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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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16-08-1997 дата публикации

УСТРОЙСТВО ДЛЯ БЕСКОНТАКТНОГО ИЗМЕРЕНИЯ ЛИНЕЙНЫХ ПЕРЕМЕЩЕНИЙ

Номер: RU0000004782U1
Автор: Вулах Владимир Моисеевич[UA], Кусенко Владимир Анатольевич[UA], Луговой Андрей Федорович[UA], Хрестовой Юрий Леонтьевич[UA]
Принадлежит: Хрестовой Юрий Леонтьевич

Устройство для бесконтактного измерения линейных перемещений, содержащее датчик трансформаторный и преобразователь сигналов, выход которого соединен с отображающим прибором, отличающееся тем, что устройство содержит блок согласования, вход которого подключен к выходу трансформаторного датчика, а выход соединен с преобразователем сигналов, при этом последний выполнен в виде электронно-вычислительного устройства, выход которого соединен с отображающим прибором. (19) RU (11) (13) 4 782 U1 (51) МПК F01D 19/02 (1995.01) G01B 7/14 (1995.01) РОССИЙСКОЕ АГЕНТСТВО ПО ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ (12) ОПИСАНИЕ ПОЛЕЗНОЙ МОДЕЛИ К СВИДЕТЕЛЬСТВУ (21), (22) Заявка: 5039391/06, 30.01.1992 (46) Опубликовано: 16.08.1997 (71) Заявитель(и): Хрестовой Юрий Леонтьевич (UA) (73) Патентообладатель(и): Хрестовой Юрий Леонтьевич (UA) U 1 4 7 8 2 R U Ñòðàíèöà: 1 U 1 (57) Формула полезной модели Устройство для бесконтактного измерения линейных перемещений, содержащее датчик трансформаторный и преобразователь сигналов, выход которого соединен с отображающим прибором, отличающееся тем, что устройство содержит блок согласования, вход которого подключен к выходу трансформаторного датчика, а выход соединен с преобразователем сигналов, при этом последний выполнен в виде электронно-вычислительного устройства, выход которого соединен с отображающим прибором. 4 7 8 2 (54) УСТРОЙСТВО ДЛЯ БЕСКОНТАКТНОГО ИЗМЕРЕНИЯ ЛИНЕЙНЫХ ПЕРЕМЕЩЕНИЙ R U (72) Автор(ы): Хрестовой Юрий Леонтьевич[UA], Вулах Владимир Моисеевич[UA], Кусенко Владимир Анатольевич[UA], Луговой Андрей Федорович[UA] RU 4 782 U1 RU 4 782 U1 RU 4 782 U1 RU 4 782 U1 RU 4 782 U1

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Номер записи: 1
10-01-2004 дата публикации

УСТРОЙСТВО ПУСКА ЭНЕРГОБЛОКА ТЕПЛОЭЛЕКТРОСТАНЦИЙ

Номер: RU0000035374U1
Автор: Дунаев Л.Л., Козлов С.К., Степанченко В.И., Сухоруков Е.М.
Принадлежит: Открытое акционерное общество "Ленинградский Металлический завод"

1. Устройство пуска энергоблока теплоэлектростанций, выполненное по однобайпасной схеме и содержащее трубопроводы, регенеративные подогреватели, парогенератор с промежуточным перегревом пара, цилиндры высокого и среднего давления (ЦВД и ЦСД) паровой турбомашины, снабженные регулирующими клапанами и стопорными клапанами, быстродействующую редукционно-охладительную установку (БРОУ), установленную на трубопроводе, соединяющем трубопровод свежего пара с конденсатором паровой турбины на участке перед стопорным клапаном ЦВД, установку РОУ, установленную на паропроводе, соединяющем трубопровод свежего пара с трубопроводом холодно промежуточного перегрева (ХПП) на участке перед стопорным клапаном ЦВД, а также задвижку, установленную на трубопроводе, соединяющем трубопровод горячего промежуточного перегрева (ГПП) с конденсатором турбины на участке перед стопорным клапаном ЦСД, отличающееся тем, что устройство дополнительно снабжают обратным клапаном, установленным на трубопроводе ХПП на участке между ЦВД и местом врезки отвода трубопровода на регенеративный подогреватель, трубопроводом байпаса обратного клапана на трубопроводе ХПП, который снабжают регулирующей и (или) запорной арматурой, а также регулирующим клапаном, установленным на трубопроводе, соединяющем трубопровод ГПП с конденсатором паровой турбины, который соответственно снабжают регулятором давления пара. 2. Устройство пуска энергоблока по п.1, отличающееся тем, что параметр уставки давления пара в трубопроводе ГПП выбирается постоянным и в интервале 20-90% от величины параметра уставки по давлению за РОУ. 3. Устройство пуска энергоблока по пп.1 и 2, отличающееся тем, что его дополнительно снабжают трубопроводом с запорной арматурой, соединяющим трубопроводы на участке после регулирующих клапанов ЦВД с конденсатором паровой турбины. 4. Устройство пуска энергоблока по пп.1 и 2, отличающееся тем, что его дополнительно снабжают трубопроводом с запорной арматурой, соединяющим камеру регулирующей ступени ЦВД с ...

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Номер записи: 2
10-09-2012 дата публикации

ЭНЕРГЕТИЧЕСКИЙ БЛОК С ОБЪЕДИНЕННЫМ СТОПОРНО-РЕГУЛИРУЮЩИМ КЛАПАНОМ НА ЛИНИЯХ ПОДВОДА ПАРА К ПАРОВОЙ ТУРБИНЕ И СО СТОПОРНЫМИ КЛАПАНАМИ НА ЛИНИЯХ СБРОСА ПАРА В КОНДЕНСАТОР

Номер: RU0000120144U1
Автор: Авруцкий Георг Давидович, Лазарев Михаил Васильевич
Принадлежит: Открытое акционерное общество "Всероссийский дважды ордена Трудового Красного Знамени теплотехнический научно-исследовательский институт"

Энергетический блок, содержащий паровую турбину с цилиндрами высокого, среднего и низкого давления и конденсатором, а также линии подвода к указанной турбине пара соответствующего давления с запорно-регулирующей арматурой, установленной по меньшей мере на линии подвода пара высокого давления, линию отвода пара на промперегрев и по меньшей мере одну быстродействующую редукционно-охладительную установку, подключенную по меньшей мере к линии подвода пара высокого давления и соединенную на выходе сбросной линией с указанным конденсатором непосредственно или через линию отвода пара на промперегрев, отличающийся тем, что паропроводная запорно-регулирующая арматура выполнена в виде одного для каждой линии подвода пара к турбине объединенного стопорно-регулирующего клапана, а на каждой сбросной линии или на объединяющей их общей сбросной линии перед конденсатором дополнительно установлен стопорный клапан. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (51) МПК F01D 19/00 (13) 120 144 U1 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ (21)(22) Заявка: ПОЛЕЗНОЙ МОДЕЛИ К ПАТЕНТУ 2012123422/28, 07.06.2012 (24) Дата начала отсчета срока действия патента: 07.06.2012 (72) Автор(ы): Авруцкий Георг Давидович (RU), Лазарев Михаил Васильевич (RU) (45) Опубликовано: 10.09.2012 Бюл. № 25 1 2 0 1 4 4 R U Формула полезной модели Энергетический блок, содержащий паровую турбину с цилиндрами высокого, среднего и низкого давления и конденсатором, а также линии подвода к указанной турбине пара соответствующего давления с запорно-регулирующей арматурой, установленной по меньшей мере на линии подвода пара высокого давления, линию отвода пара на промперегрев и по меньшей мере одну быстродействующую редукционноохладительную установку, подключенную по меньшей мере к линии подвода пара высокого давления и соединенную на выходе сбросной линией с указанным конденсатором непосредственно или через линию отвода пара на промперегрев, отличающийся тем, что паропроводная запорно-регулирующая ...

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Номер записи: 3
20-05-2013 дата публикации

УСТРОЙСТВО ДЛЯ ПУСКА ЭНЕРГОБЛОКА

Номер: RU0000128245U1
Автор: Баранов Вячеслав Николаевич, Николаев Сергей Федорович, Рульковский Алексей Владимирович
Принадлежит: Открытое акционерное общество "Сибтехэнерго" - инженерная фирма по наладке, совершенствованию технологий и эксплуатации электро-энергооборудования предприятий и систем

Устройство для пуска энергоблока, содержащее, как минимум, один паровой котел, как минимум, одну главную паровую задвижку, установленную на соответствующем участке внутри выходного паропровода, как минимум, одного парового котла, байпас, присоединенный своими выводами параллельно выводам, как минимум, одной главной паровой задвижки, как минимум, одну турбину, содержащую цилиндр низкого давления, цилиндр среднего давления, подсоединенный своей внутренней полостью к внутренней полости цилиндра низкого давления и через первый стопорный клапан к выходу промежуточного пароперегревателя, как минимум, одного парового котла, и цилиндр высокого давления, подсоединенный своей внутренней полостью к выходу второго стопорного клапана, включенного в разрыв входного паропровода, как минимум, одной турбины и к входу промежуточного пароперегревателя, как минимум, одного парового котла и редукционно-охладительную установку, подсоединенную своим первым и вторым входами к соответствующим внутренним полостям выходного паропровода, как минимум, одного парового котла, своим третьим входом к выходу первого датчика давления пара, установленного своим входом во внутренней полости выходного паропровода, как минимум, одного парового котла, своим первым выходом к циркводоводу и своим вторым выходом к первому входу конденсатора, подсоединенного своим вторым входом к внутренней полости цилиндра низкого давления, как минимум, одной турбины, при этом устройство для пуска энергоблока снабжено регулятором давления, установленным своим входом во внутренней полости входного паропровода, как минимум, одной турбины и своим выходом к управляющему входу дроссельно-регулирующего клапана байпаса. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (51) МПК F01D 19/00 (13) 128 245 U1 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ (21)(22) Заявка: ПОЛЕЗНОЙ МОДЕЛИ К ПАТЕНТУ 2012139079/06, 12.09.2012 (24) Дата начала отсчета срока действия патента: 12.09.2012 (45) Опубликовано: 20.05.2013 Бюл. № 14 1 ...

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Номер записи: 4
26-01-2012 дата публикации

Systems and methods for controlling the startup of a gas turbine

Номер: US20120017602A1
Автор: Brian Patrick Hansen, Christopher Edward LaMaster, David August Snider, Timothy Edward DeJoris
Принадлежит: General Electric Co

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

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Номер записи: 5
20-06-2013 дата публикации

System and method for warming up a steam turbine

Номер: US20130152587A1
Автор: Harold Lamar Jordan, JR., John Edward Sholes, JR., Tsungpo Lin
Принадлежит: General Electric Co

A system for warming up a steam turbine includes a gas turbine and a controller operably connected to the gas turbine. The controller is programmed to receive a plurality of measured input signals and control the gas turbine to produce an exhaust having a desired energy. A first measured input signal is reflective of a measured operating parameter of the gas turbine and a second measured input signal is reflective of an operating parameter of the steam turbine. A method for warming up a steam turbine includes sending a plurality of measured input signals to a controller, wherein a first measured input signal reflects a measured operating parameter of a gas turbine and a second measured input signal reflects an operating parameter of the steam turbine. The method further includes controlling the gas turbine based on the plurality of measured input signals and producing an exhaust from the gas turbine, wherein the exhaust has a desired energy.

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Номер записи: 6
04-07-2013 дата публикации

Methods and systems for turbine line replaceable unit fault detection and isolation during engine startup

Номер: US20130173135A1
Автор: Kyusung Kim
Принадлежит: Honeywell International Inc

Systems and methods for isolating a performance anomaly within one or more line replaceable units (LRUs) on a gas turbine engine by monitoring the start up transient are presented. The system comprises a set of sensors, an anomaly detector and a fault isolation reasoner. Each sensor of the set monitors at least one operating parameter of at least one engine component. The anomaly detector is configured to detect an anomaly in a component by comparing a particular value of an operating parameter to a base line value of that parameter. The specific cause of the startup anomaly is isolated utilizing a set of component reasoners that is based on the nature of the detected anomaly. The key events during the engine startup are identified by the combination of monitoring physically relevant phases of a startup and monitoring the engine control schedule. The values at these key events are used for comparing at the anomaly detector.

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Номер записи: 7
19-09-2013 дата публикации

PUMP, PUMP SYSTEM, METHOD OF CONTROLLING PUMP, AND COOLING SYSTEM

Номер: US20130243566A1
Автор: MIYAZAKI Takehide
Принадлежит: FUJITSU LIMITED

A pump includes: an impeller that moves fluid; a housing section, provided adjacent to a channel for the fluid, that communicate with the channel; and a controller that positions the impeller in the channel during a driving of the impeller and houses the impeller in the housing section during a stoppage of driving of the impeller. 1. A pump comprising:an impeller that moves fluid;a housing section, provided adjacent to a channel for the fluid, that communicate with the channel; anda controller that positions the impeller in the channel during a driving of the impeller and houses the impeller in the housing section during a stoppage of driving of the impeller.2. The pump according to claim 1 , further comprising claim 1 ,an electromagnet section provided in a location opposite to the housing section such that the channel is disposed therebetween,wherein the impeller includes a magnetic element controlled by the electromagnet section.3. The pump according to claim 2 , wherein the controller energizes the electromagnet section and positions the impeller in the channel during the driving of the impeller claim 2 , and the controller stops energizing the electromagnet section and houses the impeller in the housing section during the stoppage of driving of the impeller.4. The pump according to claim 2 , wherein the impeller includes a permanent magnet as the magnetic element.5. The pump according to claim 2 , wherein the controller positions the impeller in the channel using attraction of the magnetism of the electromagnet section during the driving of the impeller claim 2 , and the controller houses the impeller in the housing section using repulsion of the magnetism of the electromagnet section during the stoppage of driving of the impeller.6. The pump according to claim 2 , further comprising claim 2 ,a motor that rotates the electromagnet section,wherein the controller positions the impeller in the channel during a driving of the motor, and the controller houses the ...

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Номер записи: 8
07-11-2013 дата публикации

Method for starting a turbomachine

Номер: US20130291551A1
Автор: Hubert Pascal Verdier, Luc Reberga, Philippe Etchepare, Pierre Giralt
Принадлежит: Turbomeca SA

A method of starting a turbine engine, including a re-try performed if a main injector has not ignited when a shaft has reached a first predetermined speed value, the re-try including: a stopping during which a starter and the ignitor device are stopped; a second ignition during which fuel is injected into the combustion chamber, the ignitor device being actuated, the second ignition being performed when a speed of rotation of the shaft reaches a second predetermined speed value; and a second starting during which the starter is actuated once more to drive the shaft in rotation.

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Номер записи: 9
07-11-2013 дата публикации

Motor

Номер: US20130294888A1
Автор: Atsushi Yokoyama, Itsuro Sawada
Принадлежит: HITACHI LTD

A motor is provided which can detect a rotor temperature with high precision with a simple configuration not taking an influence on a temperature caused by circulation of a cooling oil into account. In a motor including a rotor, a stator arranged around the rotor, and a temperature sensor, the rotor includes an oil reservoir unit that reserves an oil on a rotating shaft line in an interior thereof, and the temperature sensor detects a temperature of the oil reserved in the oil reservoir unit.

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Номер записи: 10
28-11-2013 дата публикации

Neural network-based turbine monitoring system

Номер: US20130318018A1
Автор: Prabhanjana Kalya, Trevor Valder Jones
Принадлежит: General Electric Co

A neural network-based system for monitoring a turbine compressor. In various embodiments, the neural network-based system includes: at least one computing device configured to monitor a turbine compressor by performing actions including: comparing a monitoring output from a first artificial neural network (ANN) about the turbine compressor to a monitoring output from a second, distinct ANN about the turbine compressor; and predicting a probability of a malfunction in the turbine compressor based upon the comparison of the monitoring outputs from the first ANN and the second, distinct ANN.

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Номер записи: 11
02-01-2020 дата публикации

SYSTEM AND METHOD FOR PROVIDING END-USE SPECIFIC CUSTOMIZATION OF GAS TURBINE ENGINE OPERATION

Номер: US20200002019A1
Автор: "OBrien Timothy Ray", Petterson Brian, Riley Harold, Topper Paul
Принадлежит: HONEYWELL INTERNATIONAL INC.

A system and method provide aircraft-specific customization of gas turbine engine operation. The system includes a gas turbine engine, a first processing unit, and an engine controller. The first processing unit is configured to selectively transmit an activation key. The engine controller is in operable communication with the first processing unit and the gas turbine engine. The engine controller is configured to receive the activation key transmitted by the first processing unit and is operable, upon receipt of the activation key, to: verify the received activation key is correct, enable operational parameters in the gas turbine engine and the engine controller when the received activation key is correct, and control the gas turbine engine using the enabled operational parameters. 1. A system for providing end-use specific customization of gas turbine engine operation , the system comprising:a gas turbine engine;a first processing unit configured to transmit an activation key, the activation key having one or more operational parameters associated therewith; and verify the received activation key is correct by comparing the received activation key to one or more known-to-be-valid activation keys,', 'enable the one or more operational parameters associated with the activation key in the gas turbine engine and the engine controller when the received activation key is correct, and', 'control the gas turbine engine using the enabled operational parameters., 'an engine controller in operable communication with the first processing unit and the gas turbine engine, the engine controller configured to receive the activation key transmitted by the first processing unit and operable, upon receipt of the activation key, to2. The system of claim 1 , further comprising:a controller memory storage unit disposed within the engine controller, the controller memory storage unit having at least one known-to-be-valid activation key stored therein.3. The system of claim 1 , further ...

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Номер записи: 12
07-01-2021 дата публикации

COMPRESSED AIR ENERGY STORAGE POWER GENERATION APPARATUS AND COMPRESSED AIR ENERGY STORAGE POWER GENERATION METHOD

Номер: US20210003031A1
Автор: NAKAMICHI Ryo, Sato Takashi
Принадлежит: Kabushiki Kaisha Kobe Seiko Sho (Kobe Steel, Ltd.)

A compressed air energy storage power generation device includes motors, compressors that compress air, an accumulator tank that accumulates compressed air, expanders to driven by the compressed air supplied from the accumulator tank, generators, and a control device that controls driving of the motors. The control device includes a power supply command receiver that receives a power supply command, a priority setting unit that sets priority to the motors so that the motor whose elapsed time from stop is shorter has higher priority, a number-of-units determination unit that determines the number of the motors to be driven on the basis of an amount of input power indicated by the power supply command, and a drive unit that drives the motors in the descending order of the priority until the number of the driven motors becomes equal to the number of motors to be driven determined by the number-of-units determination unit. 1. A compressed air energy storage power generation device , comprising:a plurality of motors driven by input power;a plurality of compressors driven by the motors, respectively, to compress air;an accumulator tank configured to accumulate compressed air compressed by the compressors;an expander driven by the compressed air supplied from the accumulator tank;a generator driven by the expander to supply output power to a supply destination; anda control device configured to control driving of the motors, whereinthe control device includesa power supply command receiver configured to receive a power supply command indicating an amount of the input power before the input power is supplied,a priority setting unit configured to set priority to the motors so that the motor whose elapsed time from stop is shorter has higher priority,a number-of-units determination unit configured to determine the number of the motors to be driven on the basis of the amount of the input power indicated by the power supply command, anda drive unit configured to drive the ...

