УСТРОЙСТВО ДЛЯ ИЗМЕРЕНИЯ ТЕМПЕРАТУРЫ В ПРОТОЧНОМ КАНАЛЕ ПЕРВИЧНОГО ПОТОКА ДВУХКОНТУРНОГО ТУРБОРЕАКТИВНОГО ДВИГАТЕЛЯ

Изобретение относится к измерительной технике и может быть использовано для измерения температуры в первичном потоке двухвального двухконтурного турбореактивного двигателя. Изобретение предоставляет устройство для измерения температуры на входе компрессора в проточном канале первичного потока двухконтурного турбореактивного двигателя. Устройство содержит воздухонепроницаемую пустотелую конструкцию, образующую соединительный кронштейн (36b) разделительного корпуса (30) турбореактивного двигателя и выполненную с возможностью радиально проходить через проточный канал (16) для первичного потока, и проточный канал (18) для вторичного потока турбореактивного двигателя. Соединительный кронштейн (36b) имеет по меньшей мере одно воздухозаборное отверстие (44), открывающееся в проточный канал первичного потока на входе компрессора, и по меньшей мере одно воздуховыпускное отверстие (46), выполненное так, чтобы вести в зону турбореактивного двигателя, где окружающее давление меньше давления в проточном ...

ДАТЧИК ТУРБУЛЕНТНОСТИ КОМПРЕССОРА ТУРБОМАШИНЫ

FIELD: measuring equipment. SUBSTANCE: according to the present invention, a system for measuring turbulence of flow (18) of a turbomachine, in particular a turbomachine compressor, is proposed. System (30) contains: first receiving element (47) with first pressure sensor (52) and first hole (48); second receiving element (54) with second pressure sensor (58) and second hole (56) made at an angle relatively to first hole (48); and temperature sensor (53). System (30) is designed for calculating at least two components of the flow speed direction based on data from pressure sensors (52; 58) and temperature sensor (53). Holes are made in a blade shank, on the front edge at a level of the inner shell. EFFECT: obtaining the turbulence sensor of the turbomachine compressor. 19 cl, 5 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 757 091 C2 (51) МПК F01D 17/02 (2006.01) F01D 17/08 (2006.01) F04D 27/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (52) СПК F01D 17/02 (2021.08); F01D 17/085 (2021.08); F04D 27/001 (2021.08); F04D 29/542 (2021.08) (21)(22) Заявка: 2018116234, 30.04.2018 (24) Дата начала отсчета срока действия патента: (73) Патентообладатель(и): САФРАН АЭРО БУСТЕРС СА (BE) Дата регистрации: 11.10.2021 Приоритет(ы): (30) Конвенционный приоритет: 05.05.2017 BE 2017/5316 (43) Дата публикации заявки: 30.10.2019 Бюл. № 31 (45) Опубликовано: 11.10.2021 Бюл. № 29 2 7 5 7 0 9 1 R U (54) ДАТЧИК ТУРБУЛЕНТНОСТИ КОМПРЕССОРА ТУРБОМАШИНЫ (57) Реферат: Согласно настоящему изобретению относительно первого отверстия (48); и датчик предложена система измерения турбулентности (53) температуры. Система (30) предназначена потока (18) турбомашины, в частности для вычисления по меньшей мере двух компрессора турбомашины. Система (30) компонентов направления скорости потока на содержит: первый приемный элемент (47) с основании данных от датчиков (52; 58) давления первым датчиком (52) давления и первым и датчика (53) температуры. ...

ДАТЧИК ТУРБУЛЕНТНОСТИ КОМПРЕССОРА ТУРБОМАШИНЫ

ТЕРМОУПРАВЛЯЕМЫЙ УЗЕЛ ДЛЯ ГАЗОТУРБИННОЙ СИСТЕМЫ (ВАРИАНТЫ) И СПОСОБ ПОТОКА ОХЛАЖДАЮЩЕГО ВОЗДУХА

... 1. Термоуправляемый узел для газотурбинной системы, содержащий:элемент теплопередачи, имеющий первую часть и вторую часть, при этом первая часть расположена внутри первой полости, имеющей первую температуру, а вторая часть расположена во второй полости, имеющей вторую температуру, причем элемент теплопередачи проходит через полую стенку, и первая температура больше, чем вторая температура;термочувствительный элемент, расположенный внутри второй полости и функционально связанный с элементом теплопередачи, иустройство регулирования потока, расположенное внутри второй полости и выполненное с возможностью смещения в ответ на изменение температуры в первой полости.2. Термоуправляемый узел по п.1, в котором первая полость имеет первое давление, а вторая полость имеет второе давление, при этом второе давление больше, чем первое давление.3. Термоуправляемый узел по п.2, в котором устройство регулирования потока содержит тарелку клапана и шток клапана, проходящий от тарелки клапана к термочувствительному ...

Vorrichtung zur Einstellung verschiedener Vorschubgeschwindigkeiten des Werkzeugs bei Werkzeugmaschinen

NACHWEIS VON HEISSEN BEREICHEN IN GAS TURBINEN

Dampfturbine insbesondere für solarthermische Kraftwerke

Die Erfindung betrifft eine Dampfturbine, insbesondere für solarthermische Kraftwerke, umfassend eine Anzahl von Innenbauteilen, wobei die Anzahl von Innenbauteilen wenigstens, einen Rotor 1 mit einer Anzahl von am Rotor 1 angeordneten Laufschaufeln 2, sowie ein Leitschaufelträger 3 mit einer Anzahl von im Leitschaufelträger 3 angeordneten Leitschaufeln 4 umfasst. Die Innenbauteile der Dampfturbine sind mittels einer induktiven Beheizung 5 beheizbar. Des Weiteren umfasst die Erfindung ein Verfahren zum Betreiben einer solchen Dampfturbine.

Method for manufacturing temperature sensor for measuring gaseous and liquid medium, involves arranging temperature sensor in casing

The method involves arranging a temperature sensor in a casing (4). A microstructure (5) of a depth of 20 to 80 micrometer is applied on the casing with a laser shaping or with a microlithographic procedure. The microstructure is treated by an energy pulsing. A coating is made from nitride, carbide, boron oxide or a mixture of all these materials. An independent claim is included for a temperature sensor for measuring the gaseous and liquid medium.

Temperaturerfassung in einer Gasturbine

Ein Temperaturdetektor (10) enthält ein erstes Metall (4) und ein zweites Metall (6), das sich von dem ersten Metall unterscheidet. Das erste Metall enthält mehrere Drähte, und das zweite Metall enthält einen Draht. Die mehreren Drähte aus dem ersten Metall sind mit dem Draht aus dem zweiten Metall an parallelen Verbindungen (8) verbunden. Ein weiterer Temperaturdetektor enthält mehrere Widerstandstemperaturdetektoren. Die mehreren Widerstandstemperaturdetektoren sind an mehreren Verbindungen miteinander verbunden. Ein Verfahren zum Erfassen einer Temperaturveränderung einer Komponente (12) einer Turbine enthält ein Bereitstellen eines Temperaturdetektors, der ein erstes Metall und ein zweites Metall enthält, das sich von dem ersten Metall unterscheidet, wobei das erste und das zweite Metall an mehreren Verbindungen mit der Komponente in Kontakt stehend miteinander verbunden sind, und Erfassen irgendeiner Spannungsveränderung an irgendeiner Verbindung.

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 (10). The turbomachine (10) comprises a high temperature fluid source, at least one fluid distribution pipe (14, 15) adapted to distribute said fluid to different parts of the turbomachine (10) and/or the aircraft (20) which is intended to be equipped with said turbomachine (10), a turbomachine compartment in which the distribution pipe (14, 15) 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 (10) comprising such ...

Improved temperature measurement

APPARATUS FOR DETERMINING THERMAL STRESS IN THE SHAFT OF A STEAM OR GAS TURBINE

... 1362631 Determining thermal stress in a turbine shaft KRAFTWERK UNION AG 13 Oct 1972 [16 Oct 1971] 47476/72 Heading G1N The average temperature of the shaft of a gas or steam turbine is determined by calculation based on the measured temperature at the surface and is used as an indication of the stress in the shaft. As shown Fig. 1, a temperature sensor 5 is located on the inner wall of the turbine housing 1, 2 to develop a signal # o representing the surface temperature of the shaft 3. This signal is fed to a comparator 9 together with a signal # m developed in a computer 7 representing the average shaft temperature, based on the known thermal conductivity of the shaft material and dimensions of the shaft, and the difference # o -# m is a measure of the thermal stress in the shaft.

Modulating cooling airflows

Cooling airflow is modulated by means of interacting metering apertures formed in members 42, 46 that can move in relation to each other according to changes in operating temperature. The modulation method may be applied to a gas turbine engine airfoil, having a wall (42) provided with a cooling effusion hole 40 therein for film cooling the external surface 52 of the wall 42. A member 46 attached (at one edge or at a point between two metering apertures) to the internal surface 48 of the wall 42 is provided with an aperture 44 which at least partially overlaps the cooling effusion hole 40. The airfoil wall 42 and member 46 are formed from materials having different coefficients of thermal expansion whereby over a temperature range, the aperture 44 and cooling effusion hole 40 interact to a greater or lesser extent to modulate the flow of cooling air therethrough.

Gas turbine engine airflow temperature sensor

A temperature sensor 20, for measuring the temperature of air flowing in a substantially annular path in the compressor stage 29, is positioned in proximity to the inner diameter of the annular flow path forward of the compressor stage 29 where the measured temperature of the compressor inlet air, during periods of water ingestion, is not that of the lower wet bulb temperature but more akin to the actual air temperature. The sensor 20 comprises a coil (38, Figure 2) filled with helium gas under pressure and is surrounded by a rainshield 35. The signal from the sensor is used as a variable for controlling the compressor inlet guide vanes 22, 23. ...

Shaft break detection

RADIATION PROBE

Improvements in temperature responsive regulating arrangements

... 1,121,804. Valves. DAIMLER-BENZ A.G. 18 Feb., 1966 [24 Feb., 1965], No. 7283/66. Heading F2V. [Also in Divisions F1, G1 and G3] A thermally actuated drain valve connected to a pressure chamber 10, Fig. 1 (not shown), in which is mounted a pressure-responsive diaphragm regulator for an aircraft engine, serves to regulate the fuel feed to the engine and comprises a heatsensitive tubular element 13, Fig. 2, a displaceable rod insert 14, and a toggle lever system 20, 22 which magnifies the relative movement between the thermal elements and actuates a pneumatic regulator housed in lateral socket 26 of tubular pillar 5. The tubular element 13 which may be made of steel is closed at its upper end 16 and is provided at the other with a guide bush 15. The displaceable insert 14 which may be made of quartz is fitted with a steel intermediate 17 and a piston 18 slidable in a bush 15. Lever 20 is pivotally connected at 19 and 21 to the piston 18 and a second lever 22. The lower end of 22 is supported ...

TEMPERATURE MEASURING ASSEMBLY FOR THE NOZZLE GUIDE RING OF A GAS TURBINE

Exhaust gas temperature sensor

Solar energy and external source steam complementary power generation apparatus

SOLAR ENERGY AND EXTERNAL SOURCE STEAM COMPLEMENTARY POWER GENERATION APPARATUS

Solar energy and external source steam complementary power generation apparatus

Solar energy and external source steam complementary power generation apparatus

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

Organic Rankine Cycle system

The application discloses an organic Rankine Cycle system with a generating unit, a condenser for condensing an organic work fluid, a feeder pump for circulating the organic work fluid and an evaporator (14) for evaporating the organic work fluid. The generating unit comprises a high-pressure screw expander and a low-pressure screw expander, which are connected in series, wherein the high-pressure screw expander and the low-pressure screw expander are mechanically connect- able to a generator, which is provided between the high- pressure screw expander and the low-pressure screw expander. The ORC system comprises a by-pass line for bypassing the high-pressure screw expander. The bypass line comprises a control valve for opening and closing the by-pass line.

Solar energy and external source steam complementary power generation apparatus

A solar energy and external source steam complementary power generation apparatus comprising a solar steam generation device, an external source steam regulator (15), a turboset (2) and a generator (1). A steam output end of the solar steam generation device is connected to a high-pressure steam inlet (3) of the turboset (2) through a first regulating valve (15); a steam output end of the external source steam regulator (15) is connected to the high-pressure steam inlet (3) of the turboset (2) through a second regulating valve (20) and a second switching valve (19). A low-pressure steam outlet (4) of the turboset (2) is connected to a circulating water input end of the solar steam generation device through a condenser (5), a deaerator (6), a water feed pump (7) and a first switching valve (16) in turn. An output end of the water feed pump (7) is connected to an external source steam water return bypass (11) through a fourth switching valve (23).

METHOD AND APPARATUS FOR MONITORING THE PERFORMANCE OF A GAS TURBINE SYSTEM

A method for monitoring performance of a gas turbine system (20) comprises providing a plurality of combustor cans (30); placing a plurality of temperature sensors (40) circumferentially around an exhaust plane of the plurality of combustor cans; operating the plurality of combustor cans while varying a plurality of gas turbine operating parameters, where exhaust gas issues from each combustor can of the plurality of combustor cans during operation; measuring temperature of the exhaust gas in the exhaust plane using the plurality of temperature sensors to obtain a plurality of individual temperature measurements; determining a correlation of the individual temperature measurements of exhaust gas temperature with corresponding individual combustor cans of the plurality of combustor cans issuing the exhaust gas; and developing a swirl model (70), where the model uses the correlation to predict swirl values in the exhaust plane as a function of the operating parameters.

ADAPTIVE TEMPERATURE CONTROL SYSTEM FOR THE SUPPLY OF STEAM TO A STEAM TURBINE

... 24 The invention relates to a combined heat recovery steam generator and steam turbine. An adaptive temperature controller establishes a target temperature for controlling the boiler temperature so that the steam admitted on the boiler follows a constant enthalpy when trying to match temperature of steam and rotor temperature.

TURBINE IMPULSE CHAMBER TEMPERATURE DETERMINATION METHOD AND APPARATUS

TURBINE IMPULSE TEMPERATURE DETERMINATION METHOD AND APPARATUS A method and apparatus for determining the steam temperature in the impulse chamber at the first stage exit of a multistage high pressure steam turbine utilizes measurement of steam pressure in the impulse chamber and steam pressure and temperature at the exhaust as inputs to a digital computer. The functional relationships among steam pressure, temperature, specific volume, enthalpy and entropy are stored in the computer memory, and used with these measured quantities to iteratively calculate the steam temperature at the impulse chamber.

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.

MODULATED HYBRID VARIABLE AREA TURBINE NOZZLE FOR GAS TURBINE ENGINE

The present disclosure is directed to a variable area turbine nozzle. The variable area turbine nozzle includes a first vane segment, a second vane segment arranged with the first vane segment, and a trailing edge segment arranged with the first and second vane segments. The vane also includes a first actuating system for pivoting the second vane segment with respect to the first vane segment and a second actuating system for pivoting the trailing edge with respect to the first and second vane segments.

ACTIVE TEMPERATURE MONITORING IN GAS TURBINE COMBUSTORS

Acoustic pyrometry-based active temperature monitoring of gas turbine combustors, including industrial gas turbine (IGT) combustors is incorporated into the combustion monitoring and control system by addition of an acoustic transmitter or acoustic transceiver that transmits a sound wave in a line-of-sight with a plurality of thermoacoustic sensors, such as dynamic pressure sensors. Sound transmission time-of-flight is measured by the controller and correlated with path temperature along the line-of-sight. Path(s) of acoustic transmission serve as absolute temperature measurement that optionally is used for calibrating dominant mode passive bulk temperature measurement. In an integrated thermoacoustic pressure-based sensor and monitoring/control system embodiment, the controller correlates performance of an combustion thermoacoustic properties in order to identify combustion anomalies by wavelet or Fourier analysis techniques, determine bulk temperature characteristics within the combustor ...

ELECTRONIC CIRCUITRY FOR HIGH-TEMPERATURE ENVIRONMENTS

A circuitry adapted to operate in a high-temperature environment of a turbine engine is provided. A relatively high-gain differential amplifier (102) may have an input terminal coupled to receive a voltage indicative of a sensed parameter of a component (20) of the turbine engine. A hybrid load circuitry may be coupled to the differential amplifier. A voltage regulator circuitry (244) may be coupled to power the differential amplifier. The differential amplifier, the hybrid load circuitry and the voltage regulator circuitry may each be disposed in the high-temperature environment of the turbine engine.

DEVICE FOR MEASURING THE TEMPERATURE IN A FLOW CHANNEL OF THE PRIMARY FLOW OF A BYPASS TURBOJET ENGINE.

L'invention concerne un dispositif de mesure de la température dans une veine d'écoulement de flux primaire d'un turboréacteur à double flux en entrée de compresseur, comprenant une structure creuse et hermétique formant bras de liaison (36b) d'un carter intermédiaire (30) et destinée à traverser radialement une veine d'écoulement du flux primaire (16) et une veine d'écoulement du flux secondaire (18) du turboréacteur, le bras de liaison (36b) ayant au moins un orifice d'entrée d'air (44) destiné à s'ouvrir dans la veine d'écoulement du flux primaire en entrée d'un compresseur et au moins un orifice de sortie d'air (46) destiné à déboucher dans une zone du turboréacteur où la pression environnante est inférieure à la pression dans la veine d'écoulement du flux primaire en entrée du compresseur, le dispositif comprenant en outre une sonde de température (48) dont l'élément sensible est disposé à l'intérieur du bras de liaison.

Appareil de commande automatique de la température des gaz d'échappement d'une installation motrice à turbine à gaz

Dispositif de sécurité pour une turbine à gaz.

Temperaturfühleinrichtung an axial durchströmter Turbomaschine

Sicherheitsvorrichtung für Turbinen.

Verfahren zur Überwachung der zulässigen Temperaturänderungen, insbesondere in Wärmeströmungsmaschinen

Verfahren zum Bestimmen der Eintrittstemperatur einer Gasturbine

Gasturbinenanlage

Selbsttätige Sicherung gegen Katzbuckeln der Gehäuse thermischer Strömungsmaschinen

Vorrichtung zur wählbaren Einstellung von verschiedenen Vorschubgeschwindigkeiten für den hydraulischen Schubkolbenantrieb von Werkzeugmaschinen

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.

Temperature detector i.e. thermo element grid, for e.g. burner pipe, of gas turbine, for detecting temperature deviation, has metal with set of wires that are connected with another set of wires of another metal at parallel connections

The detector has two different metals (4, 6), where each metal exhibits a set of wires. The set of wires of the metal (4) is connected with the set of wires of the metal (6) at parallel connections (8). Resistance temperature detectors are connected with each other at a set of connection points, where the detectors are made of different materials. The detector is connected with an individual monitoring device, which detects a rigid signal, so as to detect increase in temperature at the detector. Independent claims are also included for the following: (1) a method for detecting a temperature change of a component of a turbine (2) a method for detecting a temperature of a component of a turbine.

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.

System for adjustment the amount of air in a gas turbine with an temperature-activated valve.

Es ist ein System zur Einstellung der Menge an Luft, die durch eine Druckgrenze in einer Gasturbine hindurch geliefert wird, offenbart, das einen an der Druckgrenze angeordneten Durchgang (30) enthält. Ferner ist in dem Durchgang (30) ein temperaturaktiviertes Ventil (32) montiert, das konfiguriert ist, um bei einem vorbestimmten Temperaturschwellenwert auszulösen. Insbesondere löst das temperaturaktivierte Ventil (32) aus, um von einer Schliessstellung zu einer Offenstellung umzuschalten, wenn die lokale Temperatur an dem temperaturaktivierten Ventil (32) den vorbestimmten Temperaturschwellenwert erreicht oder überschreitet, um Luft zu ermöglichen, durch den Durchgang zu strömen.

System for adjusting the quantity of air in a gas turbine with a temperature-activatable valve.

