СИСТЕМА УПРАВЛЕНИЯ ТЕМПЕРАТУРОЙ ГАЗОТУРБИННОГО ДВИГАТЕЛЯ С НАГРЕВАТЕЛЬНЫМ ЭЛЕМЕНТОМ ДЛЯ ГАЗОТУРБИННОГО ДВИГАТЕЛЯ

РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2015 139 402 A (51) МПК F01D 21/12 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21)(22) Заявка: 2015139402, 26.02.2014 (71) Заявитель(и): СИМЕНС АКЦИЕНГЕЗЕЛЛЬШАФТ (DE) Приоритет(ы): (30) Конвенционный приоритет: (72) Автор(ы): РОДРИГЕС Хосе Л. (US) 13.03.2013 US 13/798,213 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 13.10.2015 R U (43) Дата публикации заявки: 18.04.2017 Бюл. № 11 (86) Заявка PCT: (87) Публикация заявки PCT: WO 2014/163900 (09.10.2014) A Адрес для переписки: 129090, Москва, ул. Б. Спасская, 25, строение 3, ООО "Юридическая фирма Городисский и Партнеры" R U (57) Формула изобретения 1. Система управления температурой газотурбинного двигателя, содержащая: внешний кожух, окружающий узел профилей газотурбинного двигателя, расположенный соосно во внешнем кожухе так, чтобы между внешним кожухом и узлом профилей имелась полость; первый воздушный эжектор, расположенный над горизонтальной центральной линией внешнего кожуха для выпуска нагретого воздуха в полость, в которой первый воздушный эжектор сформирован из корпуса первого воздушного эжектора с по меньшей мере одним выпускным каналом, расположенным в корпусе первого воздушного эжектора; и по меньшей мере один нагревательный элемент, выступающий в полость для нагревания воздуха в полости. 2. Система по п. 1, в которой по меньшей мере один нагревательный элемент расположен радиально внутри от внешней поверхности корпуса первого воздушного эжектора и в котором выпускное отверстие по меньшей мере одного выпускного канала первого выпускного эжектора расположено на поверхности, обращенное назад по потоку. 3. Система по п. 1, далее содержащая направляющую потока текучей среды, проходящую поперечно так, чтобы по меньшей мере один нагревательный элемент Стр.: 1 A 2 0 1 5 1 3 9 4 0 2 (54) СИСТЕМА УПРАВЛЕНИЯ ТЕМПЕРАТУРОЙ ГАЗОТУРБИННОГО ДВИГАТЕЛЯ С НАГРЕВАТЕЛЬНЫМ ЭЛЕМЕНТОМ ДЛЯ ГАЗОТУРБИННОГО ДВИГАТЕЛЯ 2 0 1 5 1 3 ...

Способ расхолаживания паровой турбины

Изобретение относится к области энергетики и позволяет исключить время, требуемое для проведения консервации теплоэнергетического оборудования при выводе его в ремонт, либо в резерв на срок, превышающий трое суток. Это достигается совмещением процесса консервации с периодом останова блока в режиме расхолаживания турбины под нагрузкой. Ввод реагентов, аммиака и гидразина производят в контур работающего блока после перевода пара, поступающего в турбину в состоянии насыщения, и заканчивают их ввод по завершении расхолаживания турбин. Такое решение позволяет одновременно с первичным трактом обеспечить качественную гидразинную консервацию вторичного тракта, паровой турбины и турбинного оборудования, что при использовании обычных технологий требует значительных дополнительного времени и средств при невысокой степени надежности консервации. Термическую устойчивость гидразина в этом случае обеспечивают ограничением температуры среды по тракту блока - не выше 300°С и дозированием аммиака по условию ...

Устройство для расхолаживания паровой турбины

NACHWEIS VON HEISSEN BEREICHEN IN GAS TURBINEN

Mechanism for the monitoring of the permissible changes of temperature in heat force plants

Switching configuration to the protection of steam turbines against Temperaturstürze of the live steam

HIGH PRESSURE ROTOR STRESS DAMAGE ACCUMULATING METHOD

... - 16 - 54,115 A method for accumulating stress damage induced by temperature differentials in a rotor of a high pressure steam turbine utilizes a representation of stress damage corresponding to a period of continuous temperature change. A counter variable associated with the representation of stress damage is incremented each time there is a significant change in direction of change in stress induced in the rotor. Accumulated stress damage is calculated by summing the products of each counter variable times a coefficient of stress damage corresponding to that counter variable. Accumulated stress damage is added to previously accumulated stress damage, calculated prior to resetting of the counter variables, to produce total accumulated stress damage. The total accumulated stress damage is printed on a permanent storage medium, such as paper, is compared with an alarm setpoint which, if exceeded, results in a message to the operator and may be used to control the operation of the steam turbine ...

TEMPERATURE PROBE ASSEMBLY FOR GAS TURBINE ENGINE

COOLDOWN CONTROL SYSTEM FOR A COMBINED CYCLE ELECTRICAL POWER GENERATION PLANT

METHOD AND SYSTEM FOR DETECTING AN ABNORMAL ENGINE START

Herein provided are methods and systems for detecting an abnormal engine start of a gas turbine engine. An inter-turbine temperature of the engine is measured during engine start. The inter-turbine temperature is compared to an inter-turbine temperature threshold which depends on at least one additional parameter. An abnormal engine start is detected when the inter-turbine temperature exceeds the threshold. The at least one additional parameter may comprise engine rotational speed. The at least one additional parameter may comprise time.

SYSTEM AND METHOD FOR MONITORING FOR SAND PLUGGING IN GAS TURBINE ENGINES

A system and method of monitoring for sand plugging in a gas turbine engine includes sensing differential pressure across a combustor during engine operation. The sensed differential pressure is processed to determine an amount of sand plugging of combustor cooling holes, and an alert is generated when the amount of sand plugging exceeds a predetermined threshold.

TURBINE ENGINE SHUTDOWN TEMPERATURE CONTROL SYSTEM WITH NOZZLE INJECTION FOR A GAS TURBINE ENGINE

A turbine engine shutdown temperature control system (10) configured to limit thermal gradients from being created within an outer casing (12) surrounding a turbine blade assembly (14) during shutdown of a gas turbine engine (16) is disclosed. By reducing thermal gradients caused by hot air buoyancy within the mid-region cavities (18) in the outer casing (12), arched and sway-back bending of the outer casing (12) is prevented, thereby reducing the likelihood of blade tip rub, and potential blade damage, during a warm restart of the gas turbine engine (16). The turbine engine shutdown temperature control system (10) may operate during the shutdown process where the rotor (26) is still powered by combustion gases or during turning gear system operation after shutdown of the gas turbine engine, or both, to allow the outer casing (12) to uniformly, from top to bottom, cool down.

COMPONENT AND METHOD OF FABRICATING THE SAME

A component for a gas turbine engine (100) is provided. The component includes a cooling aperture (194, 196) and a plug (204) filling at least a portion of the cooling aperture to prevent airflow through the cooling aperture. The plug is configured to melt at a predetermined temperature during operation of the gas turbine engine to permit airflow through the cooling aperture.

Verfahren zur Überwachung der durch ungleichmässige Wärmeverteilung verursachten gegenseitigen Verkrümmung des Gehäuses und des Läufers von Turbomaschinen und Einrichtung zur Durchführung des Verfahrens.

Schaltungsanordnung zum Schutze von Dampfturbinen gegen Temperaturstürze des Frischdampfes

Verfahren zur Überwachung der zulässigen Temperaturänderungen, insbesondere in Wärmeströmungsmaschinen

Thermocouple Assembly.

Eine Thermoelementanordnung (50) enthält eine Thermoelementsonde (52), die innerhalb einer Sondenisolierhülse (72) starr enthalten ist. Ferner ist ein Schutzrohr (56) vorgesehen, das ein erstes Ende, ein zweites Ende und einen hohlen Abschnitt aufweist, der sich in einer Längsrichtung des Schutzrohrs (56) von dem ersten Ende zu dem zweiten Ende erstreckt, wobei der hohle Abschnitt eingerichtet ist, um die Thermoelementsonde und die Sondenisolierhülse darin aufzunehmen. Eine Strahlungsabschirmung ist mit dem Schutzrohr in der Nähe des zweiten Endes des Schutzrohrs integral ausgebildet. Eine Gewindemutter (84) steht mit einem Gewindeabschnitt des Schutzrohrs in der Nähe des ersten Endes des Schutzrohrs in Gewindeeingriff, um bei einer Eingriffsverbindung mit dem Schutzrohr die Thermoelementsonde und die Sondenisolierhülse positionsmässig zu fixieren. Eine solche Thermoelementanordnung kann insbesondere in Turbinensystemen verwendet werden.

Thermocouple Assembly.

Eine Thermoelementanordnung (50) enthält eine Thermoelementsonde (52), die innerhalb einer Sondenisolierhülse (72) starr enthalten ist. Ferner ist ein Schutzrohr (56) vorgesehen, das ein erstes Ende, ein zweites Ende und einen hohlen Abschnitt aufweist, der sich in einer Längsrichtung des Schutzrohrs (56) von dem ersten Ende zu dem zweiten Ende erstreckt, wobei der hohle Abschnitt eingerichtet ist, um die Thermoelementsonde und die Sondenisolierhülse darin aufzunehmen. Eine Strahlungsabschirmung ist mit dem Schutzrohr in der Nähe des zweiten Endes des Schutzrohrs integral ausgebildet. Eine Gewindemutter (84) steht mit einem Gewindeabschnitt des Schutzrohrs in der Nähe des ersten Endes des Schutzrohrs in Gewindeeingriff, um bei einer Eingriffsverbindung mit dem Schutzrohr die Thermoelementsonde und die Sondenisolierhülse positionsmässig zu fixieren. Eine solche Thermoelementanordnung kann insbesondere in Turbinensystemen verwendet werden.

Thermal picture giving system for a turbine.

Die Erfindung betrifft ein Bildgebungssystem (36) mit mindestens einer Kamera, das konfiguriert ist, um ein erstes Bild (108) einer umlaufenden Komponente (56) in einem Innenraum einer Turbine (18) unter Verwendung einer ersten Integrationszeit aufzunehmen, ein zweites Bild (110) der umlaufenden Komponente (56) in dem Innenraum der Turbine (18) unter Verwendung einer zweiten Integrationszeit, die sich von der ersten Integrationszeit unterscheidet, aufzunehmen und das erste Bild (108) von dem zweiten Bild (110) zu subtrahieren, um ein Differenzbild (112) zu erhalten. Eine zweidimensionale Temperaturkarte von der umlaufenden Komponente wird auf der Basis der Signale bestimmt.

Thermal picture giving system for a turbine.

Die Erfindung betrifft ein Bildgebungssystem (36) mit mindestens einer Kamera, das konfiguriert ist, um ein erstes Bild (108) einer umlaufenden Komponente (56) in einem Innenraum einer Turbine (18) unter Verwendung einer ersten Integrationszeit aufzunehmen, ein zweites Bild (110) der umlaufenden Komponente (56) in dem Innenraum der Turbine (18) unter Verwendung einer zweiten Integrationszeit, die sich von der ersten Integrationszeit unterscheidet, aufzunehmen und das erste Bild (108) von dem zweiten Bild (110) zu subtrahieren, um ein Differenzbild (112) zu erhalten. Eine zweidimensionale Temperaturkarte von der umlaufenden Komponente wird auf der Basis der Signale bestimmt.

Defect mode recognition mechanism.

Die Einrichtung dient zur Erkennung von Problemen an Turbinenschaufeln in Echtzeit und bietet durch Einbezug von physikalisch basierten Korrekturen und Temperaturmodellmethoden eine im Vergleich zu bekannten Methoden genauere Vorhersagefähigkeit für die Lebensdauerabschätzung von Turbinenteilen im Heissgaspfad. Die Einrichtung verwendet Pyrometerdaten (12, 24) und Betriebsdaten (14, 26) zur Generierung von physikalisch basierten Korrekturen (18, 30) der Pyrometerdaten sowie physikalisch basierte Schaufeltemperaturabschätzungen (20) und Defektsignaturen (32).

System and method for detecting an abnormality in a combustion section of a gas turbine.

Die Erfindung betrifft ein System (60) und ein Verfahren zum Erkennen einer Anomalie in einem Verbrennungsabschnitt einer Gasturbine. Das System (60) umfasst mehrere mit einem Verbrennungsabschnitt verknüpfte Brennkammern, mehrere thermische Sensoren (50), die um eine Abgassektion (22) einer Gasturbine angeordnet sind, und eine Verarbeitungsschaltung (62) mit einem Speicher (70). Das Verfahren schliesst das Empfangen von den mehreren thermischen Sensoren (50), die um die Abgassektion (22) der Gasturbine angeordnet sind, der Abgasprofildaten der Gasturbine ein. Das Verfahren analysiert ferner die Abgasprofildaten, um statistische Merkmale zu berechnen, die mit einem Spitze-Tal-Muster verknüpft sind. Das Verfahren stellt ferner, unter Verwendung eines Maschinenlernalgorithmus, fest, dass die statistischen Merkmale anormal sind. Als Reaktion auf die Feststellung verarbeitet das Verfahren die Abgasprofildaten für einen vorbestimmten Zeitraum und meldet eine Anomalie in einem Verbrennungsabschnitt ...

Fiber Bragg lattice Messpaket and system for temperature measurement in gas turbines.

Ein Faser-Bragg-Gitter-Mehrpunkte-Temperaturmesssystem (44) weist ein Fasermesskabelpaket (52) und mehrere entlang einer Innenoberfläche einer Wand in Umfangsrichtung verteilte Klemmvorrichtungen (50) zum Befestigen des Fasermesskabelpakets auf. Das Fasermesskabelpaket weist ein auf einem Faser-Bragg-Gitter basierendes Messkabel (53) auf, das wenigstens eine optische Faser (12), mehrere in die optische Faser eingeschriebene Bragg-Gitter (14) und eine Gewebelage und ein die optische Faser umgebendes Hüllrohr aufweist. Das Mehrpunkte-Fasermesssystem weist eine Lichtquelle zum Übertragen von Licht an die Bragg-Gitter und ein reflektiertes Licht empfangendes Detektormodul auf. Jede Klemmvorrichtung weist wenigstens ein Strahlungs-T-Stück (54) auf und definiert wenigstens ein Montageloch zum Befestigen des Fasermesskabels.

Fiber-Bragg grating- measuring package and system for measuring temperature in gas turbines.

Ein Faser-Bragg-Gitter-Mehrpunkte-Temperaturmesssystem (44) weist ein Fasermesskabelpaket (52) und mehrere entlang einer Innenoberfläche einer Wand in Umfangsrichtung verteilte Klemmvorrichtungen (50) zum Befestigen des Fasermesskabelpakets auf. Das Fasermesskabelpaket weist ein auf einem Faser-Bragg-Gitter basierendes Messkabel (53) auf, das wenigstens eine optische Faser (12), mehrere in die optische Faser eingeschriebene Bragg-Gitter (14) und eine Gewebelage und ein die optische Faser umgebendes Hüllrohr aufweist. Das Mehrpunkte-Fasermesssystem weist eine Lichtquelle zum Übertragen von Licht an die Bragg-Gitter und ein reflektiertes Licht empfangendes Detektormodul auf. Jede Klemmvorrichtung weist wenigstens ein Strahlungs-T-Stück (54) auf und definiert wenigstens ein Montageloch zum Befestigen des Fasermesskabels.

Fiber Bragg lattice Messpaket and system for temperature measurement in gas turbines.

Ein Faser-Bragg-Gitter-Mehrpunkte-Temperaturmesssystem (44) weist ein Fasermesskabelpaket (52) und mehrere entlang einer Innenoberfläche einer Wand in Umfangsrichtung verteilte Klemmvorrichtungen (50) zum Befestigen des Fasermesskabelpakets auf. Das Fasermesskabelpaket weist ein auf einem Faser-Bragg-Gitter basierendes Messkabel (53) auf, das wenigstens eine optische Faser (12), mehrere in die optische Faser eingeschriebene Bragg-Gitter (14) und eine Gewebelage und ein die optische Faser umgebendes Hüllrohr aufweist. Das Mehrpunkte-Fasermesssystem weist eine Lichtquelle zum Übertragen von Licht an die Bragg-Gitter und ein reflektiertes Licht empfangendes Detektormodul auf. Jede Klemmvorrichtung weist wenigstens ein Strahlungs-T-Stück (54) auf und definiert wenigstens ein Montageloch zum Befestigen des Fasermesskabels.

Turbine engine temperature control system with heating element for a gas turbine engine

Turbo expander with temperature intelligent protective device

METHOD FOR REDUCING SPEED IN THE EVENT OF BREAKAGE OF THE TURBINE SHAFT OF A GAS TURBINE ENGINE

La présente invention porte sur une méthode pour réduire la vitesse de rotation, dans un moteur à turbine à gaz, d'une turbine comprenant un rotor (6) entraînant un arbre (8) et mobile en rotation à l'intérieur d'un stator (7), en cas de rupture dudit arbre. Cette méthode est caractérisée par le fait qu'elle consiste à mesurer (11) la température en un point sur une surface du stator (10A) située en aval du rotor (6), transmettre le signal de mesure à un moyen de commande (100) du freinage du rotor, ledit moyen de commande étant agencé pour commander le freinage du rotor lorsque la température atteint un seuil. L'invention porte également sur le dispositif.

IMPROVEMENTS WITH the SYSTEMS OF DEVICE CONTROL

L'invention concerne un système de commande pour appareils. Ce système comprend un premier détecteur sensible aux radiations d'une première plage de fréquences reçues de l'appareil pour engendrer un signal de commande de sortie representatif d'une caractéristique de fonctionnement de l'appareil, un second détecteur sensible aux radiations d'une seconde plage de fréquences pour engendrer un second signal de sortie caractéristique d'un événement transitoire survenant pendant l'utilisation de l'appareil, ledit événement étant également détecté par le premier détecteur, et des moyens sensibles à la génération du second signal de sortie pour modifier le premier signal de sortie au moins pendant la durée de l'événement. Application à la commande des moteurs à turbine à gaz The invention relates to a control system for apparatus. This system comprises a first detector responsive to radiations of a first range of frequencies received from the apparatus to generate an output control signal representative of an operating characteristic of the apparatus, a second detector responsive to radiations of a first frequency range received from the apparatus. second frequency range for generating a second output signal characteristic of a transient event occurring during use of the apparatus, said event also being detected by the first detector, and means responsive to generation of the second output signal for modify the first output signal at least for the duration of the event. Application to the control of gas turbine engines

MULTI THERMOCOUPLE FOR GAS TURBINE EXHAUST GAS, SENSING THE TEMPERATURE OF THE EXHAUST GAS

PURPOSE: A multi thermocouple for gas turbine exhaust gas is provided to prevent damage and bending due to vibration or bending by measuring the temperature without direct contact with inner part of the gas turbine. CONSTITUTION: A fixing unit(10) is installed at an exhaust gas outlet of a gas turbine. An external protection part(30) is inserted into the fixing unit and is combined to the fixing unit. An internal protection part(50) is inserted into the external protection part and is combined to the external protection part. A thermal sensor(70) is installed in an internal protection part and senses the heat of the exhaust gas. A first coupling unit(20) couples the fixing unit with the external protection part. A second coupling unit(40) couples the external protection part with the internal protection part. © KIPO 2009 ...

증기 터빈을 냉각하는 방법

... 본 발명은 증기 터빈(2)의 이론적 최대 냉각율을 결정하고, 증기의 열 에너지가 사전 설정된 냉각율을 초과하거나 그 아래로 떨어지지 않도록 증기 발생기(6)를 동작시키는 자동화 시스템에 관한 것이다.