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Номер записи: 13
08-01-2015 дата публикации

Combined cycle power plant and method for operating such a combined cycle power plant

Номер: US20150007577A1
Автор: Camille Pedretti, Christoph Ruchti, Hongtao Li, Tjiptady NUGROHO
Принадлежит: Alstom Technology AG

The invention relates to a combined cycle power plant including a gas turbine the exhaust gas outlet of which is connected to a heat recovery steam generator, which is part of a water/steam cycle, whereby, for having a large power reserve and at the same time a higher design performance when operated at base load, the gas turbine is designed with a steam injection capability for power augmentation. For having a large power reserve at improved and optimized design performance when the plant is being operated at base load, the gas turbine includes at least one combustor, and a compressor for providing cooling air for that gas turbine, which is extracted from the compressor and cooled down in at least one cooling air cooler. The steam for steam injection is generated in said cooling air cooler, whereby said steam is injected into an air side inlet or outlet of said cooling air cooler and/or directly into said at least one combustor. The heat recovery steam generator is equipped with a supplementary firing, which is at least a single stage supplementary firing to increase the high pressure steam production and providing augmentation power as power reserve to a grid when required.

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Номер записи: 14
27-01-2022 дата публикации

SYSTEM AND METHODS FOR CONTROLLING SURGE MARGIN IN THE COMPRESSOR SECTION OF A GAS TURBINE ENGINE

Номер: US20220025824A1
Автор: Burkholder Graham Adam, Iwrey Benjamin Michael
Принадлежит:

Systems and methods are disclosed for controlling surge margin in the compressor section of a gas turbine engine. A first compressor section and a second compressor section are in fluid communication with a bypass conduit. An auxiliary turbine and discharge conduit are positioned in the bypass conduit. Fluid flow from the compressor sections into the bypass conduit is controlled by bypass control valves. 1. A system for controlling surge margin in a compressor section of a gas turbine engine , the system comprising: one or more compressor stages defining a first compressor section flowpath; and', 'a first compressor section discharge in fluid communication with the first compressor section flowpath;, 'a first compressor section comprisinga first compressor section bypass port positioned along the first compressor section and in fluid communication with the first compressor flowpath; one or more compressor stages defining a second compressor section flowpath, the second compressor section flowpath in fluid communication with the first compressor section flowpath; and', 'a second compressor section discharge in fluid communication with the second compressor section flowpath;, 'a second compressor section comprisinga second compressor section bypass port positioned along the second compressor section and in fluid communication with the second compressor section flowpath;a bypass conduit, extending between the first compressor section bypass port and the second compressor section bypass port;a first compressor section bypass control valve positioned in the bypass conduit downstream of the first compressor section bypass port;a second compressor section bypass control valve positioned in the bypass conduit downstream of the second compressor section bypass port;an auxiliary turbine positioned in the bypass conduit between the first compressor section bypass control valve and the second compressor section bypass control valve;a discharge conduit coupled to and in fluid ...

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Номер записи: 15
14-01-2021 дата публикации

GAS TURBINE ENGINE ELECTRICAL GENERATOR

Номер: US20210010382A1
Автор: DAVIES Paul R.
Принадлежит:

An aircraft gas turbine engine () comprises a main engine shaft (), a main engine shaft bearing arrangement () configured to rotatably support the main engine shaft () and an electric machine () comprising a rotor () and a stator (). The rotor () is mounted to the main engine shaft () and is rotatably supported by the main engine shaft bearing arrangement (), and the stator () is mounted to static structure () of the gas turbine engine (). 1. An aircraft gas turbine engine comprising:a main engine shaft;a main engine shaft bearing arrangement configured to rotatably support the main engine shaft; andan electric machine comprising a rotor and a stator; whereinthe rotor is mounted to the main engine shaft and is rotatably supported by the main engine shaft bearing arrangement, and the stator is mounted to static structure of the gas turbine engine.246. A gas turbine engine according to claim 1 , wherein the stator of the electric machine is cantilevered from the static structure () of the gas turbine engine.332. A gas turbine engine according to claim 2 , wherein the electric machine stator () is mounted by a mount member extending generally rearward or generally forward from a gas turbine engine static structure.4. A gas turbine engine according to claim 1 , wherein the main engine shaft comprises a radially inner portion and a radially outer portion separated by an annular space claim 1 , and joined at one end.5. A gas turbine engine according to claim 4 , wherein the electric machine rotor is mounted to the radially outer portion of the main engine shaft6. A gas turbine engine according to claim 5 , wherein the radially inner and radially outer portions may be joined by a fusible connector.7. A gas turbine engine according to claim 1 , wherein the main shaft bearing arrangement comprises a first bearing and a second bearing claim 1 , wherein the first bearing may comprise a radial load bearing claim 1 , and the second bearing may comprise a thrust bearing.8. A gas ...

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Номер записи: 16
10-01-2019 дата публикации

METHOD FOR COUPLING TWO SUB-SHAFTS

Номер: US20190010865A1
Автор: Winkel Michael
Принадлежит: SIEMENS AKTIENGESELLSCHAFT

A method for coupling a first sub-shaft, which has a first turbomachine and a generator connected to a mains supply, to a second sub-shaft, which has a second turbomachine, by means of an overrunning clutch, has the following steps: a) rotating the second sub-shaft with a starting rotational speed which is lower than the rotational speed of the first sub-shaft; b) measuring the mains frequency of the mains supply; c) measuring a differential angle between the first sub-shaft and the second sub-shaft; d) accelerating the second sub-shaft with an acceleration value which is produced using the mains frequency measured in step b), the differential angle and the starting rotational speed, and therefore the overrunning clutch couples the two sub-shafts to each other with a previously determined target coupling angle. 1. A method for coupling a first sub-shaft , which has a first fluid-flow machine and a generator connected to a mains supply , to a second sub-shaft , which has a second fluid-flow machine , by means of an overrunning clutch , comprising the steps:a) rotating the second sub-shaft with an initial rotational speed which is lower than the rotational speed of the first sub-shaft;b) measuring the mains frequency of the mains supply;c) measuring a differential angle between the first sub-shaft and the second sub-shaft;d) accelerating the second sub-shaft with an acceleration value which is produced by using the mains frequency measured in step b), the differential angle and the initial rotational speed, so that the overrunning clutch couples the two sub-shafts to each other with a previously determined target coupling angle;e) measuring a new mains frequency during the accelerations of the second sub-shaft;f) in the event that the new mains frequency is different from the mains frequency measured in step b), accelerating the second sub-shaft with a changed acceleration value, which is produced by using the new mains frequency.2. The method as claimed in claim 1 , ...

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Номер записи: 17
09-01-2020 дата публикации

POWER PLANT METHODS AND APPARATUS

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

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

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Номер записи: 18
03-02-2022 дата публикации

METHOD FOR MONITORING THE OPERATING STATE OF AN OVERPRESSURE VALVE

Номер: US20220034234A1
Автор: DENEUVE Sébastien Jean Fernand
Принадлежит: SAFRAN AIRCRAFT ENGINES

The invention relates to a method for monitoring the operating state of an overpressure valve of a turbine engine, the turbine engine comprising a fluid circuit, at least one pressure sensor for the fluid in the fluid circuit, a temperature sensor for the fluid in the fluid circuit, said overpressure valve being configured to limit the maximum fluid pressures in the fluid circuit, and the method comprising the following steps:—(E) determining an opening or closing indicator of the overpressure valve on the basis of the change in the fluid pressure over time;—(E) determining an operating state of the valve as a function of a fluid threshold temperature and of the determined opening or closing indicator of the overpressure valve. 1. A method for monitoring the operating state of a turbomachine pressure relief valve , the turbomachine comprising a fluid circuit , at least one fluid pressure sensor in the fluid circuit , a fluid temperature sensor in the fluid circuit , said pressure relief valve being configured to limit the maximum fluid pressures in the fluid circuit and to open if the fluid temperature is smaller than a threshold fluid temperature , and the method comprising the following steps:{'b': '2', '(E) determining an indicator of opening or closing of the pressure relief valve from the temporal evolution of the fluid pressure;'}{'b': '3', '(E) determining an operating state of the valve as a function of a fluid temperature measured by the fluid sensor, of a fluid threshold temperature and of the determined indicator of opening or closing of the pressure relief valve.'}22. The method for monitoring the operating state of a turbomachine pressure relief valve according to the preceding claim , wherein the step (E) of determining an indicator of opening or closing of the pressure relief valve is carried out as a function of the derivative or of the second derivative of the fluid pressure as a function of time.32. The method for monitoring the operating state of ...

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Номер записи: 19
25-01-2018 дата публикации

PRE-START MOTORING SYNCHRONIZATION FOR MULTIPLE ENGINES

Номер: US20180022463A1
Автор: Celiberti Louis A., Dunn James W., Kmetz Christopher P., Teicholz Matthew D.
Принадлежит:

An aspect includes a system for pre-start motoring synchronization for multiple engines of an aircraft. The system includes a first engine starting system of a first engine and a controller. The controller is operable to synchronize a motoring time of the first engine starting system with one or more other engine starting systems of one or more other engines of the aircraft by extending the motoring time of the first engine starting system to match, within a synchronization tolerance, the motoring time of the one or more other engine starting systems in a pre-start motoring sequence. 1. A system for pre-start motoring synchronization for multiple engines of an aircraft , the system comprising:a first engine starting system of a first engine; anda controller operable to synchronize a motoring time of the first engine starting system with one or more other engine starting systems of one or more other engines of the aircraft by extending the motoring time of the first engine starting system to match, within a synchronization tolerance, the motoring time of the one or more other engine starting systems in a pre-start motoring sequence.2. The system as in claim 1 , wherein the motoring time of the first engine starting system is synchronized with the one or more other engine starting systems by comparing an initial value of the motoring time of the first engine starting system with an initial value of the motoring time of the one or more other engine starting systems and selecting a largest value as the motoring time for the first engine starting system and the one or more other engine starting systems.3. The system as in claim 2 , wherein the controller provides the initial value of the motoring time of the first engine starting system to one or more other controllers and receives the initial value of the motoring time of the one or more other engine starting systems from the one or more other controllers.4. The system as in claim 2 , wherein the controller maintains ...

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Номер записи: 20
25-01-2018 дата публикации

CROSS ENGINE COORDINATION DURING GAS TURBINE ENGINE MOTORING

Номер: US20180022464A1
Автор: Berry James K., Clauson Jesse W., Gelwan David
Принадлежит:

A system is provided for cross engine coordination during gas turbine engine motoring. The system includes a first gas turbine engine of a first engine system, a first air turbine starter of the first engine system, a first starter air valve of the first engine system, and a controller. The controller is operable to command the first starter air valve to control delivery of compressed air to the first air turbine starter during motoring of the first gas turbine engine, monitor cross engine data of a second gas turbine engine of a second engine system to detect a present condition or a commanded action that modifies an aspect of the compressed air received at the first starter air valve, and command an adjustment to the first engine system to compensate for the modified aspect of the compressed air based on the cross engine data. 1. A system for cross engine coordination during gas turbine engine motoring , the system comprising:a first gas turbine engine of a first engine system;a first air turbine starter of the first engine system;a first starter air valve of the first engine system; anda controller operable to command the first starter air valve to control delivery of compressed air to the first air turbine starter during motoring of the first gas turbine engine, monitor cross engine data of a second gas turbine engine of a second engine system to detect a present condition or a commanded action that modifies an aspect of the compressed air received at the first starter air valve, and command an adjustment to the first engine system to compensate for the modified aspect of the compressed air based on the cross engine data.2. The system as in claim 1 , wherein the compressed air is driven by an auxiliary power unit of the aircraft claim 1 , a ground cart claim 1 , or a cross engine bleed.3. The system as in claim 1 , wherein the controller commands the first starter air valve based on one or more of: an engine speed of a starting spool of the first gas turbine ...

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Номер записи: 21
25-01-2018 дата публикации

MULTI-ENGINE COORDINATION DURING GAS TURBINE ENGINE MOTORING

Номер: US20180023413A1
Автор: Bostwick David M., Chowdhury Subhradeep, Gelwan David, Schwarz Frederick M.
Принадлежит:

A system is provided for multi-engine coordination of gas turbine engine motoring in an aircraft. The system includes a controller operable to determine a motoring mode as a selection between a single engine dry motoring mode and a multi-engine dry motoring mode based on at least one temperature of a plurality of gas turbine engines and initiate dry motoring based on the motoring mode. 1. A system for multi-engine coordination of gas turbine engine motoring in an aircraft , the system comprising:a controller operable to determine a motoring mode as a selection between a single engine dry motoring mode and a multi-engine dry motoring mode based on at least one temperature of a plurality of gas turbine engines and initiate dry motoring based on the motoring mode.2. The system as in claim 1 , wherein the at least one temperature is a measured core engine temperature or an oil temperature.3. The system as in claim 1 , wherein dry motoring is inhibited when the aircraft is not on the ground.4. The system as in claim 1 , wherein the motoring mode is further determined based on a plurality of performance parameters that are based on one or more of: an ambient condition claim 1 , performance limitations of a compressed air source and each air turbine starter driven by the compressed air source claim 1 , engine drag claim 1 , and parasitic factors.5. The system as in claim 4 , wherein the performance parameters are determined based on one or more of: an ambient air temperature claim 4 , an ambient pressure claim 4 , and an oil temperature.6. The system as is claim 1 , wherein the compressed air source is an auxiliary power unit of the aircraft claim 1 , a ground cart claim 1 , or a cross engine bleed.7. The system as in claim 1 , wherein the controller is further operable to monitor a speed of each of the gas turbine engines when dry motoring is active and switch from the multi-engine dry motoring mode to the single engine dry motoring mode based on one or more of the gas ...

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Номер записи: 22
25-01-2018 дата публикации

AIR SUPPLY CONTROL DURING MOTORING OF A GAS TURBINE ENGINE

Номер: US20180023479A1
Автор: Clauson Jesse W., Gelwan David
Принадлежит:

A system for motoring a gas turbine engine of an aircraft is provided. The system includes an air turbine starter, a starter air valve operable to deliver compressed air to the air turbine starter, and a controller. The controller is operable to control motoring of the gas turbine engine, detect a fault condition that prevents the controller from maintaining a motoring speed below a threshold level, and command a mitigation action that reduces delivery of the compressed air to the air turbine starter based on detection of the fault condition. 1. A system for motoring a gas turbine engine of an aircraft , the system comprising:an air turbine starter;a starter air valve operable to deliver compressed air to the air turbine starter; anda controller operable to control motoring of the gas turbine engine, detect a fault condition that prevents the controller from maintaining a motoring speed below a threshold level, and command a mitigation action that reduces delivery of the compressed air to the air turbine starter based on detection of the fault condition.2. The system as in claim 1 , wherein the compressed air is driven by an auxiliary power unit of the aircraft.3. The system as in claim 2 , wherein the controller relays the command for the mitigation action to the auxiliary power unit through an engine control interface using a digital communication bus.4. The system as in claim 3 , wherein the mitigation action comprises opening one or more bleed valves to purge the compressed air.5. The system as in claim 4 , wherein the controller receives state information of the one or more bleed valves through the engine control interface.6. The system as is claim 1 , wherein the mitigation action comprises shutting one or more supply valves of the compressed air.7. The system as in claim 1 , wherein the fault condition comprises a stuck open position of the starter air valve.8. The system as in claim 1 , wherein the fault condition comprises a pressure surge of the compressed ...

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Номер записи: 23
26-01-2017 дата публикации

Start-Up Control Device and Start-Up Control Method for Power Plant

Номер: US20170023933A1
Автор: Atsushi Yamashita, Eunkyeong Kim, Kazunori Yamanaka, Miyuki Kawata, Norihiro Iyanaga, Takuya Yoshida, Tatsuro Yashiki, Yasuhiro Yoshida
Принадлежит: Mitsubishi Hitachi Power Systems Ltd

To provide a start-up control device and a start-up control method for a power plant capable of changing the start-up completion estimated time to a desired time simply and safely while starting the power plant. The start-up control device includes an equipment state quantity acquisition unit acquiring an equipment state quantity of the power plant, a start-up schedule calculation unit calculating a current start-up schedule based on the equipment state quantity and a first thermal stress limiting value and calculating a start-up schedule changing plan based on the equipment state quantity and a second thermal stress limiting value, an equipment operation amount calculation unit calculating an equipment operation amount of the power plant based on the current start-up schedule, a screen display unit displaying respective start-up completion estimated times of the current start-up schedule and the start-up schedule changing plan, and an instruction input unit instructing the start-up schedule calculation unit to perform switching from the current start-up schedule to the start-up schedule changing plan.

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Номер записи: 24
28-01-2021 дата публикации

METHOD FOR OPERATING A STEAM TURBINE

Номер: US20210028730A1
Автор: KOWALSKI Matthias, SIEVERT Roland
Принадлежит: SIEMENS AKTIENGESELLSCHAFT

A method for operating a steam turbine, wherein the pressure of the cooling medium in the generator is changed not only for cooling but also for increasing or decreasing the torque of the generator on the steam turbine, this being utilized for the purpose of the start-up or shut-down process. 1. A method for operating a steam turbine , wherein the steam turbine has a rotatably mounted steam turbine rotor and a housing which is arranged around the steam turbine rotor , wherein the rotor is coupled in terms of torque to a generator rotor of an electrical generator , the method comprising:cooling the generator with a cooling medium, wherein a cooling pressure of the cooling medium in the generator is set,exerting a torque by the generator rotor on the steam turbine rotor,changing the torque from the generator rotor to the steam turbine rotor by means of a change in the cooling pressure.2. The method as claimed in claim 1 ,wherein an increase in the cooling pressure leads to an increase in the torque from the generator rotor to the steam turbine rotor.3. The method as claimed in claim 1 ,wherein a reduction in the cooling pressure leads to a reduction in the torque from the generator rotor to the steam turbine rotor.4. The method as claimed in claim 1 ,wherein the cooling pressure is changed during a startup process of the steam turbine.5. The method as claimed in claim 1 ,wherein the cooling pressure is changed during the shutdown process of the steam turbine.6. The method as claimed in claim 1 ,wherein an automation system for regulating the cooling pressure is designed such that an increase in the pressure and/or in the mass flow of the steam into the steam turbine is realized within specific limits.7. The method as claimed in claim 6 ,wherein the automation system is furthermore designed such that a change, or a reduction, in the mass flow of the steam into the steam turbine is realized within specific limits.8. The method as claimed in claim 7 ,wherein the change ...