Es ist ein System zur Einstellung der Menge an Luft, die durch eine Druckgrenze in einer Gasturbine hindurch geliefert wird, offenbart, das einen an der Druckgrenze angeordneten Durchgang (30) enthält. Ferner ist in dem Durchgang (30) ein temperaturaktivierbares Ventil (32) montiert, das konfiguriert ist, um bei einem vorbestimmten Temperaturschwellenwert auszulösen. Insbesondere löst das temperaturaktivierbare Ventil (32) aus, um von einer Schliessstellung zu einer Offenstellung umzuschalten, wenn die lokale Temperatur an dem temperaturaktivierbaren Ventil (32) den vorbestimmten Temperaturschwellenwert erreicht oder überschreitet, um Luft zu ermöglichen, durch den Durchgang zu strömen. It is a system for adjusting the amount of air delivered through a pressure boundary in a gas turbine disclosed having a passage (30) disposed at the pressure boundary. Further, mounted in the passageway (30) is a temperature activatable valve (32) configured to initiate at a predetermined temperature threshold. In particular, the temperature-activatable valve (32) triggers to switch from a closed position to an open position when the local temperature at the temperature-activatable valve (32) reaches or exceeds the predetermined temperature threshold to allow air to flow through the passage.

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).

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.

Procedure for installing temperature monitoring means in a fluid-flow machine plant.

Die Erfindung betrifft ein Verfahren zum Installieren von Temperaturüberwachungsmitteln in einer Strömungsmaschinenanlage, wobei die Temperaturüberwachungsmittel von wenigstens einer Thermofarbe gebildet sind. Das Verfahren umfasst die folgenden Schritte: Auswählen wenigstens einer hinsichtlich ihrer Temperatur zu überwachenden Komponente der Strömungsmaschinenanlage (S10), Auswählen einer Thermofarbe mit einer auf die Temperatur der zu überwachenden Komponente angepassten Reaktionstemperatur (S20), und Aufbringen der Thermofarbe auf die hinsichtlich ihrer Temperatur zu überwachende Komponente (S30). Dabei wird als wenigstens eine hinsichtlich ihrer Temperatur zu überwachende Komponente eine Komponente der Strömungsmaschinenanlage ausgewählt, welche aufgrund ihrer Temperatur hinsichtlich ihrer Durchströmung mit einem Prozessfluid überwacht werden soll.

Procedure around installing functional monitoring means.

Beim Verfahren zum Installieren von Funktionsüberwachungsmitteln in einer Strömungsmaschinenanlage sind die Funktionsüberwachungsmittel von wenigstens einer Thermofarbe gebildet. Das Verfahren weist folgende Schritte auf: Auswählen wenigstens einer hinsichtlich ihrer Funktion zu überwachenden Komponente der Strömungsmaschinenanlage (S10), Auswählen einer bestimmten Thermofarbe für die hinsichtlich ihrer Funktion zu überwachende Komponente (S20), und Aufbringen der Thermofarbe auf die hinsichtlich ihrer Funktion zu überwachende Komponente (S30), wobei die Thermofarbe auf wenigstens eine hinsichtlich ihrer Durchströmung mit einem Prozessfluid zu überwachende Komponente der Strömungsmaschinenanlage aufgebracht wird.

Thermal Coutrolor

SYSTEM FOR DETECTING ABNORMALITY OF TEMPERATURE WITHIN THE COMPARTMENT INTER VEINS OF A TURBOFAN ENGINE

Pyrometer for measuring gas turbine exhaust temp. - has conduit filled with insulation and damping polystyrene foam

Detector of overheating

METHOD FOR DETECTING LEAKAGE OF FLUID IN A TURBOMACHINE AND FLUID DELIVERY SYSTEM

IMPROVEMENTS WITH the SYSTEMS OF DEVICE CONTROL

CONTROL SYSTEM AND METHOD FOR GAS TURBINE INLET-AIR WATER-SATURATION AND SUPERSATURATION SYSTEM

METHOD OF INSTRUMENTING A COMPONENT

A method of instrumenting a first component (210) for use in a combustion turbine engine (10) wherein the first component (210) has a surface contacted by a second component during operation of the combustion turbine engine (10). The method may include depositing an insulating layer (260) on the surface of the first component (210) and depositing a first conductive lead (232, 254) on the insulating layer (260). A piezoelectric material (230) may be deposited in electrical communication with the first conductive lead (232, 254) and a second conductive lead (236, 256) may be deposited in electrical communication with the piezoelectric material (230) and be insulated from the first conductive lead (232, 254) to form a sensor (50) for detecting pressure exerted on the surface of the first component (210) during operation of the combustion turbine engine (10) ...

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 ...

Apparatus and method for measuring turbine temperature

A temperature sensing device for a turbine of an engine and a method for measuring the temperature of the turbine are disclosed. The turbine includes a turbine stage coupled to a rotatable shaft and an outer casing. First and second sensor holders are disposed between the rotatable shaft and the outer casing, and first and second temperature sensors disposed on the first and second sensor holders, respectively. Each of the first and second sensor holders has only one temperature sensor disposed thereon, the first and second temperature sensors are disposed at first and second distances from the rotatable shaft respectively, and the first and second distances are different.

Method and device for identifying the operating condition of a turbine

The invention relates to a method for identifying the operating condition of a turbine during operation. According to said method, a hot waste gas flows through a waste gas housing and the temperature of the waste gas in said housing is detected using temporal resolution. The aim of the invention is to provide a method for identifying the operating condition of a turbine during operation, which identifies and displays systematic errors. To achieve this, the numerous measured temperature values for the waste gas are respectively detected using local resolution with reference to the origin of an imaginary Cartesian co-ordinate system. The focal point of the temperature distribution is then determined, a vector between the origin of the Cartesian co-ordinate system and the focal point of the temperature distribution being used as an indicator for the operating condition of the turbines.

Turbine impulse chamber temperature determination method and apparatus

A method and apparatus for determining the steam temperature in the impulse chamber at the first stage exit of a multistage high pressure steam turbine utilizes measurement of steam pressure in the impulse chamber and steam pressure and temperature at the exhaust as inputs to a digital computer. The functional relationships among steam pressure, temperature, specific volume, enthalpy and entropy are stored in the computer memory, and used with these measured quantities to iteratively calculate the steam temperature at the impulse chamber.

Method for determining limit exceedance

A method and system for determining a limit exceedance of an operating parameter in a steam turbine system. Measurement data associated with the operating parameter is received, and a limit exceedance is determined when the rate of change in the received data over a predefined period of time exceeds a predefined limit. A control action is taken when a limit exceedance has been determined.

Methods for detecting water induction in steam turbines

A method of detecting water induction in a steam turbine that may include the steps of: measuring the temperature of one of the steam lines of the steam turbine at regular intervals; recording the temperature measurements; and determining, from the recorded temperature measurements, whether there has been a sharp decrease followed by a gradual rise in the temperature of the steam line. The method further may include the steps of calculating the rate of change of the decrease in temperature of the steam line and the rate of change of the increase in temperature of the steam line. The sharp decrease followed by a gradual rise in the temperature of the steam line may include a decrease in temperature followed by an increase in temperature wherein the rate of change of the decrease in temperature exceeds the rate of change of the rise in temperature.

PROBE HOLDER FOR TURBINE ENGINE SENSOR

A turbine is provided and includes a component having a body, which is rotatable about a rotor centerline and which is formed to define a cavity radially proximate to a point of measurement interest defined at a radial distance from the centerline, a sensor to measure a condition at the point of measurement interest, a communication system by which condition measurements are transmittable from the sensor to a non-rotating recording system and a probe holder insertible into the cavity to secure the sensor proximate to the point of measurement interest.

SYSTEM AND METHOD OF MEASURING TURBINE VANE COOLING AIR CONSUMPTION DURING ENGINE OPERATION

Vanes for use in gas turbine engines and methods of measuring cooling air flow through vanes are disclosed herein. Each vane includes an airfoil and an end wall. The airfoil is shaped to interact with hot gasses moving along a primary gas path during operation of the gas turbine engine. The end wall is coupled to the airfoil and shaped to define a boundary of the primary gas path near a radial end of the airfoil. The end wall includes a platform that is exposed to the primary gas path and a projection that extends away from the platform and is located outside the primary gas path.

MULTI-CHANNEL MULTI-RANGE TRANSDUCER

There is described a multi-channel, multi-range transducer for measuring a parameter, the transducer comprising N channels and M sensing elements, the M sensing elements centered on distinct calibration points of distinct measuring ranges, the M sensing elements distributed across the N channels of the transducer, wherein sensing elements having adjacent measuring ranges are provided in different ones of the N channels.

Integrated gas turbine engine support and sensor

An example integrated support and sensor includes a longitudinal member to support an inner duct relative to an outer duct, and a sensor received within a bore of the longitudinal member and configured to collect a measurement from a flow path bounded by the inner duct.

APPARATUS AND METHOD FOR MEASURING TURBINE TEMPERATURE

A temperature sensing device for a turbine of an engine and a method for measuring the temperature of the turbine are disclosed. The turbine includes a turbine stage coupled to a rotatable shaft and an outer casing. First and second sensor holders are disposed between the rotatable shaft and the outer casing, and first and second temperature sensors disposed on the first and second sensor holders, respectively. Each of the first and second sensor holders has only one temperature sensor disposed thereon, the first and second temperature sensors are disposed at first and second distances from the rotatable shaft respectively, and the first and second distances are different. 1. A temperature sensing device for measuring temperature in a turbine of an engine , wherein the turbine includes a turbine stage coupled to a rotatable shaft and an outer casing , comprising:first and second sensor holders disposed between the rotatable shaft and the outer casing;a first temperature sensor disposed on the first sensor holder at a first radial distance from the rotatable shaft; anda second temperature sensor disposed on the second sensor holder at a second radial distance from the rotatable shaft;wherein each of the first and second sensor holders has only one temperature sensor disposed thereon, and the first and second distances are different.2. The temperature sensing device of claim 1 , including a third sensor holder disposed between the rotatable shaft and the outer casing claim 1 , wherein the third sensor holder is free of a temperature sensor.3. The temperature sensing device of claim 1 , further including a ring that encircles the rotatable shaft claim 1 , and the first and second sensor holders are secured to the ring.4. The temperature sensing device of claim 3 , wherein first and second sensor holders are secured to the casing.5. The temperature sensing device of claim 1 , wherein the first and second sensor holders are cantilevered from the outer casing.6. The ...

Method for determination of the temperature, mass-averaged over a flow cross-section, of a gas flow in a gas turbine

The invention relates to a method for determination of a temperature, mass-averaged over a flow cross-section, of a gas flow in a gas turbine or the like, particularly during partial load operation of the gas turbine. The invention also relates to a control apparatus, which can be operated using the method according to the invention, for controlling a gas turbine installation. The method according to the invention comprising the steps of the temperature value of the gas flow being detected by a sensor or sensors at at least one position in the gas flow in the area of the flow cross-section, of determination of a correction value for correction of the temperature value for compensation for non-uniformities in the temperature profile of the gas flow across the flow cross-section as a function of at least one operating-point-specific parameter, and of correcting the temperature value, which is recorded by a sensor or sensors, by the correction value.

Method for correcting a temperature value of a pyrometer in a gas turbine

Temp. correction method for pyrometer in gas turbine The method involves measuring values in a stationary state. A further temp. value is derived from the measured values to form a comparison value from which the pyrometer temp. value is corrected based on the comparison value. State values are continuously acquired during the operating phase and changes in the state values are continuously checked. The measurement values are stored when it is detected that the changes have fulfilled a defined condition corresp. to the stationary state. The state parameters are throttle position, engine inlet temp., inlet press., high press. revolution rate, low press. revolution rate and flight attitude.

СПОСОБ И СИСТЕМА ДЛЯ ОПРЕДЕЛЕНИЯ ПРЕВЫШЕНИЯ ОГРАНИЧЕНИЯ РАБОЧЕГО ПАРАМЕТРА В СИСТЕМЕ ПАРОВОЙ ТУРБИНЫ

Изобретение относится к способу определения превышения ограничения рабочего параметра в системе паровой турбины. Согласно изобретению принимают данные измерения, связанные с рабочим параметром, определяют совокупную кривую скорости изменения для рабочего параметра для заданного периода времени, сравнивают совокупную кривую с заданной для заданного периода времени, определяют, когда совокупная кривая пересекает заданную кривую скорости изменения, и осуществляют управляющее воздействие, если имело место пересечение. 2 н. и 8 з.п. ф-лы, 9 ил.

ТУРБИННАЯ УСТАНОВКА, РАБОТАЮЩАЯ НА ВЛАЖНОМ ВОЗДУХЕ

Изобретение направлено на сокращение времени, необходимого для запуска, и предотвращение чрезмерного увеличения тепловых нагрузок на лопатках турбины. Турбинная установка, работающая на влажном воздухе, включает в себя компрессор; камеру сгорания; турбину; блок рекуперации тепла выхлопных газов для рекуперации тепла выхлопных газов турбины для получения высокотемпературной влаги; систему подачи топлива, имеющую клапан регулировки расхода топлива; блок получения температуры выхлопных газов для получения температуры выхлопных газов, выпускаемых во время приведения в движение турбины; блок вычисления показателя влажности газа сгорания для определения показателя влаги, содержащейся в газе сгорания; блок вычисления верхнего предела температуры выхлопных газов для установления верхнего предела температуры выхлопных газов на основе показателя влажности газа сгорания и отношения давлений; блок вычисления разности температур выхлопных газов для определения разности между верхним пределом температуры ...

УСТРОЙСТВО ДЛЯ ИЗМЕРЕНИЯ ТЕМПЕРАТУРЫ В ПРОТОЧНОМ КАНАЛЕ ПЕРВИЧНОГО ПОТОКА ДВУХКОНТУРНОГО ТУРБОРЕАКТИВНОГО ДВИГАТЕЛЯ

... 1. Устройство для измерения температуры на входе компрессора в проточном канале первичного потока двухконтурного турбореактивного двигателя, причем устройство содержит воздухонепроницаемую пустотелую конструкцию, образующую соединительный кронштейн разделительного корпуса турбореактивного двигателя и выполненную с возможностью радиально проходить через проточный канал для первичного потока и проточный канал для вторичного потока турбореактивного двигателя, причем соединительный кронштейн имеет по меньшей мере одно воздухозаборное отверстие, открывающееся в проточный канал первичного потока на входе компрессора, и по меньшей мере одно воздуховыпускное отверстие, выполненное так, чтобы вести в зону турбореактивного двигателя, где окружающее давление меньше давления в проточном канале первичного потока на входе компрессора, причем устройство дополнительно включает в себя датчик температуры, чувствительный элемент которого размещен внутри соединительного кронштейна.2. Устройство по п. 1, в ...

УСТРОЙСТВО ГЕНЕРАЦИИ СОЛНЕЧНОЙ ЭНЕРГИИ И ВНЕШНИЙ ПАРОВОЙ ИСТОЧНИК ДОПОЛНИТЕЛЬНОЙ ЭЛЕКТРОЭНЕРГИИ

... 1. Солнечная и внешняя паровая гибридная система генерации электроэнергии, содержащая солнечный парогенератор, внешний регулятор пара (15), турбоагрегат (2), и генератор (1) мощности, соединенный с турбоагрегатом (2), отличающаяся тем, что выходной конец солнечного парогенератора соединен с входом (3) пара высокого давления турбоагрегата (2) через первый регулирующий клапан (18); выходной конец для пара внешнего регулятора (15) пара также соединен с входом (3) пара высокого давления турбоагрегата (2) через второй регулирующий клапан (20) и второй переключающий клапан (19); выход (4) пара низкого давления турбоагрегата (2) соединен с входным концом конденсационного аппарата (5), а выходной конец конденсационного аппарата (5) соединен с входным концом деаэратора (6); выходной конец деаэратора (6) соединен с входным концом насоса (7) подачи воды; выходной конец насоса (7) подачи воды соединен с входным концом оборотной воды солнечного парогенератора через первый переключающий клапан (16); ...

УСТРОЙСТВО И СВЯЗАННАЯ С НИМ СИСТЕМА КОНТРОЛЯ

... 1. Устройство, включающее:корпус ротора;наборы лопаток ротора, выходящих радиально из корпуса ротора, распределенные по оси вдоль корпуса ротора;разделительную область, разделяющую два соседних набора из упомянутых наборов лопаток ротора по оси вдоль корпуса ротора;проводящий элемент, расположенный в упомянутой разделительной области, для создания электрического тока имодуль, электрически соединенный с упомянутым проводящим элементом, для приема электрического тока из проводящего элемента и для питания по меньшей мере одного устройства контроля, размещенного на корпусе ротора.2. Устройство по п.1, в котором упомянутый модуль включает по меньшей мере одно из следующего: выпрямитель, регулятор напряжения, беспроводной приемник или беспроводной передатчик.3. Устройство по п.2, также включающее соединительную линию, электрически соединяющую упомянутый проводящий элемент и упомянутый модуль.4. Устройство по п.1, также включающее соединительную линию, электрически соединяющую упомянутый модуль ...

Verfahren zur Steuerung einer Turbine eines Abgaswärmerückgewinnungssystems

Verfahren zur Steuerung einer Turbine eines Abgaswärmerückgewinnungssystems, bei dem Wärme von Abgas ein Arbeitsfluid mittels eines in einem Abgasrohr vorgesehenen Wärmetauschers verdampft und der Turbine das Arbeitsfluid zugeführt wird, aufweisend Messen einer Innentemperatur des Wärmetauschers (S211), und Drehen der Turbine (S212) in einer umgekehrten Richtung, wenn die gemessene Innentemperatur gleich einer vorbestimmten Temperatur oder kleiner ist.

Verfahren zur Erkennung einer Fehlstellung der Winkellage einer in einem Verdichter angeordneten, um ihre Längsachse schwenkbaren Verdichterleitschaufel

Die Erfindung betrifft ein Verfahren zur Erkennung einer Fehlstellung der Winkellage einer in einem Verdichter (5) angeordneten, um ihre Längsachse (23) schwenkbaren Verdichterleitschaufel (19), wobei der Verdichter (5) Teil einer Gasturbine (1) ist, die zudem eine Brennkammer (6) umfasst, bei dem:- eine Verdichteraustrittstemperatur (T) über mehrere, im Bereich zwischen einem Verdichteraustritt (29) und einem Brennkammereintritt (31) angeordnete Temperatursensoren (33) gemessen wird, wobei die Temperatursensoren (33) in Umfangsrichtung betrachtet unterschiedliche Positionen aufweisen und jeder Temperatursensor (33) ein Messsignal (M, M, M, M) liefert,- wenn eine plötzliche stufenartige Veränderung (S) von zumindest einem Messsignal (M) erfasst wird, während zumindest ein anderes Messsignal (M, M, M) unverändert bleibt, eine Fehlstellung erkannt wird.Durch das Verfahren ist es möglich, ohne zusätzlichen konstruktiven Aufwand im Betrieb des Verdichters (5) eine Fehlstellung der Winkellage ...

TEMPERATURFUEHLER FUER TURBOMASCHINEN-LUFTSTROEMUNG

Air temperature sensor having a bushing

Control or monitoring of temperature

Apparatus and method for determining transient temperature and stress distributions in turbomachines and system components as a function of operating conditions where direct measurements on the rotating components are prevented. The apparatus includes a microprocessor which computes temperature and stress distributions in real time for components of complex shapes. The apparatus employs a memory containing a set of standard temperature distributions under particular operating conditions and the temperature stresses in the component are estimated on the basis of the closest temperature distributions in the set. The apparatus can be embodied as an on-board in-flight LCF monitor of aircraft engine rotors or as an LCF monitor of a turbomachine for power generation such as a stationary turbine generating unit.