TURBINE ENGINE SHUTDOWN TEMPERATURE CONTROL SYSTEM WITH NOZZLE INJECTION FOR A GAS TURBINE ENGINE

A turbine engine shutdown temperature control system (10) configured to limit thermal gradients from being created within an outer casing (12) surrounding a turbine blade assembly (14) during shutdown of a gas turbine engine (16) is disclosed. By reducing thermal gradients caused by hot air buoyancy within the mid-region cavities (18) in the outer casing (12), arched and sway-back bending of the outer casing (12) is prevented, thereby reducing the likelihood of blade tip rub, and potential blade damage, during a warm restart of the gas turbine engine (16). The turbine engine shutdown temperature control system (10) may operate during the shutdown process where the rotor (26) is still powered by combustion gases or during turning gear system operation after shutdown of the gas turbine engine, or both, to allow the outer casing (12) to uniformly, from top to bottom, cool down.

AIR PURGING UNIT FOR AN OPTICAL PYROMETER OF A GAS TURBINE ENGINE

In order to measure the temperature of the mid-span first stage rotor blade (16) of a gas turbine engine, an optical pyrometer (42) is mounted in the inner casing (32) of the gas turbine engine and includes an elongated sight tube (50) extending from the optical lens (46) of the pyrometer and through the wall of the engine separating the inner casing from the rotor. The sight tube (50) includes an array of spaced apertures (54) extending therethrough in the vicinity of the optical lens, with each aperture extending at an acute angle to the longitudinal axis of the sight tube away from the optical lens. Pressurized air within the inner casing (32) passes through the array of apertures and effectively forms a conically-shaped fluid screen for preventing smoke, dust, fumes or other contaminants from contaminating the optical lens (46). A secondary fluid screen may be provided by mounting the free end of the sight tube in an enlarge opening (34) in the wall of the engine casing, whereby a secondary ...

Cooldown control system for a combined cycle electrical power generation plant

In a combined cycle electrical power generator plant, the shut-down process includes a cooldown control period which is minimized before shutting down the gas turbine by detecting first whether a non-steaming condition has been reached and whether the gas turbine has been reduced to minimum load.

Turbomachinery heat transfer system

A heat management system for turbomachinery is provided. The heat management system includes a thermal delivery system configured to providing heating, cooling, or a combination thereof, to a turbomachinery. The thermal delivery system includes a first heat transfer conduit and a second heat transfer conduit. The second heat transfer conduit is disposed on the turbomachinery adjacent to the first heat transfer conduit. The heat management system additionally includes a controller operatively coupled to the thermal delivery system and configured to control the heating, the cooling, or the combination thereof, of the turbomachinery via the thermal delivery system.

TAABINNO SHUJOKIONDOTEIKATORITSUPUSOCHI

Способ расхолаживания паровой турбины

Способ расхолаживания паровой турбины

Einrichtung zum Schutz von Turbomaschinenlagern gegen UEbererwaermung

Air temperature sensor having a bushing

DETECTION OF GAS TURBINE ENGINE HOT SECTION CONDITION

A system and a method for detecting gas turbine engine hot section condition using temperature measurements during engine operation. The system comprises a sensing unit for sensing a temperature distribution across a hot combustion gas stream generated by a gas turbine engine combustor. A signal processor receives temperature signals from the sensing unit and generates a combustor malfunction signal when the difference between a maximal temperature and a minimal temperature of the sensed temperature distribution is greater than a predetermined acceptable delta value.

TURBINE BLADE (BUCKET) HEALTH MONITORING AND PROGNOSIS USING NEURAL NETWORK BASED DIAGNOSTIC TECHNIQUES IN CONJUNCTION WITH PYROMETER SIGNALS

Oxidation of turbine buckets may cause unexpected and expensive turbine failures. Turbine bucket oxidation condition may be estimated to predict remaining useful bucket life during operation of a turbine by processing time-varying temperature distributions measured with a pyrometer of at least one rotating turbine bucket.

CONTROL SYSTEMS FOR APPARATUS

Afterheat intelligent self-adaption turbine power generation system

Vapor supplementing and cooling system of zero-output low-pressure cylinder

Steam turbine system

Control method for turbine set starting and stopping

PERFECTIONNEMENTS AUX SYSTEMES DE COMMANDE D'APPAREILS

L'invention concerne un système de commande pour appareils. Ce système comprend un premier détecteur sensible aux radiations d'une première plage de fréquences reçues de l'appareil pour engendrer un signal de commande de sortie representatif d'une caractéristique de fonctionnement de l'appareil, un second détecteur sensible aux radiations d'une seconde plage de fréquences pour engendrer un second signal de sortie caractéristique d'un événement transitoire survenant pendant l'utilisation de l'appareil, ledit événement étant également détecté par le premier détecteur, et des moyens sensibles à la génération du second signal de sortie pour modifier le premier signal de sortie au moins pendant la durée de l'événement. Application à la commande des moteurs à turbine à gaz ...

CORRECTED PARAMETER CONTROL METHOD FOR A TWO-SHAFT GAS TURBINE

A corrected parameter control method for a two-shaft gas turbine, of the type in which the protection of the said turbine is provided by a first control loop which controls the opening of fuel valves to keep the gas temperature Tfire at the inlet to a first wheel of the said turbine and the fuel/air ratio F/A within specified limits: this control is provided in such a way that the exhaust temperature TX has values calculated by a linear approximation, in other words as the sum of a reference temperature TXbase to which are added corrections relating to a single environmental or operating parameter which differs from the reference parameter; a second control loop, which controls the opening of a valve (bleed valve) located between the outlet of the axial compressor and the atmosphere, controls the F/A ratio: this control is provided in such a way that the exhaust temperature has values calculated by a linear approximation. © KIPO & WIPO 2007 ...

METHOD AND SYSTEM FOR DETERMINING A CHARACTERISTIC OF A ROTATING MACHINE

A rotating machine has a stationary portion, and a rotating portion. The stationary portion and the rotating portion having a fluid passage therebetween. The stationary portion comprising a first fluid channel, a well, and a second fluid channel spaced apart from the first fluid channel. The first fluid channel fluidically is coupled to receive fluid from the fluid passage. A sensor is coupled to the stationary portion and is disposed at the well.

Turbine engine and method of cooling thereof

A turbine engine including a core engine cowl including a compartment, a cooling airflow source positioned within the compartment, and a full authority digital engine control (FADEC) system coupled in communication with the cooling airflow source. The FADEC system is configured to determine a flight status of the turbine engine, and actuate the cooling airflow source when the turbine engine is not in flight, and before the turbine engine has been shut down, such that heat is exhausted from the compartment.

Gas turbine plant with high detection sensitivity of extraordinary state

A gas turbine plant includes a combustion section, a turbine section, an exhaust section, a temperature detecting unit, and a monitoring unit. The combustion section combusts fuel using air to generate combustion gas. The turbine section is driven with the combustion gas from the combustion section. The exhaust section is connected to the turbine section to exhaust the combustion gas from the turbine section. The temperature detecting unit is provided in the exhaust section to measure a temperature of the combustion gas. The monitoring unit generates a warning signal based on a tolerable level and data corresponding to a temporal change of the temperature measured by the temperature detecting unit to indicate an extraordinary state of the gas turbine plant.

GAS TURBINE ENGINE STARTER REDUCTION GEAR TRAIN WITH STACKED PLANETARY GEAR SYSTEMS

According to an aspect, a system for a gas turbine engine (54) includes a reduction gear train (122) operable to drive rotation of a starter gear train (132) that interfaces to an accessory gearbox (70) of the gas turbine engine. The reduction gear train includes a starter interface gear that engages the starter gear train, a core-turning clutch (124) operably connected to the starter interface gear, and a plurality of stacked planetary gear systems (150) operably connected to the core-turning clutch and a core-turning input (128). The system also includes a mounting pad including an interface to couple a core-turning motor (110) to the core-turning input of the reduction gear train.

УСТРОЙСТВО УПРАВЛЕНИЯ ТУРБИНЫ И СПОСОБ РЕГУЛИРОВАНИЯ ЦИКЛА НАГРУЖЕНИЯ ТУРБИНЫ

Изобретение предназначено для управления турбины. Устройство управления турбины обеспечивает регулирование цикла изменения нагрузки турбины с использованием блока ограничения, на который подается величина для переменного задания интервала времени t v процесса изменения нагрузки и в котором определение регулировочного параметра VAR турбины для осуществления цикла изменения нагрузки производится на интервале времени t v с учетом максимально допустимого граничного значения. В блоке определения износа производится предварительное определение усталости материала для цикла изменения нагрузки, реализованного в соответствии с регулировочным параметром VAR турбины. Изобретение также относится к способу регулирования цикла изменения нагрузки турбины. Такое выполнение турбины и такой способ позволяет достигнуть гибкое, соответствующее эксплуатационным требованиям к выработке электрической энергии изменение рабочих условий турбины. 2 с. и 8 з.п.ф-лы, 2 ил. Гэсбтс пы сэ (19) РОССИЙСКОЕ АГЕНТСТВО ПО ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ ВИ "” 2 193 671. (51) МПК? 13) С2 Е ОТО 19/02, 21/12 12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ РОССИЙСКОЙ ФЕДЕРАЦИИ (21), (22) Заявка: 99112196/06, 07.11.1997 (24) Дата начала действия патента: 07.11.1997 (30) Приоритет: 08.11.1996 ОЕ 19646182.0 (43) Дата публикации заявки: 10.04.2001 (46) Дата публикации: 27.11.2002 (56) Ссылки: СВ 1546352 А, 23.05.1979. СН 390947 А, 31.08.1965. $Ц 1132032 А, 30.12.1984. 5Ц 1250663 АЛ, 15.08.1986. $Ц 1459336 АЛ, 10.09.1996. ОЕ 2605689 А, 04.08.1977. Ц$ 4228359 А, 14.10.1980. 4$ 4558227, 10.12.1385. (85) Дата перевода заявки РСТ на национальную фазу: 08.06.1999 (86) Заявка РСТ: ОЕ 97/02607 (07.11.1997) (87) Публикация РСТ: \М/О 98/21451 (22.05.1998) (98) Адрес для переписки: 129010, Москва, ул. Б.Спасская, 25, стр.3, ООО "Юридическая фирма Городисский и Партнеры", Ю.Д.Кузнецову, рег.№ 595 (71) Заявитель: СИМЕНС АКЦИЕНГЕЗЕЛЛЬШАФТ (0Е) (72) Изобретатель: ГОБРЕХТ Эдвин (ОЕ), ЛАНГБАИН Рольф (ПЕ) (73) Патентообладатель: СИМЕНС ...

Устройство для расхолаживания паровой турбины

Система защиты газотурбинного двигателя

СИСТЕМА ЗАЩИТЫ ГАЗОТУРШННО- ГО ДВИГАТЕЛЯ, содержащая послейова- тельно соединенные датчик температуры газов перёд турбиной, первый усилитель, основной корректиру1мций контур компенсации постоянной времени датчика температуры, второй усюштель и блок защиты двигателя, о т л и ч а - ю щ а я с я тем, что, с целью повышения надежности защиты на режимах, отличных от номинального, система содержит дополнитёльнйё корректирующие контуры, подключенные к основному через коммутатор." ...

GRAPHISCHE BENUTZERSCHNITTSTELLE FÜR DAMPFTURBINENBETRIEBSBEDINGUNGEN

Verfahren und Vorrichtung zur Online-Messung von Defekten bei Turbinenwärmedämmschichten

TURBINENLEITEINRICHTUNG SOWIE VERFAHREN ZUR REGELUNG EINES LASTWECHSELVORGANGS EINER TURBINE

Detecting bearing thermal anomalies

A system for identifying misalignments in a shaft 14, or bearing wipe in a bearing that supports a shaft, of an electrical machine 11 comprising a turbine 12 and a generator 10. The system includes obtaining bearing metal temperature (BMT) readings from a first BMT sensor 26 proximate to the turbine and a second BMT sensor 28 proximate the generator, and obtaining operational data including lube oil inlet temperature, speed and power. The system for identifying misalignments includes providing a warning in response to the first sensor reporting a temperature increase and the second sensor reporting a temperature decrease. The system for identifying bearing wipe includes either or both of i) steady state bearing wipe analysis that issues a warning in response of one of the sensors reporting a temperature increase, and ii) transient state bearing wipe analysis that issues a warning in response to a detected spike from one of the sensors during a start-up or coast-down of the electrical machine ...

TURBINE LOW PRESSURE BYPASS SPRAY VALVE CONTROL SYSTEM AND METHOD

AIR PURGING UNIT FOR AN OPTICAL PYROMETER OF A GAS TURBINE ENGINE

... .degree. In order to measure the temperature of the mid-span first stage rotor blade of a gas turbine engine, an optical pyrometer is mounted in the inner casing of the gas turbine engine and includes an elongated sight tube extending from the optical lens of the pyrometer and through the wall of the engine separating the inner casing from the rotor. The sight tube includes an array of spaced apertures extending therethrough in the vicinity of the optical lens, with each aperture extending at an acute angle to the longitudinal axis of the sight tube away from the optical lens. Pressurized air within the inner casing passes through the array of apertures and effectively forms a conically-shaped fluid screen for preventing smoke, dust, fumes, or other contaminants from contaminating the optical lens. A secondary fluid screen may be provided by mounting the free end of the sight tube in an enlarged opening in the wall of the engine casing, whereby a secondary, generally cylindrical flow of ...

FIRE MITIGATION SYSTEM FOR GAS TURBINE ENGINE

The described gas turbine engine includes a fire mitigation system in fluid system thereof, and includes an air-introduction component located in a fluid conveying conduit upstream of a liquid pump of the fluid system. The air-introduction component has a sacrificial element which remains in place during normal operation of the gas turbine engine but has a heat-induced failure point lower than tat of a remainder of the fluid conveying conduit such that it fails when exposed to a threshold temperature greater than the heat-induced failure point. Failure of the sacrificial element allows air introduction into the fluid conveying conduit upstream of the liquid pump, thereby starving the liquid pump in the event of a fire condition generating the threshold temperature.

PROCESSES AND SYSTEMS FOR MODELING BY NEURAL NETWORKS OF PARTS OF TURBINES

Procédés et systèmes pour empêcher des jeux dans une turbine. Dans une forme de réalisation, un procédé peut comprendre l'application (704) d'au moins un paramètre de fonctionnement comme entrée à au moins un modèle de réseau neuronal, la modélisation (706), à l'aide du modèle de réseau neuronal, d'une dilatation thermique d'au moins une pièce de turbine et l'exécution (708) d'une action de commande au moins en partie sur la base de la dilatation thermique modélisée de la ou des pièces de turbine. Un exemple de système peut comprendre une unité de commande servant à déterminer '702) et appliquer (704) les paramètres de fonctionnement comme entrées au modèle de réseau neuronal, à modéliser (706) la dilatation thermique à l'aide du modèle de réseau neuronal et à exécuter (708) une action de commande au moins en partie sur la base de la dilatation modélisée.

Structure and method to mitigate rotor bow in turbine engine

A gas turbine engine including a first rotor assembly comprising a first drive shaft extended along a longitudinal direction; a housing coupled to the first rotor assembly to provide rotation of the first rotor assembly around an axial centerline; a first accessory assembly, wherein the first accessory assembly sends and/or extracts energy to and from the first rotor assembly; and a first clutch assembly disposed between the first rotor assembly and the first accessory assembly. The first clutch assembly engages and disengages the first rotor assembly to and from the first accessory assembly.

Gas turbine and method of monitoring the operation of such a gasturbine

Es soll ein Verfahren zur Betriebsüberwachung einer Gasturbine (1) mit einer Anzahl von jeweils eine thermische Schutzschicht (23), insbesondere eine TBC-Schutzschicht, aufweisenden und mit jeweils mindestens einem integriertem Kühlmittelkanal (29) versehenen Turbinenschaufeln (12, 14) angegeben werden, das auf möglichst einfache Weise eine zuverlässige Erkennung von Beschädigungen an der jeweiligen Schutzschicht (23) während des Betriebs der Gasturbine (1) ermöglicht. Dazu wird erfindungsgemäß anhand einer Temperaturerhöhung des im Kühlmittelkanal (29) einer Turbinenschaufel (12, 14) strömenden Kühlmittels (K), vorzugsweise Kühlluft, auf eine Beschädigung der thermischen Schutzschicht der Turbinenschaufel (12, 14) geschlossen.

СПОСОБ И УСТРОЙСТВО ДЛЯ УМЕНЬШЕНИЯ СКОРОСТИ ВРАЩЕНИЯ РОТОРА В СЛУЧАЕ РАЗРУШЕНИЯ ВАЛА ТУРБИНЫ ГАЗОТУРБИННОГО ДВИГАТЕЛЯ

Изобретение относится к способу, предназначенному для уменьшения в газотурбинном двигателе скорости вращения турбины, содержащей ротор, приводящий в движение тот или иной вал и имеющий возможность вращаться внутри статора, в случае разрушения упомянутого вала. Этот способ отличается тем, что он состоит в измерении температуры в некоторой точке на поверхности статора, располагающейся по потоку позади ротора, в передаче сигнала этого измерения в средства управления торможением ротора, причем это средство управления выполнено таким образом, чтобы включать торможение ротора в том случае, когда упомянутая температура достигает некоторого предварительно определенного порогового значения. Изобретение относится также к устройству, предназначенному для реализации этого способа. Технический результат - обеспечение простоты и эффективности данных способа и устройства. 2 н. и 7 з.п. ф-лы, 3 ил.

СИСТЕМА И СПОСОБ ЗАЩИТЫ КОНСТРУКТИВНОЙ ЦЕЛОСТНОСТИ ПИЛОНА ДВИГАТЕЛЯ

Группа изобретений относится к системам и способу защиты конструктивной целостности пилона двигателя. Система содержит два контрольных устройства, установленных рядом друг от друга возле пилона двигателя, контроллер. Для защиты конструктивной целостности пилона двигателя определяют с использованием контроллера отказ первого или второго контрольного устройства, при отказе обоих контрольных устройств уменьшают рабочий параметр газотурбинного двигателя. 3 н. и 17 з.п. ф-лы, 22 ил.

Способ защиты турбомашины

Способ защиты турбомашины от неравномерного прогрева

Устройство для ограничения температуры газов двухвальной газотурбинной установки

A method for detecting overpressure inside a compartment associated with a gas turbine nacelle

SYSTEM AND METHOD FOR DETECTING INLET TEMPERATURE DISTORTION OF AN ENGINE

A system and method for detecting inlet temperature distortion of an engine are described. The method comprises obtaining an outside air temperature from at least one first sensor, obtaining an inlet temperature of the engine from at least one second sensor, determining an inlet temperature distortion based on a difference between the outside air temperature and the inlet temperature, comparing the inlet temperature distortion to a threshold, and issuing an alert when the inlet temperature distortion exceeds the threshold.

SYSTEM AND METHOD FOR DYNAMIC ENGINE MOTORING

There is provided a dynamic motoring system and method for an aircraft engine. Motoring of the engine is initiated for an initial motoring duration and at an initial motoring interval. At least one engine parameter is measured in real-time during the motoring, the at least one engine parameter comprising a temperature of the engine. The initial motoring duration and the initial motoring interval are modified in real-time, based on a value of the at least one engine parameter during the motoring, to obtain a modified motoring duration and a modified motoring interval. The motoring continues for the modified motoring duration and at the modified motoring interval, with a speed of rotation of the engine being controlled using the modified motoring interval.