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Номер записи: 25
17-02-2022 дата публикации

TURBINE ENGINE AND METHOD OF COOLING

Номер: US20220049619A1
Автор: Ansari Amid, Gillingham Thomas Earl, Hon Robert Charles, McCambridge Michael Scott
Принадлежит:

A method of mitigating thermal rotor bow in a rotor assembly of a turbine engine may include performing a plurality of motoring cycles. The plurality of motoring cycles may include receiving feedback on a temperature within a turbine engine in a post-shutdown state, actuating a starter motor when the temperature is greater than a predetermined threshold, operating the starter motor for a motoring time to exhaust some residual heat from the turbine engine, and shutting down the starter motor after the motoring time. 120-. (canceled)21. A method of mitigating thermal rotor bow in a rotor assembly of a turbine engine , the method comprising:performing a plurality of motoring cycles, the plurality of motoring cycles comprising:receiving feedback on a temperature within a turbine engine in a post-shutdown state;actuating a starter motor when the temperature is greater than a predetermined threshold;operating the starter motor for a motoring time to exhaust some residual heat from the turbine engine; andshutting down the starter motor after the motoring time.22. The method of claim 21 , wherein the motoring time comprises a predetermined duration.23. The method of claim 21 , wherein operating the starter motor for the motoring time comprises operating the starter motor until the temperature is reduced below a second predetermined threshold.24. The method of claim 21 , comprising:receiving feedback on a running time of the turbine engine; andperforming the plurality of motoring cycles if the running time of the turbine engine is greater than a predetermined running time-threshold.25. The method of claim 21 , wherein actuating the starter motor comprises:actuating the starter motor at a preset time after a full stop command corresponding to the post-shutdown state.26. The method of claim 25 , wherein the preset time allows some thermal rotor bow to form before actuating the starter motor.27. The method of claim 21 , comprising:allowing some thermal rotor bow to form when ...

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Номер записи: 26
17-02-2022 дата публикации

STARTER/GENERATOR

Номер: US20220049648A1
Автор: Bennett Brian R., Clemens Stanford, Hughes Melissa, Renback Randal
Принадлежит:

A starter generator located within a sump region of a turbofan engine and coupled to an adapter shaft. The adapter shaft rotationally coupled to the high pressure shaft, forward of a high pressure shaft bearing, and secured by a spanner nut. The engine makes use of two pluralities of electrical conductors, the first extends through an electrical conduit defined by a forward strut extending from the sump region to the outward casing, the second extends axially away from the electric starter. Each of the first plurality of electrical conductors makes reversible contact with a respective one of the second plurality of electrical conductors via an elbow/pin connector, producing a tight turn in area of limited space. 1. A gas turbine engine comprising:a high pressure spool and a low pressure spool, the low pressure spool including a low pressure shaft operably connected to a fan, the high pressure spool including a high pressure shaft operably connected to a high pressure turbine, the low pressure shaft and the high pressure shaft being co-axial with one another;a rotor of an electric starter generator coupled to the high pressure shaft;a stator disposed radially outward of the rotor;a high pressure shaft bearing;a forward strut supporting the high pressure shaft bearing; anda plurality of conductors electrically coupled to the stator and extending radially through the forward strut to an outer casing of the gas turbine engine.2. The gas turbine engine of claim 1 , wherein the plurality of conductors comprise a first plurality of conductors claim 1 , further comprising a second plurality of conductors electrically coupled between the rotor and the first plurality of conductors claim 1 , wherein the second plurality of conductors extend substantially axially.3. The gas turbine engine of claim 2 , further comprising a pin connector connecting conductors of the first plurality of conductors and conductors of the second plurality of conductors.4. The gas turbine engine of ...

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Номер записи: 27
31-01-2019 дата публикации

Air turbine starter

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

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

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Номер записи: 28
07-02-2019 дата публикации

SYSTEM AND METHOD FOR ROTATING A GAS TURBINE ENGINE DURING A MOTORING CYCLE

Номер: US20190040799A1
Автор: Bostwick David M., Clauson Jesse W., Gelwan David
Принадлежит: UNITED TECHNOLOGIES CORPORATION

Systems and methods for rotating a gas turbine engine during a motoring cycle are provided. The system may comprise a controller in electronic communication with an auxiliary power unit (APU), a starter air valve, and a gas turbine engine. The APU may supply compressed air to the starter air valve which may supply the compressed air to an engine starter in mechanical communication with the engine. The rotational speed of the engine may be controlled by the engine starter based on the pressure of the compressed air received from the starter air valve. The controller may be configured to control airflow and air pressure through the system, by modulating the airflow from the APU and/or from the starter air valve. 1. A system , comprising:a sensor configured to measure a rotational speed of the gas turbine engine;a controller in electronic configuration with a starter air valve, an auxiliary power unit (APU), and the sensor; and receiving, by the controller, the rotational speed of the gas turbine engine from the sensor;', 'transmitting, by the controller, an APU command to the APU, wherein the APU command is based on the rotational speed of the gas turbine engine and is configured to control a pressure of the supply airflow to the starter air valve; and', 'transmitting, by the controller, a starter air valve command to the starter air valve, wherein the starter air valve command is based on the engine sensor feedback and is configured to control an output pressure of the airflow to the engine starter., 'a tangible, non-transitory memory configured to communicate with the controller, the tangible, non-transitory memory having instructions stored thereon that, in response to execution by the controller, cause the controller to perform operations comprising2. The system of claim 1 , wherein the operations further comprise the step of controlling claim 1 , by the controller claim 1 , a speed of rotation in the gas turbine engine by modulating the output pressure of the ...

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Номер записи: 29
06-02-2020 дата публикации

Gas Turbine Engine Heaters

Номер: US20200040762A1
Автор: Abbott Michael T., Boyce Benjamin J.
Принадлежит:

An engine heater system for heating a diesel engine of a vehicle. The engine heater system including a gas turbine. A heat exchanger communicatively coupled to an exhaust of the gas turbine. An electric generator including connection members to couple to a battery of the vehicle, and a shaft rotatably attached between the gas turbine and the electric generator. The heat exchanger utilizes the exhaust of the gas turbine to keep the diesel engine of the vehicle within a desired temperature range, and the electric generator charges the battery when the gas turbine rotates the shaft. 1. An engine heater system for heating a diesel engine of a vehicle , the engine heater system comprising:a gas turbine;a heat exchanger communicatively coupled to an exhaust of the gas turbine;an electric generator including connection members to couple to a battery of the vehicle; anda shaft rotatably attached between the gas turbine and the electric generator;wherein the heat exchanger utilizes the exhaust of the gas turbine to keep the diesel engine of the vehicle within a desired temperature range, and the electric generator charges the battery when the gas turbine rotates the shaft.2. The engine heater system of claim 1 , wherein the engine heater system is onboard of the vehicle.3. The engine heater system of claim 1 , wherein the vehicle comprises a locomotive claim 1 , a ship claim 1 , or a truck.4. The engine heater system of claim 1 , wherein the electric generator further includes connection members to couple to an electric motor of a coolant pump.5. The engine heater system of claim 1 , wherein the heat exchanger utilizes the exhaust of the gas turbine to heat an engine oil of the diesel engine of the vehicle to keep the diesel engine within the desired temperature range.6. The engine heater system of claim 1 , wherein the heat exchanger utilizes the exhaust of the gas turbine to heat an engine coolant of the diesel engine of the vehicle to keep the diesel engine within the ...

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Номер записи: 30
06-02-2020 дата публикации

Combustor Systems

Номер: US20200041130A1
Автор: Benjamin J. Boyce, Michael T. ABBOTT
Принадлежит: Hotstart Inc

An engine heater system for heating a diesel engine of a vehicle. The engine heater system including a gas turbine. A heat exchanger communicatively coupled to an exhaust of the gas turbine. An electric generator including connection members to couple to a battery of the vehicle, and a shaft rotatably attached between the gas turbine and the electric generator. The heat exchanger utilizes the exhaust of the gas turbine to keep the diesel engine of the vehicle within a desired temperature range, and the electric generator charges the battery when the gas turbine rotates the shaft.

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Номер записи: 31
19-02-2015 дата публикации

METHOD FOR OPERATING AN ELECTRIC UNIT FOR A PUMPED-STORAGE POWER PLANT

Номер: US20150048623A1
Автор: Hillberg Claes, Schaub Christoph, Stephan Carl-Ernst, Traxler-Samek Georg
Принадлежит: ABB TECHNOLOGY AG

A pump-storage power plant, such as an electric unit, for this purpose can include a rotating electric synchronous machine and a frequency converter as well as a method for operating the electric unit. An exemplary method provides that the frequency converter is used to start the turbine and an output of the electric machine is fed directly into the current network after start-up, for example. Another exemplary method provides that the frequency converter is used to start the pump and the pump is started directly from rest and under load of a flooded pump or a water column, for example. Another exemplary method provides that the electric machine is synchronised with a frequency of the current network and is operated synchronously with the current network independent of the operating state of the pump or the turbine and supplies active power and reactive power. 1. A method for operating an electric unit for a pumped-storage power plant , wherein the electric unit includes a rotating electric synchronous machine and a frequency converter , wherein the frequency converter is connected to a stator of the synchronous machine , and wherein the synchronous machine is connected to a turbine and to an electric grid via the frequency converter , the method comprising:running up the turbine from standstill by generating a current flow in the electric grid via the frequency converter with continuous conversion of a frequency of the synchronous machine in an entire speed range of the turbine into a frequency of the electric grid.2. A method for operating an electric unit for a pumped-storage power plant , wherein the electric unit includes a rotating electric synchronous machine and a frequency converter , wherein the frequency converter is connected to a stator of the machine , and wherein the synchronous machine is connected to a pump and to an electric grid via the frequency converter , the method comprising:running up the pump from standstill by generating a current flow in ...

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Номер записи: 32
03-03-2022 дата публикации

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

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

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

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Номер записи: 33
03-03-2022 дата публикации

Air turbine starter

Номер: US20220065168A1
Автор: David Raju Yamarthi, Eliel Fresco Rodriguez, Parmeet Singh CHHABRA, Sagar Paramashivaiah, Shiloh Montegomery Meyers, Steven Ryan Kerley
Принадлежит: General Electric Co, Unison Industries LLC

An air turbine starter for starting an engine includes a starter housing defining an inlet, an outlet, and a flow path extending between the inlet and the outlet. A turbine section is located within the starter housing and includes a turbine member having a central disk and a set of airfoils spaced circumferentially about the central disk, as well as a sealing structure located within the starter housing.

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Номер записи: 34
26-02-2015 дата публикации

Apparatus and method for servicing gas turbine engines

Номер: US20150052910A1
Автор: Devin Patrick Perkins, William Lawrence Byrne
Принадлежит: General Electric Co

The present disclosure relates to an apparatus having an elongated body configured to be inserted into a tubular structure extending between a first combustor and a second combustor of a gas turbine engine. A movable arm may be positioned proximate to a first end of the elongated body, and the movable arm may be configured to engage a surface of the first combustor when the elongated body is placed within the tubular structure. A drive member may be accessible near a second end of the elongated body, and the drive member may be configured to rotate within the elongated body and to drive the movable arm along a longitudinal axis of the elongated body toward the second end to separate the tubular structure from the second combustor.

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Номер записи: 35
26-02-2015 дата публикации

Aircraft engine constant frequency starter/generator

Номер: US20150054283A1
Автор: David Dimitri Karipides, Hao Huang
Принадлежит: GE AVIATION SYSTEMS LLC

A constant frequency starter/generator for a turbine engine includes a first inverter/converter, a second inverter/converter, a DC link electrically connecting the first inverter/converter to the second inverter/converter, and an electric machine having a synchronous main machine, wherein the constant frequency starter/generator is operable in a start mode and a run mode.

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Номер записи: 36
05-03-2015 дата публикации

Gas Turbine Combustion System

Номер: US20150059353A1
Автор: Akinori Hayashi, Tomohiro Asai, Yasuhiro Akiyama
Принадлежит: Mitsubishi Hitachi Power Systems Ltd

The present invention provides a gas turbine combustion system capable of minimizing unburned content of a gas fuel under all load conditions from partial load to rated load. A gas turbine combustion system includes: a plurality of gas fuel burners 32, 33; an IGV 9 that adjusts a flow rate of air to be mixed with a gas fuel; and a control system 500 that temporarily reduces an air flow rate from a reference flow rate to a set flow rate by outputting a signal to the IGV 9 when a combustion mode is switched from a partial combustion mode in which the gas fuel is burned with part of the gas fuel burners 32, 33 to a full combustion mode in which the gas fuel is burned with all of the gas fuel burners 32, 33.

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Номер записи: 37
01-03-2018 дата публикации

Advanced Startup Counter Module For A Valve And Actuator Monitoring System

Номер: US20180058248A1
Автор: REIGL Martin
Принадлежит:

The present application provides a method of evaluating fatigue damage in a turbine by a data acquisition system. The method may include the steps of receiving a number of operating parameters from a number of sensors and based upon the operating parameters, determining: a run time from start-up until the turbine reaches X percent load and a start-up temperature transient from start-up until the turbine reaches X percent load, and calculating: a run time ratio of the determined run time until the turbine reaches X percent load to a predetermined run time, a start-up temperature ratio of the determined start-up temperature transient to a predetermined start-up temperature transient, and a fatigue severity factor by averaging the run time ratio and the start-up temperature ratio. Based upon the determined fatigue severity factor, altering one or more of the operating parameters and/or initiating repair procedures. 1. A method of evaluating fatigue damage in a turbine by a data acquisition system , comprising:receiving a plurality of operating parameters from a plurality of sensors; a run time from start-up until the turbine reaches X percent load; and', 'a start-up temperature transient from start-up until the turbine reaches X percent load;, 'based upon the plurality of operating parameters, determining a run time ratio of the determined run time until the turbine reaches X percent load to a predetermined run time;', 'a start-up temperature ratio of the determined start-up temperature transient to a predetermined start-up temperature transient; and', 'a fatigue severity factor by averaging the run time ratio and the start-up temperature ratio; and, 'calculatingbased upon the determined fatigue severity factor, altering one or more of the plurality of operating parameters and/or initiating repair procedures.2. The method of claim 1 , wherein the determining step further comprises determining a stand-still time from shut-down to start-up.3. The method of claim 2 , ...

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Номер записи: 38
04-03-2021 дата публикации

A METHOD FOR STARTING UP A GAS TURBINE ENGINE OF A COMBINED CYCLE POWER PLANT

Номер: US20210062677A1
Автор: Keune Christian, Tham Kok-Mun, Wappler Nicolas Benjamin
Принадлежит:

The invention relates to a method for starting up a gas turbine engine of a combined cycle power plant. The method includes applying load to the gas turbine engine and increasing the load until a predetermined combustor firing temperature is reached, while keeping the adjustable inlet guide vanes in a start position adapted to reduce the mass flow of air into the compressor; further increasing the load of the gas turbine engine while opening the adjustable inlet guide vanes and keeping the predetermined combustor firing temperature constant until the inlet guide vanes reach an end position adapted to increase the mass flow of air into the compressor; further increasing the load of the gas turbine engine while keeping the adjustable inlet guide vanes in the end position until a predetermined load of the gas turbine engine is reached. 1. A method for starting up a gas turbine engine of a combined cycle power plant , the gas turbine engine including a compressor , a combustor and a turbine , the compressor providing compressed air to the combustor for combustion with a fuel to produce a working fluid and the turbine receiving the working fluid to produce power; the compressor comprising adjustable inlet guide vanes , the adjustable inlet guide vanes being adjustable between a fully closed position for minimizing the mass flow of air into the compressor and a fully open position for providing the maximum mass flow of air into the compressor wherein the method comprises the steps of:step 1: applying load to the gas turbine engine and increasing the load until a predetermined combustor firing temperature is reached, while keeping the adjustable inlet guide vanes in a start position adapted to reduce the mass flow of air into the compressor, whereby the predetermined combustor firing temperature is chosen to be an emission-compliant temperature,step 2: further increasing the load of the gas turbine engine while opening the adjustable inlet guide vanes and keeping the ...

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Номер записи: 39
04-03-2021 дата публикации

Systems and Methods for Proactive Operation of Process Facilities Based on Historical Operations Data

Номер: US20210062681A1
Автор: Alabdulmohsen Mohammed Tawfeeq, Amminudin Kamarul Ariffin
Принадлежит:

Provided are techniques for proactively operating gas-oil separation plant (GOSP) type process facilities that include determining historical operational characteristics of a GOSP for a past time interval using historical operational data for the GOSP, determining expected operating characteristics of the GOSP for a subsequent time interval using the historical operational characteristics, determining an operating plan for the GOSP using the expected operating characteristics, and operating the GOSP in accordance with the operating plan. 1. A method of operating a gas oil separation plant (GOSP) , the method comprising: oil production;', 'power consumption;', 'gas export;', 'crude export;', 'sour gas export;', 'natural gas liquids (NGL) export;', 'fuel gas consumption; and', 'energy key performance indicator (KPI);, 'obtaining operational data for the GOSP, the operational data indicative of operational characteristics of the GOSP observed over a historical time interval, the historical time interval comprising an interval of time preceding a given point in time, the operational characteristics comprising (a) for each month of the historical time interval, an average monthly value determined based on values of the operational characteristic over the month;', '(b) for each week of the historical time interval, an average weekly value determined based on values of the operational characteristic over the week; and', '(c) for each day of the historical time interval, a daily value determined based on a value of the operational characteristic for the day:, 'determining, based on the operational data, historical operational characteristics of the GOSP for the historical time interval, the historical operational characteristics comprising, for each of the operational characteristics (a) an expected next month value determined based on the average monthly values for the operational characteristic;', '(b) an expected next week value determined based on the average weekly ...