RADIATION PYROMETER SYSTEM

Isothermal de-iced sensor

Temperature control apparatus for turbine casings

... 903,947. Turbines. NAPIER & SON Ltd., D. June 18, 1959 [July 11, 1958], No. 22272/58. Class 110 (3). The casing of a turbine which is cooled by a flow of cooling air has means for controlling the flow of cooling air through a chamber in the casing in response to the temperature of the casing adjacent the cooling air chamber. The turbine casing 1 is double walled and formed with a series of air cooling chambers 2, 3, 4, 5, 6 and 7 each with a valve assembly 8 delivering cooling air to the chamber through an inlet 10. The cooling air may be tapped from the compressor or a forwardly facing inlet in the aircraft and the exhaust from each chamber may be returned to the working fluid. Each valve 8 is actuated by a steel band 12 which extends from a pin 13 on the valve to a pin 14 fixed to the casing, thus covering the major part of two adjacent chambers. Since the casing is formed of aluminium alloy, changes of temperature will cause movement of the band relative to the casing. This will result ...

Radiation pyrometer system

A radiation pyrometer system for a gas-turbine engine, or the like, has a radiation pyrometer (10) that supplies signals to a detector unit (20). The detector unit (20) includes an inverter (21) that inverts the pyrometer signals and supplies the inverted signals to one electrode of a capacitor (24) via a diode (23). The other electrode of the capacitor (24) is grounded, a resistor (25) being connected across the capacitor so that it is slowly discharged. The charge on the capacitor (24) approximately follows the high- voltage/low-temperature signals, which are reinverted by a processing unit (26) to give an averaged temperature indication (27). Periodically, the diode (23) is shorted for brief intervals by a switching circuit (30), so that the charge on the capacitor drops, producing a low-voltage/high-temperature spike representative of instantaneous temperature. These spikes, after reinversion, are fed to a storage device (28) with a long time period so as to produce a signal which follows ...

Optical radiation pyrometer

To be of most use as an input signal for the control system of a gas turbine aeroengine, a pyrometer-derived turbine blade temperature signal should represent the average temperature of the hottest parts of the blades with fast and accurate response when the average temperature of the hottest parts changes with engine conditions. The invention achieves this by providing the pyrometer with an optical system adapted to give the pyrometer's photo-diode a large field of view which is rectangular at the face of the turbine rotor and which extends an integer number of inter-blade passage widths in the circumferential direction and a portion of the length of the blade aerofoils in the radial direction. The large rectangular field of view is achieved by masking the optical system and arranging that it cooperates with a small aperture in the wall of the turbine gas passage in such a way that at the aperture the field of view lies entirely within the boundary of the aperature, the field of view expanding ...

Improvements in or relating to gas temperature sensing unit or probe of thermocoupletype

... 784,597. Measuring temperature. CANTLIN, J. H., and ANDERSON, E. E. Aug. 22, 1955 [Aug. 23, 1954], No. 24181/55. Class 40(1). A temperature sensing unit comprises an elongated probe 3 containing a thermocouple 8, 9 and a supporting member 20 having a central bore in which the probe 3 is received, this bore having a flared end at 25 so shaped as to damp out vibrations of the probe. The thermocouple wires 8, 9 are mounted in insulating material 11 in the probe 3 and the latter is a tight fit in the support 20, which comprises inner and outer flanges 23, 22 and a part 21 on which fits a flange 30 adapted to be bolted to the wall of a chamber into which the probe projects to sense the temperature of gas flowing therethrough. The flange 22 has an inturned lip between which and a ceramic mass 14 is housed a spring metal ring 15 for compensating for expansion difference between the support member 20 and the mass 14. Housed in the mass 14 are threaded connections 12, 13 for the thermocouple leads ...

Starting pointer for steam and gas turbines

DEVICE FOR HEADING FOR AN ELEMENT FROM A FORM MEMORY ALLOY

PYROMETER MOUNTING PLATE FOR A GAS TURBINE WITH CLOSED COOLING CIRCUIT

MATCHING STEAM AND TURBINE TEMPERATURE

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.

Thermal control system for fault detection and mitigation within a power generation system

A system includes a radiation sensor configured to direct a field of view toward at least one conduit along a fluid flow path into a heat exchanger. The radiation sensor is configured to output a signal indicative of a temperature of the at least one conduit. The system also includes a controller communicatively coupled to the radiation sensor. The controller is configured to determine the temperature based on the signal, to compare the temperature to a threshold range, and to adjust a fluid flow through the fluid flow path or the at least one conduit if the temperature deviates from the threshold range.

Thermocouple and method of forming a thermocouple on a contoured gas turbine engine component

A method of forming a thermocouple ( 12 ), including: depositing a first material on a component ( 10 ) to form a first leg ( 14 ); depositing a second material through a mask ( 30 ) to form a pattern ( 50 ) on the component ( 10 ), the pattern ( 50 ) forming a plurality of discrete second leg junction ends ( 20 ) and a continuous patch ( 52 ) of the second material comprising indiscrete lead ends of the second legs ( 16 ), each second leg junction end ( 20 ) spanning from a respective junction ( 18 ) with the first leg ( 14 ) to the continuous patch ( 52 ); and laser-ablating the continuous patch ( 52 ) to form discrete lead ends ( 22 ) of the second legs ( 16 ), each lead end ( 22 ) electrically connected to a respective junction end ( 20 ), thereby forming discrete second legs ( 16 ).

Method for monitoring the clearance of a kinematic link between a control member and a receiving member

The method consists, based on an operating parameter of the turbojet engine, in: displacing said control member ( 11 ) in a direction as far as a first position (P 1 ) for which the receiving members ( 5 ) are rotated so as to take up the clearance of the kinematic link ( 12 ), then displacing said control member in the direction opposing the previous direction, as far as a second position (P 2 ) when a variation of the selected operating parameter is observed, and in ascertaining the travel of the control member ( 11 ) between the two positions corresponding to the total clearance of the kinematic link ( 12 ), and comparing the ascertained value of said travel of the control member with a predetermined limit value and, if it is observed that the ascertained value of the travel of the control member is greater than said limit value, to carry out monitoring of the kinematic link ( 12 ).

Method of positioning a control surface to reduce hysteresis

A method of determining the actual position of a control surface ( 27 ). The method comprises receiving a signal ( 34 ) representative of a required position of the control surface ( 27 ), repositioning the control surface ( 27 ) in response to the signal ( 34 ) by moving an actuator ( 26 ), measuring a secondary position indicator, calculating the actual position of the control surface ( 27 ) on the basis of the secondary position indicator and, comparing the actual position with the required position.

Exhaust Gas Temperature Sensor Including a Vibration Reducing and/or Modifying Sleeve

A temperature sensor system includes a temperature sensor, a cable having an end coupled to the temperature sensor, and a stop flange coupled to the cable. The temperature sensor system further includes a vibration reducing and/or modifying sleeve positioned against the stop flange. The sleeve includes a body portion defining a through passage configured to receive and retain at least a portion of the cable. The sleeve is configured to provide stability and reduce vibrational stress to the temperature sensor system. The sleeve is configured to be added to the temperature sensor system during assembly of the system and/or to be added after the temperature sensor system is fully assembled.

METALLIC SEAL ASSEMBLY, TURBINE COMPONENT, AND METHOD OF REGULATING AIRFLOW IN TURBO-MACHINERY

A metallic seal assembly, a turbine component, and a method of regulating flow in turbo-machinery are disclosed. The metallic seal assembly includes a sealing structure having thermally-responsive features. The thermally-responsive features deploy from or retract toward a surface of the sealing structure in response to a predetermined temperature change. The turbine component includes the metallic seal assembly. The method of regulating flow in turbo-machinery includes providing the metallic seal assembly and raising or retracting the thermally-responsive features in response to the predetermined temperature change. 1. A metallic seal assembly , comprising:a sealing structure having thermally-responsive features;wherein the thermally-responsive features deploy from or retract toward a surface of the sealing structure in response to a predetermined temperature change.2. The metallic seal assembly of claim 1 , wherein the thermally-responsive features include a first metallic layer and a second metallic layer.3. The metallic seal assembly of claim 2 , wherein the first metallic layer and the second metallic layer have a misfit strain of between about 5% and about 40%.4. The metallic seal assembly of claim 1 , wherein one or both of the first metallic layer and the second metallic layer include material selected from the group consisting of nickel claim 1 , iron claim 1 , cobalt claim 1 , stainless steel claim 1 , aluminum claim 1 , copper claim 1 , magnesium claim 1 , gold claim 1 , platinum MCrAlY claim 1 , and combinations thereof.5. The metallic seal assembly of claim 1 , wherein the thermally-responsive features include a portion of the metallic seal assembly.6. The metallic seal assembly of claim 1 , wherein the metallic seal assembly is a metallic woven seal.7. The metallic seal assembly of claim 1 , wherein the sealing structure has a first coefficient of thermal expansion and the thermally-responsive feature has a second coefficient of thermal expansion claim ...

SYSTEM AND METHODS FOR CBV DIAGNOSTICS

Methods and systems are provided for diagnosing compressor bypass valve degradation. In one example, a method may include indicating degradation of a compressor bypass valve coupled in a compressor bypass based on intake aircharge temperature measured upstream of a compressor inlet via an air charge temperature sensor. 1. A method for diagnosing a continuously variable compressor bypass valve of an engine , comprising:adjusting continuously variable compressor bypass valve responsive to operating conditions of the engine; andindicating degradation of a compressor bypass valve coupled in a compressor bypass based on intake aircharge temperature being different then a threshold temperature measured upstream of a compressor inlet, and changing engine operating parameters due to the indication.2. The method of claim 1 , wherein if the compressor bypass valve is stuck open claim 1 , changing engine operation includes close a wastegate valve.3. The method of claim 1 , wherein if the compressor bypass valve is stuck closed claim 1 , changing engine operation include increasing flow through the compressor.4. The method of claim 3 , wherein increasing flow through the compressor includes adjusting a throttle position.5. The method of claim 3 , wherein increasing flow through the compressor includes adjusting an exhaust gas recirculation (EGR) rate.6. The method of claim 1 , wherein the intake aircharge temperature is measured by a temperature sensor coupled at a junction of the compressor bypass and an air intake passage at the compressor inlet.7. The method of claim 1 , wherein the compressor bypass is configured to recirculate boosted aircharge from downstream of the compressor and upstream of a charge air cooler to the compressor inlet.8. The method of claim 1 , wherein the indicating includes claim 1 , during higher boost conditions claim 1 , indicating degradation of the compressor bypass valve based on intake aircharge temperature being higher than a first threshold ...

GAS TURBINE, SEALING COVER, SEALING TELEMETRY ASSEMBLY, AND MANUFACTURING METHOD THEREOF

At least one embodiment of the present invention provides a sealing telemetry assembly used for a gas turbine. The gas turbine includes at least one turbine disk, and the sealing telemetry assembly includes a sealing cover and at least one power supply apparatus. The sealing cover is used to cover the turbine disk, and the sealing cover includes a cavity forming portion and a cover. At least one installation cavity is provided within the cavity forming portion, and the cover covers and is fixed to the cavity forming portion. The power supply apparatus is configured in the installation cavity. A gas turbine, a sealing cover, and a manufacturing method of a sealing telemetry assembly are also provided. They can improve working performance of the gas turbine, reduce production costs, and monitor an internal working environment of the gas turbine. 1. A sealing telemetry assembly useable for a gas turbine , the gas turbine including at least one turbine disk , the sealing telemetry assembly comprising: a cavity forming portion, at least one installation cavity being provided within the cavity forming portion, and', 'a cover, the cover covering and being fixed to the cavity forming portion; and, 'a sealing cover, the sealing cover being usable to cover the turbine disk, and the sealing cover includingat least one power supply apparatus, configured in the at least one installation cavity.2. The sealing telemetry assembly of claim 1 , wherein the cover is provided with a plurality of wire insertion holes such that upon the cover covering the cavity forming portion claim 1 , a corresponding one of the plurality of wire insertion holes is in communication with corresponding one of the at least one installation cavity.3. The sealing telemetry assembly of claim 1 , further comprising:at least one sensor, configured in the at least one installation cavity, wherein the at least one power supply apparatus is electrically connected to the at least one sensor.4. The sealing ...

METHOD OF COLLECTING RADIATION INFORMATION OF TURBINE BLADE

A method of collecting radiation information of a turbine blade, the method including: 1) collecting a radiated light from the surface of the turbine blade, analyzing the radiated light using a spectrometer to calculate compositions and corresponding concentrations of combustion gas; 2) calculating an absorption coefficient of the combustion gas at different concentrations; 3) calculating a total absorption rate of the combustion gas at different radiation wavelengths under different concentrations of component gases; 4) obtaining a relationship between the radiation and a wavelength; 5) finding at least 3 bands with a least gas absorption rate; 6) calculating a distance between a wavelength of a strongest radiation point of the turbine blade and the center wavelength, and selecting three central wavelengths closest to the wavelength with the strongest radiation; and 7) acquiring radiation data of the turbine blade in the windows obtained in 6). 2. The method of claim 1 , wherein a wavelength λof the three bands obtained in 6) corresponding to a minimum absorption rate of the combustion gas is calculated claim 1 , and a distance d between the wavelength λand a center wavelength of a corresponding band is calculated; and a band in the range of λ±d in the three bands are determined as the acquisition windows. Pursuant to 35 U.S.C.§ 119 and the Paris Convention Treaty, this application claims foreign priority to Chinese Patent Application No. 201710523299.2 filed Jun. 30, 2017, the contents of which and any intervening amendments thereto are incorporated herein by reference. Inquiries from the public to applicants or assignees concerning this document or the related applications should be directed to: Matthias Scholl P. C., Attn.: Dr. Matthias Scholl Esq., 245 First Street, 18th Floor, and Cambridge, Mass. 02142.The invention relates to a method of collecting radiation information of a turbine blade.Conventionally, to measure the temperature of turbine blades, a ...

VALVE SYSTEM FOR A FLUID CONDUIT SYSTEM IN AN AIRCRAFT ENGINE AND METHOD FOR THE OPERATION OF A VALVE SYSTEM FOR A FLUID CONDUIT SYSTEM IN AN AIRCRAFT ENGINE

A valve system for a fluid line system in an aircraft engine, which fluid line system has at least one fluid line wherein the at least one fluid line has at least one check valve, wherein the valve position of an actuator in the at least one check valve is changeable, in particular automatically changeable, in dependence on the pressure ratios in each case acting on the at least one check valve. The valve system has a monitoring means for recording the respective valve position, in particular the open position and/or the closed position of the actuator, in dependence on at least one measurement value, wherein a signal is output in dependence on the recorded valve position. The valve system furthermore has a means for setting a minimum required sealing-air stream. The invention also relates to a valve control method.

GAS TURBINE AND METHOD FOR OPERATING THE GAS TURBINE

A gas turbine includes an intake tract and a compressor having a compressor flow channel. The compressor further includes an inlet guide vane row positioned in the compressor flow channel having inlet guide vanes that can be adjusted. The gas turbine has an icing sensor unit having at least one sensor arranged between a first compressor blade row and a first compressor guide vane row. The first compressor blade row is thereby arranged in the compressor flow channel directly downstream of the inlet guide vane row, and the first compressor guide vane row is arranged directly downstream of the first compressor blade row. A method detects an imminent icing of the compressor, and the compressor is safeguarded therefrom such that at least inlet guide vanes of the inlet guide vane row are adjusted such that the acceleration of an intake air mass flow is reduced. 1. A gas turbine comprising an intake section and a compressor having a compressor flow duct , wherein the compressor has an inlet guide blade row with adjustable inlet guide blades , which is positioned in the compressor flow duct , the gas turbine comprising:an icing sensor unit comprising at least one sensor arranged between a first compressor rotor blade row and a first compressor guide blade row, wherein the first compressor rotor blade row is arranged immediately downstream of the inlet guide blade row and the first compressor guide blade row is arranged immediately downstream of the first compressor rotor blade row in the compressor flow duct,wherein the icing sensor unit has at least one air humidity sensor and, in addition, at least one pressure sensor and one temperature sensor, which are both arranged between the first compressor rotor blade row and the first compressor guide blade row.2. The gas turbine as claimed in claim 1 ,wherein the icing sensor unit has at least one air humidity sensor and at least one pressure sensor and one temperature sensor, which are arranged between the first compressor ...

COMBINED HEAT AND POWER SYSTEM AND OPERATING METHOD OF COMBINED HEAT AND POWER SYSTEM

A combined heat and power system is provided with a Rankine cycle passage, a heat medium passage, an evaporator, an expander, a condenser, a pump, a temperature sensor, a sensor, and a controller. The evaporator receives the heat from the heat medium to heat a working fluid. The temperature sensor detects the temperature of the heat medium after radiating heat for heating the working fluid. The sensor detects the pressure of the working fluid flowing between the outlet of the evaporator and the inlet of the expander. The controller adjusts the rotation speed of the pump based on the temperature detected by the temperature sensor, and in addition, adjusts the rotation speed of the expander based on the pressure detected by the sensor. 1. A combined heat and power system comprising:a Rankine cycle passage in which a working fluid flows;a heat medium passage in which a heat medium supplied from a heat source flows;an evaporator that is disposed in the Rankine cycle passage and that directly or indirectly receives heat from the heat medium to heat the working fluid;an expander that is disposed in the Rankine cycle passage and that expands the working fluid flowing from the evaporator to generate rotational power;a condenser that is disposed in the Rankine cycle passage and that cools the working fluid flowing from the expander;a pump that is disposed in the Rankine cycle passage and that pumps the working fluid flowing from the condenser to the evaporator;a temperature sensor that detects a temperature of the heat medium after radiating heat for heating the working fluid;a sensor for determining a pressure of the working fluid flowing between the outlet of the expander and inlet of the expander in the Rankine cycle passage; anda controller that controls a rotation speed of the pump based on the temperature detected by the temperature sensor and that controls a rotation speed of the expander based on the pressure determined based on the result of the detection by the ...

Method for securing the operation of a turbomachine

A method of making safe operation of a rotary assembly of a turbomachine including a turbine and a rotary machine, the method anticipating an event of exceeding a predetermined threshold speed by repetitively performing a prediction cycle including: measuring magnitudes relating to operation of the turbomachine, including real speed of rotation of its rotary assembly; based on the magnitudes, estimating driving and resisting torques applied to the rotary assembly; preparing a representative value representative of the difference between these two torques; and calculating a predicted speed of rotation for the rotary assembly at a given time horizon based on the representative value and the real speed of rotation. An action is taken on the operation of the turbomachine to limit an extent to which its rotary assembly exceeds the threshold speed in the event of the predicted speed of rotation exceeding the threshold speed.

Active Waveguide Excitation and Compensation

An environmental condition may be measured with a sensor () including a wire () having an ultrasonic signal transmission characteristic that varies in response to the environmental condition by sensing ultrasonic energy propagated through the wire using multiple types of propagation, and separating an effect of temperature on the wire from an effect of strain on the wire using the sensed ultrasonic energy propagated through the wire using the multiple types of propagation. A positive feedback loop may be used to excite the wire such that strain in the wire is based upon a sensed resonant frequency, while a square wave with a controlled duty cycle may be used to excite the wire at multiple excitation frequencies. A phase matched cone () may be used to couple ultrasonic energy between a waveguide wire () and a transducer (). 1. A method of measuring an environmental condition with a sensor of the type that includes a wire having an ultrasonic signal transmission characteristic that varies in response to the environmental condition , the method comprising:sensing ultrasonic energy propagated through the wire using multiple types of propagation; andseparating an effect of temperature on the wire from an effect of strain on the wire using the sensed ultrasonic energy propagated through the wire using the multiple types of propagation.2. The method of claim 1 , further comprising exciting the wire using the multiple types of propagation.3. The method of claim 2 , wherein exciting the wire using the multiple types of propagation comprises exciting the wire at multiple excitation frequencies.4. The method of claim 3 , wherein exciting the wire at multiple excitation frequencies comprises exciting the wire at a first excitation frequency that propagates ultrasonic energy primarily as a longitudinal wave claim 3 , and exciting the wire at a second excitation frequency that propagates ultrasonic energy primarily as a shear wave.5. The method of claim 1 , wherein separating the ...