OPERATIONS SUPPORT SYSTEMS AND METHODS FOR CALCULATING AND EVALUATING TURBINE TEMPERATURES AND HEALTH

An operations support system is provided for an engine with a turbine having a turbine inlet. The system includes a diagnostic engine model unit configured to receive engine data from the engine and to generate diagnostics data based on the engine data, the diagnostics data including scalars. The system further includes an engine-specific model unit coupled to the diagnostic engine model unit and configured to receive the scalars from the diagnostic engine model unit and configured to generate turbine inlet temperature information for the engine using a thermodynamic model. The thermodynamic model is based on component maps associated with the engine. The system further includes a storage unit coupled to the engine-specific model unit and configured to store the turbine inlet temperature information.

DEVICE FOR DETECTING TIE STRINGS, ESPECIALLY FOR A SYSTEM FOR DETECTING LEAKS AND OVERHEATING ON A PIPE IN A PIPING SYSTEM

METHOD AND CONTROL SYSTEM FOR STOPPING A GAS TURBINE.

PROCESS AND SYSTEM TO DETECT FRICTIONS IN A STEAM TURBINE

Procédé (40) pour détecter des frottements entre des pièces (17, 22) d'une turbine (10) à vapeur, le procédé comprenant : la détection (42) d'une température à une pluralité d'endroits (24, 25) sur un carter de la turbine à vapeur, la comparaison (44) des températures détectées de la pluralité d'endroits ; la détection (46, 48, 50) des frottements entre les pièces si un emplacement de la pluralité d'emplacements a une température détectée supérieure à la température détectée aux autres endroits de la pluralité d'endroits, et le signalement (52, 56) du frottement comme se situant à un emplacement proche de celui de la pluralité d'endroits qui a la température détectée plus élevée.

APPARATUS FOR CONTROLLING THRUST AND COOLING BEARING USING COMPRESSED AIR

The present invention relates to an apparatus for controlling thrust and cooling a bearing using compressed air. According to the present invention, the apparatus for controlling thrust and cooling a bearing using compressed air comprises: a shaft where a rotation body is mounted; a housing surrounding the shaft at a predetermined distance from the shaft to form a flow passage where air compressed by the rotation body flows; a plurality of supply flow passages as a passage where the compressed air is supplied toward the flow passage to be separately installed at predetermined positions on the flow passage; a valve installed on the plurality of supply flow passages; a pressure sensor separately installed on the plurality of supply flow passages; and a control unit which controls an amount of the compressed air supplied via each supply flow passage by producing displacement information of the shaft from the pressure of each supply flow passage measured by the pressure sensor and controlling ...

TEMPERATURE CONTROL SYSTEM OF SWITCHING OFF OF THE MOTOR TURBINE INJECTION NOZZLE FOR A GAS TURBINE

METHOD AND SYSTEM FOR SOAK-BACK MITIGATION BY ACTIVE COOLING

A method of mitigating soak-back in a gas turbine engine including an engine core compartment and an active engine core compartment cooling system are provided. The active engine core compartment cooling system includes an aperture extending through a core engine cowl forming a radially outer wall of the engine core compartment. The active engine core compartment cooling system also includes a cooling fan mounted within the engine core compartment and including a cooling fan inlet and a cooling fan outlet. The cooling fan inlet is coupled in flow communication with the aperture. The cooling fan outlet is coupled in flow communication with the engine core compartment. The active engine core compartment cooling system further includes a cooling fan controller configured to at least one of control a rotational speed of the cooling fan and control a position of at least one flow control valve coupled in series flow communication with the cooling fan. 1. An active engine core compartment cooling system comprising:an aperture extending through a core engine cowl that forms a radially outer wall of the engine core compartment;a cooling fan mounted within the engine core compartment and comprising a cooling fan inlet and a cooling fan outlet, the cooling fan inlet coupled in flow communication with said aperture, the cooling fan outlet coupled in flow communication with the engine core compartment; anda cooling fan controller configured to at least one of control a rotational speed of said cooling fan and control a position of at least one flow control valve coupled in series flow communication with said cooling fan.2. The system of claim 1 , wherein said aperture extends from the engine core compartment to a bypass duct at least partially surrounding the engine core compartment.3. The system of claim 1 , wherein said cooling fan is electrically powered.4. The system of claim 1 , wherein said gas turbine engine comprises a rotor and a stator claim 1 , said cooling fan ...

OVERHEAT SENSOR SYSTEM

SYSTEM AND METHOD FOR DETECTION OF EXCESSIVE FLOW IN A FLUID SYSTEM

There is provided a system and method for detecting excess flow in an engine fluid system (200, 200'), the method comprising sensing a temperature of a fluid flowing in a fluid line (202) of the fluid system (200, 200'), the fluid line (202) located downstream of a fluid flow restrictor (204) configured to receive the fluid from a source (210) upstream thereof and to flow the fluid from the source (210) into the fluid line (202) downstream thereof, comparing the temperature to a temperature threshold, and when the temperature is beyond the temperature threshold, detecting excess flow of the fluid in the fluid line (202) and outputting an excess flow indication accordingly.

VERFAHREN ZUM BETREIBEN EINER TURBINE

TEMPERATURE PROBE ASSEMBLY FOR GAS TURBINE ENGINE

TEMPERATURE PROBE ASSEMBLY FOR GAS TURBINE ENGINE A self-contained temperature probe assembly for sensing the disc cavity temperature of a gas turbine engine is shown. The assembly includes a thermocouple probe comprising an upper tube and a lower tube housing the probe leads. The lower tube extends from the cylinder housing through the blade ring to guide the probe tip through a hollow vane to adjacent a rotor disc and includes a tapered portion for sealing engagement with a tapered aperture in the blade ring as biased by a coil spring. The upper tube extends outwardly from the turbine cylinder to the probe head. The adjacent ends of the two tubes are retained in a standard flange in predetermined spaced relation against outward withdrawal and the lead wires are coiled within the space to maintain a slack condition to prevent transmission of vibration of the lead wires into the probe head and also prevent the rather fragile wires from supporting any weight of the probe during shipping ...

METHOD FOR OPERATING A GAS TURBINE AND ALSO GAS TURBINE FOR CARRYING OUT THE METHOD

The invention relates to a method for operating a gas turbine (10), which especially feeds power to a local isolated power supply network, and which comprises a compressor (11) for compressing combustion air which is drawn in from the environment, a combustion chamber (15) for combusting supplied fuel by means of the compressed combustion air, a turbine (12) which is driven by the hot gas from the combustion chamber (15), and a generator (13), which is driven by the turbine (12), for generating electric power. With such a method, an improvement of controlling is achieved by one or more parameters of the gas turbine (10) being measured or determined, by the effective thermal output power (P GT) of the gas turbine (10) being calculated from the measured or determined parameters, and by the calculated effective thermal output power (P GT) being used for controlling the gas turbine (10).

Corrected parameter control method for a two-shaft gas turbine

Fault early warning method and system for steam turbine generator units

本发明涉及设备故障预警与诊断领域，公开了一种汽轮发电机组故障预警方法及系统。其中，该方法包括：确定针对一台汽轮发电机组的多个故障预警内容；针对每个故障预警内容，选择相关联的检测参数；从电厂的PI服务器获取所选择的检测参数；将所获取的检测参数与对应检测参数的实时预测值相比较，根据检测参数与所述实时预测值之间的残差值来判断是否存在异常；以及当存在异常检测参数时，对于该异常检测参数关联的故障预警内容进行预警。通过上述技术方案，通过将从电厂PI服务器获取的检测参数对应到故障预警内容实现故障检测及预警。

turbine with improved balancing device

PROCESS AND CONTROL DEVICE Of STOP Of a GAS TURBINE.

Système de commande d'arrêt d'une turbine à gaz (T), comprenant des moyens de mesure (1) de la vitesse de rotation (θ) de l'arbre de la turbine (T) et des moyens de commande (3) du taux d'ouverture de vannes (V) d'alimentation de la turbine (T) en combustible. Le système comprend des moyens de mesure (2) de la température (T°) à l'échappement de la turbine (T), et en ce que les moyens de commande (3) comprennent des moyens de régulation (10) de la décélération de l'arbre apte à déterminer le taux d'ouverture des vannes (V) d'alimentation en combustible à partir de la température à l'échappement (T°) et de la vitesse de rotation (0) de l'arbre.

THERMAL CONTROL VALVE PROVIDED WITH OVERHEAT AND PRESSURE CONTROL DEVICE

The present invention relates to a thermal control valve provided with an overheat and pressure control device and, more specifically, provides a valve having an inlet unit in which an inlet coupling is formed and an outlet unit in which an outlet coupling is formed, wherein a thermal control device is more installed in the outlet unit, the thermal control device is composed of a connection pipe unit forming connection couplings at both ends and forming coupling holes on side surfaces to face each other and an injection unit installed in the connection pipe unit, and the injection unit includes a nozzle unit coupled to the coupling holes and having one end arranged within the connection pipe unit, a supply unit installed on an upper part of the connection pipe unit, and a connection pipe connecting the nozzle unit to the supply unit, thereby installing the thermal control device in the valve and regularly injecting water via a nozzle to efficiently lower pressure and temperature of vapor ...

MIXED BEARING DEVICE AND DRIVING METHOD THEREOF

The present invention relates to a mixed bearing device and a method of driving the same, wherein a mixed bearing device according to the present invention comprises a pair of first journal bearings installed on both sides of a thrust collar installed on a rotating shaft; A pair of first and second journal bearings respectively provided between the pair of first journal bearings and the thrust collar and having a first jet part capable of jetting fluid in the direction of the axis of rotation and a second jet part capable of jetting fluid into the thrust collar, Journal Bearing; A displacement sensor for detecting an axial movement in a direction opposite to a direction in which the rotary shaft is moved by rotation; And a thrust collar for spraying the fluid through one of the pair of second journal bearings on the basis of the detection value detected by the sensor, And a control unit for controlling the moving unit. Accordingly, when a thrust collar is mounted on both sides of the thrust collar, a bearing capable of jetting fluid can be provided, and when the axial movement of the rotary shaft in the opposite direction to the axial movement of the rotary shaft in response to axial movement of the rotary shaft, When the temperature of the journal bearing becomes higher than the set reference temperature during the rotation of the rotary shaft, the high-pressure fluid is injected through the journal bearing provided with the jetting portion. In this case, A bearing device capable of cooling the journal bearing and thus prolonging its service life, and a drive method thereof are provided.

VARIABLE-SIZED COOLING AIR FLOW PATH

A cooling air flow path (182) through an air cycle machine can include an inlet (184), at least one bearing (170) downstream from the inlet (184) and in fluidic connection with the inlet (184), an outlet downstream from the at least one bearing (170) and in fluidic connection with the at least one bearing, and an adjustment device (188) downstream from the at least one bearing (170) and in fluidic connection with the at least one bearing (170) and the outlet (186) with the adjustment device (188) configured to vary a flow of cooling air through the flow path by adjusting the cross-sectional area of the flow path. A corresponding method of cooling at least one bearing in an air cycle machine.

CONTROL OF POWER GENERATION SYSTEM BY VISUALLY MONITORING COMPONENT DURING OPERATION

Embodiments of the present disclosure include a method for controlling a power generation system (152), the method including: detecting a heat distribution across a component of a power generation system (152) from a thermal output of the component, during operation of the power generation system (152); calculating a projected heat distribution across the component based on a library (300) of modeling data for the power generation system (152); calculating whether a difference between the heat distribution and the projected heat distribution exceeds a thermal threshold; adjusting the power generation system (152) in response to the difference exceeding the predetermined threshold, wherein the adjusting includes modifying an operating setting of the power generation system (152).

SYSTEMS AND METHODS FOR OPERATING A TURBINE ENGINE

A turbine system (100) includes a compressor section (104), an inlet cooling system (122) coupled upstream of the compressor section (104) and configured to cool ambient air entering the compressor section (104), and a turbine section (108) coupled in flow communication with the compressor section (104) and including at least one hot gas path component (140). The system further includes a controller (144) configured to receive feedback parameters indicative of a temperature of the at least one hot gas path component (140), estimate a remaining life of the at least one hot gas path component (140) based on the received feedback parameters, determine a desired power output of the turbine system (100) based on the estimated remaining life of the at least one hot gas path component (140) and a cooling capacity of the inlet cooling system (122), and control operation of the turbine system (100) to cause the turbine system (100) to generate the desired power output.

Method and apparatus for detecting rub in a turbomachine

A system for detecting a rub in a turbomachine, comprising: a turbomachine (10); sensors monitoring turbomachine conditions; and an on site monitor (12) in communication with the sensors, and loaded with instructions to implement a method for detecting a rub in the turbomachine.

GAS TURBINE POWER PLANT

PROBLEM TO BE SOLVED: To provide a gas turbine power plant that ensures high sensitivity of detection of anomaly occurrence even if a blade path temperature is fluctuated without an anomaly, in a gas turbine power plant that monitors the blade path temperature to detect an anomaly in a combustor. SOLUTION: The gas turbine power plant comprises the combustor 3 for generating fuel gas 10, a turbine 2 driven by the fuel gas 3 to emit exhaust gas 11 from a turbine outlet, temperature measuring instruments 13 for measuring temperatures near the turbine outlet, and a monitoring device 15 for generating an alarm signal indicative of an anomaly in the gas turbine power plant according to a temperature change as a change with time in the temperatures near the turbine outlet. COPYRIGHT: (C)2002,JPO ...

System and method for removing heat from a turbomachine

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

Neural network-based turbine monitoring system

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.

STEAM TURBINE SHELL DEFLECTION FAULT-TOLERANT CONTROL SYSTEM, COMPUTER PROGRAM PRODUCT AND RELATED METHODS

Various approaches include: obtaining temperature data indicating temperatures of distinct zones in an upper half of a steam turbine shell and a lower half of a steam turbine shell; determining whether a difference between a temperature of a zone in the upper half of the steam turbine shell and a temperature of a neighboring zone in the lower half of the steam turbine shell exceeds a threshold; and initiating a change in a state of a thermal element in at least one of an adjacent zone to at least one of the zone in the upper half of the steam turbine shell or the neighboring zone in the lower half of the steam turbine shell in response to determining the difference exceeds the threshold. 1. A system comprising: obtaining temperature data indicating temperatures of distinct zones in the upper half of the steam turbine shell and the lower half of the steam turbine shell, the thermal element having corresponding distinct zones as the upper half of the steam turbine shell and the lower half of the steam turbine shell;', 'determining whether a difference between a temperature of a zone in the upper half of the steam turbine shell and a temperature of a neighboring zone in the lower half of the steam turbine shell exceeds a threshold; and', 'initiating a change in the state of the thermal element in at least one of an adjacent zone to at least one of the zone in the upper half of the steam turbine shell or the neighboring zone in the lower half of the steam turbine shell in response to determining the difference exceeds the threshold., 'at least one computing device configured to control a state of a thermal element in contact with a steam turbine shell having an upper half and a lower half, by performing actions including2. The system of claim 1 , wherein the distinct zones includes approximately ten zones in the upper half of the steam turbine shell and approximately ten zones in the lower half of the steam turbine shell.3. The system of claim 1 , wherein the at least ...

TURBOMACHINERY HEAT MANAGEMENT SYSTEM

A system is provided, including a heat management system. The heat management system includes a thermal delivery system configured to providing heating, cooling, or a combination thereof, to a first zone of a turbomachinery, and a controller operatively coupled to the thermal delivery system and configured to control the heating, the cooling, or the combination thereof, of the first zone, to minimize or to eliminate positional changes, structural changes, or a combination thereof, in one or more components of the turbomachinery due to thermal energy. 1. A system , comprising: a thermal delivery system configured to providing heating, cooling, or', 'a combination thereof, to a first zone of a turbomachinery; and', 'a controller operatively coupled to the thermal delivery system and configured to control the heating, the cooling, or the combination thereof, of the first zone, to minimize or to eliminate positional changes, structural changes, or a combination thereof, in one or more components of the turbomachinery due to thermal energy., 'a heat management system, comprising2. The system of claim 1 , wherein the controller is configured to independently control the heating claim 1 , the cooling claim 1 , or the combination thereof claim 1 , of the first zone from the heating claim 1 , the cooling claim 1 , or the combination thereof claim 1 , of a second zone of the turbomachinery.3. The system of claim 1 , wherein the one or more components comprise a lower shell mechanically coupled to an upper shell of a gas turbine engine claim 1 , and wherein the controller is configured to control the heating claim 1 , the cooling claim 1 , or the combination thereof claim 1 , by deriving a temperature difference between the lower shell and the upper shell.4. The system of claim 3 , wherein the controller is configured to control the heating claim 3 , the cooling claim 3 , or the combination thereof claim 3 , by comparing the temperature different to a temperature difference ...

PLANT CONTROL APPARATUS, PLANT CONTROL METHOD AND POWER PLANT

In one embodiment, a plant control apparatus controls a power plant that includes a combustor to burn fuel with oxygen introduced from an inlet guide vane to generate gas, a gas turbine driven by the gas from the combustor, a heat recovery steam generator to generate steam using heat of an exhaust gas from the gas turbine, and a steam turbine driven by the steam from the heat recovery steam generator. The apparatus controls an angle of the inlet guide vane before a start of the steam turbine to a first angle, controls the angle of the inlet guide vane after the start of the steam turbine to a second angle larger than the first angle, and reduce the angle of the inlet guide vane from the second angle to the first angle or more during the predetermined period. 2. The apparatus of claim 1 , wherein the second output controller continuously reduces the angle of the inlet guide vane from the second angle to the first angle or to the third angle during the predetermined period such that the angle of the inlet guide vane is the second angle at a start time of the predetermined period and the angle of the inlet guide vane is the first angle or the third angle at a completion time of the predetermined period.3. The apparatus of claim 1 , wherein the angle controller calculates a setting value of temperature rising speed of a temperature of the exhaust gas during the predetermined period claim 1 , and controls the angle of the inlet guide vane based on the setting value of the temperature rising speed.4. The apparatus of claim 3 , wherein the angle controller calculates the setting value of the temperature rising speed by dividing a difference between a setting value of the temperature of the exhaust gas at the start time of the predetermined period and a setting value of the temperature of the exhaust gas at the completion time of the predetermined period by the predetermined period.5. The apparatus of claim 4 , whereinthe setting value of the temperature of the exhaust gas ...

PARTIALLY REDUNDANT ELECTRONIC CONTROL SYSTEM

An asymmetrical electronic control system for a gas turbine, which is designed to control a set of functions associated with logic input data or data from sensors and associated with output data, in particular for an actuator, the system including a primary electronic control unit configured to process the entire set of functions; a secondary electronic control unit, partially redundant with the primary unit, configured to process only a strict subset of sufficient functions to operate or start the gas turbine in an acceptable degraded mode when the primary unit is faulty; a redundant or main chain selection and switching module for selecting one or other of the primary and secondary units in order to control the gas turbine according to the operating state of the primary unit. 1. An asymmetric electronic control system of a gas turbine configured to control a set of functions associated with logic input data or coming from sensors and associated with output data especially for actuator(s) , said system comprising:a primary electronic control unit, configured to process the entire set of functions,wherein the control system electronic also comprises:a secondary electronic control unit, partially redundant with the primary unit, configured to process only a strict subset of functions sufficient to maintain in operation or start the gas turbine according to a degraded mode acceptable when the primary unit is in default,a selection and switching module for the selection and switching of one or the other of the primary and secondary units for regulating the gas turbine as a function of an operating state of said primary unit.2. The control system according to claim 1 , wherein the strict subset of sufficient functions corresponds to the vital functions of the gas turbine.3. The control system according to claim 1 , wherein the primary unit and the secondary unit are dissimilar in terms of architecture.4. The control system electronic according to claim 1 , wherein the ...