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Номер записи: 40
20-02-2020 дата публикации

AIR TURBINE START SYSTEM

Номер: US20200056547A1
Автор: Short Keith E., Walker Daniel Richard
Принадлежит:

An air turbine starter device includes a gear assembly, a rotor arranged in a cavity of a housing and operably connected the gear assembly, a first manifold having a cavity with a first manifold port operative to direct compressed air to the rotor, and a second manifold having a cavity with a second manifold port operative to direct compressed air to the rotor. The first manifold is larger than the second manifold, the second manifold is fluidly connected in parallel with the first manifold, and the first manifold port and the second manifold port are operative to drive the rotor in a common direction for starting a gas turbine connected to the gear assembly. Air turbine starter systems and methods of starting gas turbine engines are also described. 1. An air turbine starter device comprising:a gear assembly;a rotor arranged in a cavity of a housing, wherein the rotor is operably connected the gear assembly;a first manifold having a cavity with a first manifold port operative to direct compressed air to the rotor; anda second manifold having a cavity with a second manifold port operative to direct compressed air to the rotor,wherein the first manifold is larger than the second manifold, wherein the second manifold is fluidly connected in parallel with the first manifold, and wherein the first manifold port and the second manifold port are operative to drive the rotor in a common direction.2. The device of claim 1 , wherein the first manifold includes a greater number of ports than a number of ports in the second manifold.3. The device of claim 1 , wherein the cavity of the first manifold defines a first compressed air flow path that flows through the cavity of the first manifold claim 1 , through the port of the first manifold claim 1 , and through a nozzle that is communicative with the cavity of the housing.4. The device of claim 1 , wherein the cavity of the second manifold defines a second compressed air flow path that flows through the cavity of the second ...

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Номер записи: 41
12-03-2015 дата публикации

System for inductive heating of turbine rotor disks

Номер: US20150068216A1
Автор: Harald Nimptsch, Stefan Kulig, Sven Exnowski
Принадлежит: SIEMENS AG

A turbine rotor with at least one rotor disk is provided. The turbine rotor includes a heating arrangement for heating at least a part of the rotor disk. The heating arrangement has a conductor for conducting electric current. The conductor is positioned such that in presence of the electric current in the conductor, Eddy current is generated in the part of the rotor disk. The electric current is an alternating current. The Eddy currents so generated in the part of the rotor disk result in inductive heating of the part of the rotor disk.

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Номер записи: 42
11-03-2021 дата публикации

METHOD FOR DETECTING THE IGNITION OF A TURBINE ENGINE

Номер: US20210071582A1
Автор: DJELASSI Cedrik, RAILLARD Nicolas, WIDEMANN Adel Cedric Abir
Принадлежит: SAFRAN AIRCRAFT ENGINES

The invention relates to a method (E) for detecting the ignition of a turbine engine combustion chamber, the method (E) comprising the steps of: receiving (E) a first measurement of the exhaust gas temperature downstream from the combustion chamber, before an attempt to ignite said combustion chamber; receiving (E) a temperature threshold; receiving (E) a secondary detection criterion; updating (E) the received temperature threshold as a function of the secondary detection criterion received; receiving (E) a second measurement of the exhaust gas temperature, after the attempt to ignite the combustion chamber; comparing (E) the updated temperature threshold with the difference between the first and second exhaust gas temperature measurements; and determining (E) the state of ignition of the combustion chamber. 1. A method comprising:before an attempt to ignite a combustion chamber of a turbine engine, receiving a first measurement of exhaust gas temperature downstream of the combustion chamber;receiving a temperature threshold anda secondary detection criterion;updating the temperature threshold depending on the secondary detection criterion;after the attempt to ignite the combustion chamber, receiving a second measurement of the exhaust gas temperature; andcomparing the updated temperature threshold and the difference between the first measurement and the second measurement of the exhaust gas temperature anddetermining an ignition state of the combustion chamber corresponding to a success or to a failure of the ignition attempt.2. The method according to claim 1 , wherein receiving a first measurement of the exhaust gas temperature is implemented at an end of a phase of initiation of a starting sequence of the turbine engine claim 1 , when the exhaust gas temperature is minimal.3. The method according to claim 1 , wherein updating of the temperature threshold consists of a reduction of a value of the threshold if the secondary criterion is validated claim 1 , and of ...

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Номер записи: 43
15-03-2018 дата публикации

AIRCRAFT TURBINE ENGINE WITH PLANETARY OR EPICYCLIC GEAR TRAIN

Номер: US20180073384A1
Автор: Bordoni Nils, Kubiak Guillaume Patrice, LEMARCHAND Kevin Morgane
Принадлежит:

Aircraft turbine engine comprising a low-pressure spool that comprises a low-pressure shaft (), means () for taking off power from said low-pressure shaft, and a fan () that is driven by said low-pressure shaft by means of a reduction gear (), said reduction gear comprising at least one first element () that is connected to said low-pressure shaft for conjoint rotation, at least one second element () that is connected to said fan for conjoint rotation, and at least one third element () that is connected to a stator casing of the turbine engine, characterised in that said at least one third element is connected to said stator casing by disengageable connection means (), and comprising at least one member that can move from a first position in which said at least one third element is fixedly connected to said stator casing into a second position in which said at least one third element is separated from said stator casing and is free to rotate about said longitudinal axis. 1. An aircraft turbine engine comprising a low-pressure spool that comprises a low-pressure shaft that connects a rotor of a low-pressure compressor to a rotor of a low-pressure turbine , and a high-pressure spool that comprises a high-pressure shaft that connects a rotor of a high-pressure compressor to a rotor of a high-pressure turbine , the low-pressure and high-pressure shafts extending along the same longitudinal axis (A) , the turbine engine further comprising means for taking off power from said low-pressure shaft , and a fan that is driven by said low-pressure shaft by means of a planetary or epicyclic reduction gear , said reduction gear comprising at least one first element that is connected to said low-pressure shaft for conjoint rotation , at least one second element that is connected to said fan for conjoint rotation , and at least one third element that is connected to a stator casing of the turbine engine , characterised in that said at least one third element is connected to said ...

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Номер записи: 44
16-03-2017 дата публикации

GAS TURBINE ENGINE COMPRISING A STARTER ENGAGED WITH A LOW-PRESSURE BODY

Номер: US20170074169A1
Автор: CHALAUD Sebastien, GARASSINO Alain Pierre, Waissi Bellal
Принадлежит: SAFRAN AIRCRAFT ENGINES

A multi-body gas turbine engine, especially an aircraft engine, comprising at least one low-pressure rotating body , a high-pressure rotating body, and a starter to rotate the high-pressure body in order to start the engine, wherein the starter is coupled to the low-pressure body and the engine comprises a first disengageable coupling device disposed between the low-pressure body and the high-pressure body , for rotatably connecting the high-pressure body to the low-pressure body so as to allow the starting of the engine by means of the starter. 1. Multi-spool gas turbine engine ( comprising: at least one rotating low-pressure body , a rotating high-pressure body , and a starter motor , the starter motor being coupled to the low-pressure body , the engine further comprising a first disengageable coupling device which is interposed between the low-pressure body and the high-pressure body in order to rotatably connect the high-pressure body to the low-pressure body in order to make it possible to start up the engine the starter motor , wherein the first coupling device is designed so as to be movable between:a first position, in which the coupling device is engaged so that the low-pressure body drives the high-pressure body,a second position, in which the coupling device is disengaged once a speed of the low-pressure body falls below that of the high-pressure body.2. Turbine engine according to claim 1 , wherein the first coupling device is of the freewheel type.3. Turbine engine according to claim 2 , wherein the low-pressure body comprises a shaft that is mounted coaxially in or on a shaft of the high-pressure body claim 2 , the first freewheel coupling device being mounted between the shafts of the low-pressure and high-pressure bodies.4. Turbine engine according to either claim 2 , wherein the first coupling device comprises a free wheel having jamming elements.5. Turbine engine according to claim 1 , comprising a gearbox for driving accessory equipment of the ...

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Номер записи: 45
18-03-2021 дата публикации

GAS TURBINE ENGINE

Номер: US20210079807A1
Автор: BRADBROOK Stephen J.
Принадлежит: ROLLS-ROYCE PLC

A gas turbine engine comprising: a combustor configured to initiate combustion; and a turbine comprising a stator vane ring defining a plurality of passageways between adjacent vanes; wherein at least one of the passageways is provided with a restrictor which defines a temporary gas washed surface for the stator vane ring and is configured to be ablated upon initiation of combustion to reveal an operational gas washed surface of the stator vane ring. A method of starting a gas turbine engine is also described. 1. A gas turbine engine comprising:a combustor configured to initiate combustion; anda turbine comprising a stator vane ring defining a plurality of passageways between adjacent vanes;wherein at least one of the passageways is provided with a restrictor which defines a temporary gas washed surface for the stator vane ring and is configured to be ablated upon initiation of combustion to reveal an operational gas washed surface of the stator vane ring.2. The gas turbine engine of claim 1 , wherein the passageway comprises circumferentially extending endwalls between adjacent vanes; and wherein the restrictor is provided on an operational gas washed surface of the endwalls.3. The gas turbine engine of claim 1 , wherein the restrictor is a coating provided on the endwalls claim 1 , and wherein the coating at least partially covers an operational gas washed surface of the endwalls.4. The gas turbine engine of claim 3 , wherein the coating is formed from tin or an alloy of lead and tin.5. The gas turbine engine of claim 1 , wherein the restrictor is provided on the operational gas washed surface of a vane delimiting the passageway.6. The gas turbine engine of claim 5 , wherein the restrictor is a coating provided on a vane delimiting the passageway and wherein the coating at least partially covers the operational gas washed surface of the respective vane.7. The gas turbine engine of claim 6 , wherein the coating completely covers the operational gas washed surface ...

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Номер записи: 46
31-03-2022 дата публикации

CONTROL OF ROTOR STRESS WITHIN TURBOMACHINE DURING STARTUP OPERATION

Номер: US20220098996A1
Автор: Baker Dean Alexander, Di Palma Steven, Frazer Austin Daniel, Nagel Bruce Frederick, Toth Carl Raymond
Принадлежит:

Embodiments of the disclosure provide a method for controlling steam pressure within a turbine component. The method includes calculating a predicted stress on a rotor of the turbine component based on a predicted steam flow with the inlet valve in a minimum load position, a rotor surface temperature, and an inlet steam temperature, and determining whether the predicted stress exceeds a threshold. If the predicted stress exceeds the threshold, the inlet valve adjusts to a warming position. When steam in the discharge passage reaches a target pressure, the exhaust valve partially closes while maintaining the warming position of the inlet valve. If a safety parameter of the turbine component violates a boundary, the exhaust valve partially opens while maintaining the warming position of the inlet valve. When the predicted stress does not exceed the threshold, the inlet valve opens to at least the minimum load position. 1. A method for controlling steam pressure within a turbine component during a startup operation , the turbine component being fluidly coupled between an inlet having an inlet valve for controlling steam flow into the turbine component and an exhaust having an exhaust valve for controlling steam flow to a discharge passage , the method comprising:adjusting the exhaust valve to a fully open position and the inlet valve to a fully closed position;calculating a predicted stress on a rotor of the turbine component based on a predicted steam flow with the inlet valve in a minimum load position, a rotor surface temperature, and an inlet steam temperature;determining whether the predicted stress exceeds a threshold;in response to the predicted stress exceeding the threshold, adjusting the inlet valve to a warming position that is less open than the minimum load position, such that a steam flow through the turbine component pressurizes the discharge passage;in response to steam in the discharge passage reaching a target pressure, partially closing the exhaust ...

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Номер записи: 47
09-04-2015 дата публикации

Exhaust Heat Recovery Device

Номер: US20150096297A1
Автор: HARAGUCHI Tomonori, Wada Hirofumi
Принадлежит:

An exhaust heat recovery device provided with a Rankine cycle, capable of achieving improvements in start-up performance of the Rankine cycle and an efficient operation (actuation) of the Rankine cycle. An exhaust heat recovery device that recovers and uses exhaust heat of an engine includes: a Rankine cycle including a heater , an expander , a condenser , and a pump ; a bypass flow passage that allows refrigerant to circulate while bypassing the expander ; a bypass valve that opens and closes the bypass flow passage ; and a control unit . When starting up the Rankine cycle , the control unit executes control to actuate the pump with the bypass valve open, and then to close the bypass valve when a parameter indicating the condensation capacity of the condenser becomes a predetermined value or more. 1. An exhaust heat recovery device comprising:a Rankine cycle in which a heater configured to heat and vaporize refrigerant by exhaust heat of an external heat source, an expander configured to generate power by expanding the refrigerant passed through the heater, a condenser configured to condense the refrigerant passed through the expander, and a pump configured to send the refrigerant passed through the condenser to the heater are disposed in a circulation passage of the refrigerant;a bypass flow passage that allows the refrigerant to circulate while bypassing the expander;a bypass valve that opens and closes the bypass flow passage; anda control unit that, when starting up the Rankine cycle, executes control to actuate the pump with the bypass valve open, and then to close the bypass valve when a parameter indicating condensation capacity of the condenser becomes a predetermined value or more.2. The exhaust heat recovery device according to claim 1 , further comprising:a pressure difference determining unit that determines a pressure difference between a high-pressure side and a low-pressure side of the Rankine cycle,wherein when starting up the Rankine cycle, the ...

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Номер записи: 48
19-03-2020 дата публикации

GAS TURBINE COMBINED CYCLE FOR HIGH FLEXIBILITY

Номер: US20200088064A1
Автор: Boulden Mark S., Gülen Seyfettin C., Yarinovsky Ilya
Принадлежит: Bechtel Infrastructure and Power Corporation

A combined cycle power generation plant has parallel, normally-independent power generation trains, each having a gas turbine in line with a heat recovery steam generator. In a “parked” or spinning reserve operational state, combustion is discontinued at the gas turbine of one power generation train, which is placed on a turning gear. Combustion at the other power train is reduced, preferably to a minimum emissions-compliant level (NOx, CO) of the gas turbine operated at low level combustion. A bypass duct with controllable dampers apportions exhaust from the operating gas turbine to the heat recovery steam generators of both power trains. This maintains an elevated temperature in both heat recovery steam generators and enables fast restart. 1. A combined cycle power plant , comprising:at least two gas turbines operable to combust fuel during operation and supplying torque to at least one electrical generator via a shaft, each of the gas turbines producing an exhaust flow during operation, the exhaust flow being coupled in a flow path to at least one of two or more heat recovery steam generators, each of the heat recovery steam generators being associated with a respective one of the gas turbines in a power train, the heat recovery steam generators producing steam from the exhaust flow of the gas turbines during operation for extraction of further energy by a steam turbine;operational controls configured to assume a low load operational state of the combined cycle power plant wherein an active one of the two or more gas turbines is operated at a predetermined low load level and another of the two or more gas turbines is substantially shut down;a bypass duct for defining a flow path for gas turbine exhaust from an outlet of one of the gas turbines in one of the power trains to an inlet of the heat recovery steam generators of the other power trains;wherein in the low load operational state, the bypass duct conveys a portion of the exhaust flow produced by the active ...

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Номер записи: 49
05-04-2018 дата публикации

DEVICE AND METHOD FOR GAS TURBINE UNLOCKING

Номер: US20180094585A1
Автор: BALDASSARRE Antonio, BETTI Tommaso, Lazzeri Marco, Marcucci Daniele, Merlo Roberto, Meucci Stefano, Viti Filippo
Принадлежит:

An aeroderivative gas turbine including an air intake plenum; a compressor with a compressor air intake in fluid communication with the air intake plenum; a combustor; a high pressure turbine; a power turbine. A forced air-stream generator is arranged in fluid communication with the air intake plenum. A shutter arrangement is provided in a combustion-air flow path, arranged and controlled to close the combustion-air flow path for pressurizing said air intake plenum by means of the forced air-stream generator to a pressure sufficient to cause pressurized air to flow through the aeroderivative air turbine. 1. A method for unlocking a rotor in an aeroderivative gas turbine following shutdown of the aeroderivative gas turbine , the method comprising:arranging an air intake plenum of the aeroderivative gas turbine in fluid communication with a combustion-air flow path of the aeroderivative gas turbine, a compressor air intake, and a forced air-stream generator;arranging and controlling a shutter arrangement to selectively open and close the combustion-air flow path, wherein the shutter arrangement is in the combustion-air flow path through which air enters the air intake plenum;selectively opening and closing, by at least one shutter in the shutter arrangement, a plurality of air passageway defined between respective pairs of adjacent parallel arranged silencer panels, each air passageway having an air outlet aperture; andcooling the rotor when the rotor is locked following shut down of the aeroderivative gas turbine, by closing the shutters of the shutter arrangement and generating an overpressure in the air intake plenum by using the forced air-stream generator, the overpressure being sufficient to force pressurized air through the locked rotor of the aeroderivative gas turbine.2. The method according to claim 1 , wherein the overpressure ranges between 0.05 and 0.3 Bar above ambient pressure.3. The method according to claim 1 , wherein the overpressure ranges between ...

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Номер записи: 50
12-05-2022 дата публикации

Method for starting a turbine engine in cold weather and system for starting a turbine engine

Номер: US20220145804A1
Автор: Clément Dupays, Gwenole Yann Le Pache
Принадлежит: Safran Aircraft Engines SAS

A method for starting a turbine engine in cold weather, including a starting system intended for rotating a drive shaft of the turbine engine. The method includes the following steps: a pre-starting step in which a first starting signal is generated to control the drive shaft in a first direction of rotation about a longitudinal axis and in a second opposite direction of rotation in an alternating manner; and a starting step in which a second starting signal is transmitted to the starting system in order for the latter to drive the drive shaft of the turbine engine in a normal direction of rotation and in which the drive shaft is rotated until a rotation speed that causes the turbine engine to start.

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Номер записи: 51
28-03-2019 дата публикации

CASING POSITION ADJUSTMENT DEVICE

Номер: US20190093514A1
Автор: HAMADA Katsuhisa, Hori Takumi, SAEKI Kentarou, UEHARA Hidekazu
Принадлежит:

In a steam turbine including a rotor including a free side end fixed by a journal bearing (not illustrated) in a radial direction and a fixed side end fixed by a thrust bearing in an axial direction, and a casing including a fixed side end fixed by the thrust bearing in the axial direction (rotor axial direction), a casing position adjustment device is configured to adjust an axial position of the casing with respect to the rotor due to thermal expansion. The casing position adjustment device includes: a low-pressure casing end plate, which is an end plate oriented to a free side in the axial direction in a low-pressure casing of the casing, and has a diaphragm shape deformable in the axial direction; and actuators, which deform the low-pressure casing end plate so that the low-pressure casing end plate extends toward the free side in the axial direction. 115-. (canceled)16. A casing position adjustment device in a steam turbine including a rotor including a free side end fixed by a journal bearing in a radial direction and a fixed side end fixed by a thrust bearing in an axial direction , and a casing including a fixed side end fixed by the thrust bearing in the axial direction , the casing position adjustment device configured to adjust an axial position of the casing with respect to the rotor due to thermal expansion , the casing position adjustment device comprising:a low-pressure casing end plate, which is an end plate oriented to a free side in the axial direction in a low-pressure casing of the casing, and has a diaphragm shape deformable in the axial direction; andactuators, which deform the low-pressure casing end plate such that the low-pressure casing end plate extends toward the free side in the axial direction.17. A casing position adjustment device according to claim 16 , wherein the casing is fixed by anchor bolts on the fixed side in the axial direction with respect to the low-pressure casing end plate.18. A casing position adjustment device ...