TEMPERATURE CONTROL SYSTEM FOR GAS COMBUSTION ENGINES AND METHOD OF USING THE SAME

A method of managing the thermal output of a gas combustion engine having a plurality of combustion zones uses a temperature control system integrated with the engine to provide digital thermal signals to a control unit. The control unit determines when to adjust an engine operating parameter based on an analysis of the thermal signals. The temperature control system includes a plurality of smart thermal sensors with at least one sensor for each combustion zone, a communication bus, and a control unit. Each smart thermal sensor converts the measured temperature from an analog thermal signal to a digital thermal signal. 1. A temperature control system integrated with a gas combustion engine that includes a plurality of combustion zones; the temperature control system comprising:a plurality of smart thermal sensors, wherein the smart thermal sensors are located such that at least one smart thermal sensor measures a temperature in real-time for each of the combustion zones;a communication bus through which a thermal signal from each of the smart thermal sensors is transmitted; anda control unit that receives the thermal signals from the communication bus;wherein the control unit uses the thermal signals to adjust one or more operating parameters of the gas combustion engine.2. The temperature control system according to claim 1 , wherein the smart thermal sensor outputs a digital signal to the communication bus.3. The temperature control system according to claim 2 , wherein the smart thermal sensor comprises a thermocouple element claim 2 , an analog to digital signal converter claim 2 , and optionally claim 2 , a protective sheath.4. The temperature control system according to claim 1 , wherein the gas combustion engine is a gas turbine engine or a gas piston engine.5. The temperature control system according to claim 4 , wherein the gas combustion engine is a gas turbine engine.6. The temperature control system according to claim 1 , wherein number of combustion ...

Determination of a fuel delivery fault in a gas turbine engine

A method of determining a fuel delivery fault in a gas turbine engine is provided, the engine having a combustor, a combustor fuel system for delivering fuel to the combustor, and a turbine which is driven by hot gas from the combustor. The method includes comparing a measured turbine gas temperature profile against a predicted turbine gas temperature profile. The method further includes comparing a measured combustor instability against a predicted combustor instability. The method further includes indicating that a fuel delivery fault in the combustor fuel system has been detected when both the measured turbine gas temperature profile and the measured combustor instability differ from their predicted values by more than respective predetermined thresholds.

RUNOUT DETECTION DEVICE

In a runout detection device for detecting runout of a rotating member, a displacement unit abuts on the rotating member, and is displaced in accordance with displacement of the rotating member while the rotor abuts on the displacement unit. An elastic member elastically deforms in accordance with displacement of the displacement unit. A heat flux sensor detects a heat flux generated by elastic deformation of the elastic member. The runout detection device is configured to detect runout of the rotating member based on the heat flux detected by the heat flux sensor. 1. A runout detection device for detecting runout of a rotating member , the runout detection device comprising:a displacement unit that abuts on the rotating member, and is displaced in accordance with displacement of the rotating member while the rotating member abuts on the displacement unit;an elastic member that elastically deforms in accordance with displacement of the displacement unit; anda heat flux sensor that detects a heat flux generated by elastic deformation of the elastic member,the runout detection device being configured to detect runout of the rotating member based on the heat flux detected by the heat flux sensor.2. The runout detection device according to claim 1 , wherein:the displacement unit includes a roller portion that rotates following rotation of the rotating member while the roller portion abuts on the rotating member.3. The runout detection device according to claim 1 , further comprising:an abnormality determining unit configured to determine whether the rotating member is abnormally run out in accordance with a value of the heat flux detected by the heat flux sensor.4. The runout detection device according to claim 3 , wherein:the abnormality determining unit is configured to, when it is determined that the value of the heat flux detected by the heat flux sensor exceeds a predetermined threshold value, determine that the rotating member is abnormally run out.5. The runout ...

AIR TEMPERATURE SENSOR HAVING A BUSHING

An air temperature sensor for use on an aircraft can include a housing defining an interior and having a trailing edge, a temperature sensor having a distal end and located within the interior, a support tube surrounding at least a portion the temperature sensor, an element shroud surrounding at least a portion of support tube, and a bushing isolating the trailing edge of the housing from the distal end of temperature sensor. 1. An air temperature sensor assembly , the air temperature sensor assembly comprising:a housing defining an interior and having a trailing edge;a temperature sensor having a distal end and located within the interior;a support tube surrounding at least a portion the temperature sensor;an element shroud surrounding at least a portion of support tube; anda bushing isolating the trailing edge of the housing from the distal end of temperature sensor.2. The air temperature sensor assembly of wherein the bushing is press fit between the element shroud and the support tube.3. The air temperature sensor assembly of wherein the bushing further comprises an aperture through a length of the bushing.4. The air temperature sensor assembly of wherein the support tube is press fit into the aperture of the bushing.5. The air temperature sensor assembly of wherein the distal end of the temperature sensor is spaced from an end wall of the bushing.6. The air temperature sensor assembly of wherein an outer wall of the bushing is press fit into the distal end of the element shroud.7. The air temperature sensor assembly of wherein the bushing further comprises a lip for acting as a stop for element shroud.8. The air temperature sensor assembly of wherein the bushing holds the support tube and element shroud in fixed relationship relative to one another.9. The air temperature sensor assembly of further comprising a gap between the support tube and element shroud.10. The air temperature sensor assembly of wherein the gap is uniform about a circumference of the ...

Fixation device for turbine and method for applying fixation

The invention provides a fixation device for a turbine, including a flange mounted on a housing of the turbine and a nut assembly received in the flange to apply fixation to an component inside the housing. The flange is fixed to the housing by a plurality of first bolts and comprises a central threaded hole. The nut assembly comprises a nut body with a first hole formed along the central axis of the nut body and a plurality of second holes formed around the central axis, and a plurality of second bolts received in the respective second holes. The nut body is formed with thread on its outer circumferential surface and fitted within the central threaded hole of the flange. The second bolts are screwed in the second holes to apply fixation against the component inside the housing of the turbine. The nut assembly further comprises a plurality of sleeves received in the respective second holes, and the plurality of second bolts are received in the respective sleeves. The fixation device in the present invention is able to apply for small and restricted space condition, which makes it possible to position the device very close to the split plane of the turbine. Further, the whole structure of the fixation device is simple with lightweight and easy to assemble with standard tools.

GAS TURBINE SWIRL DETECTION

A non-transitory computer readable medium with instructions stored thereon, the instructions executable by one or more processors for calculating base swirl in a gas turbine; and calculating relative swirl in the gas turbine. Also, a method for gas turbine maintenance, comprising identifying a combustor in need of repair or replacement within a gas turbine; and repairing or replacing the combustor; wherein said identifying comprises calculating base swirl of the gas turbine and calculating relative swirl of the gas turbine in order to associate a gas path from a thermocouple to the combustor in need of repair or replacement. 1. A non-transitory computer readable medium with instructions stored thereon , wherein the instructions are executable by one or more processors configured to perform calculating base swirl and relative swirl in a gas turbine.2. The non-transitory computer readable medium of claim 1 , wherein calculating base swirl comprises calculating (a) unsteady pressure amplitude as a function of angular position within the gas turbine and/or (b) mean-subtracted exhaust temperature as a function of angular position within the gas turbine.3. The non-transitory computer readable medium of claim 1 , wherein calculating base swirl comprises calculating (a) unsteady pressure amplitude as a function of angular position within the gas turbine and (b) mean-subtracted exhaust temperature as a function of angular position within the gas turbine.4. The non-transitory computer readable medium of claim 1 , wherein calculating base swirl comprises determining an average angular offset between an unsteady pressure amplitude as a function of an angular position within the gas turbine and a mean-subtracted exhaust temperature as a function of angular position within the gas turbine claim 1 , wherein the average angular offset is a function of a gas turbine load.5. The non-transitory computer readable medium of claim 1 , wherein calculating base swirl comprises measuring a ...

SYSTEM AND METHOD FOR MONITORING TEMPERATURE OF A GAS TURBINE ENGINE

A method and system for monitoring a temperature of a gas turbine engine are described. The method comprises obtaining individual sensor readings from functioning temperature sensors of a sensor array, where a number of the functioning temperature sensors is less than a total number of temperature sensors in the sensor array; applying correction factors to the individual sensor readings of the functioning temperature sensors based on deviations of the individual sensor readings from a total average temperature of all the temperature sensors in the array, to obtain corrected individual sensor readings; and determining a corrected total average temperature as a sum of the corrected individual sensor readings divided by the number of functioning temperature sensors. 1. A method for monitoring a temperature of a gas turbine engine , the method comprising:obtaining individual sensor readings from functioning temperature sensors of a sensor array, where a number of the functioning temperature sensors is less than a total number of temperature sensors in the sensor array;applying correction factors to the individual sensor readings of the functioning temperature sensors based on deviations of the individual sensor readings from a total average temperature of all the temperature sensors in the array, to obtain corrected individual sensor readings; anddetermining a corrected total average temperature as a sum of the corrected individual sensor readings divided by the number of functioning temperature sensors.2. The method of claim 1 , further comprising:determining the total average temperature when all of the temperature sensors in the array are functioning; andrecording the difference between each one of the individual sensor readings and the total average temperature for all of the temperature sensors in the array.3. The method of claim 1 , wherein the correction factors correspond to a difference between the total average temperature and a respective one of the ...

MEASURING DEVICE AND METHOD FOR AN AIRCRAFT ENGINE AND AN AIRCRAFT ENGINE

The invention relates to a measuring device for an aircraft engine, characterized by at least one probe device for measuring a physical and/or chemical state in at least one measuring space within the aircraft engine, wherein the at least one measuring space is fluidically connected to a cavity, and at least one air-conducting device, which is fluidically coupled to the cavity in such a manner that a fluid flow, in particular a gas flow, can be removed from the at least one cavity to a pressure sink. The invention also relates to an aircraft engine and to a measuring method. 1. A measuring device for an aircraft engine ,whereinat least one probe device for measuring a physical and/or chemical state in at least one measuring space within the aircraft engine, wherein the at least one measuring space is fluidically connected to a cavity, andat least one air-conducting device, which is fluidically coupled to the cavity in such a manner that a fluid flow, in particular a gas flow, can be removed from the at least one cavity to a pressure sink.2. The measuring device according to claim 1 , wherein the air-conducting device as the fluidic connection has a duct and/or an opening in a wall between the cavity and the pressure sink.3. The measuring device according to claim 1 , wherein the at least one probe device has a sensor for temperature claim 1 , pressure claim 1 , particles and/or a chemical composition.4. The measuring device according to claim 1 , wherein the at least one measuring space is arranged in a static part of the aircraft engine.5. The measuring device according to claim 1 , wherein the at least one measuring space is arranged in a vane of a turbine and/or of a compressor of the aircraft engine.6. The measuring device according to claim 5 , wherein the vane is the first static vane of a low-pressure turbine in the flow direction.7. The measuring device according to claim 1 , wherein the at least one measuring space is designed as an annular space between ...

Method for Operating a Turbo Machine

A system and method for determining performance of an engine is provided. The system includes two or more sensors configured in operable arrangement at two or more respective positions at a flowpath. The system includes one or more computing devices configured to perform operations, the operations include acquiring, via the two or more sensors, parameter sets each corresponding to two or more engine conditions different from one another, wherein each parameter set indicates a health condition at a respective location at the engine; comparing, via the computing device, the parameter sets to determine the respective health condition corresponding to the respective location at the engine; and generating, via the computing device, a health condition prediction based on the compared parameter sets. 1. A system for determining performance of an engine , the system comprising two or more sensors configured in operable arrangement at two or more respective positions at a flowpath , and wherein the system comprises one or more computing devices configured to perform operations , the operations comprising:acquiring, via the two or more sensors, parameter sets each corresponding to two or more engine conditions different from one another, wherein each parameter set indicates a health condition at a respective location at the engine;comparing, via the computing device, the parameter sets to determine the respective health condition corresponding to the respective location at the engine; andgenerating, via the computing device, a health condition prediction based on the compared parameter sets.2. The system of claim 1 , the operations comprising:determining, via comparing the parameter sets, one or more locations of a health deterioration contributor over a circumferential, radial, or axial range of the flowpath.3. The system of claim 2 , wherein determining one or more locations of the health deterioration contributor is a function of at least a measurement range of the sensor ...

Probe placement within a duct of a gas turbine engine

An inter-turbine duct is positioned between a high pressure turbine and a low pressure turbine of a gas turbine engine. The inter-turbine duct includes an inner annular wall and an outer annular wall spaced apart from the inner annular wall along a radial direction to define an annular flow passage. The inter-turbine duct includes a plurality of circumferentially spaced vanes positioned within the flow passage and at least one temperature probe is positioned upstream of the vanes at a circumferential location that is between thirty and seventy percent of a circumferential distance between the leading edges of adjacent vanes.

ACTIVE CLEARANCE CONTROL SYSTEM FOR GAS TURBINE ENGINE WITH POWER TURBINE

A method of controlling a power turbine running clearance between blade tips and a case structure. The method includes the step of adjusting an active clearance control system fluid flow based upon a power turbine speed to obtain a desired running clearance in a power turbine. 1. A method of controlling a power turbine running clearance between blade tips and a case structure , the method comprising the step of:adjusting an active clearance control system fluid flow based upon a power turbine speed to obtain a desired running clearance in a power turbine.2. The method of claim 1 , comprising the step of supplying the active clearance control system with compressor bleed air.3. The method of claim 1 , wherein the adjusting step includes varying a position of a control valve.4. The method of claim 3 , wherein the adjusting step is performed according to a schedule claim 3 , the schedule correlating the position to the power turbine speed.5. The method of claim 4 , wherein the power turbine speed relates to a power turbine power setting.6. The method of claim 4 , wherein the adjusting step includes commanding the control valve to the position only upon reaching a discrete power turbine speed.7. The method of claim 6 , wherein the discrete power turbine speed is 100% of an available power turbine speed.8. The method of claim 6 , wherein the discrete power turbine speed is 55% of an available power turbine speed.9. The method of claim 3 , comprising a step of measuring an exhaust gas temperature claim 3 , and a step of shifting the schedule upon reaching a first threshold exhaust temperature above a base exhaust gas temperature claim 3 , the first threshold exhaust temperature indicative of component deterioration increasing the power turbine running clearance.10. The method of claim 1 , wherein the power turbine is mechanically disconnected to a gas generator portion of a gas turbine engine.11. The method of claim 10 , wherein the power turbine is mechanically connected ...

Actively brazed joint and method of processing

A method of processing a joint, including forming an actively brazed joint in a vacuum furnace, wherein the actively brazed joint is formed from at least two components coupled together by a volume of a joining metal alloy having a solidus temperature and a liquidus temperature, wherein the joining metal alloy is heated to a first temperature that is higher than the liquidus temperature in the vacuum furnace. The method also includes cooling the actively brazed joint to a second temperature lower than the solidus temperature, and maintaining the second temperature within the vacuum furnace for a predefined duration to form at least one region of segregated crystallization within the volume of the joining metal alloy, the at least one region of segregated crystallization is configured to increase the liquidus temperature of a layer of brazed metal, formed from the joining metal alloy, between the at least two components.

EXHAUST GAS TEMPERATURE SENSING PROBE ASSEMBLY

A temperature sensing probe having a tip and a first thermocouple junction located nearer the tip and a second thermocouple junction located nearer an attachment point for the temperature sensing probe assembly, and a housing positioned around at least a portion of the temperature sensing probe and having a set of inlet openings and having a set of exhaust openings, wherein a stream of air flows through the housing. 1. A temperature sensing probe assembly , comprising:a temperature sensing probe having a tip and a first thermocouple junction located nearer the tip and a second thermocouple junction located nearer an attachment point for the temperature sensing probe assembly; anda housing positioned around at least a portion of the temperature sensing probe and having a set of inlet openings and having a set of exhaust openings;wherein a stream of air flows through the housing from the inlet opening to the set of exhaust openings to establish a flow path through the housing and outputs of the first thermocouple junction and second thermocouple junction define an output for the temperature sensing probe and where the set of inlet openings and the set of exhaust openings are configured to increase the stream of air flowing around the second thermocouple junction as compared to an amount of the stream of air flowing around the first thermocouple junction.2. The temperature sensing probe assembly of wherein the set of inlet openings and the set of exhaust openings are configured to increase a percentage of the stream of air flowing around the second thermocouple junction such that a time lag of the second thermocouple junction is decreased compared to the first thermocouple junction.3. The temperature sensing probe assembly of wherein the set of inlet openings is a lengthened inlet opening that extends from at least a portion of the first thermocouple junction to at least a portion of the second thermocouple junction.4. The temperature sensing probe assembly of wherein ...

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.

System for routing rotatable wire bundles of turbomachine

A system for routing rotatable wire bundles which extend from a rotor shaft of a turbomachine includes a plurality of wire bundles which extend outwardly from an inner passage of the rotor shaft of the turbomachine. An annular wire barrel is coupled to an end of the rotor shaft. A plurality of thru-holes is defined within and/or by the wire barrel. The plurality of thru-holes is annularly arranged therein. Each thru-hole extends through an aft wall of the wire barrel and is circumferentially spaced from adjacent thru-holes. Each wire bundle extends individually through a corresponding thru-hole of the plurality of thru-holes.

REMOTE TEMPERATURE MEASUREMENT SYSTEM FOR GAS TURBINE ENGINE

A remote temperature measurement system for a gas turbine engine includes an optical emitter/receiver in communication with the control system and a probe system embedded within a component of the gas turbine engine, the probe system within a line-of-sight of the optical emitter/receiver, the control system operable to determine a local temperature of the component in response to optical communication with the probe system. 1. A remote temperature measurement system comprising:a control system;an optical emitter/receiver in communication with the control system; anda probe system embedded within a component of the gas turbine engine, the probe system within a line-of-sight of the optical emitter/receiver, the control system operable to determine a local temperature of the component in response to optical communication with the probe system.2. The system as recited in claim 1 , wherein the component is a rotor blade.3. The system as recited in claim 1 , wherein the probe system comprises a resonant probe in communication with an optical port via a waveguide.4. The system as recited in claim 3 , wherein the resonant probe is embedded below a surface of the component.5. The system as recited in claim 4 , wherein the optical port is within the line-of-sight of the optical emitter/receiver.6. The system as recited in claim 3 , wherein the resonant probe comprises thermographic phosphor films in which changes in temperature affects the luminescence of the thermographic phosphor films.7. The system as recited in claim 3 , wherein the resonant probe t operates as an antenna for light.8. The system as recited in claim 3 , wherein the resonant probe comprises a material designed for resonance in a desired spectral region.9. The system as recited in claim 3 , wherein the resonant probe comprises dielectric materials designed for resonance in a desired spectral region.10. The system as recited in claim 1 , wherein the component is additively manufactured.11. A probe system ...

Gas Turbine Exhaust Thermocouple Assembly

Thermocouple assemblies for high temperature applications are provided. The thermocouple assembly includes a protection tube; and a thermocouple probe within the protection tube. The thermocouple probe includes a cable connector at a first end and extending along a longitudinal axis to a free second end. A protective housing assembly, which extends around the thermocouple probe, extends from the cable connector to a tapered end of the protective housing assembly. The protective housing assembly includes an installation unit having a fixed transition joint. An oversheath extends between the installation unit and the tapered end. The free second end of the thermocouple probe extends along the longitudinal axis beyond the tapered end of the oversheath. 1. A thermocouple assembly comprising:a protection tube;a thermocouple probe positioned within the protection tube, the thermocouple probe fixedly connected to a cable connector at a first end and extending along a longitudinal axis to a free end opposite the first end; an installation unit having a fixed transition joint; and', 'an oversheath extending between the installation unit and the tapered end;', 'wherein the oversheath terminates at the tapered end of the protective housing assembly; and', 'wherein the free end of the thermocouple probe extends along the longitudinal axis beyond the tapered end of the oversheath., 'a protective housing assembly at least partially surrounding the thermocouple probe, the protective housing assembly extending from the cable connector to a tapered end of the protective housing assembly, the protective housing assembly comprising2. The thermocouple assembly of claim 1 , wherein the protective housing assembly further comprises a protection cover extending from the fixed transition joint to the cable connector.3. The thermocouple assembly of claim 1 , wherein the oversheath is continuous along a longitudinal direction parallel to the longitudinal axis.4. The thermocouple assembly of ...