LIFING AND PERFORMANCE OPTIMIZATION LIMIT MANAGEMENT FOR TURBINE ENGINE

A control for a multi-shaft turbine engine system using electrical machines seeks optimal system performance while accommodating hard and soft component limits. To accommodate the component limits, the control may generate a number of possible operating point options reflecting potential trade-offs in performance, lifing, efficiency, or other objectives. 1. A control for a turbine engine system comprising a plurality of components including a multi-shaft turbine engine and one or more electrical machines coupled to the shafts of the turbine engine , the control comprising:a constraint analyzer to determine applicable component limits based on current operating conditions of the turbine engine system, wherein each of the component limits defines an operating region in which, if the component limit is exceeded, the life or safety of the component may be compromised; anda limit management optimizer to generate a desired operating point and one or more possible operating points for the system based on the current operating conditions, the applicable component limits, and an optimization objective, wherein the one or more possible operating points each represents a functional trade-off involving a reduction in a component function to maintain the component limits, an objective trade-off involving a modification of the optimization objective to maintain the component limits, or a modification of one or more of the component limits.2. The control of claim 1 , wherein the limit management optimizer selects the desired operating point or one of the possible operating points claim 1 , and communicates a control signal to one or more system controllers for the system to achieve the selected operating point.3. The control of claim 2 , wherein the control signal comprises a power extraction control signal and the control communicates the control signal to a generator control unit configured to control the operation of a generator coupled to one of the shafts of the turbine ...

Method for reconstructing non-uniform circumferential flow in gas turbine engines

A method for reconstructing nonuniform circumferential flow in a turbomachine is disclosed which includes receiving one or more wavenumbers of interest, receiving positional information for a plurality of circumferential positions of a plurality of instrumentation probes, receiving signals from the plurality of instrumentation probes to generate a spatially under-sampled data, and from the spatially under-sampled data determining a multi-wavelet approximation reconstructing circumferential flow field.

GAS TURBINE GENERATOR TEMPERATURE DC TO DC CONVERTER CONTROL SYSTEM

A system includes a DC to DC converter coupled with a load, a power source bus coupled with an input of the DC to DC converter, and an energy storage device. The energy storage device and an output of the DC to DC converter are coupled with a load bus, which supplies the load. The power source bus is supplied power by a generator being driven by a gas turbine. During operation, an operational temperature of the gas turbine may be received by the controller. The controller may dynamically adjust a demand output of the DC to DC converter in response to the operational temperature of the gas turbine exceeding a predetermined threshold temperature value for a predetermined period of time. 1. A system comprising:a gas turbine operable at a rated constant speed to rotate an output shaft;a temperature sensor configured to output a temperature signal indicative of an operational temperature of the gas turbine;a generator rotatably coupled with the output shaft and operable to output electric power;a DC to DC converter configured to receive electric power from the generator, the DC to DC converter coupled with a load bus;an energy storage device coupled with the load bus; anda controller configured to receive the temperature signal and dynamically adjust a demand output of the DC to DC converter in response to the operational temperature of the gas turbine exceeding a predetermined threshold temperature value for a predetermined period of time.2. The system of claim 1 , wherein the controller is further configured to dynamically adjust the demand output lower in proportion to a duration of time that the operational temperature exceeds the predetermined threshold temperature value.3. The system of claim 1 , wherein the controller is further configured to dynamically adjust the demand output lower in proportion to a difference between the operational temperature of the gas turbine and the predetermined threshold temperature value.4. The system of claim 1 , wherein the ...

CONTROL DEVICE, GAS TURBINE, CONTROL METHOD, AND PROGRAM

A control device controls a temperature of a shaft seal portion provided around a rotating shaft of a rotating machine to an appropriate temperature by adjusting an amount of the cooling air to be supplied to the shaft seal portion. The control device calculates a sensitivity indicated using the temperature of the shaft seal portion with respect to a flow rate of the cooling air supplied to the shaft seal portion and controls the flow rate of the cooling air so that the sensitivity has a predetermined target value on the basis of the calculated sensitivity. When the sensitivity is calculated, the flow rate is varied in a predetermined range having a certain flow rate as a center. The sensitivity of the temperature at the flow rate as a center is calculated from the variation in the temperature of the shaft seal portion with respect to the variation in the flow rate. 1. A control device configured to control a temperature of a shaft seal portion provided around a rotating shaft of a rotating machine , wherein a flow rate of cooling air is controlled so that a sensitivity indicated by a temperature of the shaft seal portion with respect to the flow rate of the cooling air supplied to the shaft seal portion is to be a predetermined target value.2. The control device according to claim 1 , wherein a predetermined target value associated with the sensitivity is a value of the sensitivity with respect to the flow rate in which the temperature of the shaft seal portion is within an allowable range among sensitivities of a flow rate with respect to the flow rate in a predetermined range from a boundary between a flow rate of the cooling air at which an absolute value of the sensitivity is larger than 0 and a flow rate of the cooling air at which the absolute value of the sensitivity is 0.3. The control device according to claim 2 , wherein the predetermined target value associated with the sensitivity is a value of the sensitivity at a flow rate smaller by a predetermined ...

SYSTEMS AND METHODS OF SERVICING EQUIPMENT

A method of detecting damage to a gas turbine engine, the method including observing a thermal response of the engine during a thermal transition occurring when the engine transitions between an elevated temperature and a lesser temperature; determining potential damage to the gas turbine engine based on the observed thermal response of the gas turbine engine; and generating an action in response to the determined potential damage to the gas turbine engine.

Disc Cavity Thermocouple Upgrade

An arrangement to prevent thermocouple chafing with a guide tube within a rotor disc cavity during gas turbine operation is provided. The arrangement includes an interstage seal housing, a guide tube, and a thermocouple including a tip portion, an elongated portion, a head portion, and an antichafing strip. The guide tube is disposed in a radially extending bore of the interstage seal housing. The tip portion extends radially inward into the rotor disc cavity, the elongated portion is disposed at least partially within the guide tube, and the head portion is disposed radially outward of the casing. The tip portion includes a temperature sensing element which measures the temperature of the rotor disc cavity. The antichafing strip is disposed along the length of the elongated portion so that it is at least partially disposed within the guide tube. A method to prevent premature gas turbine shutdown due to thermocouople failure is also provided.

STEAM TURBINE BLADE, STEAM TURBINE, AND METHOD FOR OPERATING SAME

This steam turbine blade is provided with: a blade body () extending in a radial direction and having an airfoil profile in a cross section perpendicular to the radial direction; and a heater (H) including a heating wire disposed so as to extend along a trailing edge (Er) of the airfoil profile in the blade body (). This configuration makes it possible to further mitigate an efficiency drop due to moisture attached to the surface of the steam turbine blade (). 1. A steam turbine blade comprising:a blade body which extends in a radial direction and of which a cross-sectional shape orthogonal to the radial direction forms an airfoil; anda heater having a heating wire disposed so as to extend along a trailing edge of the airfoil in the blade body.2. The steam turbine blade according to claim 1 ,wherein the blade body is formed of a plate material in a curved state,the plate material forms the airfoil in a state in which a leading edge that is an end edge on a side opposite to the trailing edge is curved and in a state in which surfaces of the plate material facing each other abut each other on a trailing edge side, andthe heating wire is sandwiched between the surfaces facing each other.3. The steam turbine blade according to claim 1 ,wherein the blade body has a first portion including a leading edge that is an end edge on a side opposite to the trailing edge, a second portion that includes the trailing edge and is provided with the heating wire, and a heat insulation and electrical insulation portion that is provided between the first portion and the second portion and thermally and electrically insulates the first portion and the second portion from each other.4. The steam turbine blade according to claim 1 ,wherein, in the blade body, an accommodating groove that extends along the trailing edge and is recessed toward a leading edge side that is an end edge on a side opposite to the trailing edge to accommodate the heating wire is formed.5. The steam turbine blade ...

System and Method For Calibrating A Case Cooling System For A Gas Turbine Engine

A case cooling calibration system for a gas turbine engine comprises a rotor casing, and a rotor stage, rotatably mounted within the rotor casing. 1. A method of calibrating a case cooling system for a gas turbine engine , the engine comprising a rotor stage , the rotor stage being rotatably mounted within a rotor casing , the rotor casing comprising in series fluid communication , a duct , a flow control valve , and a manifold , the valve being operable to regulate an air flow through the duct to the manifold , the manifold arranged radially outwardly around the casing radially coplanar with the rotor stage , (i) positioning a temperature sensing apparatus on the rotor casing, radially outwardly of the rotor stage;', '(ii) closing the valve to prevent air flow through the duct;', '(iii) operating the engine at a fixed power setting for a first predetermined period of time;', '(iv) sensing a temperature of the rotor casing with the temperature sensing apparatus;', '(v) opening the valve to a next flow setting position;', '(vi) repeating steps (iii) to (v) until the valve is fully open;', '(vii) generating a first characteristic being representative of the variation of the rotor casing temperature with valve position for the engine operation at the fixed power setting;', '(viii) determining an engine correction characteristic from a difference between the first characteristic and a second characteristic, the second characteristic being representative of a theoretical prediction of the variation of the rotor casing temperature with valve position for the engine; and', '(ix) transmitting the engine correction characteristic to an engine control unit to calibrate the turbine case cooling system of the engine to enable a predetermined operational radial clearance to be maintained between the rotor stage and the rotor casing., 'the method comprising the steps of2. The method of claim 1 , wherein the valve is operable to regulate an air flow through the duct to the ...

SYSTEM AND METHOD FOR TURBOMACHINERY VANE PROGNOSTICS AND DIAGNOSTICS

One embodiment includes a system including an actuation system of a gas turbine system including an actuator, a positioner including one or more sensors, a motor, and a controller communicably coupled to the positioner and the motor. The actuator is coupled to one or more inlet guide vanes (IGVs) or variable stator vanes (VSVs) and configured to move the IGVs or VSVs, the positioner is configured to position the actuator so that the actuator moves the IGVs or VSVs to a desired angle, the motor is configured to drive the actuator, and the controller is configured to establish one or more baselines for one or more types of data obtained by the sensors at initialization of the gas turbine system, derive a deviation from the baselines, and perform a preventative action if a deviation that meets or exceeds a threshold is derived. 1. A system , comprising: establish one or more baselines for one or more types of data obtained by the sensors at initialization of the gas turbine system;', 'derive a deviation from the baselines; and', 'perform a preventative action if a deviation that meets or exceeds a threshold is derived., 'an actuation system of a gas turbine system comprising an actuator, a positioner including one or more sensors, a motor, and a controller system communicably coupled to the positioner and the motor, wherein the actuator is coupled to one or more inlet guide vanes (IGVs) or variable stator vanes (VSVs) and configured to move the IGVs or VSVs, the positioner is configured to position the actuator so that the actuator moves the IGVs or VSVs to a desired angle, the motor is configured to drive the actuator, and the controller system is configured to2. The system of claim 1 , wherein the controller system comprises a position controller and a gas turbine controller claim 1 , wherein the gas turbine controller is communicatively coupled to the position controller claim 1 , wherein the controller is configured to derive the deviation from the baselines by ...

COOLED COOLING AIR SAFETY THROUGH A TEMPERATURE-MONITORING LINE REPLACEABLE UNIT

A temperature detection device located downstream a cooling network coupled to a gas turbine engine and located upstream of at least one of a compressor rotor of a compressor section of the gas turbine engine and a turbine rotor of a turbine section of the gas turbine engine, is provided. The temperature detection device includes at least one thermocouple configured to detect an operational temperature of the cooling network. The temperature detection device communicates the operational temperature to a control system. 1. A temperature detection device located downstream a cooling network coupled to a gas turbine engine and located upstream of at least one of a compressor rotor of a compressor section of the gas turbine engine and a turbine rotor of a turbine section of the gas turbine engine ,wherein the temperature detection device comprises at least one thermocouple configured to detect an operational temperature of the cooling network andwherein the temperature detection device is configured to communicate the operational temperature to a control system.2. The temperature detection device of claim 1 , wherein the temperature detection device is located in a mixing chamber of the gas turbine engine.3. The temperature detection device of claim 1 , wherein the temperature detection device is located within an engine casing substantially at a re-entry point of cooled-cooling air into the engine casing.4. The temperature detection device of claim 1 , wherein the temperature detection device is located internally to the gas turbine engine.5. The temperature detection device of claim 1 , wherein the temperature detection device is mounted on a probe connecting into an engine casing of the gas turbine engine.6. The temperature detection device of claim 1 , wherein the at least one thermocouple is a plurality of thermocouples.7. The temperature detection device of claim 6 , wherein the plurality of thermocouples comprise a first thermocouple configured to detect a first ...

COOLING FLUID FLOW CONTROL SYSTEM FOR STEAM TURBINE SYSTEM AND PROGRAM PRODUCT

A cooling fluid flow control system for a turbine section of a steam turbine system and a related program product are provided. In one embodiment, a system includes at least one computing device operably connected to a cooling system. The computing device may be configured to control a flow rate of cooling fluid supplied to a steam turbine system by the cooling system by performing actions including modeling a sensitivity of a wheel space temperature to a change in the flow rate in the form of a piecewise linear relationship, the piecewise linear relationship including a flooded flow rate above which the wheel space temperature becomes insensitive to increased flow rate. The computing device also periodically modifies the flow rate of the cooling fluid supplied to the wheel space of the turbine section to approximate a minimum flooded flow rate based on the measured flow rate and the modeling. 1. A system comprising:at least one computing device operably connected to a cooling system for a turbine section of a steam turbine system for controlling a flow rate of cooling fluid supplied to a wheel space of the turbine section by the cooling system, the at least one computing device performing actions including:modeling a sensitivity of a wheel space temperature to a change in the flow rate in the form of a piecewise linear relationship, the piecewise linear relationship including a flooded flow rate above which the wheel space temperature becomes insensitive to increased flow rate;receive a measurement of the flow rate; andperiodically modifying the flow rate of the cooling fluid supplied to the wheel space of the turbine section to approximate a minimum flooded flow rate based on the measured flow rate and the modeling.2. The system of claim 1 , wherein the modeling is based on at least one of: a load of the steam turbine system and a clearance estimate of the steam turbine system.3. The system of claim 1 , wherein the modeling includes:making an initial estimate of ...

Flame detector and method

A method of detecting flame state of a combustor of a turbine engine. The method includes determining at least one of a first derivative and a second derivative of a compressor discharge pressure of a compressor of the turbine engine; determining at least one of a first derivative and a second derivative of a gas turbine exhaust gas temperature of the exhaust gases output by the turbine engine; determining at least one of a first derivative and a second derivative of a gas turbine shaft/rotor speed of the turbine engine; determining at least one of a first derivative and a second derivative of combustor dynamic pressure monitoring; and determining a flame state of a combustor of the turbine engine based on the combustor dynamic pressure monitoring, the determined derivatives of the combustion dynamics, compressor discharge pressure, gas turbine shaft/rotor speed, and gas turbine exhaust gas temperature of the exhaust gases.

HYDROGEN FUEL LEAK DETECTION SYSTEM

A fuel leak detection system for hydrogen fuel system including a monitored component. The fuel leak detection system including a sensor and controller communicatively coupled to the sensor. The sensor is positioned to monitor at least a portion of the monitored component. The sensor is configured (i) to sense a parameter corresponding to a hydrogen fuel leak of the monitored component and (ii) to generate an output. The controller is configured (i) to receive the output of the sensor, (ii) to determine, based on the output of the sensor, if a leak has occurred in the monitored component, and (iii) to generate an output indicating a fuel system leak when the controller determines that the leak has occurred in the monitored component. The monitored component may be a component of one of a fuel tank, a power generator, and a fuel delivery assembly. 1. A hydrogen fuel system comprising:a fuel tank for holding a hydrogen fuel;a power generator configured to generate power;a fuel delivery assembly extending from the fuel tank to the power generator, the fuel delivery assembly being configured to provide the hydrogen fuel from the fuel tank to the power generator in at least one of a gaseous phase and a supercritical phase;a monitored component, the monitored component being a component of one of the fuel tank, the power generator, and the fuel delivery assembly; and (a) a sensor positioned to monitor at least a portion of the monitored component, the sensor being configured (i) to sense a parameter corresponding to a hydrogen fuel leak of the monitored component, and (ii) to generate an output; and', '(b) a controller communicatively coupled to the sensor, the controller configured (i) to receive the output of the sensor, (ii) to determine, based on the output of the sensor, if a leak has occurred in the monitored component, and (iii) to generate an output indicating a fuel system leak when the controller determines that the leak has occurred in the monitored component., ...

AIR-FIRE SEAL AND ASSEMBLY COMPRISING SUCH A SEAL

An air-fire seal designed to be attached to a first tubular member of a turbomachine, such as a bleed duct, and to rest against a second member of the turbomachine, such as an intermediate casing hub, includes an attachment base having an annular shape around a reference axis (Y); a first annular fire-stop lip extending from the attachment base over a first length (L); and a second annular air-sealing lip extending from the attachment base over a second length (L) lower than the first length and facing the first lip. 111.-. (canceled)12. An assembly comprising:a first tubular member of a turbomachine provided with a flange;a second member of the turbomachine comprising a first contact surface and a second contact surface, and an attachment base having an annular shape around a reference axis, the attachment base being attached to the flange;', 'a first annular fire-stop lip extending from the attachment base over a first length and resting against the first contact surface; and', 'a second annular air-sealing lip extending from the attachment base over a second length lower than the first length and facing the first annular fire-stop lip, the second annular air-sealing lip resting against the second contact surface., 'an air-fire seal configured to be attached to the first tubular member, and to rest against the second member of the turbomachine, the air-fire seal including'}13. The assembly according to claim 12 , wherein the first tubular member is a bleed duct of the turbomachine and the second member is an intermediate casing hub of the turbomachine.14. The assembly according to claim 12 , wherein the first contact surface of the second member is perpendicular to the reference axis and wherein the second contact surface of the second member is parallel to the reference axis.15. The assembly according to claim 12 , wherein the first fire-stop lip is located radially outermost relative to the reference axis and the second air-sealing lip is located radially ...

Structure and Method to Mitigate Rotor Bow in Turbine Engine

A gas turbine engine including a first rotor assembly comprising a first drive shaft extended along a longitudinal direction; a housing coupled to the first rotor assembly to provide rotation of the first rotor assembly around an axial centerline; a first accessory assembly, wherein the first accessory assembly sends and/or extracts energy to and from the first rotor assembly; and a first clutch assembly disposed between the first rotor assembly and the first accessory assembly. The first clutch assembly engages and disengages the first rotor assembly to and from the first accessory assembly. 1. A gas turbine engine , comprising:a first rotor assembly comprising a first drive shaft extended along a longitudinal direction;a housing coupled to the first rotor assembly to provide rotation of the first rotor assembly around an axial centerline;a first accessory assembly, wherein the first accessory assembly sends and/or extracts energy to and from the first rotor assembly; anda first clutch assembly disposed between the first rotor assembly and the first accessory assembly, wherein the first clutch assembly engages and disengages the first rotor assembly to and from the first accessory assembly.2. The gas turbine engine of claim 1 , wherein the first clutch assembly is disposed at a shaft coupled to the first rotor assembly and the first accessory assembly claim 1 , wherein the first clutch assembly engages and disengages at least a portion of the shaft from the first rotor assembly and the first accessory assembly.3. The gas turbine engine of claim 1 , wherein the first clutch assembly comprises a first clutch mechanism to engage and disengage the first rotor assembly to and from the first accessory assembly claim 1 , and wherein the first clutch mechanism is disposed at a shaft coupled to the first rotor assembly and the first accessory assembly.4. The gas turbine engine of claim 1 , wherein the first clutch assembly defines one or more of a manual claim 1 , hydraulic ...