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Номер записи: 52
06-04-2017 дата публикации

Aircraft propulsion system having at least one anti-fire tank

Номер: US20170096238A1
Автор: Porte Alain, Rogero Jean Michel
Принадлежит:

A propulsion system comprising a nacelle substantially tubular around a longitudinal axis, having an inner wall extending from a front to a rear of the nacelle and by an outer wall, external of the inner wall, extending from the front to the rear of the nacelle, a turbojet comprising a fan and situated internally of the inner wall of the nacelle, at least one tank containing an extinguishing fluid, and a network of pipes hydraulically connected to the tank. The propulsion system comprises each tank being located in the nacelle, around the inner wall and internally of the outer wall. Such a propulsion system makes it possible to shift the one or more tanks, which no longer occupy the space at the mast, and makes it possible to carry a large volume of extinguishing fluid so as to be able to accommodate future regulations. 1. A propulsion system comprising:a nacelle which is substantially tubular around a longitudinal axis, defined by an inner wall extending from a front of the nacelle to a rear of the nacelle and by an outer wall, external of the inner wall, extending from the front of the nacelle to the rear of the nacelle,a turbojet comprising a fan and being situated internally of the inner wall of said nacelle,at least one tank containing an extinguishing fluid, being located inside said nacelle between the inner wall and the outer wall, anda network of pipes hydraulically connected to said at least one tank,wherein said at least one tank extends around the inner wall,wherein said at least one tank is of a form having at least one open torus portion in a plane perpendicular to the longitudinal axis.2. The propulsion system according to claim 1 , wherein said at least one tank extends angularly around the periphery of said nacelle so that the lower part of said at least one tank is above a horizontal plane tangent to a lower edge of said inner wall of said nacelle.3. The propulsion system according to claim 1 , wherein said at least one tank is situated in a ...

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Номер записи: 53
26-03-2020 дата публикации

System and Method for Measuring Clearance Gaps Between Rotating and Stationary Components of a Turbomachine

Номер: US20200096329A1
Автор: Awasthi Richa, Battu Bhanu Kishore, Siva Kumar K. G. V., Swaminathan Srinivasan, THIMMEGOWDA Shalini, Thippeswamy Vishwanath
Принадлежит:

Systems and methods for measuring the clearance gaps between rotating and stationary components of a turbomachine are provided. In one exemplary aspect, flexible and degradable sensing arrays that include a plurality of microwave sensors are utilized to sense the clearance gaps between rotating and stationary components of the turbomachine. Microwaves generated by a microwave generator are transmitted to the sensors. Upon rotation of the rotating components, the rotating components reflect the microwaves transmitted thereto. The microwave sensors capture the transmitted signal and also capture a reflected signal indicative of the transmitted signal reflected by the rotating components. The signals are then forwarded to a computing device for processing. The amplitude difference at the interference fringes between the superimposed signals is representative of the clearance gaps between the rotating and stationary components. After measuring the clearance gaps, the turbomachine may be operated and the degradable sensing array may be consumed. 1. A system , comprising:a turbomachine comprising a rotating component rotatable about an axis of rotation and a stationary component spaced from the rotating component by a clearance gap;a sensor attached to one of the stationary component and the rotating component;an electromagnetic wave generator in electrical communication with the sensor and configured to generate electromagnetic waves; and receive a transmitted signal from the sensor, wherein the transmitted signal is representative of the electromagnetic waves received by the sensor;', 'receive, as the rotating component is rotated about the axis of rotation, a reflected signal from the sensor, wherein the reflected signal is representative of the electromagnetic waves reflected by the rotating component;', 'determine a delta between an amplitude of the transmitted signal and an amplitude of the reflected signal of the transmitted signal and the reflected signal; and', ' ...

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Номер записи: 54
02-04-2020 дата публикации

Method and apparatus for estimating internal state of thermal component

Номер: US20200103227A1
Автор: Hiroshi Ito
Принадлежит: Mitsubishi Hitachi Power Systems Ltd

A method of estimating an internal state of a thermal component of the invention includes a measurement step of measuring state quantity of the thermal component, an analysis-condition creation step of creating an analysis condition, a data assimilation step of obtaining probability distribution of each temperature distribution and displacement distribution through data assimilation calculation using a contraction model, a measured value, and the analysis condition, a post-processing step of obtaining the internal state of the thermal component, an analysis step of obtaining solution vectors of the temperature distribution and the displacement distribution, and a contraction-model construction step of extracting a subspace characterizing a linear space of a vector set and constructing a contraction model using the subspace, wherein, in the data assimilation step, the probability distribution is calculated using the contraction model, and, in the analysis step and the contraction-model construction step, the contraction model is constructed.

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Номер записи: 55
07-05-2015 дата публикации

ACTIVATION CONTROL DEVICE

Номер: US20150121874A1
Автор: IYANAGA Norihiro, Katagiri Yukinori, KIM Eunkyeong, NOMURA Kenichiro, SUZUKI Fumiyuki, Yamanaka Kazunori, YASHIKI Tatsuro, Yoshida Takuya, Yoshida Yasuhiro
Принадлежит:

Provided is a steam turbine plant activation control device that can flexibly handle an initial state amount of a steam turbine plant and activate a steam turbine at a high speed. The activation control device for the steam turbine plant includes a heat source device configured to heat a low-temperature fluid using a heat source medium and generate a high-temperature fluid, a steam generator for generating steam by thermal exchange with the high-temperature fluid, a steam turbine to be driven by the steam, and adjusters configured to adjust operation amounts of the plant. 1. An activation control device for a steam turbine plant , the steam turbine plant includinga heat source device configured to heat a low-temperature fluid using a heat source medium to generate a high-temperature fluid,a steam generator for generating steam by thermal exchange with the high-temperature fluid,a steam turbine to be driven by the steam, andan adjuster for adjusting a plant operation amount,the activation control device comprising:a predicting unit for calculating a predicted value for at least one constraint to be used to control the activation of the steam turbine;an activation control parameter setting unit configured to calculate, based on an initial value of a plant state amount, an activation control parameter to be used to control the activation of the steam turbine; anda plant operation amount calculator configured to determine the plant operation amount, based on the predicted value for a constraint, the predicted value being calculated by the predicting unit, and on the activation control parameter calculated by the activation control parameter setting unit, so that the constraint does not exceed a predetermined limit.2. The activation control device according to claim 1 ,wherein the adjuster includes a heat source medium amount adjusting unit configured to adjust the amount of a heat source medium to be supplied to the heat source device and adjust the amount of heat held ...

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Номер записи: 56
07-05-2015 дата публикации

Systems and Methods for Boundary Control During Steam Turbine Acceleration

Номер: US20150125257A1
Автор: Baker Dean Alexander, Meyer John Lawrence, Toth Carl R.
Принадлежит: GENERAL ELECTRIC COMPANY

Certain embodiments of the disclosure may include systems and methods for boundary control during steam turbine acceleration. According to an example embodiment, the method can include receiving an indication the turbine is in an initial acceleration phase; receiving speed control parameter data from a plurality of sensors; receiving boundary control parameter data from a plurality of sensors; providing a control valve configured for controlling steam flow entering the turbine; determining the control valve position based on received speed control parameter data; determining the control valve position based on received boundary control parameter data; adjusting at least one boundary control parameter to the at least one boundary control parameter limit during turbine startup, wherein the value of a speed control parameter is simultaneously adjusted based on the adjusted at least one boundary control parameter; and adjusting the control valve position based at least on determined parameter data. 1. A method for starting a turbine , the method comprising:receiving an indication the turbine is in an initial acceleration phase;receiving speed control parameter data from a plurality of sensors;receiving boundary control parameter data from a plurality of sensors;providing a control valve configured for controlling steam flow entering the turbine;determining the control valve position based on received speed control parameter data;determining the control valve position based on received boundary control parameter data;adjusting at least one boundary control parameter to the at least one boundary control parameter limit during turbine startup, wherein the value of a speed control parameter is simultaneously adjusted based on the adjusted at least one boundary control parameter; andadjusting the control valve position based at least on determined parameter data;2. The method of claim 1 , further comprising: comparing the determined control valve position based on received ...

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Номер записи: 57
04-05-2017 дата публикации

Warming arrangement for a power plant

Номер: US20170122130A1
Автор: Christian Kuehne, Klaus Helbig, Wolfgang Franz Dietrich Mohr
Принадлежит: General Electric Technology GmbH

The present disclosure relates generally to power plants and more specifically to warming systems for steam turbine plants that prepare the steam plant for either start-up or stand-by operation.

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Номер записи: 58
12-05-2016 дата публикации

Method for coupling a steam turbine and a gas turbine at a desired differential angle

Номер: US20160130983A1
Автор: Gerta Zimmer
Принадлежит: SIEMENS AG

A method and an associated arrangement for coupling a rotational device, particularly a steam turbine, and a shaft device, particularly a gas turbine, includes the following steps: 1) accelerating the rotational device up to an output rotational speed that is below the rotational speed of the shaft device; 2) detecting a differential angle between the shaft device and the rotational device; and 3) accelerating the rotational device with an acceleration value that is derived from the target rotational speed difference, which is formed as a function of the detected differential angle, the acceleration and a desired target coupling angle.

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Номер записи: 59
10-05-2018 дата публикации

COMPRESSED AIR ENERGY STORAGE AND POWER GENERATION METHOD AND COMPRESSED AIR ENERGY STORAGE AND POWER GENERATION DEVICE

Номер: US20180128167A1
Автор: MATSUKUMA Masaki, SAKAMOTO Kanami, SARUTA Hiroki
Принадлежит: Kabushiki Kaisha Kobe Seiko Sho (Kobe Steel, Ltd.)

In a compressed air energy storage and power generation device, a compressed air energy storage and power generation method defines, as a reference storage value, a storage value indicating that a storage amount of air in an accumulator tank is in a predetermined intermediate state. At the reference storage value, at least one of a motor and a generator rotates at a rated rotation speed. When a storage value indicating a current storage amount in the accumulator tank is larger than the reference storage value, at least one of the motor and the generator is controlled to rotate at equal to or less than the rated rotation speed. When the storage value indicating the current storage amount in the accumulator tank is smaller than the reference storage value, at least one of the motor and the generator is controlled to rotate at equal to or more than the rated rotation speed and equal to or less than a maximum permissible rotation speed. 1. A compressed air energy storage and power generation method , comprising:driving an electric motor by fluctuating input power;compressing air by a compressor mechanically connected to the electric motor;storing the compressed air, which is supplied from the compressor, in an accumulator tank;driving an expander by the compressed air supplied from the accumulator tank; andgenerating power by a generator mechanically connected to the expander, whereinthe compressed air energy storage and power generation method comprises:defining, as a reference storage value, a storage value indicating that a storage amount of the air in the accumulator tank is in a predetermined intermediate state;at the reference storage value, controlling at least one of the electric motor and the generator to rotate at a rated rotation speed;when a storage value indicating a current storage amount in the accumulator tank is larger than the reference storage value, controlling at least one of the electric motor and the generator to rotate at equal to or less than ...

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Номер записи: 60
02-05-2019 дата публикации

PNEUMATIC STARTER SUPPLEMENTAL LUBRICATION SYSTEM

Номер: US20190128141A1
Автор: Harder Benjamin T., Pech John T.
Принадлежит:

A starter supplemental lubrication system for a gas turbine engine is provided. The starter supplemental lubrication system includes a pneumatic starter operable to drive rotation of a rotor shaft of a gas turbine engine through an accessory gearbox. The pneumatic starter is configured to receive a primary lubricant flow at a first rotational speed range and receive a supplemental lubricant flow at a second rotational speed range that is less than the first rotational speed range. The starter supplemental lubrication system also includes a supplemental lubricant pump operable to supply the supplemental lubricant flow at the second rotational speed range. 1. A starter supplemental lubrication system for a gas turbine engine , the starter supplemental lubrication system comprising:a pneumatic starter operable to drive rotation of a rotor shaft of a gas turbine engine through an accessory gearbox, the pneumatic starter configured to receive a primary lubricant flow at a first rotational speed range and receive a supplemental lubricant flow at a second rotational speed range that is less than the first rotational speed range; anda supplemental lubricant pump operable to supply the supplemental lubricant flow at the second rotational speed range.2. The starter supplemental lubrication system of claim 1 , wherein the primary lubricant flow is received from an engine lubrication system and the second rotational speed range provides insufficient lubrication from the engine lubrication system to the pneumatic starter.3. The starter supplemental lubrication system of claim 2 , further comprising:a clutch connected to a drive input of the supplemental lubricant pump and operable to selectively disengage rotation of the drive input above the second rotational speed range.4. The starter supplemental lubrication system of claim 2 , further comprising:a diverter valve operable to divert the supplemental lubricant flow from the pneumatic starter.5. The starter supplemental ...

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Номер записи: 61
23-04-2020 дата публикации

COAXIAL STARTER / GENERATOR AND AIR TURBINE STARTER

Номер: US20200123979A1
Автор: Kusnierek John, Starr Matthew J.
Принадлежит: Rolls-Royce North American Technologies Inc.

A system for starting a turbine engine is provided. The system may comprise a gearbox, a first starter, and a second starter. The gearbox may have an gearbox input shaft. The gearbox input shaft may be rotationally coupled to a spool of the turbine engine. The first starter may have a first-starter shaft. The second starter may have a second-starter shaft. The second-starter shaft may be coaxial with the first-starter shaft. The first starter and the second starter may each be coupled to the gearbox input shaft independently of one another. 1. A system for starting a turbine engine , comprising:a gearbox having a gearbox input shaft; the gearbox input shaft rotationally coupled to a spool of the turbine;a first starter having a first-starter shaft; anda second starter having a second-starter shaft, said second-starter shaft being coaxial with the first-starter shaft,wherein the first starter and second starter are each coupled to said gearbox input shaft independently of one another.2. The system of claim 1 , wherein the first starter is an electric starter and said second starter is an air turbine starter.3. The system of claim 1 , wherein the first starter separates the gearbox and the second starter.4. The system of claim 1 , wherein the second-starter shaft is located radially inward of the first-starter shaft.5. The system of claim 1 , wherein the second starter is selectively coupleable to said gearbox input shaft.6. The system of claim 1 , further comprising a second gearbox coupling said gearbox input shaft and one of said first and second starters.7. The system of claim 1 , wherein both of said first and second starters are selectively coupleable to said gearbox input shaft.8. The system of claim 1 , further comprising a mounting member connected to one of said first and second starters and to a casing of said turbine engine.9. The system of claim 8 , wherein said mounting member comprises an damping member.10. A system for starting a turbine engine claim 8 ...

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Номер записи: 62
17-05-2018 дата публикации

COMBINED CYCLE PLANT, DEVICE FOR CONTROLLING SAID PLANT, AND METHOD FOR STARTING UP SAID PLANT

Номер: US20180135468A1
Автор: KAYAHARA Masayuki, MORA Daniel Carlos, RATIA Pablo, RUBIO Elvio
Принадлежит:

A combined cycle plant, a device for controlling a combined cycle plant, and a method for starting up a combined cycle plant, wherein the time for starting up the combined cycle plant can be shortened by providing: a gas turbine having a compressor, a combustor, and a turbine; a heat recovery steam generator for generating steam by means of the exhaust heat of exhaust gas from the gas turbine; a steam turbine driven by means of the steam generated by the heat recovery steam generator; and a control device configured to set a standby load for the gas turbine during a start-up continuously to change in accordance with a change in metal temperature of the steam turbine. 116-. (cancelled)17. A combined cycle plant comprising:a gas turbine that has a compressor, a combustor, and a turbine;a heat recovery steam generator that generates steam by means of exhaust heat of exhaust gas from the gas turbine;a steam turbine that is driven by means of steam generated by the heat recovery steam generator; anda control device configured to set a standby load which is a load retained on the gas turbine when the gas turbine is started up to change continuously in accordance with a change in metal temperature of the steam turbine.18. The combined cycle plant according to claim 17 ,wherein the standby load is a function of the metal temperature and increases in accordance with a rise of the metal temperature.19. The combined cycle plant according to claim 18 ,wherein the standby load is a function including a low temperature region and a high temperature region with respect to the metal temperature, and a changing rate of the standby load with respect to the metal temperature in the low temperature region and that in the high temperature region are varied from each other.20. The combined cycle plant according to claim 19 ,wherein the changing rate of the standby load in the high temperature region is set to be greater than the changing rate of the standby load in the low temperature ...

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Номер записи: 63
30-04-2020 дата публикации

COMBINED CYCLE PLANT, CONTROL DEVICE THEREOF, AND STEAM TURBINE STARTUP METHOD

Номер: US20200132032A1
Автор: HATANO Ken, MATSUSHIRO Goichi
Принадлежит:

To provide a combined cycle plant, a control device thereof, and a steam turbine startup method that are aimed at improving the operability of a combined cycle plant by allowing a quick change of the output. A combined cycle plant is provided with: a gas turbine having a compressor, a combustor, and a turbine; a supplementary firing burner that raises the temperature of exhaust gas of the gas turbine; a heat recovery steam generator that generates steam using exhaust heat of the exhaust gas; a steam turbine that is driven by steam generated by the heat recovery steam generator; and a control device that changes both an output of the combustor and an output of the supplementary firing burner when an output of the combined cycle plant is to be changed. 1. A method of starting up a combined cycle plant , the combined cycle plant comprising:a gas turbine having a compressor, a combustor, and a turbine;a supplementary firing burner that raises a temperature of exhaust gas of the gas turbine;a heat recovery steam generator that generates steam using exhaust heat of the exhaust gas; anda steam turbine that is driven by steam generated by the heat recovery steam generator,the method comprising:changing both an output of the combustor and an output of the supplementary firing burner when an output of the combined cycle plant is to be changed; andselecting a first output change mode at startup of the steam turbine, and switching to a second output change mode after completion of warming up of the steam turbine,wherein in the first output change mode, the output of the combustor is changed and the output of the supplementary firing burner is held constant when the output of the combined cycle plant is to be changed,in the second output change mode, both the output of the combustor and the output of the supplementary firing burner are changed when the output of the combined cycle plant is to be changed, andthe first output change mode and the second output change mode are ...