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 ...

Intercooled gas turbine optimization

A control system for a gas turbine includes a controller. The controller includes a processor configured to access an operational parameter associated with the gas turbine. The processor is configured to calculate a bias based on the operational parameter, wherein the bias indicates an amount of change in a temperature of an oxidant entering a compressor of the turbine to reach a reference temperature. The processor is further configured to control the temperature of the oxidant based on the bias to improve power output of the gas turbine.

Aircraft turbomachine comprising a compartment equipped with a ventilation assembly

A turbomachine of bypass type comprising a nacelle defining a fan duct with an interduct. The turbomachine comprises at least one compartment created in the thickness of the interduct or of the nacelle. The compartment is separated from the fan duct by a cold wall and comprises at least one heat-sensitive element. The compartment further is equipped with a ventilation assembly comprising at least one ventilation opening made in the cold wall in order, in use, to cause air from the fan duct to enter the compartment. Each ventilation opening comprises a passive-opening system arranged in the compartment, the system comprising a flap able to move between an open position in which the flap uncovers the opening and a closing-off position in which the flap closes off the opening, and a passive-actuation device of the flap for moving the flap between the two positions.

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 ...

TURBINE ASSEMBLY WITH CERAMIC MATRIX COMPOSITE VANE COMPONENTS AND COOLING FEATURES

A turbine assembly according to the present disclosure includes ceramic matrix composite vanes mounted to a metallic case. The turbine assembly includes a turbine case cooling system with a vane case cooling unit configured to manage the temperature and diameter of the metallic case at the location where the ceramic matrix composite vanes are mounted so as to control circumferential movement of the vanes relative to one another during heating and cooling of the turbine assembly when used in a gas turbine engine. 1. A turbine assembly , the assembly comprisinga turbine wheel mounted for rotation about a central axis, the turbine wheel including a disk and blades extending radially outwardly from the disk away from the central axis,a vane ring including a plurality of static vanes comprising ceramic matrix composite materials,a turbine case arranged around a central axis, the turbine case including (i) a seal ring arranged around tips of the blades included in the turbine wheel to establish a blade tip clearance gap therebetween and (ii) a vane support to which at least some of the vanes included in the vane ring are mounted for movement circumferentially toward and away from one another upon contraction and expansion in diameter of the vane support caused by temperatures experienced during use of the turbine assembly, anda turbine case cooling system including (i) a tip clearance cooling air distributor configured to discharge cooling air to the seal ring arranged around the tips of the blades to manage the temperature and diameter of the seal ring such that the blade tip clearance gap is controlled and (ii) a vane case cooling air distributor configured to discharge cooling air onto the vane support of the turbine case to which the vanes of the vane ring are mounted so as to manage the temperature and diameter of the vane support such that circumferential movement of the at least some vanes caused by the vane support is controlled.2. The assembly of claim 1 , ...

METHOD FOR CONTROLLING THE OPERATION OF A GAS TURBINE WITH AN AVERAGED TURBINE OUTLET TEMPERATURE

A method is disclosed for operating a gas turbine having a compressor, a combustor, a turbine downstream of the combustor, and a total number of turbine outlet temperature measurements. The method includes locally measuring the turbine outlet temperature of the turbine with the turbine outlet temperature measurements of the respective turbine, and averaging measured temperatures of the selected turbine outlet temperature measurements to obtain an average turbine outlet temperature. The gas turbine operation is controlled depending on the determined average turbine outlet temperature. 1. Method for operating a gas turbine having a compressor , a combustor , a turbine downstream of the combustor , and a total number of turbine outlet temperature measurements , the method comprising:measuring the turbine outlet temperature of the turbine with the turbine outlet temperature measurements of the respective turbine;selecting a number of turbine outlet temperature measurements which is smaller than a total number of the turbine outlet temperature measurements;averaging the measured temperatures of the selected turbine outlet temperature measurements to obtain an average turbine outlet temperature (TAT AVG); andcontrolling the operation of the gas turbine in dependence of the average turbine outlet temperature (TAT AVG).2. Method as claimed in claim 1 , burners of the combustors upstream of the turbine are in operation.3. Method as claimed in claim 1 , wherein turbine outlet temperature measurements with specified data quality are identified claim 1 , and in that the average turbine outlet temperature (TAT AVG) is averaged based on a number of turbine outlet measurement values with specified data quality which is smaller than the total number of turbine outlet temperature measurements with geed-the specified data quality.4. Method as claimed in claim 1 , wherein a proper subset of the turbine outlet temperature measurements is selected for obtaining the average turbine ...

Housing arrangement for a gas turbine

A casing arrangement of a gas turbine includes a sensor element of elongated design that when seen in the longitudinal direction has a front end and a rear end, a first casing structure, a second casing structure arranged at a distance from the first casing structure and having a receptacle for the front end of the sensor element, and a guide structure having an elongated guide opening for the sensor element. The sensor element extends between the first casing structure and the second casing structure, while being arranged along a section in the elongated guide opening of the guide structure, where the sensor element due to the elongated guide opening is aligned and positioned such that its front end is located, and can only be located, inside the receptacle of the second casing structure.

ENGINE WITH TEMPERATURE SENSOR IN A FLOW PATH OF A FLOW CARRYING FLUID AT A HIGHER TEMPERATURE IN THE EVENT OF A FAULT, AND METHOD FOR THE ELECTRONIC DETECTION OF A FAULT DURING OPERATION OF AN ENGINE

The proposed solution relates in particular to an engine having 1. An engine havingat least one flow-guiding element within the engine, via which, during malfunction-free operation of the engine, at least one target flow of fluid is conducted along a first flow direction and via which, in the event of a malfunction within the engine, a fault flow of fluid of a higher temperature than the fluid of the target flow is conducted along a second flow direction, which differs from the first flow direction, andat least one temperature sensor which is situated in a flow path both of the target flow and of the fault flow.2. The engine according to claim 1 , wherein the at least one temperature sensor is positioned at or in the at least one flow-guiding element.3. The engine according to claim 1 , wherein the flow-guiding element is designed to guide the fault flow past the at least one temperature sensor along a second flow direction claim 1 , which is opposite the first flow direction of the target flow.4. The engine according to claim 1 , wherein the at least one flow-guiding element is formed with at least one flow duct via which the target flow and/or the fault flow are/is diverted at least once.5. The engine according to claim 1 , wherein the at least one flow-guiding element is provided in the region of a stator of a turbine of the engine.6. The engine according to claim 5 , wherein claim 5 , via the at least one flow-guiding element claim 5 , the target flow is conducted from a hollow space claim 5 , which is bordered at least partially by the stator claim 5 , in the direction of an annular space of the engine claim 5 , in which at least one guide vane of the stator is arranged.7. The engine according to claim 6 , wherein the hollow space is formed at least partially in the interior of the guide vane.8. The engine according to claim 6 , wherein the hollow space is formed at least partially between a platform of the stator and a section of a housing to which the stator ...

EROSION SUPPRESSION SYSTEM AND METHOD IN AN EXHAUST GAS RECIRCULATION GAS TURBINE SYSTEM

In an embodiment, a method includes flowing an exhaust gas from a turbine of a gas turbine system to an exhaust gas compressor of the gas turbine system via an exhaust recirculation path; evaluating moist flow parameters of the exhaust gas within an inlet section of the exhaust gas compressor using a controller comprising non-transitory media programmed with instructions and one or more processors configured to execute the instructions; and modulating cooling of the exhaust gas within the exhaust recirculation path, heating of the exhaust gas within the inlet section of the exhaust gas compressor, or both, based on the evaluation. 1. A method , comprising:flowing an exhaust gas from a turbine of a gas turbine system to an exhaust gas compressor of the gas turbine system via an exhaust recirculation path;evaluating moist flow parameters of the exhaust gas within an inlet section of the exhaust gas compressor using a controller comprising non-transitory media programmed with instructions and one or more processors configured to execute the instructions; andmodulating cooling of the exhaust gas within the exhaust recirculation path, heating of the exhaust gas within the inlet section of the exhaust gas compressor, or both, based on the evaluation.2. The method of claim 1 , wherein evaluating moist flow parameters of the exhaust gas within the inlet section of the exhaust gas compressor comprises estimating a projected droplet size and flux of the exhaust gas at a portion of the exhaust gas compressor based at least in part on the evaluation of the moist flow parameters of the exhaust gas claim 1 , wherein the cooling modulation of the exhaust gas and/or the heating modulation of the exhaust gas is made based at least partially on the projected droplet size and flux.3. The method of claim 2 , wherein evaluating moist flow parameters of the exhaust gas within the inlet section of the exhaust gas compressor comprises:monitoring relative humidity within the inlet section ...

INTELLIGENT CONTROL METHOD WITH VARIABLE THRESHOLDS BASED ON VIBRATION READINGS

A method for controlling an engine vibration of a gas turbine engine where engine vibration of the gas turbine engine is measured. The measured engine vibration is compared with a threshold value of a nominal engine vibration. A fuel supply parameter of a fuel supply to a combustion chamber of the gas turbine engine is controlled for controlling combustion dynamics of a combustion flame within the combustion chamber. The engine vibration of the gas turbine engine is indicative of the combustion dynamics of the combustion flame, so that the fuel supply is adjusted for controlling the combustion dynamics if the measured engine vibration exceeds the threshold value of the nominal engine vibration. 1. A method for controlling an engine vibration of a gas turbine engine , the method comprising:measuring the engine vibration of the gas turbine engine,comparing the measured engine vibration with a threshold value of a nominal engine vibration,controlling a fuel supply parameter of a fuel supply to a combustion chamber of the gas turbine engine for controlling combustion dynamics of a combustion flame within the combustion chamber,wherein the engine vibration of the gas turbine engine is indicative of the combustion dynamics of the combustion flame, so that the fuel supply is adjusted for controlling the combustion dynamics when the measured engine vibration exceeds the threshold value of the nominal engine vibration.2. The method according to claim 1 ,wherein the fuel supply parameter is the mass flow of fuel to the combustion chamber and/or the pilot fuel/main flow split of the combustion chamber.3. The method according to claim 1 ,wherein the threshold value of the nominal engine vibration is a top threshold value which defines an upper nominal limit of the engine vibration,wherein the fuel supply parameter is adjusted for controlling the combustion dynamics if when the measured engine vibration is higher than the top threshold value of the nominal engine vibration.4. ...

AIR AND GAS FLOW VELOCITY AND TEMPERATURE SENSOR PROBE

There is disclosed a handheld air flow velocity measurement probe that includes a bridge circuit assembly having an airflow velocity sensor that is a resistance temperature detector (RTD) and a digitally controlled resistive element to dynamically adjust and maintain the resistance of the velocity sensor within the overheat temperature predefined range. The velocity measurement also uses a separate temperature sensor to sense the temperature of the air or gas flow. A humidity sensor is also included remote from the other sensors to measure humidity in the gas flow to be measured. All of the above described components are housed at a probe tip instead of a base as in most standard handheld probes and the digital interface at the probe tip allows the user to replace a bulky, expensive telescoping antenna with stackable extender scheme. 118-. (canceled)19. A probe handle including therein a controller , a memory unit and a display electrically coupled to a bridge circuit assembly for processing and storing data generated by a bridge circuit assembly , the probe handle further including a digital interface to enable a plurality of environmental sensors to be electrically connected to the probe handle components.20. (canceled)21. A gas velocity sensor probe adapted to measure gas flow velocity and temperature , the probe comprising:a probe handle comprising a microprocessor controller and an electrical connector, and a housing;', 'a bridge circuit assembly located in the housing and comprising a bridge circuit coupled to an operational amplifier and a power output amplifier, the bridge circuit including a first leg with a heated velocity sensor and a first reference resistor, the velocity sensor configured to operate within a predefined overheat temperature range which is above an ambient temperature, the bridge circuit having a second leg comprised of reference resistors and a digitally controlled resistive element to dynamically adjust and maintain the resistance of ...

THERMAL INSPECTION SYSTEM

A thermal inspection system is provided for a gas turbine engine hot section component with a cooling passage. This thermal inspection system includes a fluid subsystem operable to supply a fluid into the cooling passage. The thermal inspection system also includes a thermal camera subsystem operable to monitor a fluid temperate difference of the fluid exiting the cooling passage relative to the input temperature of the fluid supplied to the cooling passage. 1. A thermal inspection system for a gas turbine engine hot section component with a cooling passage , the system comprising:a fluid subsystem operable to supply a fluid into the cooling passage; anda thermal camera subsystem operable to monitor a fluid temperate difference of the fluid exiting the cooling passage relative to an input temperature of the fluid supplied to the cooling passage.2. The system as recited in claim 1 , wherein the thermal camera subsystem is operable to measure temperature differences on the order of one-one hundredth of a degree C.3. The system as recited in claim 2 , wherein passage of the fluid through the cooling passage results in a temperature difference on the order of tenths of a degree C.4. The system as recited in claim 3 , wherein the cooling passage is a shaped passage.5. The system as recited in claim 4 , wherein the component is a turbine blade.6. The system as recited in claim 1 , further comprising a control subsystem operable to compare the fluid temperate difference of the fluid exiting the cooling passage to a baseline.7. The system as recited in claim 6 , wherein an acceptable maximum/minimum dimension of the cooling passage defines the baseline.8. A method of inspecting a gas turbine engine hot section component with a cooling passage claim 6 , comprising:supplying a fluid into the cooling passage; andmonitoring a fluid temperate difference of the fluid exiting the cooling passage.9. The method as recited in claim 8 , further comprising comparing the fluid temperate ...

METHOD AND SYSTEM FOR STALL MARGIN MODULATION AS A FUNCTION OF ENGINE HEALTH

A stall margin modulation (SMM) control system in communication with a gas turbine engine including a compressor is described herein. The SMM control system is configured to determine the stall margin of the compressor, operate the gas turbine engine using the determined stall margin, assess a health of the compressor, and modify the stall margin based on the assessed health of the compressor. 1. A method of modulating a compressor stall margin of a compressor based on a health of a gas turbine engine including the compressor , said method comprising:determining the stall margin of the compressor;operating the gas turbine engine using the determined stall margin;assessing a health of the compressor; andmodifying the stall margin based on the assessed health of the compressor.2. The method of claim 1 , wherein said assessing a health of the compressor comprises estimating the health of the compressor using a compressor active stability margin (CASM) sensor.3. The method of claim 1 , wherein said assessing a health of the compressor comprises estimating the health of the compressor using at least one of pressure and temperature sensors at an inlet and an exit of the compressor.4. The method of claim 1 , wherein said assessing a health of the compressor comprises estimating the health of the compressor using a health model and a parameter estimation algorithm.5. The method of claim 1 , wherein said modifying the stall margin comprises modifying the stall margin using a variable geometry of the gas turbine engine claim 1 , wherein the variable geometry includes at least one of a transient bleed valve (TBV) claim 1 , a modulated turbine cooling (MTC) valve claim 1 , a variable stator vane (VSV) claim 1 , and a compressor inlet guide vane (CIGV).6. The method of claim 5 , wherein modifying the stall margin based on the assessed health of the compressor comprises increasing the stall margin of the compressor.7. The method of claim 6 , wherein increasing the stall margin of ...

PASSIVE FLOW MODULATION OF COOLING FLOW WITH TELEMETRY

A system according to an embodiment includes: a passive flow modulation device positioned within a turbine for modulating a flow of cooling air, the passive flow modulation device including a housing containing a temperature sensitive element; and a temperature sensor attached to the housing containing the temperature sensitive element, the temperature sensor providing temperature-related data. 1. A system , comprising:a passive flow modulation device positioned within a turbine for modulating a flow of cooling air, the passive flow modulation device including a housing containing a temperature sensitive element; anda temperature sensor attached to the housing containing the temperature sensitive element, the temperature sensor providing temperature-related data.2. The system according to claim 1 , wherein the temperature-related data includes a temperature measurement at the housing containing the temperature sensitive element or data for use in a calculation of a temperature at the housing containing the temperature sensitive element.3. The system according to claim 1 , wherein the temperature sensor comprises a wireless temperature sensor or a wired temperature sensor.4. The system according to claim 3 , wherein the wireless temperature sensor includes a surface acoustic wave (SAW) sensor or a direct write sensor.5. The system according to claim 3 , wherein the wired temperature sensor includes a thermocouple or a resistive temperature detector.6. The system according to claim 1 , further comprising an interrogating system for interrogating the temperature sensor and for receiving the temperature-related data from the temperature sensor.7. The system according to claim 4 , wherein the interrogating system is located external to the turbine.8. The system according to claim 1 , further comprising an analyzing system for determining a flow rate of the cooling air based on the temperature-related data.9. The system according to claim 1 , further comprising a turbine ...

PASSIVE FLOW MODULATION OF COOLING FLOW INTO A CAVITY

A passive flow modulation device according to an embodiment includes: a temperature sensitive element disposed within a first area; a piston coupled to the temperature sensitive element, the piston extending through a wall to a second area, wherein the first area is at a higher temperature than the second area; and a valve arrangement disposed in the second area and actuated by a distal end portion of the piston, the valve arrangement tangentially injecting a supply of cooling air through an angled orifice from the second area into the first area in response an increase in temperature in the first area. 1. A passive flow modulation device , comprising:a temperature sensitive element disposed within a first area;a piston coupled to the temperature sensitive element, the piston extending through a wall to a second area, wherein the first area is at a higher temperature than the second area; anda valve arrangement disposed in the second area and actuated by a distal end portion of the piston, the valve arrangement tangentially injecting a supply of cooling air through an angled orifice from the second area into the first area in response an increase in temperature in the first area.2. The passive flow modulation device according to claim 1 , wherein the first area and the second area are located within a turbine.3. The passive flow modulation device according to claim 2 , wherein the first area is disposed between a stator and rotor of the turbine.4. The passive flow modulation device according to claim 2 , wherein the angled orifice further comprises a pre-swirl orifice or a flow inducer.5. The passive flow modulation device according to claim 2 , wherein the first area comprises a wheelspace cavity of the turbine.6. The passive flow modulation device according to claim 1 , wherein the first area contains a rotating flow of air claim 1 , and wherein the supply of cooling air is injected into the first area through the angled orifice in a direction of rotation of the ...

SYSTEM AND METHOD FOR SELECTIVELY MODULATING THE FLOW OF BLEED AIR USED FOR HIGH PRESSURE TURBINE STAGE COOLING IN A POWER TURBINE ENGINE

A method for selectively modulating bleed air used for cooling a downstream turbine section in a gas turbine engine. The method including: measuring an engine and/or aircraft performance parameter by an engine sensor device; comparing the engine and/or aircraft performance parameter to a performance threshold; determining a bleed trigger condition, if the engine and/or aircraft performance parameter crosses the performance threshold; determining a non-cooling condition, if the engine and/or aircraft performance parameter is below the performance threshold; actuating a flow control valve to an open position, in response to the bleed trigger condition, so that bleed air is extracted from the compressor section and flowed to the downstream turbine section; and terminating, in response to the non-cooling condition, the flow of the bleed air to the downstream turbine section of the engine by actuating the flow control valve to a closed position. 1. A method for selectively modulating bleed air used for cooling a downstream turbine section in a gas turbine engine; the gas turbine engine comprising a compressor section configured to produce a flow of bleed air , a combustion chamber , and the downstream turbine section configured to receive at least a portion of the bleed air; the method comprising:measuring an engine performance parameter and/or aircraft performance parameter by an engine sensor device and/or an aircraft sensor device;comparing, by a computer processor in an engine control unit, the engine performance parameter and/or the aircraft performance parameter to a performance threshold;determining a bleed trigger condition, if the engine performance parameter and/or the aircraft performance parameter crosses the performance threshold;determining a non-cooling condition, if the engine performance parameter and/or aircraft performance parameter is below the performance threshold;actuating a flow control valve to an open position, in response to the bleed trigger ...