LIGHT-OFF DETECTION SYSTEM FOR GAS TURBINE ENGINES

A system for light-off detection in a gas turbine engine according to an example of the present disclosure includes, among other things, a computing device that has memory and a processor. The computing device is configured to execute a data module and a comparison module. The data module is programmed to access data that corresponds to a present rotational speed of a gas turbine engine component. The comparison module is programmed to cause an indicator to be generated in response to determining that an acceleration rate relating to the present rotational speed meets at least one predetermined acceleration threshold, the indicator relating to an engine light-off condition. 1. A system for light-off detection in a gas turbine engine comprising:a computing device including memory and a processor, the computing device configured to execute a data module and a comparison module;wherein the data module is programmed to access data corresponding to a present rotational speed of a gas turbine engine component; andwherein the comparison module is programmed to cause an indicator to be generated in response to determining that an acceleration rate relating to the present rotational speed meets at least one predetermined acceleration threshold, the indicator relating to an engine light-off condition.2. The system as recited in claim 1 , wherein the comparison module is programmed to cause a flow rate of fuel between a fuel source and a combustor to change in response to the acceleration rate meeting the at least one predetermined acceleration threshold.3. The system as recited in claim 2 , wherein the comparison module is programmed to compare the acceleration rate and at least one command associated with the combustor.4. The system as recited in claim 3 , wherein the at least one command includes a fuel flow signal to a fuel valve and an ignition signal to an ignitor of the combustor.5. The system as recited in claim 1 , wherein the gas turbine engine component is a rotor ...

ELECTRIC MOTOR ARRANGEMENTS FOR GAS TURBINE ENGINES

A motor arrangement includes a shaft, a motor with a cage winding fixed in rotation relative to the shaft, and a generator. The generator includes a permanent magnet assembly fixed in rotation relative to the shaft. The permanent magnet assembly and the cage winding are fixed in rotation relative to one another such that the generator generates a sinusoidal AC voltage signal according to an excitation phase applied to the motor for controlling rotor distortion during cool down of a gas turbine engine. 1. A motor arrangement , comprising:a shaft;a motor with a cage winding connected to the shaft; anda generator with a permanent magnet (PM) assembly connected to the shaft, wherein the PM assembly is fixed in rotation relative to the cage winding to generate a position/speed signal that varies according to an excitation signal applied to the motor to provide slow rotation to a gas turbine engine rotor for controlling distortion during cool down.2. The motor as recited in claim 1 , further comprising an enclosure housing the motor and the generator.3. The motor as recited in claim 2 , wherein the shaft is supported for rotation within the enclosure and includes a coupling arranged outside the enclosure.4. The motor as recited in claim 2 , further comprising a temperature sensor adhesively bonded to an interior enclosure wall and arranged between the motor and the generator.5. The motor as recited in claim 2 , further comprising a connector extending between the enclosure interior and enclosure exterior.6. The motor as recited in claim 5 , further comprising a position lead coupling the connector to the generator.7. The motor as recited in claim 5 , further comprising a power lead coupling the connector to the motor.8. The motor as recited in claim 1 , further comprising a bearing supporting the shaft on a side of the motor opposite the generator and/or on a side of the generator opposite the motor.9. The motor as recited in claim 1 , further comprising an A-phase ...

Lifing and performance optimization limit management for turbine engine

A control for a multi-shaft turbine engine system using electrical machines seeks optimal system performance while accommodating hard and soft component limits. To accommodate the component limits, the control may generate a number of possible operating point options reflecting potential trade-offs in performance, lifing, efficiency, or other objectives.

SYSTEM AND METHOD FOR CONTROLLING AN AUXILIARY POWER UNIT INLET DOOR

A system and method for controlling an inlet door of an auxiliary power unit (APU) are provided. It is determined whether a condition to inhibit a start of the APU is present. If no condition to inhibit the start of the APU is present, a door-opening signal comprising instructions to cause the inlet door to be commanded to an open position in advance of a prospective command to start the APU is output. If the condition to inhibit the start of the APU is present, a door-closing signal comprising instructions to cause the inlet door to be commanded to a closed position is output. 1. A method for controlling an inlet door of an auxiliary power unit , the method comprising:determining whether a condition to inhibit a start of the auxiliary power unit is present;if no condition to inhibit the start of the auxiliary power unit is present, outputting a door-opening signal comprising instructions to cause the inlet door to be commanded to an open position in advance of a prospective command to start the auxiliary power unit; andif the condition to inhibit the start of the auxiliary power unit is present, outputting a door-closing signal comprising instructions to cause the inlet door to be commanded to a closed position.2. The method of claim 1 , further comprising receiving input data comprising at least one of a current operating state of the auxiliary power unit claim 1 , an indication as to whether an emergency shutdown of the auxiliary power unit has been commanded claim 1 , and an indication as to whether at least one operational fault causing a shutdown of the auxiliary power unit is present claim 1 , and determining from the input data whether the condition to inhibit the start of the auxiliary power unit is present.3. The method of claim 2 , further comprising determining that no emergency shutdown has been commanded and that no operational fault is present claim 2 , thereby determining that no condition to inhibit the start of the auxiliary power unit is present.4 ...

RANKINE CYCLE DEVICE

A Rankine cycle device in the present disclosure includes an evaporator as a heater, an expander, a cooler, a first temperature sensor, a second temperature sensor, and a control device. The first temperature sensor detects a temperature of the working fluid flowing from an outlet of the heater to an inlet of the expander in the circuit of the working fluid. The second temperature sensor detects a temperature of the working fluid flowing from an outlet of the expander to an inlet of the cooler. The controller controls a number of rotation of the expander based on a difference between a detected temperature of the first temperature sensor and a detected temperature of the second temperature sensor. 1. A Rankine cycle device comprising:a heater that generates a superheated vapor of a working fluid;an expander that expands the working fluid passed through the heater;a cooler that cools the working fluid passed through the expander;a first temperature sensor that detects a temperature of the working fluid flowing from an outlet of the heater to an inlet of the expander;a second temperature sensor that detects a temperature of the working fluid flowing from an outlet of the expander to an inlet of the cooler; anda controller including a processor and a memory storing a program,wherein the program, when executed by the processor, causes the controller to control a number of rotation of the expander based on a difference between the detected temperature of the first temperature sensor and the detected temperature of the second temperature sensor.2. The Rankine cycle device according to claim 1 , whereinthe program, when executed by the processor, further causes the controller to increase the number of rotation of the expander when the difference increases.3. The Rankine cycle device according to claim 1 , whereinthe program, when executed by the processor, further causes the controller to decrease the number of rotation of the expander when the difference decreases.4. The ...

Bonding probe for bonded dual walled turbine components

A bonding probe is used for bonding a cover sheet to a core to form or repair a dual wall structure. The bonding probe includes a body, an attachment end at a distal end of the body, a head at an opposite end of the body, a tip extending from the head, and a cooling passageway. The attachment end couples the body to a resistance welder. The tip extends to form a proximate end of the body. The tip includes a contacting area having a predetermined three dimensional contoured surface. The contacting area aligns with a predetermined area of a three dimensional outer surface of a cover sheet of a dual walled structure. The cooling passageway provides a passageway for a flow of cooling fluid. The cooling passageway extends through the head, and into the tip.

METHOD FOR DETECTING DAMAGE DURING THE OPERATION OF A GAS TURBINE

A method for detecting damage during the operation of a gas turbine, including the following steps: calculating an average value of individual temperature measurement values over a defined sampling time period from an ensemble of temperature sensors in or on the gas turbine; calculating the individual temperature differences between the average value and the individual temperature measurement values over the defined sampling time period; calculating the individual temperature differences for successive sampling time periods over a defined time interval; creating a first distribution by dividing the temperature differences associated with a temperature sensor for the defined time interval into temperature difference intervals; comparing the first distribution with a second distribution of temperature differences likewise divided into temperature difference intervals; and producing an operation signal on the basis of a negative result of the comparison. 1. A method for detecting damage during operation of a gas turbine , comprising:{'sub': avg,k', 'i,k', 'k', 'i, 'calculation of an average value (T) of individual temperature measurement values (T) over a predetermined sampling period (t) of an ensemble of temperature sensors (S) in or on the gas turbine,'}{'sub': i,k', 'avg,k', 'i,k', 'k, 'calculation of the individual temperature differences (ΔT) between the average value (T) and the individual temperature measurement values (T) over the predetermined sampling period (t),'}{'sub': i,k', 'k', '1, 'calculation of the individual temperature differences (ΔT) for chronologically successive sampling periods (t) over a predetermined first time interval (dt),'}{'sub': 1', 'i,k', 'i', '1', 'i,j, 'compilation of a first distribution (D) by dividing the temperature differences (ΔT) assigned to one temperature sensor (S) for the predetermined first time interval (dt) into temperature difference intervals (dT),'}{'sub': 1', '2', 'i,k', 'i,j, 'comparison of the first distribution ...

DUCT RUPTURE DETECTION SYSTEM

A system for detecting a ruptured duct transporting a high-temperature fluid within a gas turbine engine is disclosed. In various embodiments, the system includes a rupture detection line configured to extend within a first fire zone of the gas turbine engine; one or more rupture sensing elements in electrical communication with and disposed along the rupture detection line, the one or more rupture sensing elements configured to detect a presence of a heated fluid having a heated fluid temperature less than a fire temperature; and a processor configured to monitor the one or more rupture sensing elements. 1. A system for detecting a ruptured duct transporting a high-temperature fluid within a gas turbine engine , comprising:a rupture detection line configured to extend within a first fire zone of the gas turbine engine;a plurality of rupture sensing elements in electrical communication with and disposed along the rupture detection line, the plurality of rupture sensing elements configured to detect a presence of a heated fluid having a heated fluid temperature less than a fire temperature; anda processor configured to monitor the plurality of rupture sensing elements.2. The system of claim 1 , wherein the rupture detection line is configured to extend into a second fire zone.3. The system of claim 2 , wherein the rupture detection line includes a first section configured to detect a rupture of a first duct in the first fire zone and a second section configured to detect the rupture of a second duct in the second fire zone.4. The system of claim 3 , wherein the first duct is at least one of a cooling air duct claim 3 , an environmental air duct claim 3 , a de-icing duct and an oil duct.5. The system of claim 3 , wherein the second duct is at least one of an environmental air duct and a de-icing duct.6. The system of claim 2 , wherein the rupture detection line includes a first section configured to detect a rupture of a first duct in the first fire zone and a second ...

METHODS OF DETECTING ONE FAILURE IN A BURNER OF A COMBUSTOR AND TURBINE SYSTEMS

The method is used for detecting one failure in a burner of a combustor of a turbine system; the combustor comprises a plurality of burners arranged annularly; the turbine system comprises a turbine downstream of the combustor, the method comprising the steps of: A) providing a plurality of temperature sensors arranged annularly at the outlet of the turbine, B) detecting a plurality of temperatures through the plurality of temperature sensors, C) calculating a temperature spread indicator as a function of the plurality of temperatures, and D) carrying out a comparison the temperature spread indicator and a threshold; a positive result of this comparison indicates a burner failure. 1. A method of detecting one failure in a burner of a combustor of a turbine system , wherein the combustor comprises a plurality of burners arranged annularly , wherein the turbine system comprises a turbine downstream of said combustor , the method comprising the steps of:A) providing a plurality of temperature sensors arranged annularly at the outlet of said turbine,B) detecting a plurality of temperatures through said plurality of temperature sensors,C) calculating a temperature spread indicator as a function of said plurality of temperatures,andD) carrying out a comparison between said temperature spread indicator and a threshold,wherein a positive result of said comparison indicates a burner failure.2. The method of claim 1 , wherein steps A claim 1 , B claim 1 , C and D are cyclically repeated in time claim 1 , and wherein a set of consecutive positive results of said comparison indicates a burner failure.3. The method of claim 1 , wherein step C comprises the sub-steps of:C1) determining a minimum temperature in said plurality of temperatures,C2) determining a maximum temperature in said plurality of temperatures,andC3) calculating a temperature spread indicator as a difference between said maximum temperature and said minimum temperature.4. The method of claim 3 , comprising the ...

METHODS AND SYSTEMS FOR CONTROLLING TURBINE POWERED SYSTEM TO REDUCE STARTUP TIME

A method for operating a power plant may include, during shutdown of a turbine, controlling a damper to move from a first position directing turbine exhaust to enter a heat recovery system to a second position to allow the turbine exhaust to enter a bypass stack and block the turbine exhaust to the heat recovery system. While the position of the damper is maintained in the second position, fired shutdown of the turbine may be performed. In response to instructions to start the turbine, air flow in an exhaust duct for a predetermined period of time is generated, and after generating the air flow for the predetermined period of time, the turbine may be started without performing a purge sequence for the heat recovery system. After starting the turbine, the damper may be controlled between the second position and the first position. 1. A method for operating a power plant including a turbine , a heat recovery system , a bypass stack and an exhaust duct including a damper configured to direct the flow of exhaust from the turbine to the heat recovery system and/or to the bypass stack , the method comprising:before flame out during fired shutdown of the turbine, control the damper to move from a first position directing turbine exhaust to enter the heat recovery system to a second position to allow the turbine exhaust to enter the bypass stack and block the turbine exhaust to the heat recovery system; perform fired shutdown of the turbine;', 'in response to instructions to start the turbine, generate air flow in the exhaust duct for a predetermined period of time; and', 'after generating the air flow for the predetermined period of time, start the turbine without performing a purge sequence for the heat recovery system; and, 'while the position of the damper is maintained in the second position to prevent gas and/or vapor to enter the heat recovery systemafter starting the turbine, control the damper to move from the second position to the first position to allow the ...

METHOD FOR OPERATING A GAS TURBINE AT PART LOAD

The invention refers to a method for controlling part load operation of a gas turbine comprising a controller wherein a load set point of the controller is greater or equal a minimum load set point. The minimum load set point depends on a hot gas temperature that is calculated based on a hot gas temperature model. 1. A method for controlling part load operation of a gas turbine comprising a controller wherein a load set point of the controller is greater or equal a minimum load set point and wherein the minimum load set point depends on a hot gas temperature that is calculated based on a hot gas temperature model.2. Method according to claim 1 , wherein from the hot gas temperature a minimum hot gas temperature is subtracted and the difference between the hot gas temperature and the minimum hot gas temperature serves as an input to a controller claim 1 , which switches off at least one burner and/or adjusts fuel staging parameter when the difference becomes negative and which switches on at least one burner and/or readjusts a fuel staging parameter when the difference exceeds a threshold value.3. Method according to claim 1 , wherein from the hot gas temperature a minimum hot gas temperature is subtracted and the difference between the hot gas temperature and the minimum hot gas temperature serves as an input to a controller claim 1 , which determines a delta load based on the difference between the hot gas temperature and the minimum hot gas temperature.4. Method according to claim 1 , wherein a first target load is generated based on the actual power AP[MW] of the gas turbine at the moment the claimed method is activated.5. Method according to claim 4 , wherein the minimum load set point is equal to the sum of the first target load and the delta load.6. Method according to claim 4 , wherein the first target load is equal to the actual power of the gas turbine minus an offset.7. Method according to claim 1 , wherein the hot gas temperature model depends from at ...

METHOD FOR DETECTING A FLUID LEAK IN A TURBOMACHINE AND SYSTEM FOR DISTRIBUTING A FLUID

The invention relates to a method for detecting a fluid leak in a turbomachine. The turbomachine comprises a high temperature fluid source, at least one fluid distribution pipe adapted to distribute said fluid to different parts of the turbomachine and/or the aircraft which is intended to be equipped with said turbomachine, a turbomachine compartment in which the distribution pipe is at least partly accommodated, said compartment having in operation a low temperature relative to the high temperature of the fluid supplied by the fluid source. The method comprises the following steps: measuring a temperature variation in the compartment between two instants to obtain a temperature gradient; and detecting a fluid leak if the temperature gradient is greater than or equal to a threshold temperature gradient. The invention further relates to a system for distributing a high temperature fluid for a turbomachine and a turbomachine comprising such a system for distributing a fluid. 1. A method for detecting a fluid leak in an aircraft turbomachine , the turbomachine comprising:a high temperature gas fluid source which provides high temperature gas fluid,at least one gas fluid distribution pipe adapted to distribute the gas fluid to different parts of the turbomachine and/or a aircraft which is intended to be equipped with the turbomachine,a turbomachine compartment in which the distribution pipe is at least partly accommodated, the compartment containing air which has in operation a temperature and a pressure respectively lower to the temperature and the pressure of the gas fluid,the method comprising the following steps:measuring a temperature variation of the air in at least one location in the compartment between two instants to obtain a temperature gradient,detecting a gas fluid leak in the compartment if the temperature gradient is greater than or equal to a threshold temperature gradient.2. The method for detecting a leak according to claim 1 , further comprising the ...

SYSTEM AND METHOD FOR DETECTING LUBRICATED BEARING CONDITION

A monitoring system includes an analytical engine system coupled to a plurality of sensors of an engine system. The analytical engine system is configured to determine a model probability distribution based on model data, determine a distance threshold value of the model probability distribution based at least in part on a threshold percentage, determine a window probability distribution based on window data sampled from the engine system, determine a fraction of the window probability distribution that is greater than the distance threshold value, and generate a lubricant alert signal when the fraction is greater than a temperature anomaly threshold. The model data includes model temperature data and model load data. The window data includes window temperature data and window load data that is based at least in part on feedback from the plurality of sensors during operation of the engine system. 1. A monitoring system , comprising: determine a model probability distribution based on model data, wherein the model data comprises model temperature data and model load data;', 'determine a distance threshold value of the model probability distribution based at least in part on a threshold percentage;', 'determine a window probability distribution based on window data sampled from the engine system, wherein the window data comprises window temperature data and window load data that is based at least in part on feedback from the plurality of sensors during operation of the engine system;', 'determine a fraction of the window probability distribution that is greater than the distance threshold value; and', 'generate a lubricant alert signal when the fraction is greater than a temperature anomaly threshold., 'an analytical engine system coupled to a plurality of sensors of an engine system, wherein the analytical engine system is configured to2. The monitoring system of claim 1 , wherein the analytical engine system is configured to update the model data based on the window ...

METHOD FOR OPERATING A COMBINED CYCLE POWER PLANT

A method for operating a combined cycle power plant, wherein the combined cycle power plant has a gas turbine and a steam turbine and also a shutting-down device, and wherein, for shutting down the gas turbine and the steam turbine, the gas turbine and the steam turbine are operated within a time window that extends from the beginning of the shutting-down procedure at a first time to the falling of the steam temperature to a lower limit value at a second time by the shutting device in such a way that the gas turbine and the steam turbine are relieved substantially at the same time and the block power falls to zero, thermal energy that is stored in the combined cycle power plant preventing immediate falling of a steam temperature to operation below a minimum power output of the gas turbine within the time window. 1. A method for operating a combined cycle power plant , wherein the combined cycle power plant has a gas turbine and a steam turbine and also a shutting-down device , the method comprising:for shutting down the gas turbine and the steam turbine, operating the gas turbine and the steam turbine within a time window that extends from the beginning of the shutting-down procedure at a first time to the falling of the steam temperature to a lower limit value at a second time by means of the shutting-down device in such a way that the gas turbine and the steam turbine are relieved substantially at the same time and the block power falls to zero, thermal energy that is stored in the combined cycle power plant preventing immediate falling of a steam temperature to operation below a minimum power output of the gas turbine within the time window.2. The method as claimed in claim 1 ,wherein the gas turbine is assigned a gas-turbine power controller and the steam turbine is assigned a steam-turbine power controller, andwherein the gas-turbine power controller and the steam-turbine power controller are given the specified respective setpoint value with a respective ...