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Номер записи: 64
24-05-2018 дата публикации

COMPRESSOR DRIVEN BY ORC WASTE HEAT RECOVERY UNIT AND CONTROL METHOD

Номер: US20180142579A1
Автор: "DALLARA Matteo", CAMPRINI Matteo, CIONINI Filippo, De Franciscis Sergio, MANNUCCI Sergio, Palladino Marco, RIZZELLI Marco
Принадлежит:

A power converting system is described, comprising a source of waste heat and an organic Rankine cycle system. The organic Rankine cycle system in turn comprises at least a turboexpander, at least a rotating load mechanically coupled to the turboexpander and driven thereby, and a variable-speed mechanical coupling between the turboexpander and the rotating load. 1. A power converting system , the power converting system comprising:a source of waste heat;an organic Rankine cycle system, comprised of: at least a turboexpander comprising variable inlet guide vanes, at least a rotating load mechanically coupled to the turboexpander and driven thereby, and a variable-speed mechanical coupling between the turboexpander and the rotating load.2. The system of claim 1 , further comprising:a gas turbine system comprised of at least one gas turbine engine and at least a further rotating load driven by said at least one gas turbine engine; anda heat exchange system for transferring waste heat from the gas turbine system to the organic Rankine cycle system; wherein said waste heat source comprises exhaust gas from the gas turbine system.3. The system of claim 1 , wherein the further rotating load comprises at least one further turbomachine.4. The system of claim 1 , wherein the rotating load comprises at least one turbomachine.5. The system of claim 1 , wherein the organic Rankine cycle system comprises a turboexpander inlet collector and at least an inlet pressure controller arranged and configured to maintain the pressure in the turboexpander inlet collector at a steady-state turboexpander inlet pressure.6. The system of claim 5 , further comprising a further inlet pressure controller claim 5 , arranged and configured to control a by-pass valve claim 5 , connecting the turboexpander inlet collector to a low-pressure side of the organic Rankine cycle system claim 5 , the further inlet pressure controller having a pressure set-point higher than the steady-state turboexpander ...

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Номер записи: 65
07-05-2020 дата публикации

METHOD AND SYSTEM FOR SAFE GAS TURBINE STARTUP

Номер: US20200141321A1
Автор: Botarelli Claudio, BRUNI Daniele, CARNIERI Andrea, GIUNTA Bruno, QUARTIERI Eugenio, VANNI Nicola
Принадлежит:

A method for safe gas turbine startup is disclosed. The method comprises a first step wherein a fuel metering valve () arranged along a fuel delivery line is tested for possible leakages. If the leakage test is successfully passed, a subsequent turbine startup step can be performed. Further disclosed is a gas turbine engine () comprising a fuel supply system () comprised of a fuel delivery line () and a valve arrangement () positioned along said fuel delivery line (). The valve arrangement () further comprises sequentially arranged shut off valves () and a fuel metering valve (), positioned downstream of the shut off valves (). A pressure measuring arrangement () is further provided, adapted to measure fuel pressure in at least one portion of the fuel delivery line () upstream of the fuel metering valve (). 1. A method for safe gas turbine startup , comprising the following steps:{'b': 33', '21', '7', '3, 'performing a leakage test of a fuel metering valve () positioned along a fuel delivery line () and fluidly coupled with a combustor section () of the gas turbine engine (),'}when the leakage test is successfully passed, initiating a gas turbine engine startup procedure.233. The method of claim 1 , wherein the step of performing the leakage test of the fuel metering valve () further comprises the following steps:{'b': 33', '33, 'establishing a first test pressure in a closed volume upstream of the fuel metering valve (), while the fuel metering valve () is closed; wherein said first test pressure is preferably lower than a full fuel supply pressure;'}{'b': '33', 'detecting a pressure drop upstream of the fuel metering valve ();'}if the pressure drop is above a threshold value, generating a leakage alert signal;if the pressure drop is below the threshold value, executing a further step of the startup procedure.3. The method of claim 2 , wherein the step of establishing the first test pressure comprises the steps of:{'b': '33', 'establishing a full fuel supply ...

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Номер записи: 66
07-05-2020 дата публикации

DECOUPLER ASSEMBLIES FOR ENGINE STARTER

Номер: US20200141324A1
Автор: Dranschak David Allan, Meyers Shiloh Montgomery Emerson, Nayak Subrata, RODRIGUEZ Eliel Fresco, Tripathi Pallavi
Принадлежит:

An air turbine starter for starting an engine, comprising a housing defining an inlet, an outlet, and a flow path extending between the inlet and the outlet for communicating a flow of gas there through. A turbine member is journaled within the housing and disposed within the flow path for rotatably extracting mechanical power from the flow of gas. A gear train is drivingly coupled with the turbine member, a drive shaft is operably coupled with the gear train, and an output shaft is selectively operably coupled to rotate with the engine via a decoupler. 1. An air turbine starter for starting an engine , comprising:a housing defining an inlet, an outlet, and a flow path extending between the inlet and the outlet for communicating a flow of gas there through;a turbine member journaled within the housing and disposed within the flow path for rotatably extracting mechanical power from the flow of gas;a gear train drivingly coupled with the turbine member;a drive shaft operably coupled with the gear train and having ramped teeth on its output end; and an output shaft having a first end with mating ramped teeth that are selectively operably coupled to the drive shaft and a second end configured to be operably coupled to and rotate with the engine, the ramped teeth allow for driving torque transfer from the drive shaft to the output shaft and the ramped teeth slide on each other when back driving torque is transmitted such that the output shaft is moved away from the drive shaft;', 'a connector having a body with a first and second end and extending between the output shaft and the drive shaft; and', 'a magnetic coupling selectively linking the drive shaft to the output shaft via the connector, when driving torque is transmitted the connector is magnetically linked to one of the output shaft or the drive shaft via the magnetic coupling and when back driving torque is transmitted the connector is moved away from at least a portion of the magnetic coupling., 'a decoupler, ...

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Номер записи: 67
28-08-2014 дата публикации

SYSTEM AND METHOD FOR OPERATING A POWER PLANT

Номер: US20140238039A1
Автор: Hao Yongjiang, Wu Wenjie, Zhang Hua
Принадлежит: GENERAL ELECTRIC COMPANY

A system including a fuel-supply system including, an auxiliary-fuel-gas compressor configured to compress a fuel for use by a gas-turbine system, an expander configured to generate power by expanding an oxidant from the gas-turbine system, and a motor/generator configured to function in a motor mode and in a generator mode, wherein the motor/generator drives fuel compression with the auxiliary fuel-gas compressor in the motor mode, and the motor/generator generates power in the generator mode as the expander uses oxidant from the gas-turbine system to drive the motor/generator 1. A system , comprising: an auxiliary-fuel-gas compressor configured to compress a fuel for use by a gas-turbine system;', 'an expander configured to generate power by expanding an oxidant from the gas-turbine system; and', 'a motor/generator configured to function in a motor mode and in a generator mode, wherein the motor/generator drives fuel compression with the auxiliary fuel-gas compressor in the motor mode, and the motor/generator generates power in the generator mode as the expander uses oxidant from the gas-turbine system to drive the motor/generator., 'a fuel-supply system comprising2. The system of claim 1 , comprising a fuel-gas compressor/expander having both the auxiliary-fuel gas compressor and the expander as a single dual-purpose unit.3. The system of claim 1 , comprising a controller configured to change the motor/generator between the motor mode and the generator mode.4. The system of claim 3 , comprising a clutch configured to engage and disengage the auxiliary-fuel-gas compressor from the motor/generator claim 3 , wherein the controller controls operation of the auxiliary-fuel-gas compressor by engaging and disengaging the clutch.5. The system of claim 3 , wherein the controller controls the release of oxidant from the gas-turbine system to the expander.6. The system of claim 3 , comprising a primary-fuel-gas compressor.7. The system of claim 6 , wherein the controller ...

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Номер записи: 68
09-06-2016 дата публикации

SYSTEM, PROPULSION SYSTEM AND VEHICLE

Номер: US20160160677A1
Автор: Burns Donald W.
Принадлежит:

One embodiment of the present invention is a unique vehicle. Another embodiment is a unique propulsion system. Yet another embodiment is a unique system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for vehicle propulsions systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith. 120-. (canceled)21. A propulsion system for an aircraft , comprising:a gas turbine engine including a spool configured to power a propulsor;an auxiliary power unit (APU) configured to be engaged with the spool to supply power to the propulsor sufficient to taxi the aircraft;a controller configured to selectively engage the APU to the spool to taxi the aircraft without starting the gas turbine engine.22. The propulsion system of claim 21 , further comprising a clutch mechanically coupled between the APU and the spool claim 21 , wherein the clutch is configured to mechanically engage and disengage the APU respectively to and from the spool.23. The propulsion system of claim 22 , wherein the controller is configured to control the clutch to selectively engage the APU to the spool to power the propulsor to taxi the aircraft without starting the gas turbine engine.24. The propulsion system of claim 21 , wherein the controller is configured to selectively disengage the APU from the spool during one or more of takeoff claim 21 , cruise and landing modes.25. The propulsion system of claim 21 , wherein the controller is configured to selectively engage the APU to the spool during one or more of takeoff claim 21 , cruise and landing modes claim 21 , to provide supplemental power to the spool.26. The propulsion system of claim 21 , wherein the controller is configured to selectively engage the APU to the spool to start or aid in the starting of the gas turbine engine following completion of the taxiing operation.27. The propulsion ...

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Номер записи: 69
09-06-2016 дата публикации

METHOD FOR STARTING A STEAM TURBINE

Номер: US20160160692A1
Автор: GUT Jean-Marie, HAJKO Goran, KLAIBER Hansjörg, Liebig Erhard, Schoenenberger Martin
Принадлежит:

The invention relates to a method for starting a steam turbine. The method involves pre-warming the steam turbine with a steam in which 65% of an energy used to pre-warming the steam turbine is derived from a latent heat energy of the steam. 1. A method for starting a steam turbine comprising pre-warming the steam turbine with a steam wherein at least 65% of an energy used to pre-warming the steam turbine is derived from a latent heat energy of the steam.2. The method of wherein the pre-warming includes filling the steam turbine with the steam.3. The method of wherein filing the steam turbine with the steam involves flowing the steam at a rate such that a steam turbine parameter is not exceed claim 2 , wherein the steam turbine parameter is at least one of a selection of calculated stress claim 2 , measured temperature and/or a speed of a rotor of the steam turbine.4. The method of wherein filling the steam turbine with the steam involves flowing the steam with an increasing pressure gradient through the steam turbine.5. The method of wherein filling the steam turbine with the steam involves:a) filling the steam turbine at a first pressure;b) allowing a pressure decay resulting from condensing steam to a second pressure lower than the first pressure; andc) repeating steps a) and b) with a stepwise increase in the first pressure and second pressure until a predefined temperature of the steam turbine is achieved.6. The method of claim 5 , wherein the stepwise pressure increase corresponds to steam pressures of 4 barg claim 5 , 10 barg claim 5 , 16 barg and 22 barg respectively.7. The method of wherein filling the steam turbine with the steam involves:a) flowing the steam at a first pressure until a steam turbine parameter is reached; andb) repeating step a) with a stepwise increase in the pressure until a predefined temperature of the steam turbine is achieved.8. The method of claim 7 , wherein the stepwise pressure increase corresponds to steam pressures of 4 barg ...

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Номер записи: 70
23-06-2016 дата публикации

EQUIPMENT HEALTH MONITORING METHOD AND SYSTEM AND ENGINE

Номер: US20160177856A1
Автор: Martinez Alvaro, SANCHEZ Luciano
Принадлежит:

An Equipment Health Monitoring method for an engine and an Equipment Health Monitoring system for performing the method are provided. At least some of the following units are used: an Engine Simulation Unit, a Possibilistic Drift Computation Unit, a Fuzzy String Generator Unit, an Experience-based String Matching Unit and an Information Fusion and Prognosis Unit. 1. An Equipment Health Monitoring method for an engine with the following stepsa) a possibilistic drift computation unit automatically allots an upper probability distribution to drift rates of the differences between measured and predicted values generated by an engine simulation unit,b) a fuzzy string generator unit transforms the numerical sequence of upper probabilities of the drift rates generated by the possibilistic drift computation unit into a sequence of quantified terms in a fuzzy term set,c) an experience-based string matching unit compares the string of terms generated by the fuzzy string generator unit with at least one other sequence or portion of sequence of previously obtained fuzzy terms in order to determine the degree of similarity to each of the database set, andd) an information fusion and prognosis unit determining in dependence of the matching patterns or portions of the patterns resulting from the comparisons carried out in the experience-based string matching unit, providing a rate of engine deterioration indicating the current level of deterioration, the rate of deterioration change and the remaining useful life for a given level of deterioration or requirement or otherwise for engine maintenance or the most likely level of deterioration and the likelihood for the requirement or otherwise of engine maintenance of the engine under test.2. The Equipment Health Monitoring method according to claim 1 , wherein the data a possibilistic drift computation unit is measured with at least one parameter value at one location of the engine during its operation claim 1 , a data processing unit ...

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Номер записи: 71
22-06-2017 дата публикации

SYSTEM FOR THE EMERGENCY STARTING OF A TUROMACHINE

Номер: US20170175643A1
Автор: BESSE Jean-Louis Robert Guy
Принадлежит:

The invention relates to a system for emergency starting a turbine engine, characterised in that it comprises a flyer for driving the turbine engine, said flyer comprising a drum () rigidly connected to a rotary shaft (), the axes of symmetry (LL) of the drum () and of the shaft being coincident, the flyer further comprising at least one exhaust nozzle () for ejecting gas, which is positioned on the periphery of the drum () and oriented substantially tangentially to the rotation about said axis (LL), and a pyrotechnic gas generation device which is installed in the flyer and feeds said at least one exhaust nozzle (), said emergency start system further comprising a support in which the shaft of the flyer rotates, and a volute for recovering the gases, which radially surrounds the flyer and is rigidly connected to said support. 1. A system for emergency starting a turbine engine , characterised in that it comprises a flyer for driving the turbine engine , said flyer comprising a drum rigidly connected to a rotary shaft , the axes of symmetry of the drum and of the shaft being coincident , the flyer further comprising at least one exhaust nozzle for ejecting gas , which is positioned on the periphery of the drum and oriented substantially tangentially to the rotation about said axis , and a pyrotechnic gas generation device which is installed in the flyer and feeds said at least one exhaust nozzle , said emergency start system further comprising a support in which the shaft of the flyer rotates , and a volute for recovering the gases , which radially surrounds the flyer and is rigidly connected to said support.2. A system according to claim 1 , wherein the gas generation device comprises a solid propellant block.3. A system according to claim 2 , wherein a combustion chamber feeding said at least one exhaust nozzle is formed in the solid propellant block.4. A system according to claim 1 , wherein said at least one exhaust nozzle is a two-dimensional exhaust nozzle.5. ...

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Номер записи: 72
06-06-2019 дата публикации

COMPONENTS AND SYSTEMS FOR REDUCING THERMAL STRESS OF HEAT RECOVERY STEAM GENERATORS IN COMBINED CYCLE POWER PLANT SYSTEMS

Номер: US20190170022A1
Автор: Bairley Donald William, Bauver, Dang Van, II Wesley Paul, Matarrese Alessandro
Принадлежит:

Heat recovery steam generators (HRSGs) including components and systems for reducing thermal stress experienced by manifolds within the HRSGs are disclosed. The HRSG may include a manifold receiving a working fluid of the HRSG, a plurality of piping links in fluid communication with the manifold, and an enclosure surrounding the manifold and the plurality of piping links. The HRSG may also include at least one thermal element positioned within the enclosure. The thermal element(s) may surround the manifold. Additionally, or alternatively, the HRSG may include a supplemental heating system in fluid communication with an interior of the enclosure. The supplemental heating system may include a heater for heating fluid (e.g., air), and an inlet conduit in fluid communication with and positioned downstream of the heater. The inlet conduit may be formed through the enclosure to provide the heated fluid to the interior of the enclosure. 1. A heat recover steam generator (HRSG) comprising:a manifold receiving a working fluid of the HRSG;a plurality of piping links in fluid communication with the manifold;an enclosure surrounding the manifold and at least a portion of the plurality of piping links; andat least one thermal element positioned within the enclosure, the at least one thermal element surrounding the manifold.2. The HRSG of claim 1 , wherein the at least one thermal element includes:a heat storage component positioned within a casing, the heat storage component directly contacting and surrounding the manifold.3. The HRSG of claim 2 , wherein the at least one thermal element further includes:a thermally insulative shell surrounds the casing containing the heat storage component.4. The HRSG of claim 2 , further comprising:a heating component positioned within the casing containing the heat storage component, the heating component immersed within the heat storage component and at least partially surrounding the manifold; anda control system operably coupled to the ...

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Номер записи: 73
18-09-2014 дата публикации

COMPRESSOR START BLEED SYSTEM FOR A TURBINE SYSTEM AND METHOD OF CONTROLLING A COMPRESSOR START BLEED SYSTEM

Номер: US20140271110A1
Автор: Snider David August, Tillery Steven William
Принадлежит: GENERAL ELECTRIC COMPANY

A compressor start bleed system for a turbine system includes a compressor section. Also included is a turbine section disposed downstream of the compressor section. Further included is at least one duct fluidly coupled to the compressor section, wherein the at least one duct is configured to route a start bleed extraction from the compressor section to a location downstream of the turbine section. Yet further included is at least one control device of the at least one duct configured to actively modulate the start bleed extraction during a part speed operation of the turbine system. 1. A compressor start bleed system for a turbine system comprising:a compressor section;a turbine section disposed downstream of the compressor section;at least one duct fluidly coupled to the compressor section, wherein the at least one duct is configured to route a start bleed extraction from the compressor section to a location downstream of the turbine section; andat least one control device of the at least one duct configured to actively modulate the start bleed extraction during a part speed operation of the turbine system.2. The compressor start bleed system of claim 1 , further comprising a control unit comprising a control schedule.3. The compressor start bleed system of claim 2 , wherein the control unit is in operative communication with the at least one control device.4. The compressor start bleed system of claim 2 , wherein the control schedule comprises at least one operating parameter over a compressor part speed operating range.5. The compressor start bleed system of claim 2 , wherein the control schedule comprises a compressor operating limit line.6. The compressor start bleed system of claim 4 , wherein the at least one operating parameter comprises a fuel-air ratio of a combustor section of the turbine system.7. The compressor start bleed system of claim 1 , wherein the control device comprises a variable valve disposed at least partially within the at least one duct. ...

