM FOR GAS TURBINE ENGINE

Номер: US20130142630A1
Автор: Diakunchak Ihor S.
Принадлежит: SIEMENS POWER GENERATION, INC.

A turbine airfoil seal system of a turbine engine having a seal base with a plurality of seal strips extending therefrom for sealing gaps between rotational airfoils and adjacent stationary components. The seal strips may overlap each other and may be generally aligned with each other. The seal strips may flex during operation to further reduce the gap between the rotational airfoils and adjacent stationary components. 1. An airfoil seal system for airfoils of a gas turbine engine , comprising:a seal base configured to be received within a channel of a rotational airfoil proximate to a platform extending from the airfoil, wherein the seal base is generally an arcuate segment and wherein the seal base is configured to extend a length at least substantially equal to a length along an intersection between a rotational airfoil and an adjacent stationary component;a plurality of seal strips generally aligned with each other and overlapping each other, wherein the plurality of seal strips are attached to the seal base and extend generally radially inward from the seal base a length sufficient to seal a gap between the platform of the rotational airfoil and the adjacent stationary component;wherein the plurality of seal strips are flexible such that the seal strips may be flexed during operation of the gas turbine engine thereby sealing the gap between the platform of the rotational airfoil and the adjacent stationary component.2. The airfoil seal system for airfoils of a gas turbine engine of claim 1 , wherein the plurality of seal strips are formed from alloys.3. The airfoil seal system for airfoils of a gas turbine engine of claim 1 , wherein the plurality of seal strips are curved out of plane from the seal base such that when the seal base is attached to the channel of a rotational airfoil claim 1 , ends of the plurality of seal strips curve toward adjacent stationary components.4. The airfoil seal system for airfoils of a gas turbine engine of claim 3 , wherein the ...

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06-06-2013 дата публикации

Structural joint for connecting a first component to a segmented second component

Номер: US20130142643A1
Автор: Eric W. Malmborg
Принадлежит: United Technologies Corp

A structural joint includes a first flange, a second flange and a fastener with a head and a shaft. The first flange extends out from a first component to a distal first flange end. The second flange extends out from a segmented second component to a distal second flange end. The second flange includes a first lateral flange segment that extends laterally to a first flange sidewall, and a second lateral flange segment that extends laterally to a second flange sidewall, which is engaged with the first flange sidewall. The head is encased in the second flange and extends laterally into the first flange sidewall and the second flange sidewall. The shaft extends longitudinally out from the second flange and through the first flange.

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13-06-2013 дата публикации

SUBSTITUTION DEVICE FOR AIRCRAFT ENGINE

Номер: US20130145770A1
Принадлежит: AIRBUS OPERATIONS SAS

A substitution device for replacing a turbojet type of aircraft engine, with a nacelle comprising protective covers, and a support mast having two engine mounts, each of said protective covers being mounted to pivot between an open position and a closed position, said substitution device comprising a body, two anchors attaching to the engine mounts of the engine support mast, and bearing portions adapted to receive support portions belonging to the protective covers. A method for installing such a substitution device in a nacelle, which makes it possible to close the engine covers and authorize the movement of the aircraft. 2. The substitution device according to claim 1 , wherein the bearing portions are arranged substantially in an arc.5. The substitution device according to claim 1 , wherein the bearing portions are at least partially retractable.6. The substitution device according to claim 1 , further comprising a hydraulic unit and cylinders adapted for connecting the substitution device to at least the pair of covers.7. The substitution device according to claim 1 , further comprising wheels and a drawbar.8. The substitution device according to claim 1 , arranged in such a way that its center of gravity is located at or near the center of gravity of the engine which it replaces in the propulsion system.9. The substitution device according to claim 1 , further comprising lifting yokes. The present invention relates to substitution devices for an aircraft engine, in particular for turbojet engines.These substitution devices can be considered as support tools to assist with aircraft construction and maintenance. Under normal circumstances, such aircraft engines are usually attached to a supporting mast and protected by a nacelle which includes cowls (protective covers) surrounding the engine.According to known prior art, one (or several) engines must sometimes be removed for maintenance on said engine or for engine replacement. However, in order to remove an ...

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