Method And System For Determining A Characteristic Of A Rotating Machine

A rotating machine has a stationary portion, and a rotating portion. The stationary portion and the rotating portion having a fluid passage therebetween. The stationary portion comprising a first fluid channel, a well, and a second fluid channel spaced apart from the first fluid channel. The first fluid channel fluidically is coupled to receive fluid from the fluid passage. A sensor is coupled to the stationary portion and is disposed at the well.

GAS TURBINE AND OPERATING METHOD THEREOF

Provided is a gas turbine capable of achieving high-speed startup of the gas turbine through quick operation control of an ACC system during startup of the gas turbine, improving the cooling efficiency of turbine stationary components, and quickly carrying out an operation required for cat back prevention during shutdown of the gas turbine. Included are a pressurizing device () connected to a branching channel () branching from the discharge side of a compressor () and capable of carrying out an operation for introducing and pressurizing air independently from the compressor (); a temperature-control-medium supply channel () that guides compressed air pressurized at the pressuring device () to a turbine-cooling-medium channel () provided in stationary components of a turbine (); and a temperature-control-medium return channel () that guides the compressed air that has passed through the turbine-cooling-medium channel () to the discharge side of the compressor () such that the flows are combined, and the pressurizing device () is operated at startup of the gas turbine and in preparation immediately before startup to carry out temperature-raising and cooling by letting the compressed air flow in the turbine-cooling-medium channel (). The pressurizing device () is operated during shutdown of the gas turbine to exhaust the high-temperature gas remaining in the turbine (). 1. A gas turbine that supplies combustion gas generated by supplying fuel to a combustor where the fuel is combusted with compressed air compressed at a compressor to a turbine to acquire rotational power , the gas turbine comprising:pressurizing means connected to a branching channel branching from a discharge-side channel of the compressor and capable of carrying out an operation for introducing and pressurizing a temperature-control medium independently from the compressor;a temperature-control medium supply channel that guides pressurized temperature-control medium pressurized at the pressuring ...

GAS TURBINE AND OPERATING METHOD THEREOF

Provided is a gas turbine capable of achieving high-speed startup of the gas turbine through quick operation control of an ACC system during startup of the gas turbine, improving the cooling efficiency of turbine stationary components, and quickly carrying out an operation required for cat back prevention during shutdown of the gas turbine. Included are a pressurizing device () connected to a branching channel () branching from the discharge side of a compressor () and capable of carrying out an operation for introducing and pressurizing air independently from the compressor (); a temperature-control-medium supply channel () that guides compressed air pressurized at the pressuring device () to a turbine-cooling-medium channel () provided in stationary components of a turbine (); and a temperature-control-medium return channel () that guides the compressed air that has passed through the turbine-cooling-medium channel () to the discharge side of the compressor () such that the flows are combined, and the pressurizing device () is operated at startup of the gas turbine and in preparation immediately before startup to carry out temperature-raising and cooling by letting the compressed air flow in the turbine-cooling-medium channel (). The pressurizing device () is operated during shutdown of the gas turbine to exhaust the high-temperature gas remaining in the turbine (). 1. A gas turbine that supplies combustion gas generated by supplying fuel to a combustor where the fuel is combusted with compressed air compressed at a compressor to a turbine to acquire rotational power , the gas turbine comprising:pressurizing means connected to a branching channel branching from a discharge-side channel of the compressor and capable of carrying out an operation for introducing and pressurizing a temperature-control medium independently from the compressor;a temperature-control-medium supply channel that guides pressurized temperature-control medium pressurized at the pressuring ...

GAS TURBINE AND OPERATING METHOD THEREOF

Provided is a gas turbine capable of achieving high-speed startup of the gas turbine through quick operation control of an ACC system during startup of the gas turbine, improving the cooling efficiency of turbine stationary components, and quickly carrying out an operation required for cat back prevention during shutdown of the gas turbine. Included are a pressurizing device () connected to a branching channel () branching from the discharge side of a compressor () and capable of carrying out an operation for introducing and pressurizing air independently from the compressor (); a temperature-control-medium supply channel () that guides compressed air pressurized at the pressuring device () to a turbine-cooling-medium channel () provided in stationary components of a turbine (); and a temperature-control-medium return channel () that guides the compressed air that has passed through the turbine-cooling-medium channel () to the discharge side of the compressor () such that the flows are combined, and the pressurizing device () is operated at startup of the gas turbine and in preparation immediately before startup to carry out temperature-raising and cooling by letting the compressed air flow in the turbine-cooling-medium channel (). The pressurizing device () is operated during shutdown of the gas turbine to exhaust the high-temperature gas remaining in the turbine (). 1. A gas turbine that supplies combustion gas generated by supplying fuel to a combustor where the fuel is combusted with compressed air compressed at a compressor to a turbine to acquire rotational power , the gas turbine comprising:pressurizing means connected to a branching channel branching from a discharge-side channel of the compressor and capable of carrying out an operation for introducing and pressurizing a temperature-control medium independently from the compressor;a temperature-control-medium supply channel that guides pressurized temperature-control medium pressurized at the pressuring ...

CONTROL OF POWER GENERATION SYSTEM BY VISUALLY MONITORING COMPONENT DURING OPERATION

Embodiments of the present disclosure include a method for controlling a power generation system, the method including: detecting a heat distribution across a component of a power generation system from a thermal output of the component, during operation of the power generation system; calculating a projected heat distribution across the component based on a library of modeling data for the power generation system; calculating whether a difference between the heat distribution and the projected heat distribution exceeds a thermal threshold; adjusting the power generation system in response to the difference exceeding the predetermined threshold, wherein the adjusting includes modifying an operating setting of the power generation system. 1. A method for controlling a power generation system , the method comprising:detecting a heat distribution across a component of a power generation system from a thermal output of the component, during operation of the power generation system;calculating a projected heat distribution across the component based on a library of modeling data for the power generation system;calculating whether a difference between the heat distribution and the projected heat distribution exceeds a thermal threshold;adjusting the power generation system in response to the difference exceeding the predetermined threshold, wherein the adjusting includes modifying an operating setting of the power generation system.2. The method of claim 1 , wherein the library of modeling data includes at least one of operating data of the power generation system claim 1 , or operating data of a different power generation system.3. The method of claim 1 , wherein the library of modeling data includes at least one of projected operating data of the power generation system or a different power generation system.4. The method of claim 1 , wherein visually monitoring the gauge of the power generation system includes causing an infrared camera to capture an image of the ...

Turbine control method for exhaust heat recovery system

According to the present invention, a turbine control method for an exhaust heat recovery system comprises: a normal rotation step of rotating a turbine in a normal direction by means of a working fluid to produce energy; a step of measuring a temperature of the working fluid; and a reverse rotation step of rotating the turbine in a reverse direction when the measured temperature is less than a predetermined temperature. Provided is the turbine control method for an exhaust heat recovery system, which prevents damage to a turbine due to a liquid state of a working fluid remaining inside the turbine. Thus, as the damage to the turbine is prevented, efficiency of an exhaust heat recovery system can be increased.

METHOD AND SYSTEM FOR REAL-TIME NOTIFICATION ABOUT DECREASING CHARACTERISTICS OF CENTRIFUGAL COMPRESSORS

1. Реализуемый на компьютере способ формирования в реальном времени уведомлений о характеристиках центробежного компрессора из парка центробежных компрессоров, причем способ осуществляют с использованием компьютерного устройства, соединенного с интерфейсом пользователя и запоминающим устройством, при этом способ включает:прием фактической термодинамической сигнатуры компрессора, которая является уникальной для компрессора;прием значений технологических параметров компрессора во время работы компрессора;определение в реальном времени фактической характеристики компрессора с использованием значений технологических параметров компрессора;определение в реальном времени прогнозируемой характеристики компрессора с использованием принятой фактической термодинамической сигнатуры компрессора;определение отклонения характеристики компрессора с использованием фактической характеристики и прогнозируемой характеристики;сравнение отклонения характеристики с заранее заданным диапазоном пороговых значений отклонения характеристики; иформирование уведомления для пользователя с использованием результата сравнения.2. Способ по п. 1, в котором прием фактической термодинамической сигнатуры компрессора включает определение одного или более ключевых эксплуатационных показателей (KPI) для работы компрессора с использованием термодинамической сигнатуры данного компрессора.3. Способ по п. 2, дополнительно включающий сравнение одного или более показателей KPI с фактической характеристикой, чтобы генерировать одно или более отклонений характеристики KPI, связанных с одним или более показателями KPI.4. Способ РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (51) МПК G05B 23/02 (13) 2014 133 934 A (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21)(22) Заявка: 2014133934, 01.03.2013 (71) Заявитель(и): Нуово Пиньоне С.Р.Л. (IT) Приоритет(ы): (30) Конвенционный приоритет: 01.03.2012 IT CO2012A000008 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 01.10. ...

Cooldown control system for a combined cycle electrical power generation plant

Method and system for real-time control of burning without water injection with low emission of nitric oxides and diffusion combustion

FIELD: oil and gas industry. SUBSTANCE: invention refers to the method of controlling and diagnosing of malfunctions in the operation of gas turbine. To implement the method, a computer device is used togethwer with an interface device and the device with previously stored thereon sets of rules relating the real time output and input data of the gas turbine operation, in this case the input data are related to the temperature variation of the exhaust gases flow, state of the gas turbine flame detectors, turbine switching into another operating mode, the pressure drop in the fuel gas line is determined and compared with the threshold values, recommendations are given to the gas turbine operator to switch it to another mode provided the pressure diferential meets the specified range of threshold values. Additionally, the faulty combustion chamber is identified by determining the twist angle of the exhaust gases flow by determining the temperature variation from the temperature sensors and compliance with its temperature variation threshold for the specific combustion mode. EFFECT: invention expands the set of methods of control and diagnostics of malfuncations in the gas turbine operation with the help of computer, interface and memory devices, thereby providing timely provision of information about gas turbine malfuncations to prevent accidental shutdowns. 10 cl, 10 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 613 548 C2 (51) МПК G05B 23/02 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ФОРМУЛА (21)(22) Заявка: ИЗОБРЕТЕНИЯ К ПАТЕНТУ РОССИЙСКОЙ ФЕДЕРАЦИИ 2014133939, 01.03.2013 (24) Дата начала отсчета срока действия патента: 01.03.2013 Дата регистрации: Приоритет(ы): (30) Конвенционный приоритет: 01.03.2012 IT CO2012A000008 (45) Опубликовано: 17.03.2017 Бюл. № 8 (73) Патентообладатель(и): Нуово Пиньоне С.Р.Л. (IT) (56) Список документов, цитированных в отчете о поиске: US 6209310 B1, 03.04.2001. EP (85) Дата начала рассмотрения заявки PCT на ...

System for estimating turbine temperature

본 발명의 실시예에 따른 터빈의 온도 추정 시스템을 제공한다. 터빈의 온도 추정 시스템은 가스 터빈의 일 구성의 표면에 배치되는 코팅층, 상기 코팅층에 전류를 인가하여 상기 코팅층의 저항값의 변화를 측정하는 측정부 및 상기 저항값을 기초로 상기 코팅층의 온도를 유추하는 제어부를 포함하고, 상기 코팅층은 열 차폐 코팅 물질 및 온도에 따라 저항값이 변화하는 저항 물질을 포함한다. Provided is a temperature estimation system for a turbine according to an embodiment of the present invention. The temperature estimation system of the turbine infers the temperature of the coating layer based on the coating layer disposed on the surface of one component of the gas turbine, a measuring unit measuring a change in the resistance value of the coating layer by applying a current to the coating layer. And a control unit, wherein the coating layer includes a heat shield coating material and a resistance material whose resistance value changes according to temperature.

Method for detecting damage during operation of a gas turbine

본 발명은 가스 터빈의 동작 중에 손상을 검출하기 위한 방법에 관한 것으로서, 그러한 방법은: 가스 터빈 상의 또는 내의 온도 센서(S i )의 앙상블의 미리 결정된 샘플링 기간(t k )에 걸친 개별적인 온도 측정 값(T i,k )의 평균 값(T avg,k )을 계산하는 단계; 미리 결정된 샘플링 기간(t k )에 걸친 평균 값(T avg,k )과 개별적 온도 측정 값(T i,k ) 사이의 개별적 온도 차이(ΔT i,k )를 계산하는 단계, 미리 결정된 시간 간격(dt 1 )에 걸친 시간적으로 연속적인 샘플링 기간들(t k )에 대한 개별적인 온도 차이(ΔT i,k )를 계산하는 단계, 미리 결정된 시간 간격(dt 1 ) 동안 하나의 온도 센서(S i )에 할당된 온도 차이(ΔT i,k )를 온도 차이 간격(dT i,j )으로 분할함으로써, 제1 분포(D 1 )를 편성하는 단계, 제1 분포(D 1 )를, 마찬가지로 온도 차이 간격(dT i,j )으로 분할된 온도 차이(ΔT i,k )의 제2 분포(D 2 )와 비교하는 단계, 비교의 부정적 결과를 기초로 동작 신호를 생성하는 단계를 포함한다.

Method and system for advising operator action

本发明涉及用于监测和诊断燃气涡轮机的叶轮空间中的异常的系统和计算机执行的方法，所述方法使用耦合至用户接口和存储器装置的计算机装置来实施并且包括：在存储器装置中存储多个规则集，所述规则集与叶轮空间有关，所述规则集包括以实时数据输出相对于实时数据输入的关系表达式表述的至少一个规则，所述关系表达式对于叶轮空间的温度是特定的。所述方法还包括从与燃气涡轮机关联的状态监测系统接收实时和历史数据输入，所述数据输入与向叶轮空间供热的源相关，以及使用与叶轮空间温度相关的输入估计叶轮空间温度值。

Method and system for informing the characteristics of the work of the gas turbine in real time

FIELD: machine engineering. SUBSTANCE: method also includes receiving real-time input data and input data from previous time periods from the gas-turbine state monitoring system. The input data refers to the parameters influencing the characteristics of the gas turbine, periodically determining the current values of the parameters, comparing the initial values with the corresponding current values, determining the time degradation of at least one of the following: the efficiency of the gas turbine compressor, the output power of the gas turbine, the specific heat consumption to a gas turbine and a gas turbine fuel consumption based on mentioned comparison, and recommending to the gas turbine operator a set of correction actions for adjusting this deterioration. EFFECT: increase of efficiency and reliability of gas turbine operation. 10 cl, 8 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 627 742 C2 (51) МПК G01M 15/14 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (21)(22) Заявка: 2014134207, 01.03.2013 (24) Дата начала отсчета срока действия патента: 01.03.2013 Дата регистрации: (73) Патентообладатель(и): Нуово Пиньоне С.Р.Л. (IT) Приоритет(ы): (30) Конвенционный приоритет: 01.03.2012 IT CO2012A000008 (56) Список документов, цитированных в отчете о поиске: US 4249238 A, 03.02.1981. US 20020013664 A1, 31.01.2002. US 6209310 B1, 03.04.2001. RU 2010121150 A, 10.12.2011. RU 2010144075 A, 10.05.2012. (45) Опубликовано: 11.08.2017 Бюл. № 23 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 01.10.2014 (86) Заявка PCT: EP 2013/054154 (01.03.2013) (87) Публикация заявки PCT: 2 6 2 7 7 4 2 (43) Дата публикации заявки: 20.04.2016 Бюл. № 11 R U 11.08.2017 (72) Автор(ы): ФАДЛУН Эвер Авриель (IT), КАЛИДИ Абдуррахман Абдаллах (QA), САРАВАНАПРИЯН Арул (QA), ПИЕРИ Марко (IT), АСХУР Осама Найм (QA) 2 6 2 7 7 4 2 R U Адрес для переписки: 191036, Санкт-Петербург, а/я 24, "НЕВИНПАТ" (54) Способ и система для информирования ...

Method and system for rules of powerful gas turbines diagnostics

Группа изобретений относится к системе и способу контроля и диагностики аномалий во вспомогательных системах газовой турбины. Используют компьютерное устройство с пользовательским интерфейсом и запоминающим устройством для хранения множества наборов правил, связывающих входные и выходные данные реального времени для соответствующих параметров технологического процесса вспомогательных систем газовой турбины, оценивают вышеуказанные параметры с использованием принятых входных данных. Система контроля и диагностики содержит осевой компрессор, турбину низкого давления, набор правил, связывающих входные и выходные данные реального времени для соответствующих параметров технологического процесса вспомогательных систем газовой турбины. Параметры технологического процесса относятся к системе контроля радиальных вибраций и температуры металла подшипников, системе контроля минерального и гидравлического масла, межколесному пространству турбины, выпускным клапанам компрессора, распределению сгорания, контролю температуры на выпуске, системе вентиляции. Обеспечивается своевременность и точность определения неисправностей вспомогательных систем газовой турбины. 2 н. и 8 з.п. ф-лы, 5 ил. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 613 637 C2 (51) МПК G05B 23/02 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ФОРМУЛА (21)(22) Заявка: ИЗОБРЕТЕНИЯ К ПАТЕНТУ РОССИЙСКОЙ ФЕДЕРАЦИИ 2014133935, 01.03.2013 (24) Дата начала отсчета срока действия патента: 01.03.2013 Дата регистрации: (73) Патентообладатель(и): Нуово Пиньоне С.Р.Л. (IT) Приоритет(ы): (30) Конвенционный приоритет: R U 21.03.2017 (72) Автор(ы): БЬЯНУЧЧИ Давид (IT), ПУМО Антонио (IT), КРОЧИАНИ Риккардо (IT), КАЛИДИ Абдуррахман Абдаллах (QA) (56) Список документов, цитированных в отчете о поиске: US 20120016824 A1, 19.01.2012. RU 01.03.2012 IT CO2012A000008 (45) Опубликовано: 21.03.2017 Бюл. № 9 2008144241 A, 20.05.2010. EP 2345878 A2, 20.07.2011. WO 2011003688 A1, 13.01.2011. RU 2010121150 A, 10.12.2011. (85) ...

Method and system for monitoring status of plant group

FIELD: measuring equipment. SUBSTANCE: proposed system contains a database of a plant, configured to store rule sets including at least one rule expressed as at least one of the following: a physics-based model, a data-driven model and an empirical model of a component or plant system, and an expression of the relationship of real-time output data with real-time input data. The system also includes a server computer configured to receive the plant component data from the control panel of the plant unit, to generate virtual sensor outputs using at least one of the following: the physics-based model, data-driven model, and empirical model associated with the component or plant system, to transfer the plant component data and generated virtual sensor output data to the plant database for storage and to the data visualization system for the formation of analytical charts. EFFECT: creation of monitoring and diagnostic tools for the plant. 15 cl, 10 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 636 095 C2 (51) МПК G05B 23/02 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (21)(22) Заявка: 2014133941, 28.02.2013 (24) Дата начала отсчета срока действия патента: 28.02.2013 Дата регистрации: (73) Патентообладатель(и): Нуово Пиньоне СРЛ (IT) Приоритет(ы): (30) Конвенционный приоритет: 01.03.2012 IT CO2012A000008 (56) Список документов, цитированных в отчете о поиске: US 2009/0149972 A1, 11.06.2009. RU 66447 U1, 10.09.2007. WO 2005/124491 A1, 29.12.2005. WO 01/69329 A2, 20.09.2001. (45) Опубликовано: 20.11.2017 Бюл. № 32 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 01.10.2014 (86) Заявка PCT: EP 2013/054098 (28.02.2013) (87) Публикация заявки PCT: 2 6 3 6 0 9 5 (43) Дата публикации заявки: 20.04.2016 Бюл. № 11 R U 20.11.2017 (72) Автор(ы): АЛИ Мохамед (US), КАЛИДИ Абдуррахман (QA), ЧИНЕЛЛИ Филиппо (IT), МОКИ Джанни (IT), ЧИВЕЛИ Валентина (IT) 2 6 3 6 0 9 5 R U Адрес для переписки: 191036, Санкт-Петербург, а/я ...