DEVICE FOR MEASURING SURFACE TEMPERATURE OF TURBINE BLADES

A device for measuring surface-temperature of a turbine blade, the device including a probe having a front-end mirror for receiving infrared radiation of a surface on the blade, a collimation lens for refracted the infrared radiation, a PD detector to receive the infrared radiation, and a focal-length servo; and a radial-scanning servo connected to the probe. The front-end mirror, the collimation lens, and PD detector are disposed along the optical axis of the collimation lens. The focal-length servo is adapted to move the collimation lens along the optical axis of the collimation lens. The radial-scanning servo is adapted to move the probe along the optical axis of the collimation lens. The device of the invention is capable of accurately targeting a particular point on the blade having an irregular shape for temperature measurement to accurately detect the temperature distribution on the surface of the blade. 2. The device of claim 1 , wherein:said probe further comprises a transparent separation, and a protective shell comprising a protruded part and a main part;said front-end mirror is disposed within said protruded part;said focal-length servo and the remaining of said signal acquisition module are disposed within said main part;said protruded part is inserted into the housing enclosing the turbine blade, and said main part is disposed outside the housing enclosing the turbine blade;said transparent separation is disposed between the main part and said protruded part; andsaid protruded part comprises a light opening for allowing the infrared rays radiated by the surface to pass through.3. The device of claim 2 , wherein said protruded part comprises a vent opening claim 2 , and said vent opening is adapted for blowing cold air.4. The device of claim 1 , wherein:a filter lens is disposed between said PD detector and said collimation lens and along the optical axis of said collimation lens; andsaid filter lens is adapted to transmit infrared rays in a particular ...

Solar and steam hybrid power generation system

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

WATER AND ICE DETECTION

An apparatus for the detection of either or both of water and ice within a system, more specifically, but not exclusively, the detection of either or both of water or ice crystal ingestion, or ice accretion on an aerofoil, within a gas turbine engine. The apparatus and method compares the measured temperature of the first region with a second temperature value, measured at a distinct second region of the aerofoil, wherein the second radial position of the second sensor is radially offset from the first radial position of the first sensor. 1. An apparatus for detecting either or both of water or ice crystal ingestion and ice accretion on an aerofoil , within a gas turbine engine having a principal rotational axis , the apparatus comprising:a first temperature sensor for determining a first temperature value at a first radial position within a first region of the aerofoil, relative to the principal rotational axis of the gas turbine engine;a second temperature sensor for determining a second temperature value at a second radial position within a second region of the aerofoil, relative to the principal rotational axis of the gas turbine engine; and,a comparator for comparing the first temperature value with the second temperature value,wherein the second radial position of the second sensor is radially offset from the first radial position of the first sensor; and,either or both of the first temperature sensor and the second temperature sensor are positioned aft of a leading edge of the aerofoil.2. The apparatus as claimed in claim 1 , wherein the apparatus comprises a first heater for applying heat to the first region of the aerofoil.3. The apparatus as claimed in claim 1 , wherein the apparatus comprises a second heater for applying heat to the second region of the aerofoil.4. The apparatus as claimed in claim 1 , wherein the or each heater is located on or at least partially within the aerofoil.5. The apparatus as claimed in claim 1 , wherein the aerofoil is ...

METHOD OF OPTIMIZING THE LIMITATION OF DUST EMISSIONS FOR GAS TURBINES FUELED WITH HEAVY FUEL OIL.

Method for optimizing the limitation of dust emissions from a gas turbine or combustion plant comprising a line for supplying liquid fuel oil, a line for generating fuel oil atomizing air, and a central controller, wherein: a first definition step, starting from a nominal temperature of the fuel oil and a nominal pressure ratio of the atomizing air of the fuel oil, and by controlling the injection of the soot inhibitor, of a nominal operating point corresponding to the maximum permissible level of emitted dust; a second step of controlling a first parameter, taken from the group of the fuel oil temperature and the pressure ratio of the fuel oil atomizing air, in order to reach another operating point; and a third step of controlling the soot inhibitor injection to achieve the maximum permissible level of emitted dust. 2. The method according to claim 1 , wherein the three steps take place under the control of the central controller.3. The method according to claim 2 , wherein after the third step claim 2 , the central controller triggers a new claim 2 , second control step of the second parameter taken from the group of the fuel oil temperature and the atomizing air pressure ratio of the fuel oil.4. The method according to claim 1 , wherein the control of the first parameter is controlled between a minimum value and a maximum value.5. The method according to claim 4 , wherein the control of the temperature of the fuel oil is controlled between 50° C. and 135° C.6. The method according to claim 4 , wherein the pressure ratio of the fuel oil atomizing air is controlled between 1.1 and 1.8.7. A gas turbine or combustion plant comprising:a liquid fuel oil supply line connecting a fuel source to at least one combustion chamber, comprising means for controlling the temperature of the fuel oil, and means for storing and controlling the injection of a soot inhibitor,a line for generating the fuel oil atomizing air, connecting a main compressor to at least one combustion ...

APPARATUS AND METHOD FOR CO-GENERATION

A co-generation apparatus for the generation of electricity from an external source of forced air is described in which the co-generation apparatus comprises a turbine, a generator, a co-generation control unit, and an adjustable standoff. The turbine is connected to the generator for the production of electricity. The generator interface electrically connects the generator to an electrical system. The co-generation control unit is connected to the turbine and generator interface. The forced air drives the turbine. The turbine can be positioned in a turbine housing that receives the forced air. An adjustable standoff is connected to the turbine. The standoff adjusts the position of the turbine relative to the forced air. 1. A co-generation apparatus for the generation of electricity from forced air flowing continuously through a duct to a location in an external structure to be heated or cooled with the continuous forced air flow , the co-generation apparatus comprising:at least one turbine comprising turbine blades and mechanically connected to an electrical generator that produces electricity;wherein an external source is arranged at a fixed position in the duct for generating the continuous forced air flow for a fixed time period determined by detected temperature at the location to be heated or cooled and wherein the at least one turbine is moveably positioned on an exhaust side of the external source such that the turbine blades are subjected to a portion of the continuous forced air flow;a temperature sensor positioned at the location to be heated or cooled by the continuous forced air flow;a current sensor positioned to monitor current drawn by the external source for sensing a backpressure created by the turbine blades within the continuous forced air flow portion;a generator interface that electrically connects the generator to an electrical distribution system of an external structure;a co-generation control unit connected to the current sensor, the ...

HEAT FLUX MEASUREMENT SYSTEM

A turbine section according to an example of the present disclosure includes, among other things, a component including a coating on a substrate, and at least one sensor positioned a distance from the component, the at least one sensor configured to detect radiation emitted from at least one localized region of the coating at a first wavelength and configured to detect radiation emitted from the substrate corresponding to the at least one localized region at a second, different wavelength. The first wavelength and the second wavelength are utilized to determine a heat flux relating to the at least one localized region. A method of measuring a gas turbine engine component is also disclosed. 1. A turbine section comprising:a component including a coating on a substrate;at least one sensor positioned a distance from the component, the at least one sensor configured to detect radiation emitted from at least one localized region of the coating at a first wavelength and configured to detect radiation emitted from the substrate corresponding to the at least one localized region at a second, different wavelength; andwherein the first wavelength and the second wavelength are utilized to determine a heat flux relating to the at least one localized region.2. The turbine section as recited in claim 1 , comprising a controller electrically coupled to the at least one sensor claim 1 , the controller configured to determine an instantaneous value of the heat flux based upon a comparison of the first wavelength and the second wavelength.3. The turbine section as recited in claim 2 , wherein the at least one localized region includes a first localized region and a second claim 2 , different localized region claim 2 , and the controller is configured to determine a spatial gradient based upon the instantaneous value of the heat flux at the first localized region and an instantaneous value of heat flux at the second localized region.4. The turbine section as recited in claim 2 , ...

Gas Turbine

A gas turbine with a compressor, in which air can be compressed; with at least one burner having a combustion chamber, which can be supplied with the compressed air and in which a fuel can be combusted in the presence of the compressed air subject to heating the air; a turbine, in which the heated air can be expanded; a diffuser arranged, seen in flow direction of the expanded air, downstream of the turbine; a plurality of temperature sensors, dependent on the measurement values of which a thermodynamic mean temperature or mixed-out turbine outlet temperature of the expanded air can be determined. The temperature sensors are arranged in the region of a diffuser cover, which at an outlet end of the diffuser closes off a hollow space of the diffuser positioned radially inside of a flow duct of the diffuser. 1. A gas turbine , comprising:a compressor configured to compress air;a burner comprising at least one combustion chamber, which can be supplied with the air compressed in the compressor and in which a fuel, in presence of the compressed air, can be combusted subject to heating the air;a turbine configured to expand the heated air;a diffuser having a flow duct and arranged downstream of the turbine seen in flow direction of the expanded air;a diffuser cover arranged at an outlet end of the diffuser that closes off a hollow space positioned radially inside of the flow duct of the diffuser; anda plurality of temperature sensors arranged in a region of a diffuser cover that each provide a measurement value from which a thermodynamic mean temperature or a mixed-out turbine outlet temperature of the expanded air can be determined.2. The gas turbine according to claim 1 , wherein the plurality of temperature sensors claim 1 , seen in flow direction of the expanded air claim 1 , are arranged downstream of the diffuser cover.3. The gas turbine according to claim 1 , wherein the plurality of temperature sensors claim 1 , seen in flow direction of the expanded air claim 1 , ...

Axial flow turbine

An axial flow turbine of an embodiment includes: a turbine rotor provided to penetrate in an inner casing; rotor wheels formed on an outer peripheral surface of the turbine rotor in an axial direction; a gland seal part which is provided on a downstream side of the rotor wheel at a final stage and seals between the turbine rotor and the inner casing; a seal part which is provided between the rotor wheel at the final stage and the gland seal part and prevents inflow to the turbine rotor side of a working fluid; and a cooling medium supply mechanism which supplies a cooling medium directly to a wheel space surrounded by the rotor wheel at the final stage, the turbine rotor, the gland seal part and the seal part.

SENSOR DEVICE AND SENSING METHOD

A sensor device determines measured values of a property of a fluid, in particular of a gas, in a cavity of a gas turbine engine having a duct for carrying the fluid from the cavity to a sensor element. A data processing device is coupled to the sensor element and processes the measured values. The data processing device has a device for detecting changes in the measured values with respect to time, and an evaluation device, by which the changes in the measured values with respect to time can be detected. If there is a deviation in the changes in the measured values with respect to time from a predefined criterion, a signal relating to an at least partial blockage of the at least one inlet duct can be output. A measurement method is also disclosed. 1. a Sensor device for determining measured values of a property of a fluid , in particular of a gas , in a cavity of a gas turbine engine having at least one inlet duct for carrying the fluid , in particular the gas , from the cavity to a sensor element ,whereina data processing device, which is coupled to the sensor element and which processes the measured values, whereinthe data processing device has a means for detecting changes in the measured values with respect to time,the data processing device has an evaluation means, by means of which the changes in the measured values with respect to time can be detected, and wherein,if there is a deviation in the changes in the measured values with respect to time from a predefined criterion, a signal relating to an at least partial blockage of the at least one inlet duct can be output.2. The sensor device according to claim 1 , wherein the evaluation means is designed to compare changes in the measured values with respect to time to prestored basic data on changes in measured values with respect to time for the same and/or a different property of the fluid claim 1 , in particular of the gas.3. The sensor device according to claim 1 , wherein the property of the fluid claim 1 ...

Humid Air Turbine

The invention aims to shorten the time required for start-up and prevent excessive increases in the heat loads on turbine blades. A humid air turbine includes a compressor; a combustor; a turbine; an exhaust heat recovery unit for recovering the heat of turbine exhaust gas to generate high-temperature moisture; a fuel supply system having a fuel flow rate control valve; an exhaust temperature acquiring unit for acquiring a temperature of the exhaust discharged while the turbine is driven; a combustion gas moisture ratio calculating section for calculating a ratio of moisture contained in combustion gas; an exhaust temperature upper limit calculating section for setting an exhaust temperature upper limit based on the combustion gas moisture ratio and the pressure ratio; an exhaust temperature difference calculating section for calculating the difference between the exhaust temperature upper limit and the exhaust temperature; a fuel flow rate command value calculating section for calculating a fuel flow rate command value using the exhaust temperature difference; and a control command value output section for outputting a command signal to the fuel flow rate control valve based on the command value selected by a fuel flow rate command value selecting section. 1. A humid air turbine comprising:a compressor for compressing air to generate compressed air;a pressure ratio calculating section for calculating a pressure ratio of the compressor;a moisture system for supplying moisture to intake air of the compressor or the compressed air generated by the compressor;a combustor for mixing humid air generated by supplying the moisture to the intake air or the compressed air with a fuel and combusting the mixture to generate combustion gas;a combustion gas moisture ratio calculating section for acquiring a combustion gas moisture ratio that is a ratio of moisture contained in the combustion gas;a fuel supply system, having a fuel flow rate control valve, for supplying the fuel ...

Fast Response Temperature Sensors

Provided herein is a differential temperature sensor which utilizes multiple temperature sensors to quickly and accurately calculate ambient fluid temperature with a reduced response time. The provided systems and methods utilize a first fluid temperature sensor and a second probe temperature sensor to account for the thermal impact of the device on the ambient fluid temperature and the effect of heat within the device, or temperature difference between the probe and fluid temperature, on the first fluid temperature sensor measurement. 1. A temperature probe having a fast response time for measuring a fluid temperature , comprising:an instrument housing forming an interior volume and having a distal end;a first temperature sensor positioned at or extending from the distal end of the instrument housing;a second temperature sensor positioned in the interior volume of said instrument housing; anda thermal barrier thermally positioned between said first temperature sensor and said instrument housing to thermally isolate the first temperature sensor from the instrument thermal mass.2. The temperature probe of claim 1 , further comprising:a sensor platform having a distal end and a proximal end, wherein said first temperature sensor is positioned at said sensor platform distal end and said sensor platform proximal end is connected to or passes through said instrument housing distal end.3. The temperature probe of claim 2 , wherein said instrument housing comprises a sonde base and said sensor platform comprises a sonde sensor configured to operably connect to said sonde base.4. The temperature probe of claim 3 , wherein said second temperature sensor is positioned within said sensor platform or within said sonde base.5. The temperature probe of claim 1 , wherein said thermal barrier comprises an insulation layer positioned between said first temperature sensor and said second temperature sensor claim 1 , thereby thermally isolating said second temperature sensor from said ...

TURBINE FRAME COOLING SYSTEMS AND METHODS OF ASSEMBLY FOR USE IN A GAS TURBINE ENGINE

A turbine frame cooling system for use with a gas turbine engine includes an outer ring defining a cavity and a hub positioned radially inward of the outer ring. The turbine frame cooling system also includes a plurality of circumferentially-spaced first fairings coupled between the outer ring and the hub and a plurality of circumferentially-spaced second fairings coupled between the outer ring and the hub, wherein the first and second fairings are alternatingly positioned about the hub. The turbine frame cooling system also includes a plurality of circumferentially-spaced air scoops coupled to the outer ring. The plurality of air scoops extend into a bypass stream and are configured to channel a bypass air cooling flow into the cavity of the outer ring. 1. A turbine frame cooling system for use with a gas turbine engine , said turbine frame cooling system comprising:an outer ring defining a cavity;a hub positioned radially inward of said outer ring;a plurality of circumferentially-spaced first fairings coupled between said outer ring and said hub;a plurality of circumferentially-spaced second fairings coupled between said outer ring and said hub, wherein said pluralities of first and second fairings are alternatingly positioned about said hub; anda plurality of circumferentially-spaced air scoops coupled to said outer ring, wherein said plurality of air scoops extend into a bypass stream and are configured to channel a bypass air cooling flow into the cavity.2. The turbine frame cooling system in accordance with claim 1 , further comprising a plurality of independent cooling circuits claim 1 , wherein each cooling circuit comprises:an air scoop of said plurality of air scoops;a first fairing of said plurality of first fairings; anda second fairing of said plurality of second fairings, wherein said first fairing is positioned adjacent said second fairing.3. The turbine frame cooling system in accordance with claim 2 , wherein each cooling circuit of said plurality ...

AIR AND GAS FLOW VELOCITY AND TEMPERATURE SENSOR PROBE

There is disclosed a handheld air flow velocity measurement probe that includes a bridge circuit assembly having an airflow velocity sensor that is a resistance temperature detector (RTD) and a digitally controlled resistive element to dynamically adjust and maintain the resistance of the velocity sensor within the overheat temperature predefined range. The velocity measurement also uses a separate temperature sensor to sense the temperature of the air or gas flow. A humidity sensor is also included remote from the other sensors to measure humidity in the gas flow to be measured. All of the above described components are housed at a probe tip instead of a base as in most standard handheld probes and the digital interface at the probe tip allows the user to replace a bulky, expensive telescoping antenna with stackable extender scheme. 1. An air velocity sensor apparatus adapted to measure air and gas flow velocity and temperature comprising:a bridge circuit assembly including a bridge circuit coupled to an operational amplifier and a power output amplifier, the bridge circuit including a first leg with a heated velocity sensor and a first reference resistor, the velocity sensor configured to operate within a predefined overheat temperature range which is above an ambient temperature, the bridge circuit having a second leg comprised of reference resistors and a digitally controlled resistive element to dynamically adjust and maintain the resistance of the velocity sensor within the overheat temperature predefined range, the operational amplifier applying a DC voltage to enable the velocity sensor to be heated to a target temperature within the overheat temperature range;a gas flow temperature sensor for measuring the temperature of the gas or air flow to be measured; andan analog to digital converter coupled to an output of the temperature sensor and to an output of the bridge circuit assembly.2. The air velocity sensor apparatus of claim 1 , wherein the power output ...

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 ...

AIR AND GAS FLOW VELOCITY AND TEMPERATURE SENSOR PROBE

There is disclosed a handheld air flow velocity measurement probe that includes a bridge circuit assembly having an airflow velocity sensor that is a resistance temperature detector (RTD) and a digitally controlled resistive element to dynamically adjust and maintain the resistance of the velocity sensor within the overheat temperature predefined range. The velocity measurement also uses a separate temperature sensor to sense the temperature of the air or gas flow. A humidity sensor is also included remote from the other sensors to measure humidity in the gas flow to be measured. All of the above described components are housed at a probe tip instead of a base as in most standard handheld probes and the digital interface at the probe tip allows the user to replace a bulky, expensive telescoping antenna with stackable extender scheme. 1. An air velocity sensor apparatus adapted to measure air and gas flow velocity and temperature comprising:a bridge circuit assembly including a bridge circuit coupled to an operational amplifier and a power output amplifier, the bridge circuit including a first leg with a heated velocity sensor and a first reference resistor, the velocity sensor configured to operate within a predefined overheat temperature range which is above an ambient temperature, the bridge circuit having a second leg comprised of reference resistors and a digitally controlled resistive element to dynamically adjust and maintain the resistance of the velocity sensor within the overheat temperature predefined range, the operational amplifier applying a DC voltage to enable the velocity sensor to be heated to a target temperature within the overheat temperature range;a gas flow temperature sensor for measuring the temperature of the gas or air flow to be measured; andan analog to digital converter coupled to an output of the temperature sensor and to an output of the bridge circuit assembly.2. The air velocity sensor apparatus of claim 1 , wherein the power output ...

Modulated Hybrid Variable Area Turbine Nozzle for Gas Turbine Engine

The present disclosure is directed to a variable area turbine nozzle. The variable area turbine nozzle includes a first vane segment, a second vane segment arranged with the first vane segment, and a trailing edge segment arranged with the first and second vane segments. The vane also includes a first actuating system for pivoting the second vane segment with respect to the first vane segment and a second actuating system for pivoting the trailing edge with respect to the first and second vane segments. 1. A variable area turbine nozzle system , comprising: outer and inner spaced apart bands,', a first vane segment extending between the bands and fixedly joined thereto,', 'a second vane segment arranged with the first vane segment, and', 'a first actuating system for pivoting the second vane segments with respect to the first vane segments so as to vary the throat area;, 'a plurality of vanes spaced apart from each other to define a throat of minimum flow area for channeling therethrough combustion gas, each of the vanes comprising, a trailing edge segment configured with the first and second vane segments, and', 'a second actuating system for pivoting the trailing edge with respect to the first and second vane segments; and, 'wherein a subset of the vanes also comprise], 'a variable area turbine nozzle comprising at least one nozzle segment, the nozzle segment comprisinga controller configured to control the first and second actuating systems.2. The nozzle system of claim 1 , wherein vanes having trailing edge segments are mounted to the bands in a predefined alternating claim 1 , circumferential configuration with vanes without trailing edge segments.3. The nozzle system of claim 1 , wherein the controller is configured to individually control the first and second actuating systems.4. The nozzle system of claim 1 , wherein the controller is configured to control the first and second actuating systems together based on a predetermined schedule.5. The nozzle system ...