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Номер записи: 74
28-06-2018 дата публикации

GAS TURBINE COMBINED CYCLE FOR HIGH FLEXIBILITY

Номер: US20180179910A1
Автор: Boulden Mark S., Gülen Seyfettin C., Yarinovsky Ilya
Принадлежит: Bechtel Infrastructure and Power Corporation

A combined cycle power generation plant has parallel normally-independent power generation trains, each having a gas turbine in line with a heat recovery steam generator. In a “parked” or spinning reserve operational state, combustion is discontinued at the gas turbine of one power generation train, placed on turning fear. Combustion at the other power train is reduced, preferably to a minimum emissions-compliant level (NOx, CO) of the gas turbine operated at low level combustion. A bypass duct with controllable dampers apportions exhaust from the operating gas turbine to the heat recovery steam generators of both power trains. This maintains an elevated temperature in both heat recovery steam generators and enables fast restart. 1. A combined cycle power plant , comprising:at least two gas turbines operable to combust fuel during operation and supplying torque to at least one electrical generator via a shaft, each of the gas turbines producing an exhaust flow during operation, the exhaust being coupled in a flow path to at least one of two or more heat recovery steam generators, each of the heat recovery steam generators being associated with a respective one of the gas turbines in a power train, the heat recovery steam generators producing steam from the exhaust of the gas turbines during operation for extraction of further energy by a steam turbine;operational controls configured to assume a low load operational state of the combined cycle power plant wherein an active one of the two or more gas turbines is operated at a predetermined low load level and an other of the two or more gas turbines is substantially shut down;a bypass duct for defining a flow path for gas turbine exhaust from an outlet of one of the gas turbines in one of the power trains to an inlet of the heat recovery steam generators of the other power trains;wherein in the low load operational state, the bypass duct conveys a portion of the exhaust gas produced by the active one of the two or more ...

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Номер записи: 75
28-06-2018 дата публикации

STARTER AIR VALVE SYSTEMS CONFIGURED FOR LOW SPEED MOTORING

Номер: US20180179911A1
Автор: Grigorov Boris N., JR. Leo J., Selstad Tyler J., Veilleux
Принадлежит:

A starter air valve (SAV) system includes a pressure actuated SAV actuator configured to be operatively connected to a SAV, a first pressure valve configured to selectively allow pressure from a pressure source to the SAV actuator when in fluid communication with the SAV actuator, and a second pressure valve configured to selectively allow pressure from the pressure source to the SAV actuator when in fluid communication with the SAV actuator. A manual override (MOR) valve selector is disposed between the first pressure valve, the second pressure valve, and the SAV actuator, the MOR valve selector configured to selectively fluidly connect the first pressure valve and the SAV actuator in a first position and to fluidly connect the second pressure valve and the SAV actuator in a second position. 1. A starter air valve (SAV) system comprising:a pressure actuated SAV actuator configured to be operatively connected to a SAV; anda first pressure valve configured to selectively allow pressure from a pressure source to the SAV actuator when in fluid communication with the SAV actuator;a second pressure valve configured to selectively allow pressure from the pressure source to the SAV actuator when in fluid communication with the SAV actuator; anda manual override (MOR) valve selector disposed between the first pressure valve, the second pressure valve, and the SAV actuator, the MOR valve selector configured to selectively fluidly connect the first pressure valve and the SAV actuator in a first position and to fluidly connect the second pressure valve and the SAV actuator in a second position.2. The system of claim 1 , wherein at least one of the first pressure valve or second pressure valve is a pulse-width modulation solenoid valve configured to provide a duty cycle of pressure from the pressure source to the SAV actuator when in fluid communication with the SAV actuator.3. The system of claim 1 , wherein the SAV includes at least one of a butterfly valve or an inline valve ...

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Номер записи: 76
28-06-2018 дата публикации

Starter air valve systems configured for low speed motoring

Номер: US20180179912A1
Автор: Boris N. Grigorov, Leo J. Veilleux, Jr., Tyler J. Selstad
Принадлежит: Hamilton Sundstrand Corp

A starter air valve (SAV) system includes a pressure actuated SAV actuator configured to be operatively connected to a SAV, a first pressure valve configured to selectively allow pressure from a pressure source to the SAV actuator when in fluid communication with the SAV actuator, and a second pressure valve configured to selectively allow pressure from the pressure source to the SAV actuator when in fluid communication with the SAV actuator. A manual override (MOR) valve selector is disposed between the first pressure valve, the second pressure valve, and the SAV actuator, the MOR valve selector configured to selectively fluidly connect the first pressure valve and the SAV actuator in a first position and to fluidly connect the second pressure valve and the SAV actuator in a second position.

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Номер записи: 77
13-06-2019 дата публикации

GUIDE VANE CONNECTION

Номер: US20190178096A1
Автор: Humhauser Werner, Mairhanser Vitalis, Williams Stephen Royston
Принадлежит: MTU Aero Engines AG

Disclosed is a lever linkage for the rotationally fixed connection of a guide vane to a lever of a guide vane adjusting device of a turbomachine, wherein the guide vane has a vane shaft, which extends along a vertical axis. In accordance with the invention, the lever is formed in one piece at a radially outer end of an essentially hollow cylindrical clamping sleeve, which coaxially surrounds the vane shaft in sections, and the vane shaft and the clamping sleeve are coupled by way of a longitudinal side form-fitting connection or a front-end form-fitting connection, and the vane shaft can be tensioned with the clamping sleeve along the vertical axis by means of a fastening element, in particular a threaded nut. In consequence thereof, a separation of two different force flows that act on the guide vanes is obtained, as a result of which local load peaks are reduced. 1. A lever connection for rotationally fixed connection of a guide vane to a lever of a guide vane adjusting device of a turbomachine , wherein the guide vane has a vane shaft , which extends along a vertical axis , hereby characterized in that the lever is formed in one piece at a radially outer end of an essentially hollow cylindrical clamping sleeve , which coaxially surrounds the vane shaft in sections , and the vane shaft and the clamping sleeve are coupled by way of a longitudinal side form-fitting connection or a front-end form-fitting connection , and the vane shaft can be tensioned with the clamping sleeve along the vertical axis by a fastening element , in particular a threaded nut.2. The lever linkage according to claim 1 , wherein the clamping sleeve has a collar for the radial positional securing of the guide vane in a housing of the turbomachine claim 1 , wherein claim 1 , between the collar and the housing claim 1 , there is a defined gap.3. The lever linkage according to wherein claim 1 , between a radially inner end of the clamping sleeve and the collar of the clamping sleeve claim 1 , a ...

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Номер записи: 78
13-06-2019 дата публикации

System and method for rotor bow mitigation

Номер: US20190178165A1
Автор: Ioan Sabau, Jason Tremblay, Leonard Bezman, Matthew Chiasson
Принадлежит: Pratt and Whitney Canada Corp

A system and method for rotor bow mitigation for a gas turbine engine are provided. An elapsed time since a shutdown of the engine and an idle operation time of the engine prior to the shutdown are determined. A rotor bow mitigation period is determined based on the elapsed time and the idle operation time and, prior to initiating a start sequence of the engine, the engine is motored for a duration of the rotor bow mitigation period.

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Номер записи: 79
04-06-2020 дата публикации

Methods and apparatus for controlling at least part of a start-up or re-light process of a gas turbine engine

Номер: US20200173369A1
Автор: Ahmed M Y. RAZAK, Paul R. Miller, Stephen M. Husband
Принадлежит: Rolls Royce PLC

A method of controlling at least part of a start-up or re-light process of a gas turbine engine, the method comprising: determining when a flame in a combustion chamber of a gas turbine engine is extinguished, during a start-up process or re-light process or during operation; purging the combustion chamber by controlling rotation of a low pressure compressor using a first electrical machine, and controlling rotation of a high pressure compressor using a second electrical machine, the combustion chamber downstream of the low pressure compressor and high pressure compressor; and controlling rotation of the low pressure compressor using the first electrical machine, and controlling rotation of the high pressure compressor using the second electrical machine to restart the start-up process or perform the re-light process.

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Номер записи: 80
18-09-2014 дата публикации

Plant state monitoring method, plant state monitoring computer program, and plant state monitoring apparatus

Номер: US20140278237A1
Автор: Masashi Inoue, Masayuki Takahama, Naotaka Mikami, Yoshiyuki Hamaji
Принадлежит: Mitsubishi Heavy Industries Ltd

Provided is a plant state monitoring method which monitors an operation state of a plant by using the Mahalanobis distance based on the plant state amount. The method creates a first unit space as a set of data used to be a reference when judging whether the plant operation state during a start operation period is normal according to the state amount in the plant start operation period. The method also creates a second unit space as a set of data used to be a reference when judging whether the plant operation state during a load operation period is normal according to the state amount in the plant load operation period.

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Номер записи: 81
20-06-2019 дата публикации

Method and System for Mitigating Bowed Rotor Operation of Gas Turbine Engine

Номер: US20190186284A1
Автор: Orkiszewski Charles Stanley
Принадлежит:

Embodiments of systems and methods for operating a gas turbine engine defining a bowed rotor condition are generally provided. The systems and methods include rotating a rotor assembly defining a bowed rotor condition from approximately zero revolutions per minute (RPM) to within a bowed rotor mitigation speed range, in which the bowed rotor mitigation speed range is defined by a lower speed limit greater than zero RPM and an upper speed limit less than or equal to an idle speed condition of the gas turbine engine; applying a load at the rotor assembly via an energy storage device; adjusting the load to limit rotational speed or acceleration of the rotor assembly to within the bowed rotor mitigation speed range for a period of time; and removing the load to enable rotation of the rotor assembly to the idle speed condition following the period of time. 1. A method of operating a gas turbine engine with bowed rotor , the method comprising:rotating a rotor assembly defining a bowed rotor condition from approximately zero revolutions per minute (RPM) to within a bowed rotor mitigation speed range, wherein the bowed rotor mitigation speed range is defined by a lower speed limit greater than zero RPM and an upper speed limit less than or equal to an idle speed condition of the gas turbine engine;applying a load at the rotor assembly via an energy storage device;adjusting the load to limit rotational speed or acceleration of the rotor assembly to within the bowed rotor mitigation speed range for a period of time; andremoving the load to enable rotation of the rotor assembly to the idle speed condition following the period of time.2. The method of claim 1 , wherein applying a load at the rotor assembly further comprises:engaging the energy storage device via a clutch mechanism to couple the rotor assembly to the energy storage device when the rotor assembly rotates to the lower speed limit of the bowed rotor mitigation speed range.3. The method of claim 2 , wherein engaging ...

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Номер записи: 82
20-06-2019 дата публикации

Rotor bow management

Номер: US20190186359A1
Автор: Andrew Stevenson
Принадлежит: Rolls Royce PLC

A method of reducing rotor bow in a high pressure rotor of a gas turbine engine that has in axial flow a low pressure rotor and a high pressure rotor. The method involves storing bleed air from the gas turbine engine when the engine is running to provide stored pneumatic energy; and using that stored pneumatic energy after the engine has been shut-down to rotate the high pressure rotor at a speed and for a duration that reduces rotor bow. A gas turbine engine wherein rotor bow in the high pressure rotor after engine shut-down has been reduced by carrying out the aforesaid method is also disclosed.

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Номер записи: 83
12-07-2018 дата публикации

TURBOCHARGER HAVING THRUST BEARING WITH BIASED OIL FLOW

Номер: US20180195521A1
Автор: Day Andrew
Принадлежит: BORGWARNER INC.

A turbocharger includes a turbine wheel, a compressor wheel, a shaft coupled to the turbine wheel and the compressor wheel, and a thrust bearing. The thrust bearing includes a loaded side and an unloaded side. The loaded side bears a majority of axial loading caused by force imbalances between the turbine wheel and the compressor wheel during engine startup. The thrust bearing restricts oil flow to the unloaded side as compared to the loaded side during engine startup. 1. A turbocharger comprising:a turbine wheel, a compressor wheel, and a shaft coupled to the turbine wheel and the compressor wheel; anda thrust bearing having a loaded side and an unloaded side, the loaded side bearing a majority of axial loading caused by force imbalances between the turbine wheel and the compressor wheel during engine startup, wherein the thrust bearing restricts oil flow to the unloaded side as compared to the loaded side during engine startup.2. The turbocharger according to claim 1 , wherein the thrust bearing includes an oil inlet claim 1 , one or more loaded side outlets claim 1 , a loaded side circumferential channel configured to distribute oil from the oil inlet to the loaded side outlets claim 1 , one or more unloaded side outlets claim 1 , and an unloaded side circumferential channel configured to distribute oil from the oil inlet to the unloaded side outlets claim 1 , wherein the unloaded side circumferential channel is a flow restricting channel.3. The turbocharger according to claim 2 , wherein the unloaded side circumferential channel is at least one of elongated or smaller in cross-sectional size as compared to the loaded side circumferential channel.4. The turbocharger according to claim 3 , wherein the unloaded side circumferential channel is elongated in a serpentine manner.5. The turbocharger according to claim 3 , wherein the unloaded side circumferential channel is smaller in cross-sectional size as compared to the loaded side circumferential channel.6. The ...

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Номер записи: 84
02-10-2014 дата публикации

Solar and steam hybrid power generation system

Номер: US20140290246A1
Автор: Qingping Yang, Yanfeng Zhang, Yilong Chen
Принадлежит: Wuhan Kaidi Engineering Technology Research Institute Co Ltd

Solar and steam hybrid power generation system including a solar steam generator, an external steam regulator, a turboset, and a power generator. A steam outlet end of the solar steam generator is connected to a steam inlet of the turboset. A steam outlet end of the external steam regulator is connected to the steam inlet of the turboset. A steam outlet of the turboset is connected to the input end of a condenser, and the output end of the condenser is connected to the input end of a deaerator. The output end of the deaerator is connected to the input end of a water feed pump. The output end of the water feed pump is connected to a circulating water input end of the solar steam generator. The output end of the water feed pump is connected to a water-return bypass of the external steam.

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Номер записи: 85
02-10-2014 дата публикации

Steam Turbine Power Plant

Номер: US20140290249A1
Автор: KUSUMI Naohiro, NOMURA Kenichiro, SUZUKI Fumiyuki, Takahashi Yuichi, TOMIZAWA Masaaki, Yamanaka Kazunori, YASHIKI Tatsuro, Yoshida Takuya, Yoshida Yasuhiro
Принадлежит: Hitachi, Ltd.

Disclosed is a steam turbine power plant adapted to start operating safely even if prediction accuracy of its startup constraints cannot be obtained. The system calculates predictive values and current values of startup constraints of a steam turbine from process variables of plant physical quantities, next calculates in parallel both a first control input variable for a heat medium flow controller based on predictive values, and a second control input variable for a main steam control valve based on the current values, and while preferentially selecting the first control input variable, if the first control input variable is not calculated, selects the second control input variable instead. After the selection of at least one of the first and second control input variables, the system outputs an appropriate command value to the heat medium flow controller and the main steam control valve according to the kind of selected control input variable. 1. A steam turbine power plant , comprising:heat source equipment that heats a low-temperature flow by applying a heat medium and thus generates a high-temperature flow;a steam generator that generates steam using the high-temperature flow generated by the heat source equipment;a steam turbine driven by the steam generated by the steam generator;an electric generator that converts rotational motive power of the steam turbine into electric power;a controller that controls a load of a plant;a measuring instrument that measures a physical quantity of the plant;a predictive value calculating device that calculates a predictive value of a startup constraint of the steam turbine from a value measured by the measuring instrument;a first control input variable calculating device that calculates a first control input variable for the controller based upon the predictive value;a current value calculating device that calculates a current value of the startup constraint of the steam turbine based upon the value measured by the measuring ...

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Номер записи: 86
02-10-2014 дата публикации

Steam Turbine Power Plant

Номер: US20140290250A1
Автор: NOMURA Kenichiro, SUZUKI Fumiyuki, Takahashi Yuichi, TOMIZAWA Masaaki, Yamanaka Kazunori, YASHIKI Tatsuro, Yoshida Takuya, Yoshida Yasuhiro
Принадлежит: Hitachi, Ltd.

Disclosed is a steam turbine power plant adapted to start operating very efficiently by highly accurate look-ahead control of a plurality of its startup constraints. The power plant includes a fundamental startup constraint prediction device that calculates from a control input variable of the controller a prediction period about a fundamental startup constraint which is short in response time, a reference control input variables calculating device that calculates such a reference control input variable of the controller as the value predicted and calculated by the fundamental startup constraint prediction device will not exceed a limit value, other startup constraint prediction devices each calculating a corresponding prediction period of data about desired one of other startup constraints from the prediction period of reference control input variables data, other control input variable calculating devices each calculating corresponding other control input variables of the controller from the value predicted and calculated by the other startup constraint prediction device , and a control signal output device or that outputs a command value to the controller in accordance with a value selected from the reference control input variable and the other control input variable. 1. A steam turbine power plant , comprising:a heat source equipment that heats a low-temperature flow by applying a heat medium and thus generates a high-temperature flow;a steam generator that generates steam using the high-temperature flow generated by the heat source equipment;a steam turbine driven by the steam generated by the steam generator;an electric generator that converts rotational motive power of the steam turbine into electric power;a controller that controls a plant load; anda steam turbine starting control device that predicts a value of a startup constraint due to a change in physical quantities of the steam in the steam turbine, and controls the controller according to the ...

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Номер записи: 87
27-07-2017 дата публикации

PNEUMATIC DEVICE FOR RAPIDLY REACTIVATING A TURBINE ENGINE, ARCHITECTURE FOR A PROPULSION SYSTEM OF A MULTI-ENGINE HELICOPTER PROVIDED WITH SUCH A DEVICE, AND CORRESPONDING HELICOPTER

Номер: US20170211483A1
Автор: MOULON Frédéric, SERGHINE Camel, Thiriet Romain
Принадлежит:

The invention relates to a device for the rapid reactivation of a helicopter turbine engine (), characterised in that it comprises a pneumatic turbine () mechanically connected to said turbine engine () so as to be able to rotate it and ensure reactivation thereof; a pneumatic storage () connected to said pneumatic turbine () by means of a pneumatic circuit () for supplying pressurised gas to said pneumatic turbine (); a controlled fast-opening pneumatic valve () arranged on the pneumatic circuit () between said storage () and said pneumatic turbine () and suitable for being on demand placed at least in an open position in which the gas can supply said pneumatic turbine (), or in a closed position in which said pneumatic turbine () is no longer supplied with pressurised gas. 1. A device for the rapid reactivation of a helicopter turbine engine , wherein it comprises:a pneumatic turbine mechanically connected to said turbine engine so as to be able to rotate it and ensure reactivation thereof;a pneumatic storage connected to said pneumatic turbine by means of a pneumatic circuit for supplying pressurised gas to said pneumatic turbine,a controlled fast-opening pneumatic valve arranged on the pneumatic circuit between said storage and said pneumatic turbine and suitable for being on demand placed at least in an open position in which the gas can supply said pneumatic turbine, thus allowing reactivation of said turbine engine, or in a closed position in which said pneumatic turbine is no longer supplied with pressurised gas.2. The device according to claim 1 , wherein it further comprises a pressure reducer arranged on said pneumatic circuit between said pneumatic valve and said pneumatic turbine and configured to regulate the pressure of said gas supplying said pneumatic turbine.3. The device according to claim 1 , wherein said pneumatic turbine is mechanically connected to said turbine engine by means of at least one free-wheel.4. The device according to claim 1 , ...