Method and system for issuing in real time recommendations for restoring the performance of centrifugal compressors

1. Компьютерный способ выдачи в реальном времени рекомендаций по восстановлению рабочих характеристик центробежного компрессора из парка центробежных компрессоров, реализованный с использованием компьютерного устройства, соединенного с пользовательским интерфейсом и запоминающим устройством, и включающий:определение отклонения рабочих характеристик компрессора с использованием определяемых фактических рабочих характеристик компрессора и спрогнозированных рабочих характеристик компрессора;сравнение отклонения рабочих характеристик с заранее заданным пороговым диапазоном отклонения рабочих характеристик ивыдачу рекомендации пользователю в отношении по меньшей мере одного источника отклонения рабочих характеристик, при этом указанная рекомендация содержит значение восстановления рабочих характеристик, доступное для каждого источника.2. Способ по п. 1, также включающий:прием фактической термодинамической сигнатуры компрессора, которая уникальна для компрессора;прием значений параметров технологического процесса компрессора во время работы компрессора;определение в реальном времени фактических рабочих характеристик компрессора с использованием указанных значений параметров технологического процесса компрессора иопределение в реальном времени спрогнозированных рабочих характеристик компрессора с использованием указанной принятой фактической термодинамической сигнатуры компрессора.3. Способ по п. 2, в котором определение фактических рабочих характеристик компрессора и определение спрогнозированных рабочих характеристик компрессора включает определение фактических раб РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (51) МПК G05B 23/02 (13) 2014 133 943 A (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21)(22) Заявка: 2014133943, 01.03.2013 (71) Заявитель(и): Нуово Пиньоне С.Р.Л. (IT) Приоритет(ы): (30) Конвенционный приоритет: 01.03.2012 IT CO2012A000008 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 01.10.2014 R U (43) Дата ...

Gas-turbine engine combustor

The chamber has an annular configuration with fuel inlets around an inlet side. A row of guide vanes (51) is arranged at the outlet side. A number of guide vanes (511-518) have temperature sensors. A fuel supply is provided for each inlet, or a common supply may be provided for each group of adjacent inlets. The fuel supplies lie over a vane with a temperature sensor. Control units (461-468) assigned to each temperature measuring point regulate the fuel quantity. An Independent claim is included for a method for operating the gas turbine combustion chamber.

SYSTEM AND METHOD FOR PROTECTING THE STRUCTURAL STRENGTH OF THE ENGINE Pylon

РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2016 150 951 A (51) МПК B64D 45/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21)(22) Заявка: 2016150951, 23.12.2016 (71) Заявитель(и): ЗЕ БОИНГ КОМПАНИ (US) Приоритет(ы): (30) Конвенционный приоритет: (72) Автор(ы): РАЙТ Роберт С. (US) 15.03.2016 US 15/070796 Адрес для переписки: 190000, Санкт-Петербург, BOX-1125, "ПАТЕНТИКА" Стр.: 1 A 2 0 1 6 1 5 0 9 5 1 R U A (57) Формула изобретения 1. Система для защиты конструктивной целостности пилона двигателя, содержащая: первое контрольное устройство, установленное возле пилона двигателя, соединяющего газотурбинный двигатель с корпусом летательного аппарата; второе контрольное устройство, установленное возле первого контрольного устройства, при этом первое контрольное устройство и второе контрольное устройство каждое выполнено с возможностью отказа при достижении температуры переключения, указывающей на прожог корпуса двигателя во время работы газотурбинного двигателя; и контроллер, соединенный с возможностью связи с первым контрольным устройством и вторым контрольным устройством и выполненный с возможностью автоматического уменьшения рабочего параметра газотурбинного двигателя при отказе обоих указанных контрольных устройств. 2. Система по п. 1, в которой: рабочим параметром является тяга двигателя. 3. Система по п. 2, в которой: контроллер выполнен с возможностью уменьшения тяги двигателя до установки режима не на малом газе. 4. Система по п. 1, в которой: контроллер выполнен с возможностью уменьшения рабочего параметра газотурбинного двигателя, только если второе контрольное устройство отказало в течение заданного времени после отказа первого контрольного устройства. 5. Система по п. 1, дополнительно содержащая: индикатор, соединенный с возможностью связи с контроллером; причем контроллер выполнен с возможностью определения, отказало ли только одно из первого и второго контрольных устройств, и с возможностью инициирования выработки ...

Gas turbine operating method and gas turbine for carrying out the method

Co-generation and Control process of the same

본 발명에 따른 열병합 발전기는, 샤시와; 상기 샤시의 내부에 배치된 발전기와, 상기 샤시의 내부에 배치되고 상기 발전기가 전력을 생산하도록 발전기를 구동시키는 엔진과; 상기 발전기와 엔진과 중 적어도 하나의 열을 회수하여 열수요처로 전달하는 열전달부와; 상기 샤시의 내부 온도를 감지하는 온도 감지부와; 상기 샤시의 내부에 설치되고 사용온도 범위를 갖는 전장부품과; 상기 온도 감지부의 감지 온도가 설정 온도 미만이고, 상기 엔진이 정지이면, 상기 엔진에서 방출되는 열에 의해 상기 전장부품이 사용온도 범위로 승온되게 상기 엔진을 운전시키는 제어부를 포함하여, 부품 수 및 비용을 최소화하면서 전장부품을 보호할 수 있고 안전성이 높은 이점이 있다. A cogeneration unit according to the present invention includes: a chassis; A generator disposed in the interior of the chassis; an engine disposed within the chassis and driving the generator to produce power; A heat transfer unit for recovering at least one heat of the generator and the engine and transferring the heat to the heat consumer; A temperature sensing unit for sensing an internal temperature of the chassis; An electrical component installed inside the chassis and having a temperature range for use; And a control unit for operating the engine so that the electric component is heated to a use temperature range by heat emitted from the engine if the sensed temperature of the temperature sensing unit is lower than the set temperature and the engine is stopped, There is an advantage in that the electric parts can be protected while minimizing and the safety is high. 열병합 발전기, 샤시, 발전기, 엔진, 열전달부 Cogeneration generator, chassis, generator, engine, heat transfer part

Detection of gas turbine airfoil failure

A system and method for early detection of a failure of a gas turbine engine airfoil ( 10 ), such as but not restricted to a burn through of the airfoil outer skin ( 12 ). A sensor ( 52 ) provides a signal ( 54 ) responsive to a condition of fluid flowing through an outer cooling chamber ( 24 ) of the airfoil. A detected change in the condition of the fluid is correlated to a failure of the airfoil, which for example can be detected by measuring the static fluid pressure. An increase in the static pressure of fluid in the outer cooling chamber may indicate a breach in the region of the leading edge of the airfoil. A decrease in the static pressure of fluid in the outer cooling chamber may indicate a breach along other portions of the profile of the airfoil outer skin. Both pressure and temperature parameters of the fluid may be measured and coincident changes thereof correlated to a condition of failure of the airfoil.

Method and system for diagnostic rules for heavy duty gas turbines

사용자 인터페이스 및 메모리 장치에 결합된 컴퓨터 장치를 이용하여 구현된, 가스 터빈의 보조 시스템들 내의 비정상을 모니터링 및 진단하기 위한 컴퓨터-구현된 방법 및 시스템이 제공된다. 상기 방법은 상기 메모리 장치 내에 복수의 규칙 세트들을 저장하는 단계로서, 상기 규칙 세트들이 상기 가스 터빈의 보조 시스템들에 관한 것이고, 상기 규칙 세트들이 실시간 데이터 입력에 대한 실시간 데이터 출력의 관계식으로서 표현되는 적어도 하나의 규칙을 포함하고, 상기 관계식이 상기 가스 터빈의 보조 시스템과 연관된 매개변수들에 대해서 특정적인, 저장 단계, 상기 가스 터빈과 연관된 조건 모니터링 시스템으로부터의 실시간 및 이력 데이터 입력들을 수신하는 단계로서, 상기 데이터 입력들이 상기 가스 터빈의 보조 시스템들과 관련되는, 데이터 입력들을 수신하는 단계, 및 상기 수신된 입력들을 이용하여 상기 가스 터빈의 보조 시스템들과 연관된 매개변수들의 적어도 일부에 대한 값들을 추정하는 단계를 포함한다. A computer-implemented method and system are provided for monitoring and diagnosing anomalies in auxiliary systems of a gas turbine, implemented using a computer device coupled to a user interface and a memory device. The method includes storing a plurality of rule sets in the memory device, wherein the rule sets relate to auxiliary systems of the gas turbine, wherein the rule sets are represented as a relationship of real time data output to real time data input. A storing step, receiving real-time and historical data inputs from a condition monitoring system associated with the gas turbine, comprising a rule, wherein the relation is specific to parameters associated with the gas turbine's auxiliary system, Receiving data inputs, wherein the data inputs are associated with auxiliary systems of the gas turbine, and estimating values for at least some of the parameters associated with auxiliary systems of the gas turbine using the received inputs. Steps.

Gas turbine cooling stage operation method

本申请描述一种在冷却阶段期间运行燃气涡轮(1)的方法。燃气涡轮(1)提供压缩机(2)、在压缩机(2)下游的燃烧器(4)，以及在燃烧器(4)下游的涡轮(6)，其中涡轮(6)提供涡轮导叶架(50)。方法包括以下步骤：将冷却空气流(10，20，30)从压缩机(2)馈送到涡轮导叶架(50)，测量冷却空气流(10，20，30)的温度，以及测量涡轮导叶架(50)的温度。在该方法中，当涡轮导叶架(50)的温度低于冷却空气(10，20，30)的温度时，冷却空气流(10，20，30)以第一流率馈送，并且当涡轮导叶架(50)的温度高于冷却空气(10，20，30)的温度时，冷却空气流(10，20，30)以第二流率馈送，其中，第一流率大于第二流率。还描述了方法和燃气涡轮的各种实施例。

System for validating validity of sensor using control limit and method thereof

본 발명은 관리 한계를 이용한 센서 유효성 검증 시스템 및 그 방법에 관한 것이다. 본 발명에 따르면, 센서 데이터의 모수에 대한 사전 분포와 상기 센서의 과거 데이터를 이용하여 상기 모수의 사후 분포를 베이지안 기법으로 추정하는 단계와, 상기 모수의 사후 분포에 대해 목표로 하는 신용구간을 설정하고 상기 설정한 신용구간을 이용하여 센서 데이터의 관리 한계선을 설정하는 단계, 및 상기 센서의 현재 측정 데이터가 상기 관리 한계선을 이탈하는지 여부를 모니터링하여 상기 센서의 유효성을 검증하는 단계를 포함하는 관리 한계를 활용한 센서 유효성 검증 방법을 제공한다. 본 발명에 따르면, 베이지안 추론을 기반으로 관리 한계를 설정하고 이를 이용하여 현재의 센서 데이터로부터 센서의 유효성을 보다 신뢰성 있게 검증할 수 있도록 한다.

High temperature rake for suspersonic flow

An apparatus measuring the temperature and/or pressure of an exhaust gas plume from a supersonic military jet engine. The apparatus includes a rotatable airfoil having one or more sensors that are impinged by the exhaust gas flow path prior to the exhaust gas flowing over the airfoil. At least one base is attached and adapted to be mounted to a supporting surface for locating the airfoil rearward of the exhaust gas plume.

Gas turbine temp. measurement automatic stepping mechanism - consists of sector plate with arc line of holes and sensors attached to pivoted radial arm

The automatic stepping mechanism is designed to operate a test-position selector for temp measurements on gas turbine propulsion units. It comprises a sector plate (12) with a line of holes arranged on an arc (21). The temp sensor or group of sensors is attached to a radial arm (10) pivotted to the plate. The upper end of the arm is attached to a double-acting pneumatic cylinder (16) whose piston rod is attached to the upper end of a second arm (13) pivotted at the same point as the first. A slotted extension engages with a dowel (14) on the main arm. Both arms have double-acting cylinders with indexing bolts (22, 23) which engage with the holes in the plate. Limit switches on the plate (50, 51) and on the arms are connected to a logic unit which controls the stepping sequence.

AIR TEMPERATURE SENSOR

Cooldown control system for a combined cycle electrical power generation plant

ABSTRACT OF THE DISCLOSURE In a combined cycle electrical power generator plant, the shut-down process includes a cooldown control period which is minimized before shutting down the gas turbine by detecting first whether a non-steaming condition has been reached and whether the gas turbine has been reduced to minimum load.

RADIATION PYROMETRY DEVICE

L'INVENTION CONCERNE UN DISPOSITIF DE PYROMETRIE POUR TURBINE A GAZ OU SIMILAIRE, COMPRENANT UN PYROMETRE A RADIATIONS 10 A HAUTE RESOLUTION ET UN CIRCUIT DE DETECTION 20 AGENCE POUR ELIMINER LE BRUIT CAUSE PAR LA DETECTION DE PARTICULES INCANDESCENTES PAR LE PYROMETRE. LE SIGNAL EMIS PAR LE PYROMETRE EST INVERSE PAR UN INVERSEUR 21, PUIS TRANSMIS A TRAVERS UNE DIODE 23 A UN CONDENSATEUR 24 QUI EST RELIE A LA TERRE ET QUI SE DECHARGE LENTEMENT A TRAVERS UNE RESISTANCE 25. LA CHARGE DE CE CONDENSATEUR CORRESPOND APPROXIMATIVEMENT A LA TEMPERATURE MOYENNE DES AUBES. LA DIODE 23 EST COURT-CIRCUITEE PERIODIQUEMENT POUR DECHARGER LE CONDENSATEUR ET PRODUIRE UNE INDICATION DE TEMPERATURE INSTANTANEE, QUI EST STOCKEE DE MANIERE A PERMETTRE L'AFFICHAGE D'UNE TEMPERATURE DE CRETE. THE INVENTION RELATES TO A PYROMETRY DEVICE FOR A GAS TURBINE OR SIMILAR, INCLUDING A HIGH-RESOLUTION RADIATION PYROMETER 10 AND A DETECTION CIRCUIT 20 AGENCY TO ELIMINATE THE NOISE CAUSED BY THE DETECTION OF INCANDESCENT PARTICLES BY THE PYROMETER. THE SIGNAL EMITTED BY THE PYROMETER IS INVERTED BY AN INVERTER 21, THEN TRANSMITTED THROUGH A DIODE 23 TO A CAPACITOR 24 WHICH IS EARTHED AND WHICH DISCHARGES SLOWLY THROUGH A RESISTOR 25. THE CHARGE OF THIS CAPACITOR CORRESPONDS APPROXIMATELY TO THE EARTH. AVERAGE DAWN TEMPERATURE. DIODE 23 IS PERIODICALLY SHORT CIRCUITED TO DISCHARGE THE CAPACITOR AND PRODUCE AN INSTANT TEMPERATURE INDICATION, WHICH IS STORED SO AS TO ALLOW THE DISPLAY OF A PEAK TEMPERATURE.

AIR FLOW TEMPERATURE SENSOR IN A TURBOMACHINE

L'INVENTION CONSISTE A PLACER UN DETECTEUR DE TEMPERATURE 20 A L'ENTREE DU COMPRESSEUR AXIAL 29 D'UN MOTEUR A TURBINE A GAZ EN UN EMPLACEMENT SITUE A UNE DISTANCE RADIALE DU DIAMETRE EXTERIEUR 21 DU COURANT D'AIR ANNULAIRE QUI ENTRE DANS LE COMPRESSEUR SUPERIEUR A 50 DE LA DISTANCE RADIALE ENTRE LES DIAMETRES EXTERIEUR ET INTERIEUR DE CE COURANT D'AIR. ON OBTIENT AINSI UNE MESURE PLUS JUSTE DE LA TEMPERATURE A L'ENTREE DU COMPRESSEUR PENDANT LES PERIODES D'INGESTION D'EAU PAR LE MOTEUR, CE QUI PERMET DE COMMANDER LES AUBES DU STATOR VARIABLES 22, 23 EN RAPPORT AVEC CETTE CONDITION ET D'ACCROITRE AINSI LA MARGE DE DECROCHAGE DU COMPRESSEUR DANS UNE TELLE SITUATION. THE INVENTION CONSISTS OF PLACING A TEMPERATURE SENSOR 20 AT THE INPUT OF THE AXIAL COMPRESSOR 29 OF A GAS TURBINE ENGINE AT A LOCATION WITHIN A RADIAL DISTANCE FROM THE OUTSIDE DIAMETER 21 OF THE ANNULAR AIR CURRENT THAT ENTERS THE COMPRESSOR GREATER THAN 50 OF THE RADIAL DISTANCE BETWEEN THE OUTER AND INNER DIAMETERS OF THIS AIR CURRENT. THERE IS A MORE FAIR TEMPERATURE MEASUREMENT AT THE COMPRESSOR ENTRY DURING THE PERIODS OF WATER INGESTION BY THE ENGINE, WHICH ALLOWS TO CONTROL THE VANES OF THE VARIABLE STATOR 22, 23 RELATED TO THIS CONDITION AND OF INCREASE THE COMPRESSOR HANGING MARGIN IN SUCH A SITUATION.

METHOD FOR DETECTING FLUID LEAKAGE IN TURBOMACHINE AND FLUID DISPENSING SYSTEM

PROCESS FOR CONTROLLING, ADJUSTING OR CONTROLLING THERMAL TURBO-MACHINES FOLLOWING THE CRITERIA FOR THE SOLICITATION OF MATERIALS

L'INVENTION CONCERNE UNE INSTALLATION POUR COMMANDER, REGLER OU CONTROLER DES TURBOMACHINES THERMIQUES SUIVANT LE CRITERE DE LA SOLLICITATION DES MATERIAUX DES COMPOSANTS. LE PROBLEME A RESOUDRE CONSISTE A OPERER DE FACON PRECISE DANS LE CAS DE COMPOSANTS DE FORME COMPLIQUEE NE PERMETTANT PAS LES MESURES DIRECTES. L'INSTALLATION EST CARACTERISEE EN CE QU'ELLE COMPORTE UN DISPOSITIF DETERMINANT PAR INTERVALLES DE TEMPS LA REPARTITION INSTANTANEE DES TEMPERATURES DU COMPOSANT A PARTIR DE LA REPARTITION INITIALE ET A PARTIR D'UN TAUX ACTUEL DE VARIATION 9 DETERMINE PARCOMPARAISON AVEC DES VALEURS D'ECHANTILLON STOCKEES DANS UNE MEMOIRE 2 DU DISPOSITIF EN OPERANT AVEC UN SELECTEUR 3 ET PAR INTERPOLATION. L'INVENTION EST APPLICABLE NOTAMMENT AUX GROUPES MOTOPROPULSEURS D'AVIONS. THE INVENTION RELATES TO AN INSTALLATION FOR CONTROLLING, ADJUSTING OR CHECKING THERMAL TURBOMACHINES FOLLOWING THE CRITERION OF THE STRENGTH OF THE MATERIALS OF THE COMPONENTS. THE PROBLEM TO BE SOLVED CONSISTS OF OPERATING IN A PRECISE WAY IN THE CASE OF COMPONENTS OF COMPLICATED FORM DO NOT ALLOW DIRECT MEASUREMENTS. THE INSTALLATION IS CHARACTERIZED IN THAT IT INCLUDES A DEVICE DETERMINING BY INTERVALS OF TIME THE INSTANT DISTRIBUTION OF THE TEMPERATURES OF THE COMPONENT FROM THE INITIAL DISTRIBUTION AND FROM A CURRENT RATE OF VARIATION 9 DETERMINED BY PARCOMPARATION OF SAMPLES WITH VARIATIONS STORED IN A MEMORY 2 OF THE DEVICE OPERATING WITH A SELECTOR 3 AND BY INTERPOLATION. THE INVENTION IS APPLICABLE IN PARTICULAR TO AIRPLANE POWER UNITS.