Machine learned aero-thermodynamic engine inlet condition synthesis

A system for neural network compensated aero-thermodynamic gas turbine engine parameter/inlet condition synthesis. The system includes an aero-thermodynamic engine model configured to produce a real-time model-based estimate of engine parameters, a machine learning model configured to generate model correction errors indicating the difference between the real-time model-based estimate of engine parameters and sensed values of the engine parameters, and a comparator configured to produce residuals indicating a difference between the real-time model-based estimate of engine parameters and the sensed values of the engine parameters. The system also includes an inlet condition estimator configured to iteratively adjust an estimate of inlet conditions based on the residuals and adaptive control laws configured to produce engine control parameters for control of gas turbine engine actuators based on the inlet conditions.

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. 1. A method for detecting inlet temperature distortion of an engine , the method comprising: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; andissuing an alert when the inlet temperature distortion exceeds the threshold.2. The method of claim 1 , wherein issuing the alert comprises issuing the alert to a cockpit of an aircraft.3. The method of claim 1 , wherein issuing the alert comprises issuing the alert to an engine control system of an aircraft.4. The method of claim 3 , further comprising adjusting an engine operating line in response to receiving the alert as a function of the inlet temperature distortion.5. The method of claim 4 , wherein adjusting the engine operating line comprises setting the engine operating line as a function of a first parameter corresponding to the inlet temperature distortion claim 4 , a second parameter corresponding to any one of speed claim 4 , power claim 4 , and torque of the engine claim 4 , and a third parameter.6. The method of claim 5 , wherein the third parameter corresponds to any one of acceleration claim 5 , variable guide vane position claim 5 , bleed-off valve position claim 5 , and active tip clearance control.7. The ...

MONITORING DEVICE, METHOD FOR MONITORING TARGET DEVICE, AND PROGRAM

An acquisition unit is configured to acquire measurement values of a target device. The measurement values that are acquired include at least a temperature and a flow rate of an input fluid to be input to the target device, and a temperature and a flow rate of an output fluid to be output from the target device. A correction unit is configured to obtain a correction measurement value by which the measurement values are corrected through thermal equilibrium calculations based on the measurement values. A distance calculation unit is configured to calculate a Mahalanobis distance with a factor of the correction measurement value. 1. A monitoring device , comprising:an acquisition unit configured to acquire measurement values being measurement values of a target device, the measurement values including at least a temperature and a flow rate of an input fluid to be input to the target device, and a temperature and a flow rate of an output fluid to be output from the target device;a characteristic value calculation unit configured to calculate a characteristic value for showing characteristics of the target devicebased on the measurement values; anda distance calculation unit configured to calculate a Mahalanobis distance with a factor of the measurement value and the characteristic value.2. (canceled)3. The monitoring device according to claim 1 , further comprising:an atmospheric condition acquisition unit configured to acquire an atmospheric condition including at least one of an atmospheric pressure, an atmospheric temperature, and an atmospheric humidity; anda normalization unit configured to normalize the measurement values to values under a normal atmospheric condition by using the atmospheric condition that is acquired,wherein the distance calculation unit calculates the Mahalanobis distance based on the normalized measurement values and the characteristic value calculated by the characteristic value calculation unit based on the normalized measurement values.4. ...

STEAM TURBINE

A steam turbine includes an outer casing () that is provided with a first steam outlet port (), through which exhaust steam flowing through the entire length of a flow path () defined between an inner casing main body () and an outer casing main body () in a direction along an axis (O) is discharged to the outside of the outer casing (), and a second steam outlet port (), which is provided in the outer casing main body () and through which the exhaust steam passing through a portion of the flow path () or the exhaust steam not passing through the flow path () is discharged to the outside of the outer casing (); a first valve () that adjusts opening of the first steam outlet port (); and a second valve () that adjusts opening of the second steam outlet port ().

BOWED ROTOR NACELLE COOLING

The present disclosure describes ventilation systems having a reduced aerodynamic footprint. The vents in the ventilation systems are actuated with Shape Memory Alloys that actuate the vents on an as needed basis while effectively sealing the vents when not in operation. The present disclosure further describes a ventilation system in an aircraft nacelle that helps mitigate bowed rotors by cooling down the engine nacelle faster or by helping create a uniform temperature distribution in the nacelle. In various embodiments, the ventilation system comprises vents and fans embedded in the vents. 1. An apparatus , comprising:{'b': '608', 'i': 'a', 'a housing ();'}{'b': 610', '608, 'i': a', 'a, 'a vent () disposed in the housing (); and'}{'b': 612', '610', '608', '612', '644', '646', '610, 'i': a', 'a', 'a, 'a shape-memory alloy (SMA) element coupled to the vent () and configured such that when a temperature in the housing () exceeds a threshold, the SMA element changes shape (, ) to actuate the vent ();'}wherein air flows through the vent to cool an inside of the housing when the vent is actuated.2216626628634a. The apparatus of claim 1 , wherein the housing is an engine pylon () claim 1 , an electronics and equipment bay ( claim 1 , ) claim 1 , or a battery container ().3. The apparatus of claim 1 , wherein:{'b': 200', '202, 'the apparatus is a nacelle () in combination with a gas turbine engine (), and'}{'b': 608', '200, 'i': 'a', 'the housing () is the nacelle ().'}4606. The apparatus of claim 1 , wherein the vent () is modular.5608636640ab. The apparatus of claim 1 , wherein the housing () is a grille () covering a portion of an automobile engine ().6200300300202122200300300abab. In combination claim 1 , an engine housing ( claim 1 , claim 1 , ) and a gas turbine engine () comprising a rotor shaft () claim 1 , the engine housing ( claim 1 , claim 1 , ) comprising:{'b': 402', '602, 'i': 'b', 'a wall (, ); and'}{'b': 204', '304', '500', '610', '402', '602', '508', '516 ...

DEVICE FOR MEASURING THE CHARACTERISTICS OF AN AIR FLOW

A device for measuring the characteristics of an air flow intended to be mounted in an annular duct having a longitudinal axis in a turbine engine, comprising supporting means which support means for measuring the characteristics of an air flow. According to the invention, the supporting means comprise at least one first support including a main branch supporting first measuring means and a second support, structurally independent of the first support and including a main branch supporting second measuring means, with the first support and the second support being so formed that the main branch of the first support extends over a distance greater than the main branch of the second support in a common direction of extension of the branches. 1. A device for measuring the characteristics of an air flow intended to be mounted in an annular duct having a longitudinal axis in a turbine engine , comprising supporting means which support means for measuring the characteristics of an air flow , wherein the supporting means comprise at least one first support including a main branch supporting first measuring means and a second support , structurally independent of the first support and including a main branch supporting second measuring means , with the first support and the second support being so formed that the main branch of the first support extends over a distance greater than the main branch of the second support in a common direction of extension of said branches.2. A device according to claim 1 , wherein the main branch of the first support supports at least one auxiliary branch provided with first measuring means and the main branch of the second support supports at least one auxiliary branch provided with second measuring means claim 1 , with said auxiliary branches extending in a direction transverse to the direction of extension intended to correspond to the circumferential direction of the annular duct wherein the branches are mounted.4. An assembly comprising ...

METHOD AND APPARATUS FOR ADJUSTING VARIABLE VANES

According to one aspect of the present disclosure, a gas turbine engine is disclosed that includes an engine section comprising a plurality of stages of variable vanes, and also includes first and second synchronizing rings (sync-rings). Movement of the first sync-ring adjusts vane angles of a first one of the stages of variable vanes, and movement of the second sync-ring adjusts vane angles of a second one of the stages of variable vanes. At least one sensor is configured to measure a condition of the gas turbine engine. A controller is configured to move the first sync-ring independently of the second sync-ring based on data from the at least one sensor. 1. A gas turbine engine comprising:an engine section comprising a plurality of stages of variable vanes;first and second synchronizing rings (sync-rings), wherein movement of the first sync-ring adjusts vane angles of a first one of the stages of variable vanes, and movement of the second sync-ring adjusts vane angles of a second one of the stages of variable vanes;at least one sensor configured to measure a condition of the gas turbine engine; anda controller configured to move the first sync-ring independently of the second sync-ring based on data from the at least one sensor.2. The gas turbine engine of claim 1 , comprising:a first actuator configured to rotate the first sync-ring, and a different, second actuator configured to rotate the second sync-ring;wherein to move the first sync-ring independently of the second sync-ring, the controller is configured to actuate the first actuator independently of the second actuator.3. The method of claim 2 , wherein the first and second actuators are electric actuators.4. The gas turbine engine of claim 2 , wherein each sync-ring comprises:first gear teeth situated on a first side of the sync-ring that engage an actuator gear of the actuator; andsecond gear teeth situated on an opposite, second side of the sync-ring that engage vane gears of the stage of variable vanes ...

COMPONENT WITH EMBEDDED SENSOR

One exemplary embodiment of this disclosure relates to an article having a multi-layer wall structure having an embedded sensor. Further, the multi-layer wall structure and the sensor are bonded together. 1. An article , comprising:a multi-layer wall structure including an embedded sensor, the multi-layer wall structure and the sensor bonded together.2. The article as recited in claim 1 , wherein the multi-layer wall structure includes a plurality of metallic layers claim 1 , the sensor bonded to at least two of the metallic layers.3. The article as recited in claim 2 , wherein each of the metallic layers includes more than one piece of material claim 2 , wherein adjacent pieces of material establish a seam where the pieces of material abut one another claim 2 , and wherein the metallic layers are arranged such that the seams are staggered relative to the seams of adjacent layers.4. The article as recited in claim 2 , wherein the metallic layers include at least one of nickel (Ni) claim 2 , steel claim 2 , cobalt (Co) claim 2 , and titanium (Ti).5. The article as recited in claim 4 , wherein at least one of the metallic layers has a different chemical composition from at least one other metallic layer.6. The article as recited in claim 1 , wherein the sensor includes an optical fiber.7. The article as recited in claim 1 , wherein the multi-layer wall structure includes a plurality of sensors.8. The article as recited in claim 7 , wherein the plurality of sensors are selected from the group consisting of optical fibers claim 7 , pressure transducers claim 7 , temperature sensors claim 7 , thermocouples claim 7 , position sensors claim 7 , and strain gauges.9. The article as recited in claim 1 , wherein the sensor is metallurgically bonded to the multi-layer wall structure during forming of the multi-layer wall structure.10. The article as recited in claim 1 , wherein the multi-layer wall structure includes a substantially arcuate shape claim 1 , and wherein the multi ...

MAIN STEAM VALVE AND STEAM TURBINE

A main steam valve includes a cylindrical guide centered about an O-axis, a valve body disposed inside the guide so as to be slidable in the O-axis direction, a valve shaft on which the valve body moves in the O-axis direction between open and closed positions, and a casing having a flow path and a valve seat formed on an inner surface thereof. The flow path guides out a fluid guided into the casing from the inflow direction along the O-axis direction. The valve body abuts against the valve seat when the valve body is in the closed position. A valve chamber, formed in the casing, has a baffle plate provided in a region between an outer circumferential surface of the guide and an inner surface of the casing. The baffle plate interrupts swirling vortex flow with spiral vortex core extending in the circumferential direction of the O-axis of the guide. 1. A main steam valve comprising:a cylindrical guide extending centered about an axis;a valve body disposed inside the guide so as to be slidable in an axis direction;a valve shaft on which the valve body moves in the axis direction between an open position and a closed position;a casing having a flow path formed therein and having a valve seat formed on an inner surface thereof, the flow path guiding out, in an outflow direction that intersects an inflow direction, a fluid guided into the casing from the inflow direction along the axis direction, the valve body abutting against the valve seat when the valve body is in the closed position; anda valve chamber formed inside the casing, the valve chamber having a baffle plate provided in a region between an outer circumferential surface of the guide and an inner surface of the casing, the baffle plate interrupting a swirling vortex flow with spiral vortex core that extends in a circumferential direction of the axis of the guide.2. The main steam valve according to claim 1 , wherein the baffle plate includes a first plate portion that extends in the outflow direction of the ...

COMPRESSOR WATER-WASH ADVISORY

A compressor water-wash advisory system generates compressor water-wash notifications or initiates on-line water-wash cycles for a gas turbine or turbofan jet engine based on monitored health parameters of the engine. A high-fidelity model of engine compressor performance defines nominal expected values of engine performance parameters, such as compressor efficiency and air flow, as a function of current operating conditions. A tracking filter component compares the modeled performance parameters with actual calculated performance parameters obtained from sensor data, and maintains a separate actual model of engine performance that modifies the nominal performance parameter values to match the calculated parameter values using parameter modifiers. A health index is derived as a function of the parameter modifiers, and a water-wash notification is generated when the health index is indicative of a significant loss of fuel efficiency due to dirt accumulation in the engine's compressor. 1. A method , comprising:receiving, by a system comprising at least one processor, sensor data representing one or more measured engine parameters of a turbine engine;determining, by the system, one or more engine performance parameter values based on the sensor data;generating, by the system, a health index value based on a difference between the one or more engine performance parameter values and one or more expected engine performance parameter values defined in a nominal new engine model; andgenerating, by the system, a compressor water-wash advisory output in response to a determination that the health index value satisfies a defined criterion.2. The method of claim 1 , wherein the generating the health index value comprises:generating, based on the difference between the one or more engine performance parameter values and the one or more expected engine performance parameter values, one or more performance parameter modifier values that cause the one or more expected engine ...

TURBINE TEMPERATURE ESTIMATION SYSTEM

A turbine temperature estimation system controls a valve in a cooling passage to control the flow rate of cooling air supplied to a turbine component on the basis of its temperature. The system includes a coating layer formed on a surface of a component of the gas turbine; a measuring unit to supply an electric current to the coating layer and to measure a change in a resistance value of the coating layer; and a controller to estimate a temperature of the coating layer on the basis of the resistance value. The coating layer includes a heat shielding material and a resistive material whose resistance value changes with temperature. A cooling passage supplies cooling air to cool the turbine component, and the controller controls an opening of the cooling passage according to a voltage value of the coating layer. 1. A system for estimating a temperature of a gas turbine , the system comprising:a coating layer formed on a surface of a component of the gas turbine;a measuring unit configured to supply an electric current to the coating layer and to measure a change in a resistance value of the coating layer; anda controller configured to estimate a temperature of the coating layer on the basis of the resistance value,wherein the coating layer comprises a heat shielding material and a resistive material whose resistance value changes with temperature.2. The system according to claim 1 , further comprising a cooling passage for supplying cooling air to cool the component of the gas turbine claim 1 ,wherein the controller is further configured to control an opening of the cooling passage according to a voltage value of the coating layer.3. The system according to claim 2 , wherein the component of the gas turbine includes a blade claim 2 ,the cooling passage supplies cooling air to the blade, andthe measuring unit measures the resistance value of the coating layer formed on an outer surface of the blade.4. The system according to claim 2 , wherein the component of the gas ...

APPARATUS, SYSTEMS, AND METHODS FOR WIRELESS MONITORING OF GAS TURBINE ENGINE TEMPERATURE

A system for wirelessly monitoring temperatures of a gas turbine engine comprising a wireless sensor positioned on or in a component of the engine, one or more interrogating antennas capable of transmitting an RF signal to the wireless sensor and receiving an RF return signal from the wireless sensor, and a processing unit capable of interpreting the RF return signal to determine a temperature of the component inside the engine. In an embodiment, the wireless sensor comprises polymer derived ceramics (“PDC”) deposited on an Inconel surface of the engine. In an embodiment, the wireless sensor sustains temperatures up to 1000° C. during long term operation of the part of the engine. In an embodiment, the wireless sensor comprises multiple layers including a metallic patch antenna, a PDC layer, and a bond coat which provides a metallic ground plane for the sensor. 1. A system for wirelessly monitoring temperatures of a gas turbine engine , comprising:a wireless sensor positioned on a component of the gas turbine engine;one or more interrogating antennas configured to transmit an RF signal to the wireless sensor and receive an RF return signal from the wireless sensor; anda processing unit configured to interpret the RF return signal to determine a plurality of temperatures of the component of the gas turbine engine.2. The system of claim 1 , wherein the wireless sensor is deposited on an Inconel surface of the gas turbine engine.3. The system of claim 1 , wherein the wireless sensor comprises:a patch antenna;a polymer derived ceramic layer; anda bond coat.4. The system of claim 3 , wherein the patch antenna comprises an MCrAl[Ta claim 3 ,Hf claim 3 ,Si]Y coating claim 3 , wherein M is a material selected from the group consisting of Fe claim 3 , Co claim 3 , or Ni.5. The system of claim 3 , wherein the patch antenna comprises a material selected from the group consisting of platinum claim 3 , nickel claim 3 , copper claim 3 , gold claim 3 , palladium claim 3 , silver ...

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 ...

Gas turbine engine control based on characteristic of cooled air

A gas turbine engine includes a compressor section, a combustor, and a turbine section. The turbine section includes a high pressure turbine comprising a plurality of turbine blades. The gas turbine engine includes a tap for tapping air that is compressed by the compressor, to be passed through a heat exchanger to cool the air, the cooled air to be passed to the plurality of turbine blades. A sensor is located downstream of a leading edge of the combustor, and is configured to measure a characteristic of the cooled air. A controller is configured to compare the measured characteristic to a threshold and control an operating condition of the gas turbine engine based on the comparison.

TRANSIENT CONTROL TO EXTEND PART LIFE IN GAS TURBINE ENGINE

A full authority digital engine controller (FADEC) based system is also disclosed. The system includes a processor, and a tangible, non-transitory memory configured to communicate with the processor, the tangible, non-transitory memory having instructions stored thereon that, in response to execution by the processor, cause the FADEC to perform operations. The operations may include measuring a first temperature at a first sensor disposed at a first known location of an engine, measuring a second temperature at a second sensor disposed at a second known location of the engine, and estimating at least one of a stress or a strain of a part or component in the engine based on the first temperature and the second temperature. The system may control fuel flow and/or other engine effectors during a thrust transient to limit the estimated stress or the estimated strain of the component from exceeding a predetermined threshold. 1. A method of managing engine component life in a part in an engine comprising:measuring a temperature at a location of the engine;estimating at least one of a stress or a strain of the engine based on the temperature;controlling fuel flow delivered to the engine in response to at least one of the stress or the strain exceeding a predetermined value.2. The method of claim 1 , wherein the predetermined value is derived from a steady-state stress or a steady-state strain.3. The method of claim 1 , further comprising measuring at least one of a pressure or an air flow rate at the location of the engine.4. The method of claim 3 , further comprising estimating a node temperature of the part based on at least one of the temperature claim 3 , the pressure claim 3 , or the air flow rate.5. The method of claim 4 , wherein the strain is estimated based on at least one of the temperature claim 4 , the pressure claim 4 , the air flow rate claim 4 , or a rotational speed of the engine.6. The method of claim 5 , wherein the part comprises a rotor.7. The method of ...

Method and system for detecting high turbine temperature operations

Herein provided are methods and systems for detecting a high temperature condition of a gas turbine engine. A fuel flow to a combustor of the engine and a compressor outlet pressure of the engine are obtained. A ratio of the fuel flow to the compressor outlet pressure is determined. The ratio is compared to a threshold and a high temperature condition of the engine is detected when the ratio exceeds the threshold.