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Номер записи: 88
26-07-2018 дата публикации

STARTER CONTROLLER

Номер: US20180209295A1
Автор: Dranschak David Allan, Kemp Brian Christopher, Puterbaugh Theodore Scott
Принадлежит:

Systems and methods for starting an engine on an aircraft are provided. One example aspect of the present disclosure is directed to a method for starting an engine using an integrated starter. The integrated starter includes a starter air valve and an air turbine starter. The method includes receiving one or more signals indicative of one or more parameters. The method includes determining a valve setting for the starter air valve based at least in part on the one or more signals indicative the one or more parameters. The method includes providing one or more control signals to adjust a position of the starter air valve based at least in part on the valve setting. The position of the starter air valve regulates the flow of fluid into the air turbine starter. 1. A method for starting an engine using an integrated starter , the integrated starter comprising a starter air valve and an air turbine starter , the method comprising:receiving one or more signals indicative of one or more parameters;determining a valve setting for the starter air valve based at least in part on the one or more signals indicative of the one or more parameters; andproviding one or more control signals to adjust a position of the starter air valve based at least in part on the valve setting,wherein the position of the starter air valve regulates the flow of fluid into the air turbine starter.2. The method of claim 1 , wherein the valve setting is an initial setting for the starter air valve.3. The method of claim 2 , further comprising:receiving one or more environmental parameters;determining a second valve setting based on the one or more environmental parameters; andproviding one or more second control signals to adjust the position of the starter air valve based at least in part on the second valve setting.4. The method of claim 3 , wherein the one or more environmental parameters comprise a pressure.5. The method of claim 3 , wherein the one or more environmental parameters comprise a ...

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Номер записи: 89
25-06-2020 дата публикации

FAN ARRANGEMENT FOR A GAS TURBINE ENGINE

Номер: US20200200046A1
Автор: STRETTON Richard G, WILLMOT Michael C
Принадлежит: ROLLS-ROYCE PLC

A gas turbine engine for an aircraft including: engine core including a turbine; and fan including a plurality of fan blades extending radially from a hub, each fan blade having a leading and trailing edge. Turbine includes a lowest pressure turbine stage having a row of rotor blades each extending radially and having a leading and trailing edge. A fan-turbine radius difference is measured as radial distance between: a point on a circle swept by a radially outer tip of the trailing edge of each of the rotor blades of the lowest pressure stage of the turbine; and a point on a circle swept by a radially outer tip of the leading edge of each of fan blades; and a fan speed to fan-turbine radius ratio defined as: 2. The gas turbine engine of claim 1 , wherein the fan speed to fan-turbine radius ratio is in a range between 1.5 rpm/mm and 4.0 rpm/mm.3. The gas turbine engine of claim 1 , wherein the fan speed to fan-turbine radius ratio is in a range between 1.5 rpm/mm and 3.6 rpm/mm.4. (canceled)5. The gas turbine engine of claim 1 , wherein the fan-turbine radius difference is in a range between 50 cm and 120 cm.6. The gas turbine engine of claim 1 , wherein the fan-turbine radius difference is in a range between 55 cm to 85 cm claim 1 , and the fan tip radius of the gas turbine engine is in the range from 110 cm to 150 cm.7. (canceled)8. The gas turbine engine of claim 1 , wherein the maximum take-off rotational fan speed is in a range between 1450 rpm and 3020 rpm.9. The gas turbine engine of claim 1 , wherein the maximum take-off rotational fan speed is in a range between 2100 rpm and 3020 rpm claim 1 , and the fan tip radius of the gas turbine engine is in the range from 110 cm to 150 cm.10. (canceled)1149. The gas turbine engine of claim 1 , wherein a rotor of the lowest pressure turbine stage is shrouded claim 1 , and the radially outer tip of the trailing edge of each of the rotor blades is measured to the underside of the shroud ().12. The gas turbine engine of ...

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Номер записи: 90
04-07-2019 дата публикации

Combustor Assembly for a Turbine Engine

Номер: US20190203611A1
Автор: BLOOM Nicholas John, Geiser Brett Joseph, Newburn Eric Ryan, Stieg Michael Alan
Принадлежит:

A combustor assembly for a gas turbine engine includes a dome defining a slot. The combustor assembly also includes a liner at least partially defining a combustion chamber and extending between an aft end and a forward end. At least a portion of the forward end is received within the slot of the dome. The forward end of the liner defines a plurality of warming holes that allow for a warming airflow to flow therethrough to warm the forward end at a faster rate during transient operating conditions of the engine thereby reducing transient stresses and increasing liner durability. 1. A combustor assembly for a gas turbine engine defining an axial direction , a radial direction , and a circumferential direction , the combustor assembly comprising:a liner at least partially defining a combustion chamber and extending between an aft end and a forward end, the liner comprising an outer surface and an opposing inner surface, wherein the forward end of the liner defines a plurality of mounting openings spaced along the circumferential direction and a plurality of warming openings extending between the outer surface and the inner surface of the forward end.2. The combustor assembly of claim 1 , wherein the forward end of the liner defines a plurality of warming regions positioned between the plurality of mounting openings claim 1 , and wherein the forward end of the liner defines one or more of the plurality of warming openings within each of the plurality of warming regions.3. The combustor assembly of claim 1 , wherein the forward end of the liner defines one or more of the plurality of warming openings adjacent each of the plurality of mounting openings.4. The combustor assembly of claim 1 , wherein the plurality of warming openings each have a diameter between about 0.020 and about 0.080 inches.5. The combustor assembly of claim 1 , wherein the forward end defines a row of warming openings spaced along the axial direction a distance greater than a diameter of one of the ...

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Номер записи: 91
04-07-2019 дата публикации

System and Method for Removing Rotor Bow in a Gas Turbine Engine

Номер: US20190203646A1
Автор: Cannella Andrew Bryan, Dhabade Milind Chandrakant, Drummond Brian, Mittal Shivam, Orkiszewski Charles Stanley, Sharma Praveen
Принадлежит:

The present disclosure is directed to a gas turbine engine structure and method for reducing or mitigating bowed rotor. The method includes coupling a rotor assembly to a mechanical energy storage device via a clutch mechanism when the rotor assembly is at or below a speed limit below an idle speed condition; storing mechanical energy at the mechanical energy storage device via rotation of the rotor assembly at or below the speed limit; releasing mechanical energy from the mechanical energy storage device to rotate the rotor assembly following shutdown of the gas turbine engine; and rotating the rotor assembly via the mechanical energy from the mechanical energy storage device. 1. A gas turbine engine , comprising:a rotor assembly comprising a driveshaft extended along a longitudinal direction and a rotor extended along a radial direction from the driveshaft; anda mechanical energy storage device selectively coupled to a clutch mechanism, wherein the clutch mechanism is coupled to the rotor assembly and the mechanical energy storage device when the rotor assembly is at or below a speed limit defined below an idle speed condition, and wherein the clutch mechanism is decoupled from at least one of the rotor assembly or the mechanical energy storage device when the rotor assembly is above the speed limit.2. The gas turbine engine of claim 1 , wherein the mechanical energy storage device defines claim 1 , at least in part claim 1 , a mechanical energy displacement device claim 1 , wherein displacement of the mechanical energy displacement device rotates the rotor assembly.3. The gas turbine engine of claim 2 , wherein the mechanical energy displacement device defines claim 2 , at least in part claim 2 , a spring coupled to the clutch mechanism claim 2 , wherein compression or tension of the spring induces rotation of the rotor assembly.4. The gas turbine engine of claim 1 , wherein the mechanical energy storage device further comprises a timing mechanism claim 1 , ...

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Номер записи: 92
16-10-2014 дата публикации

Method for starting up a gas and steam turbine system

Номер: US20140305132A1
Автор: Edwin Gobrecht, Erich Schmid, Rainer Newald
Принадлежит: SIEMENS AG

A method for starting a gas and steam turbine system which includes a gas turbine system which includes at least one gas turbine, in addition to at least one steam turbine system which includes at least one steam turbine and at least one steam system is provided. Heat produced by the working fluid and which is released in the gas turbine is guided to the steam system in order to produce steam which drives the steam turbine. During starting, the gas turbine is started prior to the steam turbine and the steam turbine is started in the presence of the first steam in the system and is impinged upon by said steam.

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Номер записи: 93
13-08-2015 дата публикации

Method for operating a combined cycle power plant

Номер: US20150226092A1
Автор: Christoph Ruchti, Stefan Eduard Broesamle
Принадлежит: Alstom Technology AG

A method for operating a combined cycle power plant is disclosed, which has a gas turbine installation and a water-steam cycle connected to the gas turbine installation by a waste heat steam generator and has at least one steam turbine, the gas turbine installation includes a compressor, a combustion chamber, and a turbine. To cool the turbine, air compressed at the compressor is removed, cooled in at least one cooler flowed through by water, thus generating steam, and introduced into the turbine. At least with the gas turbine installation running, prior to or during the start-up of the water-steam cycle, waste heat, which is contained in the steam generated in the at least one cooler, is used to good effect for pre-heating the installation inside the combined cycle power plant.

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Номер записи: 94
02-07-2020 дата публикации

PRE-START MOTORING SYNCHRONIZATION FOR MULTIPLE ENGINES

Номер: US20200207482A1
Автор: Celiberti Louis A., Dunn James W., Kmetz Christopher P., Teicholz Matthew D.
Принадлежит:

An aspect includes a system for pre-start motoring control for multiple engines of an aircraft. The system includes a first engine starting system of a first engine and a controller. The controller is operable to control a motoring time of the first engine starting system relative to one or more other engine starting systems of one or more other engines of the aircraft by adjusting the motoring time of the first engine starting system within a tolerance of the motoring time of the one or more other engine starting systems in a pre-start motoring sequence. 1. A system for pre-start motoring control for multiple engines of an aircraft , the system comprising:a first engine starting system of a first engine; anda controller operable to control a motoring time of the first engine starting system relative to one or more other engine starting systems of one or more other engines of the aircraft by adjusting the motoring time of the first engine starting system within a tolerance of the motoring time of the one or more other engine starting systems in a pre-start motoring sequence.2. The system as in claim 1 , wherein the motoring time of the first engine starting system is controlled relative to the one or more other engine starting systems by comparing a first value of the motoring time of the first engine starting system with a first value of the motoring time of the one or more other engine starting systems and selecting a relative value as the motoring time for the first engine starting system and the one or more other engine starting systems.3. The system as in claim 2 , wherein the controller provides the first value of the motoring time of the first engine starting system to one or more other controllers and receives the first value of the motoring time of the one or more other engine starting systems from the one or more other controllers.4. The system as in claim 2 , wherein the controller maintains the motoring time of the first engine starting system as the ...

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Номер записи: 95
02-07-2020 дата публикации

PASSIVE BLADE TIP CLEARANCE CONTROL SYSTEM FOR GAS TURBINE ENGINE

Номер: US20200208533A1
Автор: Humes Ryan C., Kapadia Behram, Moody Jack, Snyder Brandon R.
Принадлежит:

The present disclosure relates to a gas turbine engine including a turbine wheel mounted for rotation about a central axis and a turbine shroud ring mounted radially outward from the turbine wheel. The turbine wheel includes a plurality of blades that are spaced apart radially from the turbine shroud ring to establish a blade tip clearance gap. The gas turbine engine further includes a blade tip clearance control system that passively controls the size of the clearance gap based on engine operation. 1. A gas turbine engine comprisinga compressor configured to pressurize air moving along a primary gas path of the gas turbine engine,a combustor fluidly coupled to the compressor to receive pressurized air discharged from the compressor and configured to ignite fuel mixed with the pressurized air, anda turbine including (i) a high-pressure section fluidly coupled to the combustor to receive combustion gases generated by fuel burned in the combustor and (ii) a low-pressure section fluidly coupled to receive the combustion gasses exiting the high-pressure section,wherein the high-pressure section includes a turbine wheel mounted for rotation about a central reference axis, a variable-diameter turbine shroud ring that extends around the turbine wheel, and a passive blade-tip clearance control system including a shroud-ring support coupled to the variable-diameter turbine shroud ring that is configured to drive motion of the turbine shroud ring radially inward or outward based on temperature of the shroud-ring support and defining at least in part a cavity located radially outward of the variable-diameter turbine shroud ring, andwherein the cavity is fluidly coupled to a bleed-air passageway that extends from the compressor to the cavity without interruption from a valve and a a cooling-air passageway that extends from the cavity to the low pressure section such that pressurized bleed air from the compressor is conducted to the cavity of the passive blade tip clearance ...

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Номер записи: 96
12-08-2021 дата публикации

Steam turbine plant and cooling method for same

Номер: US20210246809A1
Автор: Daiki Fujimura, Susumu Sekine
Принадлежит: Mitsubishi Power Ltd

A steam turbine plant is provided with: a boiler; a fuel valve; a low-temperature steam generation source; a steam turbine; a main steam line that guides steam generated in the boiler to the steam turbine; a main steam adjustment valve that is provided to the main steam line; a low-temperature steam line that guides low-temperature steam from the low-temperature generation source to a position closer to the steam turbine-side than the main steam adjustment valve in the main steam line; a low-temperature steam valve provided to the low-temperature steam line; and a control device. During a stopping process of the steam turbine plant, the control device sends a command to close the fuel valve, and then sends a command to open the low-temperature steam valve.

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Номер записи: 97
11-08-2016 дата публикации

TURBOMACHINE ACCESSORY GEARBOX BRACKET

Номер: US20160230600A1
Автор: Bettagere Lakshminarayan S., Sondeen Mark R., Van Duyn Keven, Zimmitti Jonathan F.
Принадлежит:

A gearbox assembly includes a housing structure, a shear bracket that connects the housing structure to a hanger to hold the housing structure relative to a turbomachine, and a thermal spray layer between the shear bracket and the housing structure. 1. A gearbox assembly , comprisinga housing structure;a shear bracket that connects the housing structure to a hanger to hold the housing structure relative to a turbomachine; anda thermal spray layer between the shear bracket and the housing structure.2. The gearbox assembly of claim 1 , wherein a portion of the shear bracket is coated in the thermal spray layer.3. The gearbox assembly of claim 2 , wherein the shear bracket interfaces with the housing structure through the portion.4. The gearbox assembly of claim 1 , wherein the housing structure and the shear bracket interface with each other through the thermal spray layer.5. The gearbox assembly of claim 1 , wherein the thermal spray layer is planar and lacks serrations.6. The gearbox assembly of claim 1 , including a plurality of mechanical fasteners that secure the shear bracket to the housing structure.7. The gearbox assembly of claim 1 , wherein the thermal spray comprises nickel and aluminum composite particles.8. The gearbox assembly of claim 1 , wherein the turbomachine is a land-based turbomachine.9. The gearbox assembly of claim 1 , including a gear train housed within the housing structure and a starter secured to the housing structure.10. The gearbox assembly of claim 6 , wherein the starter is a hydraulic starter.11. The gearbox assembly of claim 1 , wherein the thermal spray layer is a plasma spray layer.12. A turbomachine assembly claim 1 , comprising:a turbomachine engine;a housing structure;a gear train within the housing structure that is selectively driven by the turbomachine;a starter within the housing structure that selectively drives the turbomachine; anda shear bracket connecting a flange of the housing structure to a hanger of the turbomachine ...

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Номер записи: 98
12-08-2021 дата публикации

TURBOMACHINE WITH AN ELECTRIC MACHINE ASSEMBLY AND METHOD FOR OPERATION

Номер: US20210249978A1
Автор: Marrinan Patrick Michael, Murrow Kurt David, Smith Justin Paul, Zatorski Darek Tomasz
Принадлежит:

A turbomachine and method for operating a turbomachine comprising a first rotatable component and a second rotatable component each defining a rotatable speed mechanically independent of one another, and an electric machine electrically coupled to the first rotatable component and the second rotatable component such that a load level relative to the first rotatable component and the second rotatable component is adjustable is generally provided. The method includes adjusting a first load at a first rotor assembly of the electric machine electrically coupled to the first rotatable component such that a first speed of the first rotatable component is increased or decreased based on an engine condition and the first load; adjusting a second load at a second rotor assembly of the electric machine electrically coupled to the second rotatable component such that a second speed of the second rotatable component is decreased or increased based on the engine condition and the second load; and transferring electrical energy generated from at least one of the first rotatable component or the second rotatable component. 1. A method for operating a turbomachine , the method comprising:rotating a first rotatable component at a first speed, wherein the first rotatable component comprises a first compressor, and wherein the first rotatable component is operably coupled to a first electric machine;rotating a second rotatable component at a second speed, wherein the second rotatable component comprises a second compressor, and wherein the second rotatable component is operably coupled to a second electric machine; andtransferring energy generated from at least one of the first electric machine or the second electric machine to adjust the first speed or the second speed based on a compressor map determinative of a desired operating condition relative to one or more of a stall margin, a surge margin, an operating pressure ratio, or an operating speed.2. The method of claim 1 , wherein ...

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Номер записи: 99
09-08-2018 дата публикации

STARTER AIR VALVE SYSTEM WITH DUAL ELECTROMECHANICAL CONTROLS

Номер: US20180223738A1
Автор: Clauson Jesse W., Dehais John M., Gelwan David, Goodman Robert, Greenberg Michael D., Kelly Myles R.
Принадлежит:

According to an aspect, a system includes a starter air valve in fluid communication with an air turbine starter to drive motoring of a gas turbine engine responsive to a compressed air flow from a compressed air source. The system also includes a variable-position electromechanical device operable to adjust positioning of the starter air valve and a discrete-position electromechanical device operable to adjust positioning of the starter air valve and limit a motoring speed of the gas turbine engine below a resonance speed of the gas turbine engine responsive to a pulse width modulation control based on a failure of the variable-position electromechanical device. 1. A system comprising:a starter air valve in fluid communication with an air turbine starter to drive motoring of a gas turbine engine responsive to a compressed air flow from a compressed air source;a variable-position electromechanical device operable to adjust positioning of the starter air valve; anda discrete-position electromechanical device operable to adjust positioning of the starter air valve and limit a motoring speed of the gas turbine engine below a resonance speed of the gas turbine engine responsive to a pulse width modulation control based on a failure of the variable-position electromechanical device.2. The system as in claim 1 , wherein the compressed air source is an auxiliary power unit claim 1 , a ground cart claim 1 , or a cross-engine bleed.3. The system as in claim 1 , further comprising a pneumatic actuator operable to drive rotation of a valve plate of the starter air valve to establish a valve-controlled starter air flow to the air turbine starter based on the compressed air flow.4. The system as in claim 3 , wherein the variable-position electromechanical device and the discrete-position electromechanical device are pneumatically coupled to the pneumatic actuator.5. The system as in claim 4 , wherein the variable-position electromechanical device is positioned in a pneumatic ...

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Номер записи: 100