ROTOR FOR AN AIRCRAFT TURBOMACHINE COMPRISING A PASSIVE FIRE DETECTION DEVICE

Le rotor (3) pour une turbomachine d’aéronef ayant un axe de rotation (X-X) et comportant un corps (8), comporte en outre un dispositif de détection passive (13) d’incendie, lequel comporte au moins un élément de réaction thermique (14) porté par ledit corps (8), ledit élément de réaction thermique (14) étant configuré pour se consommer lorsqu’il est soumis à une température prédéterminée correspondant à un incendie de sorte à générer un balourd dudit corps (8), et au moins un élément de détection configuré pour détecter l’apparition dudit balourd . Figure pour l'abrégé : Figure 3 The rotor (3) for an aircraft turbine engine having an axis of rotation (X-X) and comprising a body (8), further comprises a passive fire detection device (13), which comprises at least one reaction element (14) carried by said body (8), said thermal reaction element (14) being configured to be consumed when it is subjected to a predetermined temperature corresponding to a fire so as to generate an imbalance of said body (8), and at least one detection element configured to detect the appearance of said imbalance. Figure for abstract: Figure 3

Control systems for apparatus

IN THE CANADIAN PATENT OFFICE Inventors: PETER JAMES WILLIAMS Invention: IMPROVEMENTS IN CONTROL SYSTEMS FOR APPARATUS ABSTRACT OF THE DISCLOSURE Infra-red radiation detectors are used in gas turbine engines to detect radiation produced by the turbine blades giving an indication of blade temperature. Above a given limit the signal produced by the detector is passed to the fuel control system to shut down the fuel supply of the engine. An additional detector is provided which receives the same image as the first detector but is biased to detect radiation in the visible light part of the spectrum. When incandescent particles pass through the field of vision of the detectors both show an increase in signal due to both types of radiation being increased during this transient event. The signal from the second detector is used to reduce the signal fuel the first detector by an amount sufficient to prevent the fuel supply being temporarily shut down.

INTERMEDIATE HOUSING OF A TURBOMACHINE WITH AN AERODYNAMIC PARAMETER MEASURING DEVICE, TURBINE MODULE COMPRISING SUCH AN INTERMEDIATE HOUSING AND A TURBOMACHINE EQUIPPED WITH SUCH A MODULE

L'invention concerne un carter intermédiaire (17) de turbomachine s'étendant autour d'un axe longitudinal X, le carter intermédiaire (17) comprenant une virole interne (24) et une virole externe (25) coaxiales et entre lesquelles un flux aérodynamique de la turbomachine est destiné à circuler, le carter intermédiaire comprenant au moins un bras (26) s'étendant entre la virole interne (24) et la virole annulaire externe (25) suivant un axe radial R perpendiculaire à l'axe longitudinal X, le bras (26) comprenant un bord d'attaque (27) en amont et un bord de fuite (28) en aval suivant l'axe longitudinal X. Selon l'invention, le carter intermédiaire (17) comprend un dispositif de mesure (35) de paramètres aérodynamiques du flux aérodynamique dont au moins une portion forme une partie du bord d'attaque (27) du bras (26). The invention relates to an intermediate casing (17) for a turbomachine extending around a longitudinal axis X, the intermediate casing (17) comprising an inner shell (24) and an outer shell (25) coaxial and between which an aerodynamic flow of the turbomachine is intended to circulate, the intermediate casing comprising at least one arm (26) extending between the inner shell (24) and the outer annular shell (25) along a radial axis R perpendicular to the longitudinal axis X, the arm (26) comprising a leading edge (27) upstream and a trailing edge (28) downstream along the longitudinal axis X. According to the invention, the intermediate casing (17) comprises a device (35) for measuring aerodynamic parameters of the aerodynamic flow, at least a portion of which forms part of the leading edge (27) of the arm (26).

Method and device for measuring and adjusting the deformation of the cylinder and rotor of turbomachines caused as a result of the uneven distribution of heat

Detection of gas turbine engine hot section condition

A system and a method for detecting gas turbine engine hot section condition using temperature measurements during engine operation. The system comprises a sensing unit for sensing a temperature distribution across a hot combustion gas stream generated by a gas turbine engine combustor. A signal processor receives temperature signals from the sensing unit and generates a combustor malfunction signal when the difference between a maximal temperature and a minimal temperature of the sensed temperature distribution is greater than a predetermined acceptable delta value.

Turbomachine oil system

Système huile pour turbomachine Système huile pour turbomachine, permettant de continuer d’alimenter en huile les équipements de la turbomachine en cas de survenance d’un feu au sein de la turbomachine, comprenant un circuit d’huile (2), au moins un équipement consommateur d’huile (3a, 3b, 3c), alimenté par le circuit d’huile (2), une unité de pompage, comprenant au moins une pompe à entraînement électrique (22, 4) pilotable en vitesse, alimentant le circuit d’huile (2), et une unité de commande électronique (6), configurée pour piloter la pompe à entraînement électrique (22, 4), dans lequel l’unité de commande électronique (6) comprend deux logiques distinctes de pilotage de la pompe à entraînement électrique (22, 4), et dans lequel l’unité de commande électronique (6) est configurée pour piloter la pompe à entraînement électrique (22, 4) selon la première logique par défaut et pour basculer vers la deuxième logique en cas de réception d’un signal représentatif de la présence d’un feu ou d’une surchauffe, et dans lequel l’unité de commande électronique (6) est configurée pour arrêter la pompe à entraînement électrique (22, 4) lorsqu’elle reçoit un signal de fuite en provenance d’un détecteur de fuite (62). Figure pour l’abrégé : Fig. 1.

AIR TEMPERATURE SENSOR

Un capteur de température d'air totale (90) peut inclure une partie de profil d'aile (114). La partie de profil d'aile (114) peut inclure un orifice d'entrée (120) et un orifice de sortie (122) à travers lesquels un trajet d'écoulement d'air dévié (DAP) peut s'écouler. Le capteur de température d'air totale (90) peut inclure un capteur de température (144) situé dans un carter (124) définissant le capteur de température d'air totale (90) et une gaine (140, 150) entourant le capteur de température (144). Le capteur de température (144) peut être configuré pour prendre une température totale du trajet d'écoulement d'air dévié (DAP). A total air temperature sensor (90) may include a wing profile portion (114). The wing profile portion (114) may include an inlet port (120) and an outlet port (122) through which a deflected air flow path (DAP) may flow. The total air temperature sensor (90) may include a temperature sensor (144) located in a housing (124) defining the total air temperature sensor (90) and a sheath (140, 150) surrounding the sensor temperature (144). The temperature sensor (144) can be configured to take a total temperature of the deflected airflow path (DAP).

Method and system for monitoring a condition of a gas turbine gearbox

Procédé et système de surveillance d’un état d’un réducteur d’une turbine à gaz Ce procédé de surveillance d’un état d’un réducteur d’une turbine à gaz, comprend les étapes:- d’obtention (F10) de mesures de paramètres réalisées lors d’une phase de fonctionnement de la turbine à gaz, ces paramètres comprenant des températures d’une huile de lubrification du réducteur en entrée et en sortie du réducteur, un paramètre représentatif d’un régime de la turbine à gaz, ainsi qu’au moins un paramètre de contexte ; - de sélection (F20) de mesures stables au regard d’un critère de stabilité prédéterminé ;- de normalisation (F30) des températures de l’huile de lubrification en entrée et en sortie du réducteur en utilisant les mesures des paramètres de contexte ;- d’évaluation (F40) d’un rendement thermique du réducteur en utilisant un modèle physique définissant le rendement thermique à partir d’une différence entre la température de l’huile de lubrification en sortie et en entrée du réducteur ;- et de détermination (F60) d’un état du réducteur en fonction une étape de comparaison (F50) du rendement thermique évalué par rapport à une signature de référence Figure pour l’abrégé : Fig. 6B.

Dispenser for a high-pressure turbine of a jet engine

A method for detecting overpressure inside a compartment associated with a gas turbine nacelle

A method for detecting overpressure inside a compartment associated with a gas turbine nacelle, the method comprising: a) measuring one or more predetermined operating conditions nominally affecting the temperature inside the compartment; b) determining a reference temperature for the compartment, corresponding to a nominal reference zone pressure, on the basis of the measured operating condition or conditions; c) measuring the actual temperature inside the compartment, corresponding to the actual compartment pressure; and d) using the measured actual temperature in the compartment and the determined reference temperature for the compartment to assess the gas pressure inside the compartment. In one embodiment, there is disclosed a system for assessing the gas pressure inside the compartment caused by an associated pressure system failure, comprising using a quantified mass leakage flow to assess gas pressure inside the compartment. The quantified mass leakage flow may also be used to detect excessive mass leakage flow by comparing the quantified mass leakage flow with a predetermined mass flow leakage.

Patent FR2348533B1

Method and system for real-time performance degradation advisory for centrifugal compressors

A system and computer-implemented method for generating real-time performance advisories for a centrifugal compressor of a fleet of centrifugal compressors are provided. The method includes receiving an actual thermodynamic signature of the compressor, that is unique to the compressor, receiving compressor process parameter values during operation of the compressor, determining, in real¬ time, an actual performance of the compressor using the compressor process parameter values, determining, in real-time, a predicted performance of the compressor using the received actual thermodynamic signature of the compressor, determining a performance deviation of the compressor using the actual performance and the predicted performance, comparing the performance deviation to a predetermined dynamic threshold range of performance deviation specific to operating speed, and generating a notification to a user using the comparison.

Method and arrangement for monitoring a hot gas region of a gas turbine

Die Erfindung betrifft ein Verfahren und eine Anordnung zur Überwachung eines Heißgasbereichs einer Gasturbine bei dem a) der Heißgasbereich mit einer an einem dem Heißgasbereich fernen Ort an der Gasturbine betriebenen bildgebenden Radaranordnung mittels mindestens einem Hohlleiter verbunden wird, b) der Hohlleiter an dem Ende an dem die Radaranordnung betrieben wird und der derart verschlossen ist, dass die Radaranordnung außerhalb des verschlossen Hohlraums betrieben wird und ist an dem Ende dem Heißgasbereich zugewandten Ende des Hohlleiters derart ausgestaltet ist, dass der Hohlleiter in den Heißgasbereich offen mündet oder derart für Radarwellen durchlässig vor Hitze geschirmt ist, dass die Radarwellen in den Heißbereich gelangen,, c) die Radaranordnung derart angesteuert und funktional über den Hohlleiter mit dem Heißgasraum verbunden ist, dass in zeitlichen Abständen zumindest Teile des Heißgasraums durch die Radaranordnung in zeitlichen Abständen wiederholt bildgebend erfasst werden, d) die erfassten Bilddaten einer Auswertungseinrichtung zugeführt werden, e) abhängig vom Ergebnis der Auswertungseinrichtung eine Wartung, insbesondere durch Auslösen eines Alarms, initiiert wird. The invention relates to a method and an arrangement for monitoring a hot gas area of a gas turbine in which a) the hot gas area is connected to an imaging radar arrangement operated at a location remote from the hot gas area on the gas turbine by means of at least one waveguide, b) the waveguide at the end at the radar arrangement is operated and which is closed in such a way that the radar arrangement is operated outside the closed cavity and is configured at the end of the waveguide facing the hot gas area such that the waveguide opens openly into the hot gas area or is shielded from heat so radar waves permeable is that the radar waves get into the hot region, c) the radar arrangement is driven in such a way and is functionally connected via the waveguide to the hot gas space, ...

Gas turbine, driving method thereof and gas turbine combined electric power generation plant

A steam temperature Ts and a casing air temperature Ta are measured by thermometers. The measurement results are taken into measuring devices and converted into electric signals. The electric signal is A/D converted by the measuring device and then, is sent to a control apparatus where a difference between both the temperature is calculated by a subtracter of a processor provided in the control apparatus. When an absolute value ΔT=|Ta−Ts of this difference is contained within 10° C. continuously ten times, a control signal is sent from a computing unit to a controller which is the control section, a pressure adjusting valve and the like are controlled and a cooling medium is switched to steam.

Patent FR2390781B1

Detection of gas turbine airfoil failure

A system and method for early detection of a failure of a gas turbine engine airfoil (10), such as but not restricted to a burn through of the airfoil outer skin (12). A sensor (52) provides a signal (54) responsive to a condition of fluid flowing through an outer cooling chamber (24) of the airfoil. A detected change in the condition of the fluid is correlated to a failure of the airfoil, which for example can be detected by measuring the static fluid pressure. An increase in the static pressure of fluid in the outer cooling chamber may indicate a breach in the region of the leading edge of the airfoil. A decrease in the static pressure of fluid in the outer cooling chamber may indicate a breach along other portions of the profile of the airfoil outer skin. Both pressure and temperature parameters of the fluid may be measured and coincident changes thereof correlated to a condition of failure of the airfoil

Method and apparatus for detecting rub in a turbomachine

An embodiment of the disclosed method and apparatus relates to a system for detecting a rub in a turbomachine. The system comprises: a turbomachine; sensors monitoring turbomachine conditions; and an on site monitor in communication with the sensors, and loaded with instructions to implement a method for detecting a rub in the turbomachine. An embodiment of the disclosed method relates to a method for detecting a rub in a turbomachine, the method comprising: monitoring turbomachine conditions; and determining whether a rub is occurring. Another embodiment of the disclosed apparatus relates to a storage medium encoded with a machine-readable computer program code for detecting a rub in a turbomachine, the storage medium including instructions for causing a computer to implement a method. The method comprises: obtaining data indicating turbomachine conditions; and determining whether a rub is occurring.

Composite cycle generating plant

(57)【要約】本公報は電子出願前の出願データであるた め要約のデータは記録されません。

Method and device for reducing speed in the event of breakage of the turbine shaft of a gas-turbine engine

La présente invention porte sur une méthode pour réduire la vitesse de rotation, dans un moteur à turbine à gaz, d'une turbine comprenant un rotor (6) entraînant un arbre (8) et mobile en rotation à l'intérieur d'un stator (7), en cas de rupture dudit arbre. Cette méthode est caractérisée par le fait qu'elle consiste à mesurer (11) la température en un point sur une surface du stator (10A) située en aval du rotor (6), transmettre le signal de mesure à un moyen de commande (100) du freinage du rotor, ledit moyen de commande étant agencé pour commander le freinage du rotor lorsque la température atteint un seuil. L'invention porte également sur le dispositif.

Automatic inspector for gas turbine

(57)【要約】本公報は電子出願前の出願データであるた め要約のデータは記録されません。

Rotary measuring device for outlet temperature field of combustion chamber of aero-engine

本发明公开了航空发动机燃烧室出口温度场旋转测量装置，包括通过传动机构连接的电机和旋转盘，角度传感器和测温感头均安装在旋转盘上且均与测控计算机连接，测控计算机依次连接电机控制器和电机；电机通过传动机构带动旋转盘上的测温感头旋转到设定角度位置，同时角度传感器将实际的角度位置信号反馈给测控计算机；通过安装在测控计算机上的软件进行比较，如需调整，则发出指令由电机控制器控制电机动作，以达到正确的角度位置，并进行数据的采集。本测温装置弥补传统温度场固定耙测量方法的不足，实现HB7485燃烧性能试验中对出口温度场采测密度的要求，起到缩短试验周期、节省试验经费的效果。

Variable displacement-type supercharger

This variable displacement-type supercharger comprises: a nozzle flow path which allows gas heading toward a turbine wheel from a scroll flow path to pass; a shroud-side ring and a hub-side ring which face each other in the rotational axis line direction of the turbine wheel and form the nozzle flow path therebetween; a bearing hole provided to the shroud-side ring; a bearing hole provided to the hub-side ring; and a nozzle vane disposed in the nozzle flow path and supported on both sides by the bearing holes, wherein, at room temperature, the center axial line of the bearing hole is positioned inward in the radial direction as compared to the center axial line of the bearing hole, and when a predetermined temperature difference has occurred between the shroud-side ring and the hub-side ring during operation, the center axial line is positioned outward in the radial direction as compared to the center axial line.

METHOD FOR REDUCING SPEED IN CASE OF TURBINE SHAFT BREAKAGE OF GAS TURBINE ENGINE

Detection of gas turbine engine hot section condition

Method and system for reducing heat loss from a gas turbine during shutdown

Gas turbine engine shutdown temperature control system with injection nozzle for gas turbine engine

FIELD: motors and pumps.SUBSTANCE: invention relates to turbine engines, and more particularly to systems providing start-up from an unheated state of gas turbine engines without the risk of collision of a turbine blade with radially outer sealing surfaces. Gas turbine engine shutdown temperature control system (10) is configured to limit the creation of temperature gradients in outer casing (12) surrounding turbine blade assembly (14) while gas turbine engine (16) is turned off. By reducing the temperature gradients caused by the buoyancy of the hot air in cavities (18) of the middle region in outer casing (12), the arcuate and concave bending of outer casing (12) is prevented. Thus, the possibility of abrasion of the tip of the blade and the possible damage to the blade during the restart of gas turbine engine (16) from the non-heated state are reduced. Gas turbine engine shutdown temperature control system (10) can operate during the shutdown process, when rotor (26) is still driven by the combustion gases, or during the operation of the pivoting system after the gas turbine engine has been turned off, or during both, to ensure that outer casing (12) is evenly cooled downward.EFFECT: gas turbine engine system shutdown temperature control system with an injection nozzle for a gas turbine engine is proposed.6 cl, 8 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 666 711 C2 (51) МПК F01D 25/26 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (52) СПК F01D 25/26 (2018.02) (21)(22) Заявка: 2015142073, 11.03.2014 (24) Дата начала отсчета срока действия патента: Дата регистрации: 11.09.2018 (73) Патентообладатель(и): СИМЕНС АКЦИЕНГЕЗЕЛЛЬШАФТ (DE) (56) Список документов, цитированных в отчете о поиске: US 2008310949 A1, 18.12.2008. US 03.04.2013 US 13/855,756 (43) Дата публикации заявки: 11.05.2017 Бюл. № 14 2007065274 A1, 22.03.2007. RU 2161715 C2, 10.01.2001. (45) Опубликовано: 11.09.2018 Бюл. № 26 (86) Заявка PCT: C 2 C 2 ...

Method and device for activating an element made of a shape memory alloy

A simple and cost-effective method is provided, according to which a positive temperature component (PTC) element directly controls the element made of a shape memory alloy. A simple and cost effective device for performing the method has a PTC element series-connected upstream from the element made of a shape memory alloy, in the electric circuit for the element made of a shape memory alloy.