HIGH TEMPERATURE FLAME SENSOR

A flame sensor apparatus includes a sensor assembly. The sensor assembly includes a photodiode for sensing characteristics of a flame. The photodiode outputs an electrical photocurrent. The sensor assembly includes an electrical assembly that is electrically remote from the sensor assembly. The sensor assembly includes an electric cable assembly extending from the sensor assembly to the electrical assembly. The electric cable assembly includes an electrical cable to electrically convey the photocurrent to the electrical assembly. At least the sensor assembly is configured and constructed to experience and continue to operate at a temperature at or greater than 200° C. 1. A flame sensor apparatus for flame sensing within a turbine , the apparatus including:a sensor assembly entirely located within the turbine at a first location, which is within the turbine, having a first, relatively elevated temperature, the sensor assembly including a photodiode, at the first location, for sensing characteristics of a flame within a combustion chamber of the turbine, the photodiode outputting an electrical photocurrent that has an electrical current value that is indicative of the characteristics of the flame and the sensor assembly including an electrical wire, at the first location, electrically connected to the photodiode to receive the electrical photocurrent output from the photodiode and electrically convey the electrical photocurrent;an electrical assembly that is electrically remote from the sensor assembly at a second location having a second temperature relatively lower than the first temperature at the first location; andan electric cable assembly extending from the sensor assembly, at the first location, to the electrical assembly, at the second location, and transitioning from the first location having the relatively elevated temperature to the second location having the relatively lower temperature, the electric cable assembly including an electrical cable ...

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.

PASSIVE FLOW MODULATION OF COOLING FLOW INTO A CAVITY

A passive flow modulation device according to an embodiment includes: a pressure sensitive main valve controlling a flow of a cooling fluid from a first area to a second area through an orifice; and a temperature sensitive pilot valve coupled to the pressure sensitive main valve, the temperature sensitive pilot valve configured to open at a predetermined temperature in the first area, causing a pressurization of the pressure sensitive main valve, wherein the pressurization of the pressure sensitive main valve actuates the pressure sensitive main valve to an open position, allowing the cooling fluid to flow from the first area to the second area through the orifice. 1. A passive flow modulation device , comprising:a pressure sensitive main valve controlling a flow of a cooling fluid from a first area to a second area through an orifice; anda temperature sensitive pilot valve coupled to the pressure sensitive main valve, the temperature sensitive pilot valve configured to open at a predetermined temperature in the first area, causing a pressurization of the pressure sensitive main valve,wherein the pressurization of the pressure sensitive main valve actuates the pressure sensitive main valve to an open position, allowing the cooling fluid to flow from the first area to the second area through the orifice.2. The passive flow modulation device of claim 1 , wherein the pressure sensitive main valve further includes:a pressure sensitive element disposed within a housing, the housing including a valve seat and a gas outlet port;a main piston coupled to the pressure sensitive element; anda main valve disc coupled to the main piston for selectively engaging the valve seat in response to a change in pressurization of the pressure sensitive element.3. The passive flow modulation device of claim 2 , wherein the temperature sensitive pilot valve further includes:a temperature sensitive element;a pilot piston coupled to the temperature sensitive element; anda pilot valve disc ...

Method for spatially-localized gas-phase temperature measurements through ceramic materials

A method of measuring a temperature of a thermally-insulated, high temperature system. The method includes directing a first electromagnetic energy into the high temperature system so that the first electromagnetic energy may cause multi-photon ionization of a molecular or atomic species within the high temperature system. A second electromagnetic energy resulting from the multi-photon ionization is detected through a thermally-insulating wall of the high temperature system. The detected second electromagnetic energy is related to a temperature within the high temperature system.

MULTIVARIABLE FEEDFORWARD CONTROL

A method of tracking variable states of a gas turbine engine in transient conditions includes obtaining input data representative of rotor velocity and pressure ratio; calculating a reference transient scheduled trajectory based on the input data; calculating a speed reference transient scheduled trajectory based on the input data; calculating a feedforward variable based on the reference transient scheduled trajectory; obtaining a feedback control variable; and determining a control variable based on a combination of the feedforward variable and the feedback control variable. 1. A method of tracking variable states of a gas turbine engine in transient conditions , comprising:obtaining input data representative of rotor velocity and pressure ratio;calculating a pressure ratio reference transient scheduled trajectory based on the input data;calculating a speed reference transient scheduled trajectory based on the input data;calculating a feedforward variable based on the speed reference transient scheduled trajectory and pressure ratio transient scheduled trajectory;obtaining a feedback control variable; anddetermining a control variable based on a multivariable coupled combination of the feedforward variable and the feedback control variable.2. The method of further including a step of disturbance rejection.3. The method of wherein the step of obtaining input data includes data representative of pressure and air temperature.4. The method of wherein the input data for calculating the speed reference transient scheduled trajectory is based on the pressure and air temperature.5. The method of further including a step of dynamic shaping of the feedforward variable. This non-provisional application claims the benefit of priority under 35 U.S.C. §119(e) to U.S. Provisional Patent Application No. 62/019,268, entitled “MULTIVARIABLE FEEDFORWARD CONTROL”, filed Jun. 30, 2014, which is herein incorporated in its entirety by reference.The technology described herein relates ...

Method for Operating a Turbo Machine

A system and method for determining performance of a turbine engine, and operation thereof. The system and method includes a plurality of sensors and one or more computing devices executing operations including acquiring a plurality of parameter sets each corresponding to a plurality of engine conditions in which each parameter set corresponding to each engine condition indicates a health condition at a plurality of locations at the engine; comparing the plurality of parameter sets to determine a health condition corresponding to a location at the engine; and generating a health condition prediction at the engine based on the compared parameters. 1. A system for determining performance of a turbine engine , the system comprising a plurality of sensors and one or more computing devices configured to perform operations , the operations comprising:acquiring, via a plurality of sensors, a plurality of parameter sets each corresponding to a plurality of engine conditions, in which each parameter set corresponding to each engine condition indicates a health condition at a plurality of locations at the engine;comparing, via the computing device, the plurality of parameter sets to determine a health condition corresponding to a location at the engine; andgenerating, via the computing device, a health condition prediction at the engine based on the compared parameters.2. The system of claim 1 , the operations further comprising:acquiring, via a first sensor, a first parameter set based on a first engine operating condition indicating a health condition at a first location of the engine; andacquiring, via the first sensor, a second parameter set based on a second engine operating condition indicating a health condition at a second location different from the first location.3. The system of claim 2 , the operations further comprising:acquiring, via a second sensor, a third parameter set based on the first engine operating condition indicating a health condition at the second ...

Wind funnel, gas combustion turbine and power output generator systems

Wind funnel and gas combustion turbine systems are disclosed. Air travels through a wind funnel where it is compressed, and then flows into a compression section of a gas turbine that is fueled by a hydrocarbon fuel source such as natural gas. Compressed air from the wind funnel enters the compressor section of the gas turbine at relatively high density and force, and then flows to the combustion section of the gas turbine where oxygen from the wind-compressed air is used to combust the hydrocarbon fuel supplied to the gas turbine. The combustion section drives a power output generator having first and second generators that are selectively engageable and disengageable from each other. During periods when compressed air from the wind funnel is delivered to the compression section of the gas combustion turbine, the first and second generators may be drivingly engaged with each other by a generator coupling mechanism.

GAS TURBINE SWIRL DETECTION

A non-transitory computer readable medium with instructions stored thereon, the instructions executable by one or more processors for calculating base swirl in a gas turbine; and calculating relative swirl in the gas turbine. Also, a method for gas turbine maintenance, comprising identifying a combustor in need of repair or replacement within a gas turbine; and repairing or replacing the combustor; wherein said identifying comprises calculating base swirl of the gas turbine and calculating relative swirl of the gas turbine in order to associate a gas path from a thermocouple to the combustor in need of repair or replacement. 1. A non-transitory computer readable medium with instructions stored thereon , the instructions executable by one or more processors for:calculating base swirl in a gas turbine; andcalculating relative swirl in the gas turbine.2. The non-transitory computer readable medium of claim 1 , wherein calculating base swirl comprises calculating (a) unsteady pressure amplitude as a function of angular position within the gas turbine and/or (b) mean-subtracted exhaust temperature as a function of angular position within the gas turbine.3. The non-transitory computer readable medium of claim 1 , wherein calculating base swirl comprises calculating (a) unsteady pressure amplitude as a function of angular position within the gas turbine and (b) mean-subtracted exhaust temperature as a function of angular position within the gas turbine.4. The non-transitory computer readable medium of claim 1 , wherein calculating base swirl comprises determining the average angular offset between the unsteady pressure amplitude as a function of angular position within the gas turbine and mean-subtracted exhaust temperature as a function of angular position within the gas turbine claim 1 , wherein the average angular offset is a function of gas turbine load.5. The non-transitory computer readable medium of claim 1 , wherein calculating base swirl comprises measuring ...

Turbine component instrumented to provide thermal measurements

A gas turbine component ( 49 ) may be instrumented to provide a plurality of signals indicative of thermal measurements in a high temperature combustion environment of the gas turbine. A thermocouple arrangement may include a first thermocouple leg ( 50 ) disposed within a thickness of the component. At least two or more thermocouple legs ( 52, 53, 54 ) is each electrically connected to the first leg to form individual thermocouple junctions ( 56, 57, 58, 59 ) along the first leg for conversion of respective thermal gradients to respective electrical signals, such as electromotive force (emf) based voltages. The thermocouple arrangement may be used in combination with a thermographic system ( 70 ) to calculate heat flux over a region of the turbine component.

Exhaust gas temperature indicator for a gas turbine engine

An exhaust gas temperature indicator for a gas turbine engine is disclosed in which data representing discrete overtemperature events occurring at different times is stored in a nonvolatile memory for later retrieval and display on an event-by-event basis. A character display is used to provide detailed digital, alphanumeric or other character information relating to each overtemperature event, such as the number, temperature zone, peak temperature and duration of the event. An indicator is provided for indicating the presence of unacknowledged temperature data in the memory device, and a maximum exhaust gas temperature value for an aircraft flight is stored. An analog display for continuously displaying current exhaust gas temperature values is provided in conjunction with a character display for displaying either current or stored values. Separate caution and warning indicators are utilized for alerting the flight crew to developing overtemperature conditions without the need to rely solely on an analog or digital display.

配置成提供热测量的涡轮部件

一种燃气涡轮部件(49)可以配置成在燃气涡轮的高温燃烧环境中提供指示热测量的多个信号。热电偶装置可以包括设置在部件的厚度内的第一热电偶支脚(50)。至少两个或多个热电偶支脚(52,53,54)各自电连接至第一支脚，以沿着第一支脚形成用于将各自的热梯度转换成相应的电信号的独立的热电偶接头(56,57,58,59)，电信号例如是基于电压的电动势(emf)。热电偶装置可以与热图像系统(70)联合使用以计算涡轮部件的区域上的热通量。

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.

Automatic inspection device of turbine temperature detector

(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。

A thermocouple on a contoured gas turbine engine component

써모커플(12)의 형성 방법으로서, 제 1 레그(14)를 형성하기 위해 구성요소(10) 상에 제 1 재료를 적층하는 단계, 구성요소(10) 상에 패턴(50)을 형성하기 위해 마스크(30)를 통하여 제 2 재료를 적층하는 단계로서, 이 패턴(50)은 복수의 별개의 제 2 레그 교차점 단부(20)들 및 제 2 레그(16)들의 별개의 리드 단부들을 포함하는 제 2 재료의 연속적인 패치(52)를 형성하며, 각각의 제 2 레그 교차점 단부(20)는 제 1 레그(14)와의 각각의 교차점(18)으로부터 연속적인 패치(52)까지의 범위인, 제 2 재료를 적층하는 단계, 및 제 2 레그(16)들의 별개의 리드 단부(22)들을 형성하기 위해 연속적인 패치(52)를 레이저 제거하는 단계로서, 각각의 리드 단부(22)는 각각의 교차점 단부(20)에 전기적으로 연결되고, 이에 의해 별개의 제 2 레그(16)들을 형성하는, 연속적인 패치(52)를 레이저 제거하는 단계를 포함한다.

Method (embodiments) and compressor bypass valve diagnostics system

Изобретение может быть использовано в двигателях внутреннего сгорания. Предложен способ для двигателя с наддувом. Индикация ухудшения состояния перепускного клапана компрессора исходя из температуры приточного наддувочного воздуха. Перепускной клапан компрессора подсоединен к перепускному каналу компрессора. Температура приточного наддувочного воздуха измеряется выше по потоку от входа компрессора. Раскрыты способ для двигателя с наддувом и система двигателя с наддувом. Технический результат заключается в повышении точности диагностирования ухудшения состояния перепускного клапана компрессора. 3 н. и 17 з.п. ф-лы, 4 ил. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 710 452 C2 (51) МПК F02B 37/12 (2006.01) F02D 41/22 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (52) СПК F01D 17/085 (2019.05); F01D 17/105 (2019.05); F01D 21/003 (2019.05); F02D 41/0007 (2019.05); F02D 41/22 (2019.05); F02D 41/221 (2019.05); G01M 15/042 (2019.05); G01M 15/14 (2019.05) (21)(22) Заявка: 2015147456, 05.11.2015 05.11.2015 Дата регистрации: (73) Патентообладатель(и): Форд Глобал Текнолоджиз, ЛЛК (US) 26.12.2019 10.11.2014 US 14/537,216 (43) Дата публикации заявки: 10.05.2017 Бюл. № 13 (56) Список документов, цитированных в отчете о поиске: RU 2472950 C2, 20.01.2013. US 2012014812 A1, 19.01.2012. US 7578128 B2, 25.08.2009. US 2003106539 A1, 12.06.2003. US 2004006985 A1, 15.01.2004. (45) Опубликовано: 26.12.2019 Бюл. № 36 R U (54) СПОСОБ (ВАРИАНТЫ) И СИСТЕМА ДИАГНОСТИКИ ПЕРЕПУСКНОГО КЛАПАНА КОМПРЕССОРА (57) Реферат: Изобретение может быть использовано в наддувочного воздуха измеряется выше по потоку двигателях внутреннего сгорания. Предложен от входа компрессора. Раскрыты способ для способ для двигателя с наддувом. Индикация двигателя с наддувом и система двигателя с ухудшения состояния перепускного клапана наддувом. Технический результат заключается в компрессора исходя из температуры приточного повышении точности диагностирования наддувочного ...

Exhaust system for a motor vehicle and a motor vehicle including one

Die Erfindung betrifft ein Abgassystem für ein Kraftfahrzeug, sowie ein Kraftfahrzeug mit einem solchen. Das Abgassystem weist eine drehbar gelagerte Verschlussklappe auf, die ein Verschlussteil umfasst, wobei das Verschlussteil gleichzeitig einen Strömungseingang und einen Strömungsausgang verschließen kann. The invention relates to an exhaust system for a motor vehicle, as well as a motor vehicle with such a system. The exhaust system has a rotatably mounted closure flap which comprises a closure part, wherein the closure part can simultaneously close a flow inlet and a flow outlet.

GAS TURBINE AND METHOD OF ITS OPERATION

РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2015 144 906 A (51) МПК F02C 7/047 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21)(22) Заявка: 2015144906, 20.02.2014 (71) Заявитель(и): СИМЕНС АКЦИЕНГЕЗЕЛЛЬШАФТ (DE) Приоритет(ы): (30) Конвенционный приоритет: 20.03.2013 EP 13160102.3 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 20.10.2015 (86) Заявка PCT: (87) Публикация заявки PCT: WO 2014/146854 (25.09.2014) R U (54) ГАЗОВАЯ ТУРБИНА И СПОСОБ ЕЕ ЭКСПЛУАТАЦИИ (57) Формула изобретения 1. Газовая турбина (13), включающая в себя тракт всасывания (14) и компрессор (1) с проточным каналом (4), причем компрессор (1) содержит расположенный в его проточном канале (4) ряд (3) регулируемых входных направляющих лопаток, отличающаяся тем, что газовая турбина (13) содержит сенсорный блок (17) предупреждения об обледенении, по меньшей мере, с одним датчиком, расположенным между первым рядом (5) рабочих лопаток и первым рядом (6) направляющих лопаток компрессора, причем первый ряд (5) рабочих лопаток компрессора расположен в проточном канале (4) непосредственно вниз по течению за рядом (3) входных направляющих лопаток, а первый ряд (6) направляющих лопаток - непосредственно вниз по течению за первым рядом (5) рабочих лопаток, причем сенсорный блок (17) предупреждения об обледенении содержит, по меньшей мере, один датчик (11) влажности воздуха и, кроме того, по меньшей мере, один датчик (7) давления и датчик (8) температуры, причем оба расположены между первым рядом (5) рабочих лопаток и первым рядом (6) направляющих лопаток компрессора. 2. Турбина по п. 1, отличающаяся тем, что датчик (11) влажности воздуха расположен в тракте всасывания (4). 3. Турбина по п. 1, отличающаяся тем, что сенсорный блок (17) предупреждения об обледенении содержит в проточном канале (4) компрессора между первым рядом (5) рабочих лопаток и первым рядом (6) направляющих лопаток несколько распределенных Стр.: 1 A 2 0 1 5 1 4 4 9 0 6 A Адрес для ...

Patent RU2015147456A3

`7ВУ’” 2015147456” АЗ Дата публикации: 05.06.2019 Форма № 18 ИЗПМ-2011 Федеральная служба по интеллектуальной собственности Федеральное государственное бюджетное учреждение ж 5 «Федеральный институт промышленной собственности» (ФИПС) ОТЧЕТ О ПОИСКЕ 1. . ИДЕНТИФИКАЦИЯ ЗАЯВКИ Регистрационный номер Дата подачи 2015147456/06(072978) 05.11.2015 Приоритет установлен по дате: [ ] подачи заявки [ ] поступления дополнительных материалов от к ранее поданной заявке № [ ] приоритета по первоначальной заявке № из которой данная заявка выделена [ ] подачи первоначальной заявки № из которой данная заявка выделена [ ] подачи ранее поданной заявки № [Х] подачи первой(ых) заявки(ок) в государстве-участнике Парижской конвенции (31) Номер первой(ых) заявки(ок) (32) Дата подачи первой(ых) заявки(ок) (33) Код страны 1. 14/537,216 10.11.2014 05 Название изобретения (полезной модели): [Х] - как заявлено; [ ] - уточненное (см. Примечания) СПОСОБ (ВАРИАНТЫ) И СИСТЕМА ДИАГНОСТИКИ ПЕРЕПУСКНОГО КЛАПАНА КОМПРЕССОРА Заявитель: Форд Глобал Текнолоджиз, ЛЛК, 05 2. ЕДИНСТВО ИЗОБРЕТЕНИЯ [Х] соблюдено [ ] не соблюдено. Пояснения: см. Примечания 3. ФОРМУЛА ИЗОБРЕТЕНИЯ: [Х] приняты во внимание все пункты (см. Примечания) [ ] приняты во внимание следующие пункты: [ ] принята во внимание измененная формула изобретения (см. Примечания) 4. КЛАССИФИКАЦИЯ ОБЪЕКТА ИЗОБРЕТЕНИЯ (ПОЛЕЗНОЙ МОДЕЛИ) (Указываются индексы МПК и индикатор текущей версии) Е02В 37/12 (2006.01) Е020 41/22 (2006.01) 5. ОБЛАСТЬ ПОИСКА 5.1 Проверенный минимум документации РСТ (указывается индексами МПК) Е02В37/00-[02В37/24; Н02023/00-Е02023/02; Е02041/00-Е02041/40 5.2 Другая проверенная документация в той мере, в какой она включена в поисковые подборки: 5.3 Электронные базы данных, использованные при поиске (название базы, и если, возможно, поисковые термины): Езрасепе, РАТЕМТЬСОРЕ, Рабеагсв, ОЗРТО 6. ДОКУМЕНТЫ, ОТНОСЯЩИЕСЯ К ПРЕДМЕТУ ПОИСКА Кате- Наименование документа с указанием (где необходимо) частей, Относится к гория* относящихся к ...